CN105083589A - Airplane rising, landing and taxiing performance comprehensive verification platform - Google Patents
Airplane rising, landing and taxiing performance comprehensive verification platform Download PDFInfo
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Abstract
The invention provides an airplane rising, landing and taxiing performance comprehensive verification platform integrating airplane inertia simulation, lateral wind load simulation, taxiing speed simulation, runway state simulation and brake control and very high in universality, and by means of the airplane rising, landing and taxiing performance comprehensive verification platform, all-factor simulation and testing evaluation in the airplane rising, landing and taxiing processes can be achieved. The airplane rising, landing and taxiing performance comprehensive verification platform comprises an aircraft simulation system, an undercarriage airplane system, a braking system, a lateral wind simulation loading system, a runway simulation system, a measurement and control and simulation system and the like. By means of the airplane rising, landing and taxiing performance comprehensive verification platform, the taxiing speed, the course heading, the loading force and the braking torque can be measured, and visual simulation and braking control strategy researches can be conducted as well. The airplane rising, landing and taxiing performance comprehensive verification platform can provide an early-period theory, simulation and experiment basis for active-service or researched aircraft landing gear system design, taxiing control rate design and whole airplane inertia optimal allocation. The problem that at present, the control strategy can only be researched at the test flight taxiing stage is solved, and thus the cost and risks of out-field taxiing tests are greatly lowered.
Description
Technical field
The present invention relates to a kind of takeoff and landing sliding race performance synthesis verification platform.
Background technology
Along with modern industry and scientific and technical fast development and complicated international situation, Ge great state has all stepped up the carrying out of development of new aircraft, and China has also started the tide of all types of aircraft of development.As everyone knows, the development needs experience exploration of one airplane, development, prototyping testing finally ability volume production, development time is very long, especially prototype design complete after needs carry out a large amount of ground roll-out test, just can carry out landing test, that is because only possess simple alighting gear rear wheel brake Force meansurement and brake torque Measurement and analysis ability, brake system Laws of Mechanics is detected there is certain tachnical storage, and the performance test of sliding race process can only be come by outfield sliding race test.
The sliding race performance of current aircraft and control law carry out estimating, evaluating and verification experimental verification ability, lack comprehensive simulation (airplane inertial, sliding running velocity degree, crosswind load and runway state etc.) and the performance verification equipment of complete set.Test can only be run by sliding before taking a flight test and carry out performance testing, it not only takes time and effort, and there is certain technical risk, often can not carry out comprehensive assessment to aspects such as limit wind loading rating, complicated runway environment adaptive capacitys, significantly limit sliding lifting and the comprehensive assessment of running performance of landing of aircraft.
Summary of the invention
In view of the above problems, the object of this invention is to provide a kind of takeoff and landing sliding race performance synthesis verification platform, the simulation of collection airplane inertial, the simulation of crosswind load simulated, coasting speed, runway state simulation and brake are controlled in the very strong all-around test stand of the commonality of one, can realize the total factor simulation of takeoff and landing sliding race process and test assessment.
For this reason, the invention provides a kind of takeoff and landing sliding race performance synthesis verification platform, comprising: aircraft simulation system, alighting gear wheel system, brake system, crosswind simulated loading system, runway analog system and TT&C simulation system etc.Described aircraft simulation system comprises flight simulator, clump weight, hydraulic loading system, weight according to real aircraft follows centroid position, by position and the quantity of clump weight in change of flight simulator, the centroid position of simulated flight simulator, according to the fixed position of centroid position adjustment hydraulic loading system and the flexible of hydraulic actuating cylinder, gravitational load is carried out, the weight of real simulation aircraft and centroid position, truly simulated aircraft body inertial properties at centroid position; Described alighting gear wheel and brake analog system can adopt real aircraft alighting gear or approximation system to simulate; Crosswind simulated loading system can carry out side force and the simulation of side force square according to actual crosswind loading spectrum by four cover hydraulic loading systems; Runway analog system not only can slide running velocity degree and aircraft equivalent inertia by simulated aircraft, can also pass through surface attachment material simulation runway environment; TT&C simulation system, except measuring various performance perameter (sliding running velocity degree, course heading, loading force, brake torque etc.), can also carry out vision simulation simulation and the research of brake control policy.
Described wind load simulated loading system comprises four cover hydraulic loading systems, flight simulator both sides are all designed with two hydraulic loading systems, real simulation Lateral Wind, can simulate maximum crosswind load is 7 grades, and the sliding race process of aircraft can be examined on a large scale by the impact of crosswind load.
Described hydraulic loading system comprises fixed ear base, axle, hydraulic actuating cylinder, force snesor, effect ear seat, hydraulic efficiency pressure system is fixed on framework by fixed ear base, effect ear seat acts on flight simulator, control system hydraulic control cylinder stretches, and the size of the application force acted on flight simulator is detected in real time by force snesor, realize accurately controlling in real time of loading force.
Described framework is the erecting stage of hydraulic loading system, comprises crossbeam, vertical beam, adopts van-type floor to be welded, and is designed with reinforcing rib structure, the requirement of proof strength rigidity.
Described runway analog system is made up of three cover motion simulator, and often overlap motion simulator and be independently placed in below flight simulator wheel, be subject to Action of Gravity Field, flight simulator wheel failure-free is pressed in motion simulator; Described motion simulator comprises simulation runway, motor, flower wheel, inertia disc, nut, driving wheel, bracing frame, driven by motor driving wheel rotates, and drive runway to move, the moving velocity of runway is controlled by controlling motor speed, thus the wheel speed of real simulation aircraft in sliding race process, the side of flower wheel is designed with inertia disc, and reliably fixes with nut, simulates the load of unmanned plane linear inertia by changing inertia disc mode; Consider existing type and subsequent expansion thereof, sliding running velocity degree is determined at 0 ~ 300km/h.
Wheel center, two, described flight simulator back is designed with angular encoder, detects the course angle of flight simulator in real time.
Described simulation runway according to actual needs, can lay different materials on analog orbit surface, the runway adhesion value under simulation Different climate (sleet, greasy weather gas) condition.
The present invention can carry out total factor simulation and emulation to the sliding race process of takeoff and landing, carries out brake weight closed loop control, and can provide best landing sliding race control policy and method by course feedback.
This platform also comprises control system, have test parameters on-line real time monitoring, the emulation of panorama simulation animation and course correction Real Time Control Function, and by on-line analysis assessment Optimization Software, comprehensive assessment and analysis are carried out to the sliding performance of running of unmanned plane landing, for the design of type aircraft Landing Gear System, sliding run inverse amplification factor design and complete machine inertia distribute rationally provide important theory, emulation and test basis.
The present invention can be active service or grinding the design of type Aircraft landing gear system, sliding inverse amplification factor design and the complete machine inertia of running is distributed rationally and is provided theoretical, emulation in early stage and test basis.Solving present stage can only study the difficult problem of its control policy in the sliding race stage of taking a flight test, and then significantly reduces that outfield is sliding runs experimentation cost and risk.
Accompanying drawing explanation
Fig. 1 runs performance synthesis verification platform axonometric drawing 1 according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 2 runs performance synthesis verification platform axonometric drawing 2 according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 3 runs performance synthesis verification platform birds-eye view according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 4 runs performance synthesis verification platform left view according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 5 runs performance synthesis verification platform gimbal axis mapping according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 6 runs performance synthesis verification platform framework front view according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 7 runs performance synthesis verification platform hydraulic loading device axonometric drawing according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 8 runs performance synthesis verification platform Aircraft Simulator and motion simulator front view according to the takeoff and landing of an embodiment of the invention are sliding;
Fig. 9 runs performance synthesis verification platform Aircraft Simulator and motion simulator axonometric drawing 1 according to the takeoff and landing of an embodiment of the invention are sliding;
Figure 10 runs performance synthesis verification platform Aircraft Simulator and motion simulator axonometric drawing 2 according to the takeoff and landing of an embodiment of the invention are sliding;
Figure 11 runs performance synthesis verification platform motion simulator axonometric drawing according to the takeoff and landing of an embodiment of the invention are sliding;
In figure: 1, framework; 2, Aircraft Simulator; 3, motion simulator; 4, ground; 5, hydraulic loading device; 6, crossbeam; 7, vertical beam; 8, reinforced rib; 9, fixed ear base; 10, axle; 11, hydraulic actuating cylinder; 12, force snesor; 13, ear seat is acted on; 14, brake system; 15, aircraft wheel; 16, runway is simulated; 17, motor; 18, flower wheel; 19, inertia disc; 20, nut; 21, driving wheel; 22, bracing frame.
Detailed description of the invention
Describe in detail according to the embodiment of the present invention below in conjunction with accompanying drawing.
As shown in Figure 1, magnetostrictive actuator comprises: the object of this invention is to provide a kind of takeoff and landing sliding race performance synthesis verification platform, the simulation of collection airplane inertial, the simulation of crosswind load simulated, coasting speed, runway state simulation and brake are controlled in the very strong all-around test stand of the commonality of one, can realize the total factor simulation of takeoff and landing sliding race process and test assessment.
For this reason, the invention provides a kind of takeoff and landing sliding race performance synthesis verification platform, comprising: aircraft simulation system, alighting gear wheel system, brake system, crosswind simulated loading system, runway analog system and TT&C simulation system etc.Described aircraft simulation system comprises flight simulator 2, clump weight, hydraulic loading system 5, weight according to real aircraft follows centroid position, by position and the quantity of clump weight in change of flight simulator 2, the centroid position of simulated flight, according to the fixed position of centroid position adjustment hydraulic loading system 5 and the flexible of hydraulic actuating cylinder 11, gravitational load is carried out, the weight of real simulation aircraft and centroid position, truly simulated aircraft body inertial properties at centroid position; Described alighting gear wheel and brake analog system 14 can adopt real aircraft alighting gear or approximation system to simulate; Crosswind simulated loading system can carry out side force and the simulation of side force square according to actual crosswind loading spectrum by four cover hydraulic loading systems 5; Runway analog system not only can slide running velocity degree and aircraft equivalent inertia by simulated aircraft, can also pass through surface attachment material simulation runway environment; TT&C simulation system, except measuring various performance perameter (sliding running velocity degree, course heading, loading force, brake torque etc.), can also carry out vision simulation simulation and the research of brake control policy.
Described wind load simulated loading system comprises four cover hydraulic loading systems 5, flight simulator both sides are all designed with two hydraulic loading systems 5, real simulation Lateral Wind, can simulate maximum crosswind load is 7 grades, and the sliding race process of aircraft can be examined on a large scale by the impact of crosswind load.
Described hydraulic loading system comprises fixed ear base 9, axle 10, hydraulic actuating cylinder 11, force snesor 12, effect ear seat 13, hydraulic efficiency pressure system is fixed on framework 1 by fixed ear base 9, the effect 9 of effect ear seat is on flight simulator 2, control system hydraulic control cylinder 11 stretches, and the size of the application force acted on flight simulator is detected in real time by force snesor 12, realize accurately controlling in real time of loading force.
Described framework 1 is the erecting stage of hydraulic loading system, comprises crossbeam 6, vertical beam 7, adopts van-type floor to be welded, and is designed with reinforcing rib structure, the requirement of proof strength rigidity.
Described runway analog system is made up of three cover motion simulator 3, and often overlap motion simulator 3 and be independently placed in below flight simulator wheel 15, be subject to Action of Gravity Field, flight simulator wheel 15 failure-free is pressed in motion simulator 3; Described motion simulator 3 comprises simulation runway 16, motor 17, flower wheel 18, inertia disc 19, nut 20, driving wheel 21, bracing frame 22, motor 17 drives driving wheel 21 to rotate, and drive runway 16 to move, the moving velocity of runway 16 is controlled by controlling motor 17 rotating speed, thus the wheel speed of real simulation aircraft 2 in sliding race process, the side of flower wheel 16 is designed with inertia disc 19, and reliably fix with nut 20, simulate the load of unmanned plane linear inertia by changing inertia disc 19 mode; Consider existing type and subsequent expansion thereof, sliding running velocity degree is determined at 0 ~ 300km/h.
Wheel 15 center, two, described flight simulator back is designed with angular encoder, detects the course angle of flight simulator in real time.
Described simulation runway 16 according to actual needs, can lay different materials on analog orbit surface, the runway adhesion value under simulation Different climate (sleet, greasy weather gas) condition.
The present invention can carry out total factor simulation and emulation to the sliding race process of takeoff and landing, carries out brake weight closed loop control, and can provide best landing sliding race control policy and method by course feedback.
This platform also comprises control system, have test parameters on-line real time monitoring, the emulation of panorama simulation animation and course correction Real Time Control Function, and by on-line analysis assessment Optimization Software, comprehensive assessment and analysis are carried out to the sliding performance of running of unmanned plane landing, for the design of type aircraft Landing Gear System, sliding run inverse amplification factor design and complete machine inertia distribute rationally provide important theory, emulation and test basis.
The mode of operation of an illustrative embodiments of takeoff and landing sliding race performance synthesis verification platform is as follows, also can otherwise work.
First the weight of flight simulator 2 and barycenter are regulated by counterweight mode according to the organism parameter of the tested aircraft of reality, Cross Wind Force is simulated again by side force force-input device 5, instrumentation airplane course angle is carried out, as the feedback signal of brake correction closed loop control by the angular encoder being arranged in flight simulator two trailing wheel 15 point midway.Start runway analog machine 3, namely the runway be arranged under three wheels comes simulated aircraft landing speed and equivalent inertia, control system carries out brake weight closed loop control in real time according to the change of course angle, and on simulation computer dynamic vision panorama Emulating display.By measuring, monitoring, emulation and control process analysis system carry out comprehensive assessment and evaluation to the sliding performance of running of tested unmanned plane landing, and can provide that best landing is sliding runs control policy and method.
The present invention can be active service or grinding the design of type Aircraft landing gear system, sliding inverse amplification factor design and the complete machine inertia of running is distributed rationally and is provided theoretical, emulation in early stage and test basis.Solving present stage can only study the difficult problem of its control policy in the sliding race stage of taking a flight test, and then significantly reduces that outfield is sliding runs experimentation cost and risk.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; change can be expected easily or replace, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (7)
1. takeoff and landing are sliding runs a performance synthesis verification platform, it is characterized in that, comprising: aircraft simulation system, alighting gear wheel system, brake system, crosswind simulated loading system, runway analog system and TT&C simulation system;
Described aircraft simulation system comprises flight simulator, clump weight, hydraulic loading system, weight according to real aircraft follows centroid position, by position and the quantity of clump weight in change of flight simulator, the centroid position of simulated flight simulator, according to the fixed position of centroid position adjustment hydraulic loading system and the flexible of hydraulic actuating cylinder, gravitational load is carried out, the weight of real simulation aircraft and centroid position, truly simulated aircraft body inertial properties at centroid position;
Crosswind simulated loading system can carry out side force and the simulation of side force square according to actual crosswind loading spectrum by four cover hydraulic loading systems;
Runway analog system not only can slide running velocity degree and aircraft equivalent inertia by simulated aircraft, can also pass through surface attachment material simulation runway environment;
TT&C simulation system, except measuring sliding running velocity degree, course heading, loading force and brake torque, can also carry out vision simulation simulation and the research of brake control policy.
2. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, described wind load simulated loading system comprises four cover hydraulic loading systems, flight simulator both sides are all designed with two hydraulic loading systems, real simulation Lateral Wind, can simulate maximum crosswind load is 7 grades, and the sliding race process of aircraft can be examined on a large scale by the impact of crosswind load.
3. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, described hydraulic loading system comprises fixed ear base, axle, hydraulic actuating cylinder, force snesor, effect ear seat, hydraulic efficiency pressure system is fixed on framework by fixed ear base, effect ear seat acts on flight simulator, control system hydraulic control cylinder stretches, and detects the size of the application force acted on flight simulator in real time by force snesor, realizes accurately controlling in real time of loading force.
4. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, described runway analog system is made up of three cover motion simulator, often overlapping motion simulator is independently placed in below flight simulator wheel, be subject to Action of Gravity Field, flight simulator wheel failure-free is pressed in motion simulator; Described motion simulator comprises simulation runway, motor, flower wheel, inertia disc, nut, driving wheel, bracing frame, driven by motor driving wheel rotates, and drive runway to move, the moving velocity of runway is controlled by controlling motor speed, thus the wheel speed of real simulation aircraft in sliding race process, the side of flower wheel is designed with inertia disc, and reliably fixes with nut, simulates the load of unmanned plane linear inertia by changing inertia disc mode; Consider existing type and subsequent expansion thereof, sliding running velocity degree is determined at 0 ~ 300km/h.
5. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, wheel center, two, described flight simulator back is designed with angular encoder, the course angle of real-time detection flight simulator, carry out brake weight closed loop control by course feedback, and best landing sliding race control policy and method can be provided.
6. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, described simulation runway according to actual needs, can lay different materials on analog orbit surface, the runway adhesion value under simulation Different climate (sleet, greasy weather gas) condition.
7. takeoff and landing according to claim 1 are sliding runs performance synthesis verification platform, it is characterized in that, TT&C simulation system has test parameters on-line real time monitoring, the emulation of panorama simulation animation and course correction Real Time Control Function, and carries out comprehensive assessment and analysis by on-line analysis assessment Optimization Software to the sliding performance of running of unmanned plane landing.
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| CN105511306A (en) * | 2015-11-26 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane function test console |
| CN107215480A (en) * | 2017-05-23 | 2017-09-29 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN107526303A (en) * | 2017-07-26 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Vehicle Management System simulation and verification platform |
| CN107521720A (en) * | 2017-07-14 | 2017-12-29 | 中国飞行试验研究院 | A kind of carrier green band of taking off determines method |
| CN110550233A (en) * | 2019-09-12 | 2019-12-10 | 中国商用飞机有限责任公司 | Automatic adjusting method and system for airplane front wheel turning |
| CN110816887A (en) * | 2019-11-25 | 2020-02-21 | 西安航空制动科技有限公司 | Test bench and test method for airplane wheel braking system |
| CN112015109A (en) * | 2020-09-02 | 2020-12-01 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff and front wheel lift test flight control law and design method thereof |
| CN113420418A (en) * | 2021-05-28 | 2021-09-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for judging sideslip phenomenon of airplane ground running |
| CN114088275A (en) * | 2021-11-22 | 2022-02-25 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and method |
| CN114638181A (en) * | 2022-05-18 | 2022-06-17 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting airplane takeoff performance model |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105511306B (en) * | 2015-11-26 | 2018-12-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft function test console |
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| CN107526303A (en) * | 2017-07-26 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Vehicle Management System simulation and verification platform |
| CN110550233A (en) * | 2019-09-12 | 2019-12-10 | 中国商用飞机有限责任公司 | Automatic adjusting method and system for airplane front wheel turning |
| CN110816887A (en) * | 2019-11-25 | 2020-02-21 | 西安航空制动科技有限公司 | Test bench and test method for airplane wheel braking system |
| CN110816887B (en) * | 2019-11-25 | 2023-10-24 | 西安航空制动科技有限公司 | Test bench and test method for airplane wheel brake system |
| CN112015109A (en) * | 2020-09-02 | 2020-12-01 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff and front wheel lift test flight control law and design method thereof |
| CN112015109B (en) * | 2020-09-02 | 2024-01-23 | 四川腾盾科技有限公司 | Large unmanned aerial vehicle takeoff front wheel lifting test flight control law and design method thereof |
| CN113420418A (en) * | 2021-05-28 | 2021-09-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for judging sideslip phenomenon of airplane ground running |
| CN114088275A (en) * | 2021-11-22 | 2022-02-25 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and method |
| CN114088275B (en) * | 2021-11-22 | 2024-04-05 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and measuring method |
| CN114638181A (en) * | 2022-05-18 | 2022-06-17 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting airplane takeoff performance model |
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