WO2002024529A1 - Roll on - roll off, portable aerial spraying, particulate dispersal, and refueling systems apparatus - Google Patents

Abstract

This invention relates to a new design and integration approach in the configuration, capability, and side door, hatch, or other removable pressurized plugs, useful for mounting and operating various types of roll on roll off airborne refueling systems, spraying systems, dry particulate diffusion systems, and fluid spray dispersal systems for use with aircraft in support of search and rescue operations and other missions.

Description

ROLL ON - ROLL OFF, PORTABLE AERIAL SPRAYING, PARTICULATE DISPERSAL, AND REFUELING SYSTEMS APPARATUS

Richard L. K. Woodland

FIELD OF THE INVENTION

This invention relates to an integrated, uniform, removable, portable, roll on and roll off, modular, mounting suite of aircraft-based hardware for air to air refueling systems, aerial spray systems, and dry chemical aerial dispersal systems. BACKGROUND OF THE INVENTION

Fixed and rotary wing aircraft typical of the Lockheed-Martin C-130, have been extensively modified to undertake a number of different aerial response missions which involve spraying liquid, and dispersing dry chemical, oil coagulating agents, or organic particulate, fertilizer agents, bio-remediation agents, pesticides, herbicides, defoliants, and other products from airborne delivery platforms using Roll On Roll Off spray systems, and like temporary mounted aircraft installations. Further, aircraft are extensively used around the world to undertake dynamic in flight refueling of other aircraft, using female to male drogue refueling baskets typical of systems manufactured by the Aero Union Corporation Of California, or male to female refueling probes typical of those manufactured by the Boeing Corporation of Washington.

In many Air Forces, due to high operating costs, limited aircraft acquisition, traiπing> and maintenance support funding, there are only a limited number of aircraft, which, by necessity, can be used for multiple roles using the same flight crews. An example of this situation, involves the thirty two, Lockheed-Martin C-130 aircraft of the Canadian Air Force, which are regularly used for humanitarian relief operations, search and rescue, military air lift, aerial refueling, emergency medical transport, passenger operations, and other applications. With particular emphasis on search and rescue, it is imperative that such aircraft are equipped with sensors for all weather detection of persons in peril particularly in hostile marine situations, which typically take place some distance from land. Under such circumstances search and rescue helicopters have limited range, and even if equipped with refueling systems, must be accompanied by a refueling tanker to provide fuel when the helicopter is offshore. Although other methodologies for ship based refueling operations have been devised to provide fuel from ships to helicopters by means of a snorkel assembly, ships are not as mobile as aircraft, especially In rough weather, and even faster military ships will typically take ten times longer than a Lockheed-Martin C-130 to traverse the same distance. Hence an acute problem exists wherein the capability to conduct search and rescue missions using advanced sensor suites, while providing simultaneous air to air refueling to other search and rescue aircraft, and being able to receive fuel from other aircraft, without modifying the airframes, and permitting rapid reconfiguration for other operations. Such a system does not currently exist.

Although other roll on roll off systems for C-130's have been designed for aerial spraying, and the temporary storage of fuel, these systems are not modular as to permit interoperability (spraying to refueling etc.) using the same mounting components, or without modifying the aircraft. Typically these modifications involve expensive installations for aircraft plumbing, pumping systems, storage tanks, and auxiliary power systems typical of those manufactured by Sargent Fletcher of the USA for, aerial refueling. Wing mounted refueling pods typical of those manufactured by Aero Union and Sargent Fletcher, are currently used on Lockheed-Martin C-130 and like aircraft, but also result in increased aerodynamic drag, the installation of hardpoints, pylons, additional structural weight, and permanent plumbing. These modified or dedicated aircraft platforms, can cause delays or cancellation of specialized missions due to aircraft maintenance problems, and thereby result in the acquisition of fewer aircraft to undertake these unique missions. Further, search and rescue operations depend heavily upon helicopters for extracting persons in peril, particularly in marine environments where high sea states prevent other forms of surface extraction. Although helicopter aerial refueling systems comparable to those described by Piasecki, in U.S. Patent 5393015, issued on Feb. 28, 1995, entitled "Rotary Wing Aircraft In-flight Refueling Device", have aided considerably by extending the range of helicopters to effect long range rescue at sea, on several occasions, the effect of high wind, poor visibility, and the turbulent effect of said wind on the delivery aircraft, receiving helicopter, drogue, and hose dynamics have prevented aerial refueling, which in one case resulted in the ditching and subsequent loss of a U.S. Air National Guard Pave Hawk H-60 search and rescue helicopter. In several other instances aerial refueling has been undertaken at considerable risk to helicopter and crew, where on several occasions helicopter rotors have connected with, or cut the refueling hose in half resulting in loss of the helicopter, due primarily to the curvature of the refueling hose from the delivery aircraft, In one particular case a U.S. Marine Corp. CH-53 helicopter was actively engaged in pursuing the refueling drogue and began to undertake such violent vertical maneuvers that the flexure of the rotors severed its own refueling probe. There are many documented aerial refueling accidents involving helicopters, which could have been prevented by a flat section of fuel hose and a flyable drogue, which could provide a degree of stability in turbulent air, particularly in low altitude marine rescue situations. Such a system does not currently exist.

Although the Boeing Corporation of Seattle, Washington USA, has devised a methodology of deploying a single refueling hose and drogue assembly through the floor of a V-22 Tilt Wing Rotor aircraft, the system cannot provide redundancy. The importance of redundancy and the hydraulic methodology used in reel based refueling systems as proposed in Boeing's brochure "V-22 Medium Lift Fuel Dispensing System (MLFDS)" and disclosed as same at the Aerial Refueling Systems Advisory Group (ARSAG) conference, in Phoenix, Arizona, September 18, 2000, has been cited by the U.S. Air Force in document HQ ACC/DRS.17-20 as "unreliable", and further, the existing FR-300 pod system was noted as having a Mean Time Before Failure (MTBF) of only 49 hours, in U.S. Air Force document HQ ACC/DRS. 19.

Further in the white paper published by Major Tracy W. Colburn in March of 1997, entitled "Running On Empty: The Development Of Helicopter Aerial refueling And Implications For Future USAF Combat Rescue Capabilities", prepared for the U.S. Air Force Air Command And Staff College, document reference AU/ACSC/0412/97-03. Major Tracy cited several instances where helicopter rescue, and training missions were compromised because of inoperable refueling equipment. Given the potential for catastrophic loss of an aircraft and crew because of failure of a refueling delivery system to provide fuel to a receiver aircraft, a need exists to install redundant refueling capabilities in any potential refueling tanker delivery aircraft. The MLFDS proposal by Boeing does not provide or intimate redundant capability. Further,. Boeing fails to disclose and provision for manned observation, a flyable downrigger or drogue assembly, low profile fuel tanks, and further fails to disclose graphically or texturally a pressure housing to provide the V-22 with pressurized aerial refueling operations. Another problem associated with airborne refueling systems, particularly for search and rescue, and special missions, involves the inboard palletized fuel tank reservoirs on Lockheed-Martin MC-130 or like aircraft which typically use round cylindrical tanks which are not designed for simultaneous use of the rear of the aircraft for cargo, passengers, or other equipment which may be used in conjunction with the air refueling capability. Other problems associated with inboard fuel tanks, or temporary bladders is that in an accident, the higher center of gravity of the cylindrical tanks, makes them more prone to separate from their support structure and suffer structural damage or rupture accordingly in an accident. Under said accidental circumstances, or from hostile gunfire, for example, on humanitarian relief operations, as was experienced by relief flights in Bosnia, Somalia, and Kenya within recent years, said single layer, ballistics unprotected tanks once ruptured, can result In fire and explosive detonation of the fuel. Further, most roll on roll off fuel tanks do not incorporate structural reinforcing for heavy cargo which could be loaded on top of the fuel tanks, thereby making better use of the currently unusable space, aboard the aircraft. In light of the foregoing, existing palletized cylindrical or other fuel tanks do not incorporate topside roller bearing handling systems, integrated cargo handling rails, ballistics protection, or fireproof linings.

Further, several types of existing aircraft like the U.S. Air Force Lockheed- Martin C-130 aircraft which are equipped with female fuel receptacles, require dedicated, articulated male refueling probe transfer systems installed on host aircraft like Boeing KC-135's which are uniquely configured with said dedicated, articulated, telescopic refueling booms. A roll on roll off articulated boom, male probe refueling system does not currently exist. Further, a combined non dedicated, NATO compatible drogue female refueling assembly, combined with the U.S. Air Force standard articulated boom with male probe refueling assembly would also decrease the numbers of different types of refueling aircraft and permit a high level of joint interoperability. However, such a combined male and female refueling boom assembly doe not currently exist.

Further, Lockheed Martin C-130 aircraft, are also used for aerial spraying applications which utilize roll on spray systems like the ADDSPak system employed by the Alyeska Pipeline company, In Alaska or other systems comparable to the Modular Airborne Spray System (MASS) in use with the U.S. Air Force Reserve 910^lh Airlift Wing, in^" Ohio. However, the MASS system requires alrframe modifications and plumbing to be Installed through the wings and aircraft fuselage of the Lockheed-Martin C-130. The ADDSPak system also requires pre-deployment of the spray rails on the ground which are typically deployed through the rear ramp of C-130 aircraft. Said cargo ramp is left open throughout the entire flight envelope, thereby compromising aircraft pressurization, increasing drag and resulting in cumbersome handling characteristics, restricted flight altitudes, and slower transit speeds. Further, low cost weapons of mass destruction (WMD) and combative tactics employed during the Iraq war, by terrorists, and recent wars in other countries, present unique challenges to rapid reconfiguration of spraying aircraft. For example, U.S. military experts found that Iraqi Mirages were given spray tanks to disperse biological agents and accordingly held trials as late as January 13, 1991 and further incorporated an ability to refill the Mirages with additional biological agents by air. It is documented by the U.S. military, and other United Nations specialists, that Iraq Manufactured tens of thousands of liters of concentrated Botulinium toxin, anthrax, and Aflatoxin, clostidium perfringens, a gangrene-causing biological agent, and concentrated Ricin, in solution during the early 1990's within Iraq's borders.

In Japan the terrorist group "Aum Shinrikyo" initiated chemical attacks in June 1994, in Matsumoto, Japan, which killed seven people and injured 500. Plans of the Aum Shinrikyo were discovered which revealed that they planned to produce enough Sarin gas agent to annihilate a large Japanese city by spraying it from a helicopter. These were the first instances of large-scale terrorist use of chemical agents, but a variety of incidents and reports over the last two years indicate a growing terrorist interest in these weapons. A rapidly configured, roll on, non dedicated, aerial spray system which can be loaded onto an aircraft of opportunity like a Lockheed-Martin C-5 Galaxy in minutes, not hours, to apply aerial neutralizing agents for biological, chemical or radiation threats, without requiring any airframe modifications, does not currently exist.

In other areas, spray systems are critical in protecting agriculture crops or destroying illegal drugs. For example according to the U.S. Drug Enforcement

Administration, in addition to coca production, Colombia now ranks fourth, among the world's heroin producers. Colombia pursues an active aerial eradication program and sprayed approximately 8,000 hectares of cultivated poppies in 1998.

Although aircraft like Cessna A188B Ag Trucks have been created or modified as dedicated spray aircraft to undertake smaller more select aerial spraying applications, the prolonged nature and high volume of some spraying operations, and the need for non dedicated roll on capabilities require a different approach to

, aerial spraying systems.

Further the spray rails, which are fixed or temporarily mounted in some aircraft, require that the host airframe be flown at a slower speed due to the aerodynamic forces exerted upon the spray rail assembly, and open ramps, and doorways. Hence a spray system, which does not use rails, or require open doorways, or unpressurized flight, particularly among roll on systems does not currently exist. Further no combined, unmodified, roll on aerial spray and dry chemical dispersal system, currently exists which possesses the capability of providing a GPS coordinated reference system to affect_, automatic computer controlled flow of dry particulates or spray fluids, which further interfaces with the aircraft autopilot, to initiate dispersal over an electronic geographically controlled delivery area, with variable dispersal rates to accommodate differential dispersal on varying densities of nuisance or illegal plants, pests, or lethal chemical, biological and other aerosol warfare agents on the ground or within the air within the delivery zone. Further no capability exists to integrate a temporarily mounted ballistic winds sensor package with the capability of reading the wind miles ahead of the host spraying aircraft to create a three dimensional matrix of wind currents, wind direction, and wind velocities to dynamically plot the optimum aircraft approach, dispersal or spray pattern, and flow rate, when given said variable wind parameters. Further no roll on spray or particulate dispersal system exists which also incorporates a means for accommodating a non dedicated in flight sensor to detect, analyze, characterize, and track, lethal airborne aerosols, or particulate matter, as part of a homogeneous roll on response capability.

5. All of the aforementioned special mission work systems are currently non existent, or are expensive, requiring dedicated airframes, which restrict aircraft performance, decrease safety margins, and Inhibit mission readiness.

Accordingly there is a continuing unaddressed need for a common aircraft mounting system which is highly portable, pressurized, and moves seamlessly 0 between aircraft, and utilizes side door, or other fuselage orifice mounting methodologies which do not require airframe modifications, and incorporates the capability to undertake Interchangeable applications for; refueling, refueling guidance, refueling hose stabilization, spraying, particulate dispersal, spraying, dispersal zone sensing, planning, and delivery, in conjunction with the simultaneous 5 carriage of cargo, medevac or other parallel systems in conjunction with refueling, spraying, or particulate dispersal missions.

BRIEF SUMMARY OF THE INVENTION

The current system solves the problems associated with fixed mount refueling, spraying, dry chemical or particulate dispersal systems, used in conjunction with aircraft, which are specifically modified to undertake these missions. The preferred embodiment of the current invention builds on previous patents by Richard L.K. Woodland (US patent 5927648 entitled; "Aircraft Based Sensing, Detection, Targeting, Communications, And Response Apparatus" and the improvement copending U.S. Patent Application Serial No. 08/731 ,684 entitled; "Portable Sensing, Communications, And Electronics Intelligence Aircraft Pod Apparatus") which address non dedicated, roll on roll off, pressurized, articulated mechanical mounting systems and process methodologies.

The preferred embodiment of the current invention solves the aforementioned dedicated airframe issues, and permits government authorities, and private operators to undertake response missions, and maximize utilization of cargo and fuel carrying capabilities without modifying the host aircraft. Said system achieves this enhanced portability and mission diversity by meeting the following objectives;

Objective One - minimize or eliminate the requirement for aircraft structural, electrical, and plumbing modifications associated with airborne spraying, refueling, and particulate dispersal.

Objective Two - Maintain aircraft pressurization throughout the entire flight envelope while minimizing induced drag caused by external system appendages.

Objective Three - Enhance simultaneous inboard fuel and cargo carrying capabilities, and reduce the massing envelope of current temporary roll on fuel tank system installations.

Objective Four - Enhance the safety characteristics of current temporary roil on fuel tank system installations, particularly as they relate to ballistics, fire, and crash survivability.

Objective Five - Enhance the versatility of current single mission aircraft platforms, and roll on spray systems to undertake dry particulate dispersal, wet fluid spraying, interoperable NATO and U.S. and Air Force air to air refueling. Objective Six - Enhance the portability and optimum location of the user interface control assembly for aerial spraying, particulate dispersal, and air to air refueling with particular attention focused on creating improved, direct operator standard daylight and night vision goggle visibility of the air to air refueling s operation while maintaining close proximity to said portable user interface assembly.

Objective Seven - Enhance precision host and recipient aircraft positioning and guidance prior to and during air to air refueling operations.

Objective Eight - Enhance the in flight aerodynamic stability and control of the 0 NATO compliant female drogue basket during the air to air refueling process.

Objective Nine - Create a means for simultaneous non dedicated, aircraft sensor utilization and mounting, with accurate GPS based spray dispersal patterns and precise positioning capabilities for air refueling, spraying and dry particulate dispersal. 5 The foregoing objectives are achieved by the preferred embodiment of the present invention which undertakes the integration of novel technologies, systems, and assemblies, without modifying the aircraft, and uses existing palletized cargo loading and handling systems familiar to those skilled in the art of roll on roll off and cargo restraint systems, to undertake temporary installation of the various work 0 response systems. The preceding nine objectives, are achieved by the following components and assemblies,

1) a temporarily mounted, pressurized, roll on roll off, door, panel, or hatch mounted low profile, closed system pressurized, conformal fairing with a flight controllable, female drogue, hose, reel, drogue stabilization system, 5 and guidance positioning assembly such that it does not affect aircraft pressurization,

2) a temporarily mounted, pressurized, roll on roll off, door, panel, or hatch mounted fairing, with articulated, multi axis, telescopic boom, with male and female refueling probe and collapsible drogue and hose assembly, 0 with stabilizing aerodynamic control surfaces to maintain and otherwise remotely trim the position of the refueling boom and drogue assembly, 3) a temporarily mounted, pressurized, roll on roll off, side door mounted articulated fixed mount or telescopic strut or fairing, with multi function capabilities to accommodate a low drag refueling fairing, a refueling pod assembly, a spray assembly, and a dry chemical particulate diffuser assembly,

4) a temporarily mounted, segmented, interconnected, roll on roll off, fire proof, bullet proof, explosion resistant, structurally reinforced, internally baffled, low profile fluid reservoir tank assembly capable of accommodating fuel, chemicals, bioremediation agents, or other liquids, in conjunction with heavy cargo, or passengers on the upper side of said temporary tank assembly,

5) a temporarily mounted, segmented, interconnected, roll on roll off, internally tapered, dry reservoir tank assembly with a pressurization system, and an auger dry particulate feed assembly which can simultaneously accommodate heavy cargo, or passengers on the upper side of said installed temporary tank assembly,

6) a temporarily mounted, pressurized roll on roll off, ram air actuated, low profile, hydraulic, or electrically driven support capability for spraying, refueling, and dry chemical dispersal assembly, 7) a temporarily mounted, portable GPS system used in conjunction with refueling, spraying, and particulate dispersal systems.

8) a temporarily mounted, pressurized door, hatch, or removable panel with the capability of accommodating an operator's seat, a large flat, or protruding observer bubble window, which Is used in conjunction with, and for the purpose of observing the, refueling, spraying, and particulate dispersal systems when deployed in flight.

9) a temporarily mounted, portable user interface system used in conjunction with an infra red, and video monitoring system, or other imaging sensor, and refueling, spraying, and particulate dispersal systems. 10) a temporarily mounted, portable Low Light Television (LLTV) and eyesafe laser ranging system with micro miniature range detecting radar chips and infra red proximity lighting system attached to an articulated male refueling probe or a female drogue basket and hose assembly which Is used in conjunction with refueling systems to determine the proximity of the receiving aircraft to the refueling delivery assembly.

The integration of the foregoing systems, embodied as interchangeable assemblies within the present invention, achieve the foregoing objectives, and provide the roll on roll off capability, with spraying, dry particulate dispersal, and interoperable male, and female refueling capability from one aircraft platform.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG.1 - Is a side view of a Lockheed-Martin C-130 fixed wing aircraft with portable infra red search sensor, a rear ramp roll on, conformal, female drogue assembly variant of the present invention, deployed to effect refueling of a rotary wing

Augusta-Westland EH101 Helicopter equipped with a search and rescue radar and infra red sensing pod, roll on male refueling probe assembly of the present invention.

FIG.2 - Is a side view of a plan view of a Lockheed-Martin C-130 fixed wing aircraft with a portable, forward side door mounted male probe fuel receiving system, and a rear side door pressurized, conformal, female drogue assembly variant of the present invention, deployed through to effect simultaneous refueling of two EH-101 Cormorant search and rescue helicopters depicting flyable drogues to separate the two helicopters which are used in conjunction with the present invention. FIG.3 - Is a frontal view of a Lockheed-Martin C-130 engaged in refueling two EH- 01 Cormorant search and rescue helicopters, depicting helicopter separation, and side mounted fairings equipped with telescopic, retractable sensors.

FIG. 4 - Is a perspective cutaway internal view of a Lockheed-Martin C-130 equipped with various refueling, observation, and fluid tank components of the present invention.

FIG. 5 - Is a cross section view through a Lockheed-Martin C-130 or like aircraft, depicting the various pallet mounted, pressurized pod and reel refueling, operator interface, observation, mounting, articulation, and typical medevac container components of the present invention. FIG. 6 - Is a cross section of a typical aircraft equipped depicting an articulated strut and self-contained externally mounted refueling pod, which does not require internal pressurized housings.

FIG. 7 - Is a perspective view of a low profile fluid or dry particulate tank depicting integration of cargo handling systems. Fig. 8 - Is a perspective view of a low profile fluid or dry particulate tank depicting the internal configuration and baffle assembly. FIG. 9 - Is a perspective view of a low profile fluid tank configured for spraying applications depicting pumping, pressurization, spray nozzle and fairing assemblies.

FIG. 0 - Is a plan view of a Lockheed-Martin C-130 configured for spraying applications depicting aircraft vortices locations, spray nozzle dispersal patterns and fairing assemblies.

FIG. 11 - is a perspective view of a the internal workings of an auger and pressurized dry particulate dispersal tank and fairing assembly

FIG. 12 - Is a perspective view of the internal workings of an auger and pressurized dry particulate dispersal tank with door mounted hopper feed system and fairing assembly.

FIG. 13 - Is a perspective view of a composite observer door panel, and refueling fairing equipped with a retractable sensor gimbal assembly.

FIG. 14 - Is a perspective cutaway view of a composite observer door panel, and combined portable fairing assembly equipped with a high pressure, spray system and aerial refueling assembly.

FIG, 15 - Is a perspective view of an observer door panel, and portable fairing assembly equipped with an aerial refueling assembly, hose and drogue.

FIG. 16 - Is a perspective view of a conventional fluid tank and pumping system, with an articulated telescopic or fixed length strut with multiple spray nozzles, dry particulate diffuser, and JATO stabilization strut attached to a pressurized door plug.

FIG. 17 - Is a frontal view Lockheed-Martin C-130, depicting simultaneous refueling of two EH-101 Cormorant helicopters, denoting articulated strut and refueling fairing assemblies in the upper an lower positions respectively to provide aircraft separation.

FIG. 18 - Is a perspective view of a Lockheed-Martin C-130 equipped with a pressurized door plug assembly refueling two EA-6B's using externally mounted refueling pods on articulated struts. FIG. 19 - Is a Lockheed-Martin C-141 equipped with two articulated struts refueling a Lockheed-Martin C-130 aircraft, and an EH-101 Cormorant helicopter. FIG. 20 - Is a Boeing C-17 equipped with a portable pressurized door and refueling fairing assembly engaged in the process of refueling a United States Coast Guard Sikorsky - H-60 Jayhawk helicopter equipped with a refueling probe equipped temporary fuel pod typical of those manufactured by Sergeant Fletcher. FIG. 21 - Is a C-130 aircraft equipped with an articulated male and female refueling boom engaged in the process of refueling a Lockheed-Martin C-130 Aircraft with the drogue basket retracted and collapsed, and the male probe extended for a USAF standard refueling operation.

FIG 22 - Is a C-130 aircraft equipped with an articulated male and female refueling boom engaged in the process of refueling a USCG Sikorsky H-60 Jayhawk helicopter with the male probe retracted, and the drogue basket and hose assembly extended for a NATO standards refueling operation.

FIG. 23 - Is a perspective view of a removable, portable chair mounted user interface assembly in the open and installed configuration depicting various tactile display interfaces.

DETAILED DESCRIPTION OF THE INVENTION

The invention is now described in terms of the FIGURES to more fully delineate in more detail the scope, materials, conditions, and methods of the present invention. Many of the parts and components of the present invention are hereinafter described as being "assemblies." As used herein, the word "assembly" or "assemblies" refers to the totality of related parts and pieces related to a given component and its operability, and is not to be considered as limiting to a particular part, piece, or operation. INTEGRATED MISSION SYSTEM - In general, the invention comprises a novel design and integration approach in the configuration, capability, and operation of side door, hatch, or other removable pressurized plugs, useful for mounting and operating various types of roll on roll off airborne refueling systems, spraying systems, dry particulate diffusion systems, and fluid spray dispersal systems for use with aircraft in support of search and rescue operations and other missions. One such roll on refueling configuration denoting a fuel delivery aircraft, and a fuel recipient aircraft, is shown in FIG. 1, where a search and rescue Augusta Westland EH101 Cormorant Helicopter 5, equipped with a temporarily mounted Sensor Pod Assembly 18, typical of sensor pod systems disclosed by Woodland in the copending U.S. Patent Application Serial No. 08/731,684, is being refueled by a search and rescue Lockheed-Martin C-130 Aircraft 2, equipped with a side door Gimbal Sensor 44, mounted on the forward crew door, and a JATO Telescopic Sensor Fairing Assembly 51, temporarily attached to the JATO Mount 226, wherein neither aircraft has been modified to undertake the combined search and rescue, and air to air refueling missions. Further mounting and installation methodologies have not hindered, or compromised search sensors, communications, equipment stowage, or air-drop and telemetry of a Marine Rescue Vehicle 13, and associated Marine Rescue Vehicle Telemetry 24, capabilities.

TANK & PUMPING MODULE SYSTEMS - In conjunction with or without the use of said side door Gimbal Sensor 44, and, or Sensor Pod Assembly 18, the preferred embodiment of the present invention is further described in FIGs. 4, 5, 7, 8, 9, 11, and 12, wherein a plurality of, multi mission refueling, spraying, and dry particulate dispersal capable, interconnected, segmented, structural low profile Flat Top Tank Assembly 60, means, are fastened to, or otherwise integrated with a Mounting Pallet 33, means which is installed on board an aircraft, by means of the lower rear ramp, of a Lockheed-Martin C-130 Aircraft 2, using the A/A32H-4A Cargo Handling System 34. Said Flat Top Tank Assembly 60, means being structurally engineered to support, by means of honeycomb and other structurally sound construction methodologies familiar to those skilled in the art of aircraft structures engineering, the carriage of cargo on top of the Segmented Low Profile Tank 61, and to further provide a protective and structural support for fluids, or particulate matter carried inside said Segmented Low Profile Tank 61. Said engineering methodologies and structurally sound practices as they pertain to composite materials are disclosed by Morrisey, in U.S. Patent 4511105, issued on April 16, 1985, entitled "Compartmentβd, Filament Wound, One Piece Aircraft Fuel Tanks" which are portable, but external to the aircraft, and do not address the integration of cargo carrying or handling characteristics. Removable Tank Baffles 66, provide additional structural support and serve to reduce unwanted movement of the fluid contained within the Segmented Low Profile Tank 61. Said Segmented Low Profile Tank 61, being equipped with lower and upper A A32H-4A Cargo Handling System 34, ADS rails, and upper Cargo Bearings 49, systems which are familiar to those engaged in the art of cargo handling, which are used to secure, mission packages, Mounting Pallet 33, systems and cargo on top of the low profile Flat Top Flat Top Tank Assembly 60, means. A means for addressing the necessity of having rapid assembly fuel tanks in a combative environment is disclosed by Arnold, in U.S. Patent 4790350, issued on December 18, 1988, entitled "Combat Rapid Assembly Fuel Tank" which incorporates a pylon mounted, collapsible, rapid assembled, bladder and pod based fuel tank. However, there is no consideration given to ballistics or fire protection. In light of this requirement, particularly in hostile operating areas, As depicted In FIG. 4, said portable roll on roll off Segmented Low Profile Tank 61, incorporates a basic Structural Housing 64, with multiple, optional layers of internally or externally laminated, or fastened material, including a Ballistic Lining

62, typically comprised of Spectra Fiber manufactured by the Du Pont Corporation USA, to prevent the penetration of ballistic munitions, and a Fire Proof Lining 63, typically comprised of refractory ceramic fiber blanket encapsulated with aluminum foil, manufactured by the 3M Corporation of the USA, to prevent said Segmented Low Profile Tank 61 , from detonating as a result of external fire in a crash situation. The structural composition of said Segmented Low Profile Tank 61, may consist of ferrous or non ferrous metals, composite, or plastic materials which are capable of meeting the structural engineering requirements of the present Invention, and are familiar to those skilled in the art of fabricating fuel tanks, .

Further, in the preferred embodiment of the present invention the Segmented Low Profile Tank 61, can be augmented by a second internal, flexible form and volume compliant Bladder Tank 68, similar to those described by Crago et.al. in U.S. Patent 5205427, issued on April 27, 1993, entitled "Modular Fuel Tank System" which discloses a pylon mounted, collapsible, rapid assembly, bladder pod fuel tank for external carriage, and no cargo capability. Said volume compliant Bladder Tank 68, incorporates a plurality of Removable Tank Baffles 66, which fold down with said Bladder Tank 68, for storage when it is emptied f' fluids. Said Bladder Tank 68, particularly conforming to the lower periphery of the Segmented Low Profile Tank 61, Sump Taper 80, to facilitate liquid or dry particulate removal. Said Segmented Low Profile Tank 61, being internally lined with a bladder to permit and otherwise facilitate the utilization of the same structural tank assembly for potable water, alternate chemicals, and different fuel types by simply replacing the Bladder Tank 68, without requiring a dedicated structural tank for each application. Said use of a bladder lining also serves to prevent tank corrosion when potentially corrosive agricultural, herbicides, pesticides, spray chemicals or Nuclear, Biological, and Chemical neutralizing agents are employed with the Spray System Assembly 210. Said Bladder Tank 68, or Removable Tank Baffles 66, being replaced by removing or opening the Flat Tank Lid 76, which can be locked and pivotally hinged to remove a first Bladder Tank 68, and installing a second Bladder Tank 68, or Installing a Dry Tank Assembly 90, kit, consisting of a Dry Particulate Duct 93, an Auger Assembly 94, and a Contoured Dry Tank Liner 95, which when installed, converts the Segmented Low Profile Tank 61, into a dry particulate dispersal system. The Segmented Low Profile Tank 61, is pressurized by means of a

Compressor And Pressurization System 69, which charges the Segmented Low Profile Tank 61, with inert gas to further inhibit explosion and facilitate discharge of the liquid, or dry particulate matter. Such a methodology is disclosed by Goss, U.S. Patent 6021978, issued σπ Feb. 8, 2000 entitled "Anti-Explosion Protection System For Flammable Vapors".

The fluid, dry particulate, or fuel contained within the Segmented Low Profile Tank 61, or Bladder Tank 68, will gravity drain to a Sump 65, which is connected to a universal Pipe Connection Outlet 96, located at the Sump 65, at the end of the Sump Taper 80. Fluid or particulate matter at the Sump 65, is discharged under pressure into the Fluid Piping 71, or Dry Auger Feed System 92, which will in turn deposit said dry particulate matter into a Door/Pallet Mounted Hopper 97, or directly off board of the aircraft to the spraying or diffusing discharge means. With the appropriate Bladder Tank 68, any number of pumping or processing modules may be integrated with the universal Pipe Connection Outlet 96, including but not limited to an Airborne Fuel Pumping Module 70, for air refueling operations, a Dry Auger PTO Module 9 , for dry dispersal operations, a Spray Fluids Pumping Module 86, for aerial spraying applications. The discharge force in either a dry or fluid configuration for airborne applications, is provided by said Spray Fluids Pumping Module 86, or an Airborne Fuel Pumping Module 70, or a Dry Auger PTO Module 91, and augmented by high pressure air from the Compressor and Pressurization System 69. Said Compressor and Pressurization System 69, also provides a means to purge residual fluids and particulate matter from the tanks, bladders, ducts, and piping, which discharges excess fluid out the side door of the aircraft.

Liquid pumping system modules may also effect pumping of fluid to other Segmented Low Profile Tank 61, means for the purpose of transferring fuel or other liquids from the tank for discharge through the air to air refueling system, or spray system, to other on board tanks, or for ground based fuel transfer. Said Compressor And Pressurization System 69, Spray Fluids Pumping Module 86, and Airborne Fuel Pumping Module 70, preferably being of variable flow, constant flow configuration to permit the system operator to dynamically define discharge rates, and maintain a constant rate of discharge. Another advantage of using a plurality of interconnected Segmented Low Profile Tank 61, means permits the carriage of different types, and proportions, of chemicals and water, which can be selected, and discharged as blended or mixed fluids accordingly, and moved from one tank to another as defined by the system operator. Said internal fluid transfer methodologies being familiar to those skilled in the art of aerial refueling and spraying.

Said simultaneous cargo carrying features are depicted in FIG.5 wherein a cutaway view of a Lockheed-Martin C-130 Hercules 2, depicts the simultaneous stowage of a Segmented Low Profile Tank 61, means, in conjunction with a Medevac Container 14. Although Colombo et. al, in U.S. Patent 4458864, issued on July 10, 1984 entitled "Medical Complex For Installation In A Standard Aircraft To Convert It Into An Ambulance Aircraft", the disclosure by Colombo et. Al, of the roll on medevac capability container, does not include integration of the medevac capability with Segmented Low Profile Tank 61, means, or other sensor and fuel refueling receiving, or delivery systems.

Various other emergency response equipment and container assemblies, including but not limited to' M-2 Marine Rescue Vehicle's, as disclosed in the U.S. patent issued to Woodland on January 28, 1997, entitled "Marine personnel rescue System And Apparatus", or other search & rescue equipment containers, and packages may also be carried in conjunction with the Segmented Low Profile Tank 61.

MOUNTING SYSTEMS - As denoted in FIGs. 1 through 5, 9, and FIGs. 11 through 16, the preferred embodiment of the current invention incorporates a modular side door, or Pressurized Plug 31, assembly which can be adapted for mounting on any number of airframe types including a fixed wing aircraft comparable to a Lockheed-Martin C-130 Aircraft 2, or a rotary wing aircraft comparable to an Augusta Westland EH101 Cormorant Helicopter 5. Said Lockheed-Martin C-130 Aircraft 2, can be equipped with a Refueling Probe Receiving System 170, which uses a Carter USA, Type MA-2 or Parker Aerospace of California USA MA-2 nozzle assembly, which is temporarily mounted in the forward crew doors on said aircraft or other fuselage orifices in conjunction with the simultaneous mounting of a pressure plug or side door Conformal Refueling Assembly 130. Alternatively, as depicted in FIG.21 , a USAF standard Female Fuel Receiving Receptacle 180, capability can be adapted with aerodynamic fairing for installation in the upper ditching hatch of a Lockheed-Martin C-130 Aircraft 2, or like aircraft using the "Universal Aerial Refueling Receptacle Slipway Installation (UARRSI)" manufactured by the Parker Hamilton Corporation, of California, USA, which can receive fuel from probe equipped tanker aircraft.

In other aircraft which are not equipped with rear loading ramps, for example a Lockheed-Martin P-3 Orion, aircraft, multiple smaller versions of the segmented tank refueling concept, can be loaded through the crew door to effect temporary installation on dissimilar aircraft using a Pressurized Plug 31, with comparable installation and identical pressure plug and refueling system mounting techniques. However, the present invention is principally intended for rear loaded, aircraft typical of Lockheed-Martin C-130 Aircraft 2. The present invention also allows for use of common mounting components on several types of aircraft including the Lockheed-Martin P-3 Orion, which may, or may not have rear ramp capabilities but will generally incorporate basic mounting components used to deploy and control a work system, comprising a Mounting Pallet 33, a Pressurized Plug 31, a Bubble Observation Panel 282, an Operator Seat 281, to mount a System Interface Assembly 280.

MALE RECEIVING PROBE - As depicted in FIGs. 1 through 4, 10, and 19, the preferred embodiment of the present invention incorporates a temporarily installed Refueling Probe Receiving Assembly 170, primarily intended for helicopters, but also for other fixed wing aircraft also, which provides an ability to receive fuel from another aircraft without modifications. Although Garcia etal. in U.S. Patent 5810292, issued on September 22, 1998, entitled "Aerial Refueling System With Telescoping Refueling Probe" disclose a portable female to male refueling pod with telescopic probe developed for Israeli Air Force Lockheed-Martin F-16's and applicable to other aircraft, the pod is external to the airframe, and requires plumbing to be installed in the wings and fuselage of the aircraft. By contrast the Refueling Probe Receiving Assembly 170, requires no modifications and comprises a Cantilever & Flutter Isolation Armature 174, to mount said Refueling Probe Receiving Assembly 170, a Counterweight 175, located on the inside periphery of the aircraft but preferably comprising a part of the Segmented Low profile Tank 61, assembly to compensate for the weight of said probe, fuel, and armature assemblies, a Probe Fuel Pipe 176, and Cantilever Support 177, which connects with, and otherwise is reinforced and of suitable strength structurally as to transfer and sustain the static and dynamic loads of the Refueling Probe Receiving Assembly 170, fuel, and Cantilever & Flutter Isolation Armature 174, to the Segmented Low profile Tank 61, assembly and a Pressurized Plug 31, which seals and otherwise provides a pressurized interface between the interior and exterior of the aircraft, and isolates vibration from the airframe using pneumatic, rubber, or oil filled isolation seals surrounding the periphery of the Cantilever & Flutter Isolation Armature 174. Said fuel receiving capability may be attached directly to said Segmented Low profile Tank 61, or alternatively be connected by Fluid Piping 71, means, directly to the aircraft's integral fuel tanks. The Refueling Probe Receiving Assembly 170, when used in a fixed length non-extendable configuration requires no actuation to extend or retract. However, if said Refueling Probe Receiving Assembly 170, is required to be telescopic, this can be achieved by methodologies disclosed by Perrella, in U.S. Patent 4540144, issued on September 10, 1985, entitled "Telescoping Fuel Probe" where in fuel pressure acts as hydraulic agent to extend and retract the probe. CONFORMAL REFUELING ASSEMBLY - As denoted in FIGs. 1 , through 5,

13, 14, 15, and 20, the preferred embodiment of the present invention addresses a side door mounted Conformal Refueling Assembly 130, comprised of a Conformal Fairing 131, which can extend beyond the periphery of the door or hatch frame, however, said Conformal Fairing 131, is small enough to be deployed in flight, through the host aircraft door orifice in the side of the fuselage as disclosed by Richard L.K. Woodland US patent 5927648 entitled; "Aircraft Based Sensing, Detection, Targeting, Communications, And Response Apparatus" and the copending U.S. Patent Application Serial No. 08/731,684, wherein Woodland discloses a modular pressurized, door assembly with removable panels. Although aircraft like the Lockheed-Martin EC-130 intelligence and broadcasting aircraft have large ventral fuselage antenna fairings located aft of the paratroop doors, these are permanent installations and cannot be moved between aircraft. Further, although Moss et.al. in U.S. Patent 5667170, issued on September 16, 1997, entitled "Pod Mounted Refueling System" disclose a sideward, fuselage mounted, horizontally oriented pylon or strut with refueling pod, the Moss invention is not portable, creates increased drag, and requires airframe modifications. Hence, the present invention builds upon the novel nature of said removable panels and Pressurized Plug's 31, to incorporate a Conformal Fairing Panel 132, which provides a low aerodynamic drag structural mounting and housing methodology for a female drogue refueling system which deploys the Drogue & Hose Assembly 260, from said Conformal Fairing 131. The present invention also includes a Bubble Observation Panel 282, which provides the system operator with both direct visual, and remote video observation of the refueling process. The fuel transfer mechanical actuating components are located within the periphery of the aircraft fuselage behind the Pressurized Plug 31, and generally comprise a Hose Reel Assembly 133, which deploys the Refueling Hose 135, and associated hard or soft, Collapsible Drogue Basket 264, from the trailing edge of said Conformal Fairing 131. Said Conformal Refueling Assembly 130, in the preferred embodiment of the present invention can also be used in tandem with one or more prepackaged Refueling Pod 152, means typical of the 1080 Refueling Pod manufactured by Aero Union of California, which as depicted in FIG. 5, which is mounted on a Refueling Pod Mounting Cradle 153, and affixed to the Mounting Pallet 33. Further said Refueling Pod 152, means when mounted within the pressurized fuselage of an aircraft, is housed within a first Pressure Vessel 53, means which forms the outside casing of the Refueling Pod 152, and is further connected to a second Pressure Vessel 53, means which encases the Refueling Hose 135, and provides an enclosed Pressure Vessel 53, conduit between the Refueling Pod 152, and the Pressure Plug 31, mounted within the orifice of the aircraft fuselage, as to seal the inboard refueling apparatus from the inside of the aircraft and maintain equilibrium with the outside ambient pressure at refueling altitude, Said Pressure Plug 31, being attached to a Door Plug Mounting Bracket 54, and a Door Plug Swivel Hinge 55, and being moveably installed in the open paratroop doorway of, for example a Lockheed-Martin C-130 Aircraft 2, Further said refueling, spraying, and diffuser system components including, Segmented Low Profile Tank 61, Compressor And Pressurization System 69, Airborne Fuel Pumping Module 70, Fluid Piping 71, Spray Fluids Pumping Module 86, Dry Tank Assembly 90, Dry Particulate^' Duct 93, Dry Auger PTO Module 91, Dry Auger Feed System 92, and Compressed Air/Inert Gas Lines 87, assemblies also comprise component parts of the overall system Pressure Vessel 53, means for refueling, spraying, of dry particulate distribution. Said closed pressure system being engineered and manufactured to standards which permit maintaining fuselage interior pressure values exterior to the pressure system inside the aircraft, and maintaining exterior ambient air pressure values inside the Pressure Vessel 53, means throughout the entire reservoir, distribution, pumping, and dispersal or delivery system regardless of which spraying, refueling, or particulate dispersal application is being employed.

The means described for maintaining separate pressurization values inside said first and second Pressure Vessel 53, means and the interface with the aircraft, is portable, and does not require alteration of installed aircraft pressurizations systems, or structural modifications to the airframe of the host aircraft. Further, as depicted in FIGs. 4 and 5, said Pressure Vessel 53, means are also used to encase and maintain differentia) pressure between the interior cabin of the aircraft and the outside ambient air of the palletized Hose Reel Assembly 133, and

Refueling Hose 135, in vertical, horizontal, single, dual, parallel, or perpendicular mounting and orientation configurations of the Hose Reel Assembly 133, in a manner comparable to that described for achieving differential pressure for the

Refueling Pod 152, when mounted inboard of the aircrafts pressurized fuselage. Said pressure Vessel 53, being equipped with a variety of plumbing, electrical, data, and mounting means common to those involved in engineering and manufacturing aircraft pressure structures.

In order to meet or augment pumping and refueling operations power requirements a Ram Air Turbine 231, as depicted in FIG. 13, can be used to drive an alternator, hydraulic pump, or direct mechanical force transfer system which will meet the pumping and systems requirements. The incorporation of ram air turbine assemblies is well documented within the aerial refueling industry and was also disclosed by Spotswood & Robinson, in U.S. Patent 4905937, issued on March 6, 1990, entitled "Pod Assembly With Integrated Radiofrequency Emitting And Aerial Refueling Equipment" which addressed a composite female refueling pod with vertical hose reel, an Electronics Counter Measures section, and ram air turbine for power. However, Spotswood & Robinson did not contemplate a temporary, roll on, Pressure Plug 31, Installation which, is carried within an aircraft fuselage. ^'

The present invention, also integrates within the Conformal Fairing 131, a hose guillotine mechanism of conventional design, used within the refueling industry to cut or disconnect the Refueling Hose 135, from the host aircraft in the event of an emergency. DROGUE STABILIZATION - As further depicted in FIGs. 1 through 5, 13, 14, 15, 17, 18, 19, 20, and 22, the present invention also addresses the need for an enhanced a flyable, Drogue Stabilization Circular Foil 261, and Drogue Stabilization Air Foil 262, which can be steered to an Approaching Aircraft 22, and provides; a) vertical and horizontal separation of two simultaneously deployed Drogue & Hose Assembly 260, means, b) creates a flat section of Refueling Hose 135, critical for helicopter refueling, c) steers the Drogue & Hose Assembly 260, away from localized, trailing vortices and turbulence pockets generated by the host aircraft, and d) stabilizes the Collapsible Drogue Basket 264. It has been contemplated that an integrated drogue and stabilization airfoil could be combined into one unit, however this would result in the loss of the flat hose segment required for safe helicopter refueling, and would certainly cause damage to the receiving aircraft due to frequent bow wave induced vortices which result in contact with the drogue assembly. For practical and enabling design, ail drogue manufacturers typical of West Coast Netting, of the United States, endeavor to minimize weight in the design of drogues and to keep metallic components to a minimum due to the consequences of uncontrolled aircraft contact and subsequent damage. Hence, the aforementioned desired characteristics are achieved by a plurality of Drogue Stabilization Air Foil 262, means to provide increased directional stability and dynamic, flyable control of the Collapsible Drogue Basket 264. The Drogue Stabilization Air Foil 262, serves as a mounting surface for the actuated Drogue Stabilization Air Foil Trim Tab 263, means attached to the trailing edge of the Drogue Stabilization Air Foil 262, means which act like aircraft flight control surfaces to effect roll, pitch, and yaw moments of the Drogue Stabilization Air Foil 262, assembly. Said Drogue Stabilization Air Foil. Trim Tab 263, means can be controlled by the system operator by means of a Radio Frequency Remote Control Unit 269, with built in batteries of conventional design trickle charged by means of solar photovoltaic cells also of conventional design embedded in the upper surface of the Circular Air Foil 261. Control of the Circular Air Foil 261, Drogue Stabilization Air Foil Trim Tab 263, means may also be achieved by a Hose Data And Electrical Cable 270, integrated within the Refueling Hose 135. In either wireless or hard wired control methodologies, small electro mechanical servo's typical of those used and manufactured by Teledyπe Ryan of San Diego in the micro unmanned aerial vehicle "MALD" being built for the U.S. Air Force are actuated by the system operator, by means of the System Interface Assembly 280.

Further, although Krispin & Velger disclose in U.S. Patent 5326052, issued on July 5, 1994, entitled "Controllable Hose-And-Drogue In-Flight Refueling System", they do not address portability, particularly in a roll on installation, and further base the design on a gas pressurization and thruster arrangement to maneuver the drogue. The methodology described by Krispin and Velger is complex, requiring the incorporation of a charged gas system. Further, the integration of the flyable components on the drogue does not create a segment of flat hose line, which facilitates helicopter refueling. By contrast as depicted in FIGs. 1 and 2 the present invention separates the Drogue Stabilization Circular Air Foil 261, from the Collapsible Drogue Basket 264, and thereby creates the required section of flat Refueling Hose 135, to keep helicopter rotors away from the Refueling Hose 135. The separation of said Drogue Stabilization Circular Air Foil 261, from the Collapsible Drogue Basket 264, is achieved by forward velocity of the aircraft inducing aft moving air which exerts a pulling force on the Collapsible Drogue Basket 264, away from the Conformal Fairing 131, as the Airborne Fuel Pumping Module 70, releases the Refueling Hose 135, until a low profile Male Hose lock 267, integrated at a preset length of Refueling Hose 135, interfaces with a Female Hose lock 268, affixed to the leading edge of the Drogue Stabilization Circular Air Foil 261. When the refueling Hose 135, is retracted, once the Drogue Stabilization Circular Air Foil 261, is stowed within the Conformal Fairing 131, the locking mechanism passively disengages to allow retraction of the remaining Refueling Hose 135, segment. The design also incorporates a plurality of small flexible, axially arrayed Drogue Anti Spin Foils 265, oriented around the Refueling Hose 135, adjacent to the Collapsible Drogue Basket 264, to inhibit spinning of the drogue. Said Drogue Anti Spin Foils 265, are intended to be preset at given incidence angles to. prevent spinning of the drogue around the bell housing.

ARTICULATED BOOM - As depicted in FIG. 21, a first Lockheed-Martin C- 130 Aircraft 2, is equipped with a Conformal Fairing 131, and an interoperable

NATO and U.S. Air Force standards, Articulated Boom Assembly 110, engaged in male probe to female receptacle refueling of a second Lockheed-Martin C-130

Aircraft 2. The Boeing Corporation currently manufactures, an articulated boom assembly for USAF probe based refueling, applications which can provide an adapter for hose and drogue refueling but as yet no, combined notion for simultaneous integration of both male and female capabilities with full extension and retraction capabilities exists. Further, As depicted in FIG. 22 the preferred embodiment of the present invention solves the problem of non dedicated, roll on roll off, interoperability and depicts refueling of a Lockheed-Martin C-130 Aircraft 2, refueling a Sikorsky H-60 Jayhawk 11, helicopter equipped with a portable External Tank And Male Probe Assembly 21, is equipped with a Laser Reflective RF Tag 196, to effect non dedicated localized aircraft position referencing, using a NATO based female refueling system standard. Said Articulated Boom Assembly 110, being of conventional U.S. Air Force compatible boom refueling designs manufactured by the Boeing Corporation of Washington, USA. A pod based male probe articulated refueling system is disclosed on behalf of the Boeing Corporation by Higgs et.al, in U.S. Patent 5996939, issued Dec. 7, 1999, entitled "Aerial refueling boom with translating pivof wherein a ram air turbine for power, and articulated male refueling boom are attached to bottom of a given aircraft in a pod with mounting, pumping, and fuel transfer systems transiting through a modified fuselage. The system disclosed by Higgs et. al. is not roll on, non-dedicated, or NATO/USAF interoperable without ground based installation, and requires considerable modification to the host airframe.

Although it is common practice to integrate a Collapsible Drogue Basket 264, in place of a Male Refueling Probe 114, on an articulated boom assembly as has been demonstrated by various air forces on Boeing tankers, and other aircraft, a combined dual NATO and USAF standards, interoperable, Male Refueling Probe 114, and Collapsible Drogue Basket 264, integrated into one assembly which can deploy either male or female capability from the same Articulated Boom Assembly 110, within a minute of using either standard, without landing the aircraft to exchange fuel interface devices, has not been previously undertaken and js part of the preferred embodiment of the present Invention as depicted in FIGs. 21 and 22. Further the present invention utilizes common practices for articulating, extending, and retracting, the Articulated Boom Assembly 110, which comprises a Boom Multi Axis Joint Assembly 111, which passes from the interior of the aircraft to the exterior of the aircraft by means of a Pressurized Plug 31, and employs mechanical actuation and joint systems typical of those disclosed by Ruzicka, on behalf of the Boeing Corporation, in U:S. Patent 5785276, issued on July 28, 1998, entitled; "Actuated Roll Axis Aerial Refueling Boom", wherein, the boom joint and mounting assembly permits motion about three axis of movement, or alternatively in a two axis system Kerker, U.S. Patent 4586683, issued on May 6, 1986, entitled "Rolling aerial refueling boom" which achieves two axis of boom motion. Further, as depicted in FIGs. 5 and 6, said Articulated Boom Assembly 110, transfers static system loads and dynamic flight loading to a Mounting Pallet 33, assembly by means of a Cantilever & Flutter Isolation Armature 174, which passes through the Pressurized Plug 31, and has a can utilize a Counterweight 175, for heavier loads which require internal compensation for outboard weight as illustrated in the Refueling Probe Receiving Assembly 170, depicted in FIG. 4, affixed to the Mounting Pallet 33, on a plurality of Vibration Damper 37, means to isolate said vibration and dynamic loads. The preferred embodiment of the current invention can accommodate simultaneous deployment of two Articulated Boom Assembly 110, systems from the same aircraft using removable Pressurized Plug 31, means on both sides of the aircraft fuselage thereby meeting the requirement of refueling system redundancy in the event that one system becomes inoperable, particularly in open ocean missions. Further, in FIGs. 21 and 22, said Articulated Boom Assembly 110, has extension and retraction capabilities which permit said Articulated Boom Assembly 110, to be retracted and stowed for transit when not in use and extended when engaged In the process, of refueling comparable to existing systems and methodologies employed aboard Boeing USAF standard KC-135 aircraft and McDonnell Douglas KC-10 aircraft. Said extension and retraction capability being achieved from mechanical actuation, fuel, hydraulic, or pneumatic pressure means common to those skilled in the art of refueling and landing gear actuation, and comprising a Boom 1" Stage Housing 112, which provides a cavity large enough to house a telescopic Boom 2^nd Stage Housing 113, which .provides a cavity large enough to house a telescopic Male Refueling Probe 114, which is equipped with a Boom Air Foil Stabilization Assembly 115, typical of systems disclosed by Anderson etal., U.S. Patent 4095761, issued on June 20, 1978, entitled "Aerial Refueling Spoiler", and Ishimitsu & Tinoco, U.S. Patent 4231536, issued on Nov. 4, 1980, entitled "Airfoil For Controlling Refueling Boom" to stabilize and provide dynamic control of the boom throughout its full range of motion in flight.

Further, as depicted in FIG 21, said Articulated Boom Assembly 110, also provides a mounting surface for a Video Laser Housing 203, denoting Video Field Of view 201 , and other lighting assemblies required for indication and illumination during refueling operations.

In the preferred embodiment of the present invention, the combined Articulated Boom Assembly 110, integrates a Male Refueling Probe 114, comparable to that disclosed by Oliver et.al., U,S. Patent 5092194, issued on March 3, 1992, entitled "Deployment Arrangemenf of a collapsible or retractable male refueling probe, which in the present invention is located on the upper side of the Boom 2^nd Stage Housing 113, and incorporates the Collapsible Drogue Basket 264, on the lower side of the Boom 2"^d Stage Housing 113, as to effect deployment of either male or female fuel transfer systems without interfering with the other due to aerodynamic forces exerted on said Articulated Boom Assembly 110, in flight. The present invention also incorporates standard.

The present invention can also accommodate a composite solution on a Lockheed-Martin C-130 Aircraft 2, or like aircraft with two side doors located on either side of the rear fuselage, wherein a non dedicated, roll on roll off, NATO compliant Conformal Refueling Assembly 130, with female Collapsible Drogue Basket 264, is mounted on the port side of the aircraft while an Articulated Boom Assembly 110, with Male Refueling Probe 114, is mounted on the starboard side of the aircraft.

REFUELING STRUTS - As depicted in FIGs. 5, 6, 17, 18 and 19, the preferred embodiment of the present invention also utilizes a multi-function, multi- mission, articulated strut assembly, which passes through a temporarily mounted Pressurized Plug 31, in an aircraft fuselage, and effects articulation of a Fixed length strut 222, or a Telescopic Articulated Strut 218, wherein one variant depicted in FIGs. 5 and 19, integrates a Strut Refueling Fairing Assembly 150, which is capable of articulating vertically in flight by means of two Vertical Actuator 216, assemblies, to permit simultaneous refueling from both sides of the aircraft. Fixed length strut 222, can also be a Telescopic Articulated Strut 218, capable of extending in a telescopic fashion by mechanical actuation, fuel pressure, hydraulic pressure, or pneumatic pressure, means, common to those familiar with the art of aircraft landing gear and strut assemblies to provide enhanced horizontal wing tip separation between two aircraft as denoted in FIG.s 17, and 19. When used in tandem on both sides of the aircraft, means comparable to the configuration and installation of the Articulated Boom Assembly 110, are applicable to the Strut Refueling Fairing 150, assembly which houses a female drogue, hose, and pulley, within said Strut Refueling Fairing 150, and palletized hose, reel, pumping and low profile tank and cargo assembly inboard of the aircraft fuselage.

Said Strut Refueling Fairing 150, assembly comprises a Strut 1^εt Stage Housing 213, a Strut 2^nd Stage Housing 214, a Telescopic Articulated Strut 218, and a Strut Refueling Fairing 150, which can be stabilized at the outboard periphery by a JATO Compression Stabilizer Strut 217, when mounted on a Lockheed-Martin C-130 Aircraft 2, which is attached to the Jet Assisted Take Off or JATO Mounts 226, mounts on the main gear fairings of the fuselage without incurring any airframe modifications as depicted in FIGs. 16, 17, and 18, Although the Able Corporation of the USA, has developed a similar strut and fairing concept employing a horizontal movement, piston actuation system and has disclosed same in U.S. Patent 5573206, filed by Ward issued on November 12, 1996, entitled; "Hose And Drogue Boom Refueling System, For Aircraft", the patent specifically indicates in the "Summary Of The Invention" that the invention requires fewer structural modifications, and in the "Detailed Description" of the Invention indicates the fuselage may bulge to accommodate features of the invention, further indicating airframe modifications. The preferred embodiment of the present invention uses a Fixed length strut 222, or a Telescopic Articulated Strut 218, which passes through a Pressure Plug 31, assembly without incurring any airframe modifications, even on aircraft not equipped with rear loading methodologies comparable to a Boeing 767 aircraft, which still possesses cargo floor restraint systems which do not require a Mounting Pallet 33, assembly.

The Strut Refueling Fairing 150, assembly as installed on a Lockheed-Martin C-141 Stariifter 10, is depicted in FIG 19 refueling a Lockheed-Martin C-130

Aircraft 2, and an Augusta Westland EH-101 Cormorant Helicopter 5, without any

JATO Compression Stabilizer Strut 217, means using a Telescopic Articulated Strut

218, with a Strut Refueling Fairing 150, which is equipped with a Drogue And Hose Assembly 260, depicting controlled separation of . the aircraft for simultaneous refueling. FIG 19, also indicates an arc of movement to retract said Telescopic Articulated Strut 218, rearward against the fuselage for higher speed transit when not engaged directly in refueling operations. Further, FIG. 16 also indicates retraction and extension movements of said Telescopic Articulated Strut 218, assembly in a spray configuration as mounted through a pressure Plug 31, and installed on a Lockheed-Martin C-130 Aircraft 2.

Further as depicted in FIGs. 6, and 18, the present invention also permits removal of the Strut Refueling Fairing Assembly 150, and elimination of all inboard fuselage pumping systems, to accommodate prepackaged, bolt on refueling pods typical of those manufactured by Sargent Fletcher, and Aero Union of the USA. A similar concept is disclosed by Moss et.al. in U.S. Patent 5667170, Issued on September 16, 1997, entitled "Pod Mounted Refueling System" which discloses a pylon, and female hose and drogue refueling pod to mounted at the end of the pylon away from aircraft fuselage. However, Moss fails to disclose any form of portable mounting methodology, low profile fuel tanks, simultaneous cargo carrying capability, guidance system, or roll on methodology.

When a Refueling Pod 152, means is used with a Telescopic Articulated Strut 218, or a Fixed length strut 222, the Strut Refueling Fairing 150, is removed and said Refueling Pod 152, comparable to the Aero Union 1080 pod, or Sargent Fletcher hose and female drogue refueling assembly is attached as depicted in FIG. 6, and in particular FIG 18, where a Lockheed-Martin C-130 Aircraft 2, is engaged in refueling two, Northrop Grumman A-6E Prowler Approaching Aircraft 22, using said Telescopic Articulated Strut 218, and Refueling Pod 152, assembly. SPRAY SYSTEM - As depicted in FIGs. 9, 10, 14, and 16, the present invention also includes adaptation of the roll on Segmented Low Profile Tank 61, assembly for use with a Spray Fluids Pumping Module 86, and a Spray System Assembly 210, to effect aerial spraying while the aircraft is pressurized. Said Spray System Assembly 210, comprising at least one and preferably a plurality of Spray Nozzle 211, means, with variable flow rate head adjustment, connected to Fluid Piping 71, means to transfer the Spray Fluid 221, contained within a single or multiple Segmented Low Profile Tank 61, means, with flat upper surfaces for cargo carrying capabilities, or Conventional Fuel/Spray Tanks 225, under pressure from a 529

31

Spray Fluids Pumping Module 86, to a spray dispersal assembly mounted outboard of the aircraft.

The present invention as depicted in FIGs 9, 10, 14, and 16, relative to aerial spraying first addresses one of three pressurized door plug aerial spraying methodologies which all use common tank, pumping, pressurized plug mounting, and piping means for portable non dedicated spraying applications.

The first and preferred embodiment of the present invention as depicted in FIGs 9, 10, and 14, is of a Conformal Fairing 131, which incorporates a simplified aerial spraying system for use while the aircraft is pressurized, or unpressurized. Said Conformal Fairing 131, providing an aerodynamic, low drag, mounting surface for integrating Fluid Pipe 71, means which are connected to a plurality of Cofealis Effect Fluid Line Straighteπers 233, commonly used in fire hose and nozzle assemblies to provide a more concentrated, longer stream of fluid. Said Corealis Effect Fluid Line Straighteners 233, are in turn connected to a Variable Nozzle Array 224, oriented approximately 45 degrees aft and sideways from the aircraft fuselage such that the nozzles are sized smaller to larger from the leading edge to the trailing edge of the Variable Nozzle Array 224, and that Fluid Line 71, means are of various sizes going from larger diameter at the leading edge to smaller diameter towards the trailing edge of the Conformal Fairing 131, as to effect a concentrated, straightened, controlled dispersal pattern which accommodates the forward motion of the aircraft, and ejects the Spray Fluid 221, to point "X" just below, and aft of the horizontal tail stabilizer wing tip noted on FIG.10 to mix with the stabilizer wing tip Wake Vortices 303, and also in like manner ejects the Spray Fluid 221, to point "Y" downstream aft of the main wing tip noted on FIG.10 to mix with the main wing tip Wake Vortices 303, of the aircraft. This fluid spraying methodology provides a means for achieving less drag, portable non-dedicated installation, and effects a more uniform and wider distribution of the Spray Fluid 221, by means of the tail and wing tip Wake Vortices 303. As depicted in FIG. 9, the preferred embodiment of the present invention may also use a single High Volume Nozzle Assembly 228, an use a higher volume flow rate of Spray Fluid 221 , targeted at either point "X", or Point Υ", and still achieve acceptable mixing rates and dispersal patterns for even dispersal of the Spray Fluid 221, within the trailing Wake Vortices 303, of either the taif or main wing tips. 29 ^

Further, said Spray Fluids Pumping Module 86, or the individual Spray Nozzle 211, assemblies may also be used to oscillate in rapid sequence the supply of Spray Fluid 221, thereby providing intermittent pulses of said Spray Fluid 221, and further gain a more even distribution once the Spray Fluid is injected into the high speed air stream of the aircraft. This method of oscillating pulses of water is common practice in household bathroom shower-head hardware, typical of those systems manufactured by the Teledyne Corporation of the USA.

As depicted in FIG 13 and 14, the present invention as it relates to the Conformal Fairing 131, Spray System Assembly 210, may also be mounted in tandem with other work systems, sensors, or power generation systems for self contained, augmented, or dual mission scenarios, including the integration of a retractable Gimbal Sensor 44, or other sensor, a Conformal Refueling Assembly 130, system, a Ram Air Turbine 231, a Dry Particulate Dispersal Fairing 230, or other systems disclosed herein to obtain combinations of capability obvious to those skilled in the art of integrated mission response systems.

Further as disclosed by Rameth, in U.S. Patent 5320282, issued on June 14, 1994, entitled; "Aerial Sprayer" or other fixed wing aircraft means typical of the system disclosed by Ryle, U.S. Patent 4180224, issued on December 25, 1979, entitled; "Aerial Dispersal System" which describes a plurality of trailing edge movable airfoils to disperse a fluid medium, or a novel way of integrating upper or lower control surfaces for agriculture -spraying biplanes as described by Wilson, U.S. Patent 4278221, issued on July 14, 1981, entitled; "Agriculture Spray Plane", all have described airframe modified, wing foil type of spray systems, which typically use the trailing edge of wing, or airfoil appendages mounted beneath a given wing assembly, or attached to the fuselage using various means of controlling fluid droplet size, which require airframe modifications. Further said spray systems or are not portable, and do not spray fluids into the trailing vortices of the host aircraft but rather seek through mounting, rails, multiple nozzles, spray orifices, and the like to achieve even dispersal of the fluid medium across the length of a given strut, boom, or airfoil assembly.

Further based upon more conventional methods of spraying as described by Rameth, Ryle, Wilson and others, several derivatives of the present invention are also disclosed which use more conventional spray methodologies but still embody the preferred non-dedicated side door, pressurized mounting system for a common interchangeable portable pressure Plug 31, and Spray System Assembly 210, as disclosed and depicted in FIG. 16, wherein the present invention may also incorporate a Strut 1^=l Stage Housing 213, and an extended telescopic Strut 2^nd Stage Housing 214, through to the third and final Telescopic Articulated Strut 218, assembly. Said Spray System Assembly 210, strut means when employing telescopic extension and retraction capabilities, are actuated and extended laterally away from the side of the aircraft for example, the side of a Lockheed-Martin C-130 Aircraft 2, by means of telescopic actuators common to those skilled in the art of aircraft flap and landing gear actuation systems. Said Spray System Assembly 210, being actuated vertically by means of a Vertical Actuator 216, and extended in the horizontal range of motion to retract said assembly aft for transit by a Horizontal Actuator 178, means and otherwise stabilized against aerodynamic forces caused by forward flight on Lockheed-Martin C-130 Aircraft 2, by means of a . JATO Compression Stabilizer Strut 217, affixed to the JATO mounts on said Lockheed- Martin C-130 Aircraft 2. Said JATO Compression Stabilizer Strut 217, may also employ means of mechanical actuation using a piston comparable to the aerial refueling methodology disclosed by Ward in U.S. Patent 5573206, issued on November 12, 1996, entitled; "Hose And Drogue Boom Refueling System, For Aircraft". However, the application clearly denoted here as part of the preferred embodiment of the present invention is for a temporarily mounted spray system which transits through a removable, Pressure Plug 31, and not through some other form of modified fuselage panel.

Other variants of a spray strut assembly also include a Fixed Length Strut 222, as depicted m FIGs. 5, and 6, adapted for spraying, and actuated vertically by a Vertical Actuator 216, and stabilized against high speed wind by a JATO Compression Stabilizer Strut 217. Said Fixed Length Strut 222, adapted for spraying, transferring Spray Fluid 221, through the internal portions of the strut assembly by means of Fluid Piping 71, assembly and discharging them along the trailing edge of the Fixed Length Strut 222, by means of a plurality of Spray Nozzle 221, means.

Said Spray System Assembly 210, flow rate, dispersal pattern, strut assembly extension, retraction, elevation, and lowering, being affected from the System Interface Assembly 280. Said Spray System Assembly 210, as they may utilize a fixed or variable length telescopic spray strut assembly, may be terminated at the end of the Telescopic Articulated Strut 218, or Fixed Length Strut 222, assemblies by a fairing of conventional design comparable to fairings used for terminating wing tips on aircraft, which may or may not, also be equipped with a Whitcomb Winglet, or other aerodynamic empennage to control lift, to neutralize adverse vortices, or to induce vortices which augment the spread of the Spray Fluid 221.

Further as depicted in FIGs. 1, 4, 10, 23, and 24, the present invention also addresses the requirement for a portable fluid spray & particulate Precision Dispersal Control System 240, comprised of a GPS Antenna And Fairing 27, which receives an RF based GPS Transmission 26, from a GPS Satellite 25, and displays said location data on an ATIMS Moving Map Display 242, a Geographic Information System 243, software engine, a forward cockpit Yoke Mounted Display 243, a Bioremediation Ballistic Winds Sensor 52, a special mission detection sensor 244, comprised of an infra red sensor, hyperspectral sensor, microwave radiometer, or other specialized biological, chemical, or radiation sensor, a Digital Terrain Modeling Database 245, a Computer 294, and System Interface Assembly 280, which effects precise location and release control of fluid or particulate matter dispersal over an authorized Spray Zone 246, and discontinues when the aircraft approaches a GPS correlated No Spray Zone 247, determined by said portable Computer 294, which also permits operator override for manual control of the dispersal system. The Precisian Dispersal Control System 240, is now in partial use with GPS, a user interface, and electronic map display with the Youngstown, Ohio, U.S Air Force Reserve Command's 910th Airlift Wing which are using a Differential Global Positioning System (DGPS), capability combined with computerized maps and satellite imagery, to attain substantially better delivery accuracy. However the system employed by the 910th Airlift Wing is not designed to integrate and analyze dynamic weather, humidity, temperature, wind direction, or other specialized sensor inputs typical of a Bioremediation Ballistic Winds Sensor 52, manufactured by Coherent Technologies of Colorado USA, or other mission specific sensors for in- situ dynamic flight response to mitigate, airborne chemical, biological, or radiation agents. Neither are existing systems designed to integrate with a roll on non dedicated, zero modification fluid or particulate dispersal system. DRY PARTICULATE DISPERSAL - As depicted in FIGs. 11,12, and 16, the preferred embodiment of the present invention also includes adaptation of the roll απ Segmented Low Profile Tank 61, to a Dry Tank Assembly 90, which relays said dry particulate matter using the Compressor And Pressurization System 69, in conjunction with a Dry Auger PTO Module 91, and Dry Auger Feed System 92, located within the ducting assembly which is similar to methodologies described by Sellards in, U.S. Patent 3559930, Issued on Feb. 2, 1971, entitled; "Distribution Of Particulate Material" to move and otherwise deposit said dry particulate matter into a Dry Particulate Duct 93, assembly which under pressure and with mechanical auger means common to those skilled in the art of farm implements, and crop dusting material handling systems, relays said particulate matter through the Strut 1^al Stage Housing 213, and the extended telescopic Strut 2^nd Stage Housing 214, through to the third and final Telescopic Articulated Strut 218, assembly where it connects with, a Dry Particulate Dispersal Fairing 230, which is interchangeable with the Strut Refueling Fairing 150, affixed to the end of the Telescopic Articulated Strut 218. Once the particulate matter has been relayed to the Dry Particulate Dispersal Fairing 230, assembly, negative intake pressure is provided by a free turning Ram Air Turbine 231, assembly, which receives mechanical energy from ram air derived from forward motion of the host aircraft, and is ingested through a

I Diffuser Air Intake Nacelle 238, which turns the Ram Air Turbine 231, assembly, at high speed and thereby creates a vacuum which draws the particulate matter through the Diffuser Dry Particulate Intake Vent 236, into the Diffuser Air Intake Duct 235, and into the Door/Pallet Mounted Hopper 97, assembly, Althouse & Wilcock, U.S. Patent 5671869, Issued on Sept. 30, 1997, entitled; "Fiber Chaff Disseminator" which discloses a chaff side oriented chaff hopper, or comparable to or directly into the Diffuser Ejection Assembly 234, where the dry particulate matter is directed mechanically under forced air pressure and rotationaliy actuated mechanical vanes to a Diffuser Dispersal Exhaust Vent 232, which is divided along its width by a plurality of variable spaced diffuser vanes which expand to form a wider Intake aperture the further away from the Diffuser Dry Particulate Intake Vent 236, the dry particulate matter must travel for the purpose of creating an even intake volume and consequent even dispersal pattern across the width of the Diffuser Dispersal Exhaust Vent 232. Further, as depicted in FIGs.H, and 12, the preferred embodiment of the present invention comprises a Dry Particulate Dispersal Fairing 230, assembly, which can be integrated as part of a single fixed position Conformal Fairing 131, attached to a Pressurized Plug 31, that does not require the Strut 1^al Stage Housing 213, the extended telescopic Strut 2^nd Stage Housing 214, or third Telescopic Articulated Strut 218, assemblies. Said alternate and low aerodynamically designed Conformal Fairing 131, mounted dry particulate dispersal system configuration is preferred over fixed length or telescopic, or actuated strut systems due to simplicity, reliability, and aerodynamic qualities while achieving comparable dispersal patterns.

GUIDANCE 8. PROXIMTY WARNING - As depicted in FIGs. 1 , 2, 5, 15, 20, and 21, a portable ranging and positioning refueling proximity location system which can be affixed to the Articulated Boom Assembly 110, the Conformal Refueling Assembly 130, the Strut Refueling Fairing 150, or the Strut Refueling Pod 152. The operating methodology of said Refueling Proximity Location System 190, is graphically depicted in the figure sequence denoted in FIG. 1, where the sensor, lighting, transmitter, and positional components which integrate to provide the capability for said refueling proximity location system, and generally comprise a localized radio frequency directional beam emitted from an RF Direction Finder Transmitter 192, located on the Host Refueling Aircraft 23, which can guide said Approaching Aircraft 22, to the proximity of the Host Refueling Aircraft 23, which has derived accurate position coordinates from at least one, and preferably two or more Lighted GPS Transmitter and Antenna 193, assemblies, affixed to the boom, strut, fairing, hose or pod refueling systems which are temporarily mounted on the Host Refueling Aircraft 23, and, or from Pressurized Plug 31, mounted GPS Antenna And Fairing with inboard transceiver and processor assembly. Further, Once the Approaching Aircraft 22, is in the proximity of the Host Refueling Aircraft 23, localized sensors are able to scan, range and derive the exact three dimensional GPS location of the Approaching Aircraft 22, within a controlled cartesian space of relative parameters which are then referenced with known computer based, three dimensional, solid model or wire frame datasets of the Approaching Aircraft 22, the Host Refueling Aircraft 23, the Male Refueling Probe 114, and the Collapsible Drogue Basket 264, refueling appendages. Further said Approaching Aircraft 22, may also be equipped with a portable handheld, eye safe, Laser Reflective RF Tag 196, which is used in conjunction with a Laser Illuminator 195, to provide a known reference point to calibrate said three dimensional solid model, if the pilot of Approaching Aircraft 22, carries said hand held, Laser Reflective RF Tag 196, which can be affixed to the front of the cockpit heads up display, or the inside part of the windshield with temporary fastening or adhesive means. The exact positions of these assemblies are then displayed on the System Interface Assembly 280, housed within the Host Refueling Aircraft 23.

Said accuracy and dataset referencing of the Approaching Aircraft 22, in relation to the Host Refueling Aircraft 23, is also enhanced by several sensors comprising at least one and preferable several, micro miniature, short range Radar Proximity Detection System 191, means, typical of integrated radar/antenna chip sets manufactured by Time Domain of the USA which are used to provide all weather,- general distance ranging information between the position of the Approaching Aircraft 22, and the Host Refueling Aircraft 23. In the preferred embodiment of the present invention, said proximity and ranging sensor means also comprise a scanning, range gated, eye safe Laser Illuminator 195, comparable to system manufactured by Cyberware of the USA, which can undertake multiple scans every second of the Approaching Aircraft 22, to obtain dynamic, relative distance, relative position, speed, and exact attitude configuration of the Approaching Aircraft 22, and relay this data to a Computer 294, located on the Host Refueling Aircraft 23, which interprets, and displays the data for the system operator to use, and based upon archival performance and engineering data, can determine if the Approaching Aircraft 22, is within safe flight parameters for air to air refueling, and if not Initiate either an automatic or operator controlled disconnect, or alter approach and speed of either aircraft accordingly if required. Support for the aforementioned refueling proximity location system, and methodology is substantiated In typical processing, archival data, and dynamic data fusion, routinely undertaken in simulators operated by the U.S. Air Force, which run on Intel processor based Windows NT platforms using simulation software from the Paradigm Corporation of the USA, which can effect real time simulated response to refueling operator and pilot control inputs.

The present invention also addresses visual cues under VFR flight conditions wherein the preferred embodiment of the present invention comprises Indicator Lights 197, consisting of red, yellow, and green to provide the pilot of an Approaching Aircraft 22, with Night Vision Goggle (NVG) compatible shape and color indicators which can be interpreted by the pilot under NVG situations. Said visual cues also incorporate either visible light or infra red activated broad area illumination for standard visible light, or NVG/IR filtered video use, under covert, or nighttime conditions without disclosure using an Infra Red/Visible Spot Light 200, affixed to the temporarily mounted boom, strut, or fairing, components.

Further the present invention also recognizes and solves the problem of maintaining visual contact between the system operator on the Host Refueling Aircraft 23, and the Approaching Aircraft 22, by means of a plurality of LLTV/ALLTV Video Camera 199, means, which are affixed to the temporarily mounted boom, fairing, stabilizing downrigger, drogue basket, strut or pod components and displayed at the System Interface Assembly 280.

Further, the Conformal Refueling Assembly 130, as depicted in FIG. 20, installed aboard a McDonnell Douglas C-17 12, aircraft engaged in refueling a Sikorsky H-60 Jayhawk 11, helicopter equipped with a portable External Tank And Male Probe Assembly 21,, typical of those proposed by Garcia et.al. in U.S. Patent 5810292, issued on September 22, 1998, entitled "Aerial Refueling System With Telescoping Refueling Probe" on behalf of the Sargent Fletcher Corporation of California, may be equipped with a modified Garcia θt. al "Aerial Refueling Tank System (ARTS)" External Tank And Male Probe Assembly 21, which is equipped with a Laser Reflective RF Tag 196, to effect non dedicated localized aircraft position referencing without installing the system on said Sikorsky H-60 Jayhawk 11, helicopter. SYSTEM INTERFACE - FIG. 23 - Is a^> perspective view of a non-dedicated, combined sensor, spraying, refueling, or dry particulate dispersal system, seat mounted, operator control station which houses a plurality of components and interface devices, collectively referred to. as the System Interface Assembly 280. The chair and pallet assembly are disposed within the airframe of the host aircraft and serve as the operator's control platform for controlling the temporarily mounted sensors, spraying, refueling and other components related thereto. The operator or observer sits in the Operator Chair 281, which is slidably connected to Operator Chair Rails 296. The Operator Chair Rails 296 effect forward and aft motion of the chair assembly and are in turn fastened to a Mounting Pallet 33. Mounting Pallet 33 can be moveably positioned and fixed to the aircraft floor using methods known in the art of pallet loaded aircraft, as disclosed in the aforementioned copending U.S. Patent Application Serial No. 08/731,684. The purpose of the placement as shown and described is to provide for optimum ease of operation and ergonomically sound layout for a variety of users. Person's skilled in the art of aircraft mounted control systems will recognize the advantages of each of the components described herein, both in their presence as well as their placement. In general, the components described herein permit an operator to have joystick control and keyboard (i.e., computer keyboard) interface control while at the point of observation and control of the refueling, spray, or particulate diffuser system and related components.

Said System Interface Assembly 280, comprising a Removable User Interface Assembly 284, which is typically mounted in temporary fashion, to the Operator chair 281, by means of an arm rest interface slip mount, which slides over both Armrest 297, mean s, without modifying said Operator Chair 281. Said Operator Chair 281, and connected System Interface Assembly 280, is oriented outward in a manner which is disposed to look through a Bubble Observation Panel 282, mounted within the Pressurized Plug 31, for the purpose of visually monitoring refueling events under day and night conditions using night vision goggles. Said Operator Chair 281, is preferably attached to the mounting pallet 33, to take advantage of the Bubble Observation Panel 282, however, said Removable User Interface Assembly 284, can be affixed to any crew chair within the aircraft for remote location control and operation of the temporarily mounted sensors, spraying, refueling and other work assemblies. Said System Interface Assembly 280, comprises a High Resolution Ruggedized LCD 290, for display of video, sensor, and system control attributes. When the operator so desires the High Resolution Ruggedized LCD 290, can been closed, to permit the system operator to use the backside of the said High Resolution Ruggedized LCD 290, to write on or for manned observation using an integrated removable Foam Leaning Bar 285, which is attached to the back of the High Resolution Ruggedized LCD 290, to permit the system operator, or search and rescue observer to lean forward and look through the Bubble Observation Panel 282, or to permit greater access and to undertake other control functions at, for example, a navigator's station. Said Removable User interface Assembly 284, incorporates a variety of tactile user interface devices including a Pointing Stylus 287, a Trackball 288, a Keyboard 289, a pair of Foam Wrist Pads 291, disposed on both sides of the tray assembly, and extending off the periphery in the direction of the operator, to reduce impact and stress on the operator's wrists, and a Joystick 292, which can be installed for left or right hand operation. The preferred embodiment of the present design is hard wire connected to a Computer 294, connected to the various sensors, work systems, positioning and guidance systems, aircraft power, and 1552 data bus using a Data And Power cable 298, means. Said Computer 294, can use Unix, or Windows NT, operating systems, and can be adapted to use a variety of ruggedized, high speed or proprietary computer processors. Interface with said computer processing and visual data functions, is principally by means of a variety of software control interfaces, which are actuated by the aforementioned interface devices. However, the present invention can also include a plurality of tactile switches for electro mechanically initiated functions of the various systems.

While preferred embodiments have been shown and described, various substitutions and modifications may be made without departing from the spirit and scope of the invention. Accordingly it is to be understood that the present invention has been described by way of illustration and not limitation.

Refueling Proximity BWatϊon System,

Rθder Proximity Detection System 191,

RF Direction Finder Transmitter 192,

Lighted GPS Transmitter And Antenna 193,

Laser Illuminator 195, ,^:

Laser Rθfigctive RF Tag 196, indicator Lights 197, ■

LLTV/ALLTV Video Camera 199,

Infra RedA/isible Spot Light 200,

Video Field Of View 201.

Radar Deteotion Field Of View 202,

Video/Laser Housing 203,

RF Direction Finder Transmission 204,

Spray System Assembly 210

Spray Nozzle 211,

Mounting & Interface Assemblies Strut 1^a Stage Housing 213,

Pressurized Plug 31, Strut 2"" Stage Housing 214.

Mounting Pallet 33, Vertical Actuator 216,

A/A32H-4A Cargo Handling System 34, JATO Compression Stabilizer Strut 21 ,

Vibration Damper 37, Telescopic Articulated Strut 218,

Side Door Articulated Sensor Strut 43, Spray Fluid 221 ,

Gimbal Sensor 44, Fixed Length Strut 222,

Cargo Bearings 49, Variable Nozzle Array 224,

JATO Telescopic Sensor Fairing Assembly 51, Conventional Fuel/Spray Tanks 225,

Bioremediation Ballistic Winds Sensor 52, JATO Mount 226,

Pressure Vessel 53, Wake Vortices 227,

Door Plug Mounting Bracket 54, High Volume Nozzle Assembly 228,

Door Plug Swivel Hinge 55, Corealis Effect Fluid Line Straighteπer 233,

Flat Top Tank Assembly Dry Particulate Dispersal Fairing 230

Segmented Low Profile Tank 61, Ram Air Turbine 231,

Ballistic Lining 62, Diffuser Dispersal Exhaust Vent 232,

Fire Proof Lining 63, Diffuser Ejection Assembly 234,

Structural Housing 64, Diffuser Dry Particulate Intake Vent 236,

Sump 65, Particulate Matter 237,

Removable Tank Baffles 66, Diffuser Air Intake Nacelle 238,

Bladder Tank 88,

Compressor And Pressurization System 69, Precision Dispersal Control System 240,

Airborne Fuel Pumping Module 70, ATlMS Moving Map Display 242,

Fluid Piping 71, Geographic Information System 243,

Tank Lid 76, Yoke Mounted Display 243,

Sump Taper 80, Digital Terrain Modeling Database 245,

Spray Fluids Pumping Module 86, Spray Zone 248,

Compressed Air/Inert Gas Lines 87, No Spray Zone 247,

Dry Tank Assembly 90 Drogue & Hose Assembly 260 Dry Auger PTO Module 91, Flyable Drogue Stabilization Circular Foil 261, Dry Auger Feed System 92, Drogue Stabilization Air Foil 262, Dry Particulate Duct 83, Drogue Stabilization Air Foil Trim Tab 263, Auger Assembly 94, Collapsible Drogue Basket 264, Contoured Dry Tank Liner 95, Drogue Anti Spin Surfaces 265, Pipe Connection Outlet 96, Male Hose lock 267 Door/Pallet Mounted Hopper 97, Female Hose lock 268,

Radio Frequency Remote Control Unit 269,

Articulated Boom Assembly 110, Hose Data And Electrical Cable 270,

Boom Multi Axis Joint Assembly 111,

Boom 1" Stage Housing 112, System Interface Assembly 280

Boom 2^rd Stage Housing 113, Operator Seat 281,

Male Refueling Probe 114, Bubble Observation Panel 282,

Boom Air Foil Stabilization Assembly 115, Removable User Interface Assembly 284,

Foam Leaning Bar 285,

Conformal Refueling Assembly 130, Pointing Stylus 287,

Conformal Fairing 131 , Trackball 288,

Hose Reel Assembly 133, Keyboard 289,

Refueling Hose 135, High Resolution Ruggedized LCD 290,

Strut Refueling Fairing 150, Foam Wrist Pads 291,

Refueling pod 152, Joystick 292,

Refueling Pod Mounting Cradle 153, Computer 294,

Operator Chair Rails 296

Refueling Probe Receiving Assembly 170 Armrest 297,

Cantilever & Flutter Isolation Armature 174,

Data And Power Cable 298,

Counterweight 175,

Probe Fuel Pipe 176,

Cantilever Support 177,

Horizontal Actuator 17B,

Pulley 179,

Female Fuel Reαeiviπg Receptacle 180,

Claims

I claim:

1. A roll on - roll off,- portable aerial spraying, particulate dispersal, and refueling systems apparatus.

2. The apparatus according to claim 1 comprising a temporarily mounted, pressurized, roll on roll off, door, panel, or hatch mounted low profile, closed system pressurize, conformal fairing with a flight controllable, female drogue, hose, reel, drogue stabilization system, and guidance positioning assembly such that it does not affect aircraft pressurization.

3. The apparatus according to claim 1 comprising a temporarily mounted, pressurized, roll on roll off, door, panel, or hatch mounted fairing, with articulated, multi axis, telescopic boom, with male and female refueling probe and collapsible drogue and hose assembly, with stabilizing aerodynamic control surfaces to maintain and otherwise remotely trim the position of the refueling boom and drogue assembly.

4. The apparatus according to claim 1 comprising a temporarily mounted, pressurized, roll on roll off, side door mounted articulated fixed mount or telescopic strut or fairing, with multi function capabilities to accommodate a low drag refueling fairing, a refueling pod assembly, a spray assembly, and a dry chemical particulate diffuser assembly.

5. The apparatus according to claim 1 comprising a temporarily mounted, segmented, interconnected, roll on roll off, fire proof, bullet proof, explosion resistant, structurally reinforced, internally baffled, low profile fluid reservoir tank assembly capable of accommodating fuel, chemicals, bioremediation agents, or other liquids, in conjunction with heavy cargo, or passengers on the upper side of said temporary tank assembly.

6. The apparatus according to claim 1 comprising a temporarily mounted, segmented, interconnected, roll on roll off, internally tapered, dry reservoir tank assembly with a pressurization system, and an auger dry particulate feed assembly which can simultaneously accommodate heavy cargo, or passengers on the upper side of said installed temporary tank assembly.

7. The apparatus according to claim 1 comprising a temporarily mounted, pressurized roll on roll off, ram air actuated, low profile, hydraulic, or electrically driven support capability for spraying, refueling, and dry chemical dispersal assembly.

8. The apparatus according to claim 1 comprising a temporarily mounted, portable GPS system used in conjunction with refueling, spraying, and particulate dispersal systems.

9. The apparatus according to claim 1 comprising a temporarily mounted, pressurized door, hatch, or removable panel with the capability of accommodating an operator's seat, a large flat, or protruding observer bubble window, which is used in conjunction with, and for the purpose of observing the, refueling, spraying, and particulate dispersal systems when deployed in flight.

10. The apparatus according to claim 1 comprising a temporarily mounted, portable user interface system used in conjunction with an infra red, and video monitoring system, or other imaging sensor, and refueling, spraying, and particulate dispersal systems.

11. The apparatus according to claim 1 comprising a temporarily mounted, portable Low Light Television (LLTV) and eyesafe laser ranging system with micro miniature range detecting radar chips and infra red proximity lighting system attached to an articulated male refueling probe or a female drogue basket and hose assembly which is used in conjunction with refueling systems to determine the proximity of the receiving aircraft to the refueling delivery assembly.