WO2003025962A1 - Visual indication of uninstalled control panel functions - Google Patents

Visual indication of uninstalled control panel functions Download PDF

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Publication number
WO2003025962A1
WO2003025962A1 PCT/US2002/030039 US0230039W WO03025962A1 WO 2003025962 A1 WO2003025962 A1 WO 2003025962A1 US 0230039 W US0230039 W US 0230039W WO 03025962 A1 WO03025962 A1 WO 03025962A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
switch
manually operable
control
control panel
Prior art date
Application number
PCT/US2002/030039
Other languages
French (fr)
Inventor
Mark L. Goldberg
Ken L. Snodgrass
Original Assignee
Honeywell, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Honeywell, Inc. filed Critical Honeywell, Inc.
Priority to DE60238127T priority Critical patent/DE60238127D1/en
Priority to EP02761781A priority patent/EP1428234B1/en
Publication of WO2003025962A1 publication Critical patent/WO2003025962A1/en

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
    • G01S5/02—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves
    • G01S5/0284—Relative positioning
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S11/00—Systems for determining distance or velocity not using reflection or reradiation
    • G01S11/02—Systems for determining distance or velocity not using reflection or reradiation using radio waves
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/14—Receivers specially adapted for specific applications
    • G01S19/15—Aircraft landing systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
    • G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/42—Determining position
    • G01S19/51—Relative positioning
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0004—Transmission of traffic-related information to or from an aircraft
    • G08G5/0008—Transmission of traffic-related information to or from an aircraft with other aircraft
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0004—Transmission of traffic-related information to or from an aircraft
    • G08G5/0013—Transmission of traffic-related information to or from an aircraft with a ground station
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/0017—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information
    • G08G5/0021—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information located in the aircraft
    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
    • G08G5/02—Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
    • G08G5/025—Navigation or guidance aids
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations
    • H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations
    • H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
    • H04B7/18508—Communications with or from aircraft, i.e. aeronautical mobile service with satellite system used as relay, i.e. aeronautical mobile satellite service
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L12/00—Data switching networks
    • H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
    • H04L12/40—Bus networks
    • H04L12/40006—Architecture of a communication node
    • H04L12/40019—Details regarding a bus master
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L12/00—Data switching networks
    • H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
    • H04L12/40—Bus networks
    • H04L12/40006—Architecture of a communication node
    • H04L12/40032—Details regarding a bus interface enhancer
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L12/00—Data switching networks
    • H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
    • H04L12/40—Bus networks
    • H04L12/407—Bus networks with decentralised control
    • H04L12/413—Bus networks with decentralised control with random access, e.g. carrier-sense multiple-access with collision detection (CSMA-CD)
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L67/00—Network arrangements or protocols for supporting network services or applications
    • H04L67/01—Protocols
    • H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L9/00—Cryptographic mechanisms or cryptographic arrangements for secret or secure communications; Network security protocols
    • H04L9/40—Network security protocols
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04R—LOUDSPEAKERS, MICROPHONES, GRAMOPHONE PICK-UPS OR LIKE ACOUSTIC ELECTROMECHANICAL TRANSDUCERS; DEAF-AID SETS; PUBLIC ADDRESS SYSTEMS
    • H04R3/00—Circuits for transducers, loudspeakers or microphones
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H2217/00—Facilitation of operation; Human engineering
    • H01H2217/022—Part of keyboard not operable
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L12/00—Data switching networks
    • H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
    • H04L12/40—Bus networks
    • H04L2012/40267—Bus for use in transportation systems
    • H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
    • H04L69/30—Definitions, standards or architectural aspects of layered protocol stacks
    • H04L69/32—Architecture of open systems interconnection [OSI] 7-layer type protocol stacks, e.g. the interfaces between the data link level and the physical level
    • H04L69/322—Intralayer communication protocols among peer entities or protocol data unit [PDU] definitions
    • H04L69/329—Intralayer communication protocols among peer entities or protocol data unit [PDU] definitions in the application layer [OSI layer 7]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y04—INFORMATION OR COMMUNICATION TECHNOLOGIES HAVING AN IMPACT ON OTHER TECHNOLOGY AREAS
    • Y04S—SYSTEMS INTEGRATING TECHNOLOGIES RELATED TO POWER NETWORK OPERATION, COMMUNICATION OR INFORMATION TECHNOLOGIES FOR IMPROVING THE ELECTRICAL POWER GENERATION, TRANSMISSION, DISTRIBUTION, MANAGEMENT OR USAGE, i.e. SMART GRIDS
    • Y04S40/00—Systems for electrical power generation, transmission, distribution or end-user application management characterised by the use of communication or information technologies, or communication or information technology specific aspects supporting them
    • Y04S40/18—Network protocols supporting networked applications, e.g. including control of end-device applications over a network

Definitions

  • the present invention relates generally to the field of aviation and more particularly to control panels for controlling an aircraft.
  • a standardized control panel for aircraft provides manually operable controls that are configured to activate an aircraft function if the requested aircraft function is installed on the aircraft or, are otherwise configured to activate a visual indicator if the requested aircraft function is absent from the aircraft.
  • the most preferred embodiments of the present invention provide a control panel that performs some function for each of the controls found on the control panel, even the controls for those functions that are disabled or are not included in the aircraft system under control.
  • Control panel 100 houses a plurality of manually operable controls 110, 120, 130, 140, and 150.
  • Each of controls 110- 150 may be implemented as any type of aircraft control known to those skilled in the art (e.g., knobs, buttons, switches, etc.).
  • the total number of manually operable controls illustrated in the Figure is shown to be five, those skilled in the art will understand that the various preferred embodiments of the present invention may be easily expanded to include any suitable number of controls and, if necessary, incorporate additional control panels as well.
  • controls 110-150 are coupled to one of switches 114, 124, 134, 143, 144, and 154.
  • Controls 110, 120, and 140 are operational controls that are configured to activate aircraft functions 115, 125, and 145, respectively.
  • Aircraft functions 115, 125, and 145 may be considered requestable mechanisms, any of which may be activated by a crewmember.
  • functions or requestable mechanisms may be any type of activity normally associated with controlling or operating an aircraft known to those skilled in the art.
  • controls 130 and 150 are inactive or non-operational controls and are configured to provide a visual indicator, such as display messages 170 and 180 of display panel 160, to indicate the lack of the requested aircraft function. It should be noted that although controls 130 and 150 are not connected to any aircraft function for this particular application, in another control panel application, controls 130 and 150 may be configured to activate an aircraft function. Accordingly, controls 130 and 150 may also be configured to activate some requestable mechanism in certain applications.
  • controls 110-150 will activate various aircraft functions and some of controls 110-150 were provided for functions which have either been disabled, not installed, or have otherwise been made unavailable in the operating environment for this specific aircraft.
  • control 110 when actuated, will energize switch 114, activating function 115.
  • control 120 will energize switch 124, thereby activating function 125 and, in like fashion, control 150 will energize switch 144, thereby activating control 145.
  • control 130 and control 150 are designated for requestable mechanisms or functions that are not available in this specific aircraft. Accordingly, whenever an operator actuates control 130, switch 134 is energized and a visual indication, such as message 180 displayed on display panel 160, will indicate that the function typically actuated by control 130 is temporarily disabled.
  • control 140 is connected to switch 144 and will, in the current configuration, activate function 145. However, in a different aircraft with the same control panel 100, function 145 may not be installed. In that aircraft, control 140 will be connected to switch 143. Then, when control 140 is actuated, switch 143 will be energized, displaying message 190 to indicate that the requested function is not installed.
  • control panel 100 and display panel 160 are shown as separate elements for purposes of clarity, in many applications control panel 100 and display panel 160 will be combined into a single panel.

Abstract

A standardized control panel for aircraft provides manually operable controls that are configured to activate an aircraft function if the requested aircraft function is installed on the aircraft or, are otherwise configured to activate a visual indicator if the requested aircraft function is absent from the aircraft.

Description

VISUAL INDICATION OF UNINSTALLED CONTROL PANEL FUNCTIONS
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of U.S. Provisional Patent Application No. 60/324,035, filed September 20, 2001.
BACKGROUND OF THE INVENTION
TECHNICAL FIELD
[0002] The present invention relates generally to the field of aviation and more particularly to control panels for controlling an aircraft.
BACKGROUND ART
[0003] With many present day aircraft, and particularly military aircraft, many aircraft functions are accessed or activated by manipulating some type of control (i.e., a switch, knob, button or the like). Depending on the specific function of the manipulated control, the crewmember will activate a specific aircraft function or receive some type of feedback related to the operational performance of the aircraft. In general, most of these aircraft operational and status controls are available to the crewmembers via various control panels situated in appropriate locations throughout the aircraft. The feedback received from these various controls is usually considered to be an integral part of controlling most aircraft. Since different aircraft have different operational capabilities and different flight characteristics, the number and type of controls found in each different type of aircraft may vary somewhat.
[0004] While various types of aircraft may have the same general operational characteristics, the specific functions of a given aircraft may require a number of controls not found on other aircraft. This means that an aircraft manufacturer usually designs an aircraft-specific set of controls for each different model or type of aircraft that they manufacture. While the goal of achieving certain manufacturing efficiencies may indicate the practicality of a single control panel for each particular type of aircraft, there are other considerations that come into play. For example, some of the various government agencies that approve and certify aircraft require that each and every control on a control panel provide some indication to the crewmember if a given control is non-functional or does not activate an aircraft function or feature. In general, some indication should be given to alert the crewmember that the control is non-functional. Additionally, many similar aircraft have very different functions, depending on the specific application and the needs of the customer ordering the aircraft. For example, military and commercial versions of similar aircraft require significantly different features and functions, even though the operational flight characteristics of the two aircraft may be substantially similar.
[0005] Therefore, while providing a single control panel adaptable to many different types of aircraft may be desirable, practical considerations currently limit the standardization of the controls for a given control panel. Accordingly, aircraft manufacturers routinely customize the control panel for each different set of features available to the crew for each specific type of aircraft. Not only is this less than optimal from the perspective of manufacturing efficiency, it can significantly increase the number of design requirements for a given type of aircraft, even when only minor differences exist between various models. Since each new type of aircraft must undergo testing and review prior to being certified for use, customization of the control panel can introduce delays into the approval process for aircraft when the control panels are modified.
[0006] In view of the foregoing, it should be appreciated that it would be desirable to provide methods and apparatus for standardizing aircraft control panel configurations without a separate and distinct control panels for each aircraft. It would also be desirable to maintain compliance with various government standards regarding control panel functionality without comprising design and/or manufacturing decisions. Furthermore, additional desirable features will become apparent to one skilled in the art from the foregoing background of the invention and following detailed description of a preferred exemplary embodiment and appended claims.
SUMMARY OF THE INVENTION
[0007] A standardized control panel for aircraft provides manually operable controls that are configured to activate an aircraft function if the requested aircraft function is installed on the aircraft or, are otherwise configured to activate a visual indicator if the requested aircraft function is absent from the aircraft.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] The preferred exemplary embodiment of the present invention will hereinafter be described in conjunction with the appended drawings, where like designations denote like elements, and the Figure is a schematic block diagram of a control panel according to a preferred exemplary embodiment of the present invention.
DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT
[0009] The most preferred embodiments of the present invention provide a control panel that performs some function for each of the controls found on the control panel, even the controls for those functions that are disabled or are not included in the aircraft system under control.
[0010] Referring now to the Figure, a control panel 100 in accordance with a preferred exemplary embodiment of the present invention is illustrated. Control panel 100 houses a plurality of manually operable controls 110, 120, 130, 140, and 150. Each of controls 110- 150 may be implemented as any type of aircraft control known to those skilled in the art (e.g., knobs, buttons, switches, etc.). Additionally, although the total number of manually operable controls illustrated in the Figure is shown to be five, those skilled in the art will understand that the various preferred embodiments of the present invention may be easily expanded to include any suitable number of controls and, if necessary, incorporate additional control panels as well.
[0011] Each of controls 110-150, found on control panel 100, are coupled to one of switches 114, 124, 134, 143, 144, and 154. Controls 110, 120, and 140 are operational controls that are configured to activate aircraft functions 115, 125, and 145, respectively. Aircraft functions 115, 125, and 145 may be considered requestable mechanisms, any of which may be activated by a crewmember. For purposes of this explanation, functions or requestable mechanisms may be any type of activity normally associated with controlling or operating an aircraft known to those skilled in the art. [0012] In this particular embodiment, controls 130 and 150 are inactive or non-operational controls and are configured to provide a visual indicator, such as display messages 170 and 180 of display panel 160, to indicate the lack of the requested aircraft function. It should be noted that although controls 130 and 150 are not connected to any aircraft function for this particular application, in another control panel application, controls 130 and 150 may be configured to activate an aircraft function. Accordingly, controls 130 and 150 may also be configured to activate some requestable mechanism in certain applications.
[0013] As shown in the Figure, some of controls 110-150 will activate various aircraft functions and some of controls 110-150 were provided for functions which have either been disabled, not installed, or have otherwise been made unavailable in the operating environment for this specific aircraft. For example, control 110, when actuated, will energize switch 114, activating function 115. Similarly, control 120 will energize switch 124, thereby activating function 125 and, in like fashion, control 150 will energize switch 144, thereby activating control 145. However, in this example, control 130 and control 150 are designated for requestable mechanisms or functions that are not available in this specific aircraft. Accordingly, whenever an operator actuates control 130, switch 134 is energized and a visual indication, such as message 180 displayed on display panel 160, will indicate that the function typically actuated by control 130 is temporarily disabled.
[0014] Similarly, whenever control 150 is actuated, a visual indication, such as message 170 displayed on display panel 160, will indicate that the requested function is not available. As shown in the Figure, control 140 is connected to switch 144 and will, in the current configuration, activate function 145. However, in a different aircraft with the same control panel 100, function 145 may not be installed. In that aircraft, control 140 will be connected to switch 143. Then, when control 140 is actuated, switch 143 will be energized, displaying message 190 to indicate that the requested function is not installed.
[0015] Those skilled in the art will understand that the number of messages displayed by display panel 160 and nature of the content for messages 170, 180, and 190 will be determined by the specific needs and design requirements for a given application. It should also be noted that other types of visual indicators such as flashing lights, various graphics, etc. may be employed instead of or in addition to messages 170, 180, and 190 on display panel 160. Finally, although control panel 100 and display panel 160 are shown as separate elements for purposes of clarity, in many applications control panel 100 and display panel 160 will be combined into a single panel.
[0016] From the foregoing description, it should be appreciated that methods and apparatus are provided for a standardized control panel. While certain preferred exemplary embodiments have been presented in the foregoing detailed description of the preferred exemplary embodiments, it should be appreciated that a vast number of variations in the embodiments exist. It should also be appreciated that the preferred exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description provides those skilled in the art with a convenient road map for implementing the preferred exemplary embodiments of the invention. It should also be understood that various changes may be made in the function and arrangement of elements described in the preferred exemplary embodiments without departing from the spirit and scope of the invention as set forth in the appended claims.

Claims

1. An apparatus for indicating when a requestable mechanism is absent in an aircraft, said apparatus comprising:
an aircraft control panel;
at least one manually operable control housed in said aircraft control panel;
a first switch coupled to said control panel, said first switch being configured to activate said requestable mechanism; and
a second switch coupled to said control panel, said second switch being configured to activate a visual indicator, wherein said at least one manually operable control is coupled to said first switch when said requestable mechanism is present in said aircraft and wherein said at least one manually operable control is coupled to said second switch when said requestable mechanism is absent from said aircraft.
2. The apparatus of claim 1 further comprising a display panel coupled to said control panel via said second switch, said display panel being configured to display said visual indicator.
3. The apparatus of claim 1 wherein said at least one manually operable control comprises a switch.
4. The apparatus of claim 1 wherein said at least one manually operable control comprises a knob.
5. The apparatus of claim 1 wherein said at least one manually operable control comprises a button.
6. The apparatus of claim 1 wherein said visual indicator comprises an illuminated message on a display panel.
7. The apparatus of claim 1 wherein said visual indicator comprises a flashing light on a display panel.
8. An aircraft apparatus comprising:
an aircraft control panel;
a plurality of manually operable controls housed in said aircraft control panel;
a plurality of switches coupled to said control panel, wherein a first switch of said plurality of switches is configured to activate at least one requestable mechanism, and wherein a second switch of said plurality of switches is configured to activate at least one visual indicator, wherein at least one of said plurality of manually operable controls is coupled to said first switch when said requestable mechanism is present in said aircraft and wherein said at least one of said plurality of manually operable controls is coupled to said second switch of said plurality of switches when said requestable mechanism is absent from said aircraft; and
a display panel coupled to said control panel via said second switch of said plurality of switches, said display panel being configured to display said at least one visual indicator.
9. The apparatus of claim 8 wherein said at least one manually operable control comprises a switch.
10. The apparatus of claim 8 wherein said at least one manually operable control comprises a knob.
11. The apparatus of claim 8 wherein said at least one manually operable control comprises a button.
12. The apparatus of claim 8 wherein said at least one visual indicator comprises a flashing light displayed on said display panel.
13. The apparatus of claim 8 wherein said at least one visual indicator comprises an illuminated message on a display panel.
14. A method of indicating when a requestable mechanism in an aircraft is not present in an aircraft comprising the steps of:
actuating a manually operable control on a control panel;
activating said requestable mechanism if said requestable mechanism is installed in said aircraft; and
activating a visual indicator to indicate the absence of said requestable mechanism if said requestable mechanism is not installed in said aircraft.
15. The method of claim 14 wherein said manually operable control comprises a switch.
16. The method of claim 14 wherein said manually operable control comprises a knob.
17. The method of claim 14 wherein said manually operable control comprises a button.
18. The method of claim 14 wherein said visual indicator comprises an illuminated message on a display panel.
19. The method of claim 14 wherein said visual indicator comprises a flashing light on a display panel.
PCT/US2002/030039 2001-09-20 2002-09-19 Visual indication of uninstalled control panel functions WO2003025962A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
DE60238127T DE60238127D1 (en) 2001-09-20 2002-09-19 VISUAL DISPLAY OF UNINSTALLED CONTROL PANEL FUNCTIONS
EP02761781A EP1428234B1 (en) 2001-09-20 2002-09-19 Visual indication of uninstalled control panel functions

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US32403501P 2001-09-20 2001-09-20
US60/324,035 2001-09-20

Publications (1)

Publication Number Publication Date
WO2003025962A1 true WO2003025962A1 (en) 2003-03-27

Family

ID=23261788

Family Applications (6)

Application Number Title Priority Date Filing Date
PCT/US2002/029910 WO2003026162A2 (en) 2001-09-20 2002-09-19 Telephony control in the flight deck
PCT/US2002/030039 WO2003025962A1 (en) 2001-09-20 2002-09-19 Visual indication of uninstalled control panel functions
PCT/US2002/029909 WO2003025508A2 (en) 2001-09-20 2002-09-19 Station identification for a local area augmentation system on a visual display
PCT/US2002/029908 WO2003025905A1 (en) 2001-09-20 2002-09-19 Active noise filtering for voice communication systems
PCT/US2002/030040 WO2003026174A2 (en) 2001-09-20 2002-09-19 Digital audio system
PCT/US2002/029926 WO2003025617A2 (en) 2001-09-20 2002-09-19 Annunciation of the distance to a target position in a gps landing system

Family Applications Before (1)

Application Number Title Priority Date Filing Date
PCT/US2002/029910 WO2003026162A2 (en) 2001-09-20 2002-09-19 Telephony control in the flight deck

Family Applications After (4)

Application Number Title Priority Date Filing Date
PCT/US2002/029909 WO2003025508A2 (en) 2001-09-20 2002-09-19 Station identification for a local area augmentation system on a visual display
PCT/US2002/029908 WO2003025905A1 (en) 2001-09-20 2002-09-19 Active noise filtering for voice communication systems
PCT/US2002/030040 WO2003026174A2 (en) 2001-09-20 2002-09-19 Digital audio system
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