CN104401498A - Adaptive bulging air inlet channel deformation driving device based on flexible skin - Google Patents
Adaptive bulging air inlet channel deformation driving device based on flexible skin Download PDFInfo
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- CN104401498A CN104401498A CN201410668336.5A CN201410668336A CN104401498A CN 104401498 A CN104401498 A CN 104401498A CN 201410668336 A CN201410668336 A CN 201410668336A CN 104401498 A CN104401498 A CN 104401498A
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- Prior art keywords
- profile
- seal chamber
- flexible covering
- inlet channel
- flow
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/009—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising decompression panels or valves for pressure equalisation in fuselages or floors
Abstract
The invention belongs to the technical field of aviation structural design, and relates to an adaptive bulging air inlet channel deformation driving device based on flexible skin. The driving device comprises an inflation pump (1), an inflation pipeline (2), an inflation valve (3), a deflation pipeline (4), a deflation valve (5), an inner-side sealing cavity (6), an outer-side sealing cavity (7), a pressure sensor (8), a flow sensor (9), a skin connecting belt (10) and a basic profile mounting region (11). According to the driving device, shape change of the bulging profile of an air inlet channel in a large range is realized by using a gas pressurizing way, and the shape of the bulging profile is controlled by using pressure and flow information, so that the throat area of the air inlet channel is changed, and the problem of non-adjustability of the profile of the bulging air inlet channel is solved.
Description
Technical field
The invention belongs to aeronautic structure design field, relate to a kind of self adaptation bump inlet based on flexible covering distortion actuating device.
Background technology
In the design process of supersonic fighterplane inlet channel, often face the contradiction between high low speed aerodynamic configuration, the stealthy requirement of aircraft also governs aerodynamic configuration design and the performance of inlet channel.Therefore, in the design process of supersonic inlet, be difficult to make inlet channel keep High Performance in whole flight envelope.
For solving above design challenges, propose the design concept of self adaptation bump inlet.Self adaptation bump inlet can different flight state residing for aircraft, by active control technology adaptively modifying inlet channel interior conduit (bulge) planform, regulate the throat area of inlet channel, thus meet the traffic demand of driving engine under different flight state.
Flexible covering is that a kind of mode of elasticity glued membrane and high-elasticity fiber compound that adopts is formed, larger plastic deformation can be there is under external force drives, and there is the novel covering of enough in-plane stiffness, intensity, can be used for the self adaptation shape adjustment realizing bump inlet.Based on the self adaptation bump inlet structure of flexible covering see Fig. 1, it is basic structure and working surface schematic diagram.
For realizing the distortion based on the self adaptation bump inlet of flexible covering, need to design a kind of actuating device, its drive under, not only can make flexible covering basic profile and the most high-profile between produce directional deformation, the Out-of Plane Stiffness that flexible covering is enough can also be ensured.
Summary of the invention
The technical problem to be solved in the present invention: provide a kind of self adaptation bump inlet based on flexible covering to be out of shape actuating device, one is solve the distortion driving of flexible covering and control problem, two be solve flexible covering Out-of Plane Stiffness weak, can not the problem of the outer larger load of carrying surface.
Technical scheme of the present invention is: a kind of distortion of the self adaptation bump inlet based on flexible covering actuating device, described actuating device: adopt the mode of gas pressurized to utilize inflation pump to pressurising in annular seal space, flexible covering to be out of shape; Covering connecting band is utilized to realize the coordination change of inside and outside annular seal space volume; Valve and pipeline is utilized to control gas flow; Utilize pressure sensor and flow sensor to obtain pressure and flow information, as parameter, control flexible covering to the distortion designing arbitrarily profile; Blanketing gas is utilized to provide enough Out-of Plane Stiffness for flexible covering;
Described actuating device is characterized by: described actuating device comprises inflation pump 1, loading line 2, charging valve 3, bleeder line 4, venting valve 5, inner seal chamber 6, outer side seal chamber 7, pressure sensor 8, flow sensor 9, covering connecting band 10, basic profile installing zone 11; Described inflation pump 1 is installed in the housing construction inside the profile of inlet channel basis, is communicated with respectively, for pressurising in annular seal space by loading line 2 with inner seal chamber 6 with outer side seal chamber 7; Described loading line 2, be arranged on inside the profile of inlet channel basis, one end is communicated with inflation pump, and the other end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber 6 and outer side seal chamber 7 respectively; Described charging valve 3, be arranged on loading line 2 " T " font mouth of pipe central authorities, for control air-flow to the inside annular seal space 6 or laterally annular seal space 7 flow; Described bleeder line 4, be arranged on inside the profile of inlet channel basis, one end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber 6 and outer side seal chamber 7 respectively, and the other end is communicated with aircraft body structure internal freedom; Described venting valve 5, be arranged on bleeder line 3 " T " font mouth of pipe central authorities, for control air-flow by inner seal chamber 6 or laterally annular seal space 7 outwards flow out; Described inner seal chamber 6, be inlet channel basis profile and the annular seal space that surrounds of inner side flexible covering, its two ends are separately installed with loading line 2 and bleeder line 4, its cavity volume can with the filling of gas, put and change; Described outer side seal chamber 7, for the annular seal space that inlet channel basis profile and outside flexible covering surround, blanketing gas wherein can provide the Out-of Plane Stiffness needed for flexible covering, when its volume reaches maximum, bulge profile is the most high-profile, when its volume is zero, outside flexible covering and inlet channel basis profile fit tightly; Described pressure sensor 8, has two, is embedded in the basic profile in inner seal chamber 6 and outer side seal chamber 7, for measuring the cavity pressure in inner seal chamber 6 and outer side seal chamber 7 respectively; Described flow sensor 9, is installed on the mouth of pipe of loading line 2, and for measuring gas flow rate in pipeline, pressure and flow-speed measurement result can be used as the parameter that flexible covering profile controls; Described covering connecting band 10, for a kind of flexible-belt that can provide pulling force, one end connects outside flexible covering, the other end connects inner side flexible covering, effect is when side flexible covering, under pressurising drives, deformation of cylindrical occurs, opposite side flexible covering can produce and be out of shape in the same way under its pulling force, and then discharges the gas in the annular seal space of tension side; Described basic profile installing zone 11, has two places, and wherein a place is used for fixing loading line 2, and another place is used for fixing bleeder line 4, and often locating installing zone has a through hole, for the "T"-shaped mouth of pipe of installation pipeline.
The invention has the beneficial effects as follows: provide a kind of self adaptation bump inlet based on flexible covering to be out of shape actuating device, this device utilizes gas pressurized mode to realize the alteration of form of inlet channel bulge profile in a big way, pressure and flow information is utilized to control the shape of bulge profile, thus change inlet throat area, solve the uncontrollable problem of bump inlet profile.Simultaneously, utilize the Out-of Plane Stiffness that blanketing gas is enough for flexible covering provides, solve the problem of flexible covering Out-of Plane Stiffness deficiency, thus make aircraft under different flight state, all have optimum pneumatic performance and inlet engine compatibility characteristic, there is good engineering adaptability.
Accompanying drawing explanation
Fig. 1 is that the present invention is for the self adaptation bump inlet deformation range schematic diagram based on flexible covering;
Fig. 2 is the self adaptation bump inlet distortion actuating device schematic diagram based on flexible covering;
Wherein, 1-inflation pump, 2-loading line, 3-charging valve, 4-bleeder line, 5-venting valve, 6-inner seal chamber, 7-outer side seal chamber, 8-pressure sensor, 9-flow sensor, 10-covering connecting band, 11-basis profile installing zone.
Fig. 3 is that the present invention is for inlet channel exocoel pressurising principle of work schematic diagram;
Fig. 4 is that the present invention is for inlet channel inner chamber pressurising principle of work schematic diagram;
Fig. 5 is that the present invention is for intracavity gas pressurize principle of work schematic diagram.
Detailed description of the invention
Below the specific embodiment of the present invention is described in further details.
A kind of distortion of the self adaptation bump inlet based on flexible covering of the present invention actuating device, described actuating device: adopt the mode of gas pressurized to utilize inflation pump to pressurising in annular seal space, flexible covering to be out of shape; Covering connecting band is utilized to realize the coordination change of inside and outside annular seal space volume; Valve and pipeline is utilized to control gas flow; Utilize pressure sensor and flow sensor to obtain pressure and flow information, as parameter, control flexible covering to the distortion designing arbitrarily profile; Blanketing gas is utilized to provide enough Out-of Plane Stiffness for flexible covering;
Described actuating device comprises inflation pump 1, loading line 2, charging valve 3, bleeder line 4, venting valve 5, inner seal chamber 6, outer side seal chamber 7, pressure sensor 8, flow sensor 9, covering connecting band 10, basic profile installing zone 11; Described inflation pump 1 is installed on inside the profile of inlet channel basis that (" inner side " be the side of the sensing airframe plane of symmetry, " outside " is the opposite sense of " inner side ", in housing construction down together), be communicated with outer side seal chamber 7 with inner seal chamber 6 respectively by loading line 2, for pressurising in annular seal space; Described loading line 2, be arranged on inside the profile of inlet channel basis, one end is communicated with inflation pump, and the other end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber 6 and outer side seal chamber 7 respectively; Described charging valve 3, be arranged on loading line 2 " T " font mouth of pipe central authorities, for control air-flow to the inside annular seal space 6 or laterally annular seal space 7 flow; Described bleeder line 4, be arranged on inside the profile of inlet channel basis (position is different from loading line 2), one end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber 6 and outer side seal chamber 7 respectively, and the other end is communicated with aircraft body structure internal freedom; Described venting valve 5, be arranged on bleeder line 3 " T " font mouth of pipe central authorities, for control air-flow by inner seal chamber 6 or laterally annular seal space 7 outwards flow out; Described inner seal chamber 6, be inlet channel basis profile and the annular seal space that surrounds of inner side flexible covering, its two ends are separately installed with loading line 2 and bleeder line 4, its cavity volume can with the filling of gas, put and change; Described outer side seal chamber 7, for the annular seal space that inlet channel basis profile and outside flexible covering surround, blanketing gas wherein can provide the Out-of Plane Stiffness needed for flexible covering, when its volume reaches maximum, bulge profile is the most high-profile, when its volume is 0, outside flexible covering and inlet channel basis profile fit tightly; Described pressure sensor 8, has 2, is embedded in the basic profile in inner seal chamber 6 and outer side seal chamber 7, for measuring the cavity pressure in inner seal chamber 6 and outer side seal chamber 7 respectively; Described flow sensor 9, is installed on the mouth of pipe of loading line 2, and for measuring gas flow rate in pipeline, pressure and flow-speed measurement result can be used as the parameter that flexible covering profile controls; Described covering connecting band 10, for a kind of flexible-belt that can provide pulling force, one end connects outside flexible covering, the other end connects inner side flexible covering, effect is when side flexible covering, under pressurising drives, deformation of cylindrical occurs, opposite side flexible covering can produce and be out of shape in the same way under its pulling force, and then discharges the gas in the annular seal space of tension side; Described basic profile installing zone 11, has 2 places, and wherein a place is used for fixing loading line 2, and another place is used for fixing bleeder line 4, and often locating installing zone has a through hole, for the "T"-shaped mouth of pipe of installation pipeline.
According to concrete inlet channel and duty of engine demand, select suitable inflation pump, valve, aquaseal, tubing, pressure sensor, flow sensor, covering connecting band determine dimensional parameters, the structural representation provided according to Fig. 2 can produce the self adaptation bump inlet pressurizing device based on flexible covering meeting design requirement.
The pressurising ability of described inflation pump can be selected according to the rigidity of airplane intake design load and bulge profile; Described valve has two kinds of location statuss, is realized inflation and the venting of each annular seal space by by-pass valve control state; Described pipeline according to pressurising traffic demand selection material and internal diameter, can be embedded in the pipeline mouth of pipe in basic profile, and it arranges the aerodynamic configuration do not affected in inlet channel; Described medial and lateral annular seal space is independent sealed separately, when the valve is closed, blanketing gas in chamber can be utilized to provide the out-plane strength of flexible covering; Described pressure sensor and flow sensor for gathering pressure in annular seal space and flow signal, by pressure-flow-profile corresponding relation, for the intelligent deformation of inlet channel bulge provides parameter; Described covering connecting band is for coordinating the distortion of interior outer skin, and controlling annular seal space volume, is a kind of flexible-belt providing pulling force.
The above-mentioned self adaptation bump inlet pressurizing device based on flexible covering has 3 kinds of mode of operations, one is the pressurising of outer side seal chamber, now outside flexible covering is out of shape by the object-oriented profile of basic type, outside " bulge " becomes large, simultaneously, under the effect of connecting band, inner seal cavity volume diminishes, and Fig. 3 is shown in by valve state and air flow line schematic diagram; Two is the pressurisings of inner seal chamber, and now flexible covering is by current profile to basic type facial disfigurement, and inner seal cavity volume becomes large, and meanwhile, under the effect of covering connecting band, " bulge " diminishes, and Fig. 4 is shown in by valve state and air flow line schematic diagram; Three is pressurize sealing states, now outside flexible covering is in certain specific profile, outer side seal chamber internal gas pressure is higher than ambient pressure, blanketing gas can provide enough out-plane strength for outside flexible covering, simultaneously because inner seal chamber is in communication with the outside, its internal pressure is not enough to drive covering connecting band that outside flexible covering is out of shape to the inside, the bulge that therefore this state can make outside flexible covering be formed maintain one stable shaped, during pressurize, valve state is shown in Fig. 5.
Claims (1)
1. based on a self adaptation bump inlet distortion actuating device for flexible covering, described actuating device: adopt the mode of gas pressurized to utilize inflation pump to pressurising in annular seal space, flexible covering to be out of shape; Covering connecting band is utilized to realize the coordination change of inside and outside annular seal space volume; Valve and pipeline is utilized to control gas flow; Utilize pressure sensor and flow sensor to obtain pressure and flow information, as parameter, control flexible covering to the distortion designing arbitrarily profile; Blanketing gas is utilized to provide enough Out-of Plane Stiffness for flexible covering;
Described actuating device is characterized by: described actuating device comprises inflation pump (1), loading line (2), charging valve (3), bleeder line (4), venting valve (5), inner seal chamber (6), outer side seal chamber (7), pressure sensor (8), flow sensor (9), covering connecting band (10), basic profile installing zone (11); Described inflation pump (1) is installed in the housing construction inside the profile of inlet channel basis, be communicated with outer side seal chamber (7) with inner seal chamber (6) respectively by loading line (2), for pressurising in annular seal space; Described loading line (2), be arranged on inside the profile of inlet channel basis, one end is communicated with inflation pump, and the other end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber (6) and outer side seal chamber (7) respectively; Described charging valve (3), is arranged on " T " font mouth of pipe central authorities of loading line (2), for controlling air-flow annular seal space (6) or annular seal space (7) flowing laterally to the inside; Described bleeder line (4), be arranged on inside the profile of inlet channel basis, one end is " T " font mouth of pipe, and " T " font mouth of pipe is communicated with inner seal chamber (6) and outer side seal chamber (7) respectively, and the other end is communicated with aircraft body structure internal freedom; Described venting valve (5), be arranged on bleeder line (3) " T " font mouth of pipe central authorities, for control air-flow by inner seal chamber (6) or laterally annular seal space (7) outwards flow out; Described inner seal chamber (6), for the annular seal space that inlet channel basis profile and inner side flexible covering surround, its two ends are separately installed with loading line (2) and bleeder line (4), its cavity volume can with the filling of gas, put and change; Described outer side seal chamber (7), for the annular seal space that inlet channel basis profile and outside flexible covering surround, blanketing gas wherein can provide the Out-of Plane Stiffness needed for flexible covering, when its volume reaches maximum, bulge profile is the most high-profile, when its volume is zero, outside flexible covering and inlet channel basis profile fit tightly; Described pressure sensor (8), have two, be embedded in the basic profile of inner seal chamber (6) and outer side seal chamber (7) respectively, for measuring the cavity pressure of inner seal chamber (6) and outer side seal chamber (7); Described flow sensor (9), is installed on the mouth of pipe of loading line (2), and for measuring gas flow rate in pipeline, pressure and flow-speed measurement result can be used as the parameter that flexible covering profile controls; Described covering connecting band (10), for a kind of flexible-belt that can provide pulling force, one end connects outside flexible covering, the other end connects inner side flexible covering, effect is when side flexible covering, under pressurising drives, deformation of cylindrical occurs, opposite side flexible covering can produce and be out of shape in the same way under its pulling force, and then discharges the gas in the annular seal space of tension side; Described basic profile installing zone (11), have two places, wherein a place is used for fixing loading line (2), and another place is used for fixing bleeder line (4), often locate installing zone and have a through hole, for the "T"-shaped mouth of pipe of installation pipeline.
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| CN201410668336.5A CN104401498B (en) | 2014-11-19 | 2014-11-19 | Adaptive bulging air inlet channel deformation driving device based on flexible skin |
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| CN201410668336.5A CN104401498B (en) | 2014-11-19 | 2014-11-19 | Adaptive bulging air inlet channel deformation driving device based on flexible skin |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108190034A (en) * | 2017-12-15 | 2018-06-22 | 中国航空工业集团公司成都飞机设计研究所 | A kind of flexibility variant structure |
| CN108534950A (en) * | 2018-07-09 | 2018-09-14 | 北京动力机械研究所 | The multi-channel parallel performance detecting system and detection method of inlet pressure sensor |
| CN108639357A (en) * | 2018-07-18 | 2018-10-12 | 大连理工大学 | A kind of pressurized reservoir covering with carrying and deformation one |
| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN113819854A (en) * | 2021-11-24 | 2021-12-21 | 中国飞机强度研究所 | Device and method for measuring deformation of aircraft skin in extreme cold weather test |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN113819854A (en) * | 2021-11-24 | 2021-12-21 | 中国飞机强度研究所 | Device and method for measuring deformation of aircraft skin in extreme cold weather test |
| CN113819854B (en) * | 2021-11-24 | 2022-02-08 | 中国飞机强度研究所 | Device and method for measuring deformation of aircraft skin in extreme cold weather test |
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