CN105083589B - Takeoff and landing are slided and run performance synthesis verification platform - Google Patents
Takeoff and landing are slided and run performance synthesis verification platform Download PDFInfo
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Abstract
The present invention provides a kind of takeoff and landing and slides race performance synthesis verification platform, the simulation of collection airplane inertial, crosswind is load simulated, sliding speed simulation, runway state simulation and brake are controlled in the very strong all-around test stand of versatility of one, can realize that the simulation of race process total factor and test assessment are slided in takeoff and landing, including：Aircraft simulation system, undercarriage wheel system, brake system, crosswind simulated loading system, runway simulation system and TT＆C simulation system etc., in addition to it can realize measuring running speed, course heading, loading force and brake torque, vision simulation simulation and brake control strategy research can also be carried out.The present invention can distribute theoretical offer early stage, emulation and test basis rationally for active service or the design of type Aircraft landing gear system, the design of sliding race control rate and whole machine inertia is ground.Solution can only study the problem of its control strategy in the sliding race stage of taking a flight test at this stage, and then outfield cunning race experimentation cost and risk is greatly reduced.
Description
Technical field
Slided the present invention relates to a kind of takeoff and landing and run performance synthesis verification platform.
Background technology
Fast development and complicated international situation with modern industry and science and technology, major states all step up
The carrying out of development of new aircraft, China has also started the tide of all types of aircrafts of development.It is well known that the development of an airplane is needed
Exploration, development, prototyping testing finally ability volume production are experienced, the development time is very long, is especially needed after the completion of prototype design
Carry out substantial amounts of ground roll-out experiment, can just carry out landing experiment, that because, only possess simple undercarriage rear wheel brake power
Test and brake torque measurement analysis ability, have certain technological reserve to the detection of brake system Laws of Mechanics, and cunning was run
The performance test of journey can only slide race experiment to complete by outfield.
The sliding race performance and control law of current aircraft are estimated, evaluated and verification experimental verification ability, lack complete set
Comprehensive simulation (airplane inertial, running speed, crosswind load and runway state etc.) and performance verification equipment.Before can only be by taking a flight test
It is sliding run experiment and carry out performance test, it not only takes time and effort, and there is certain technical risk, tends not to limit wind resistance energy
The aspects such as power, complicated runway environment adaptability carry out comprehensive assessment, and carrying for race performance is slided in the landing that significantly limit aircraft
Rise and comprehensive assessment.
The content of the invention
In view of the above problems, slided it is an object of the invention to provide a kind of takeoff and landing and run performance synthesis verification platform, collection flies
Machine inertia simulation, crosswind are load simulated, sliding speed simulation, runway state simulation and brake be controlled in one versatility it is very strong
All-around test stand, it is possible to achieve the simulation of race process total factor and test assessment are slided in takeoff and landing.
Therefore, the present invention provides a kind of takeoff and landing slides race performance synthesis verification platform, including：Aircraft simulation system,
Undercarriage wheel system, brake system, crosswind simulated loading system, runway simulation system and TT＆C simulation system etc..It is described to fly
Row device simulation system include flight simulator, balancing weight, hydraulic loading system, the weight according to real aircraft with centroid position,
Position and quantity by balancing weight in change of flight simulator, the centroid position of simulated flight simulator, according to centroid position
The fixed position of hydraulic loading system and stretching for hydraulic cylinder are adjusted, gravitational load is carried out in centroid position, true simulation flies
The weight and centroid position of machine, true simulation airframe inertial properties；The undercarriage wheel and brake simulation system can
It is simulated with using real aircraft undercarriage or approximation system；Crosswind simulated loading system can be logical according to actual crosswind loading spectrum
Crossing four sets of hydraulic loading systems carries out side force and the simulation of side force square；Runway simulation system be not only able to simulation aircraft running speed and
Aircraft equivalent inertia, can also be by surface attachment material simulation runway environment；TT＆C simulation system to various performances except joining
Number (running speed, course heading, loading force, brake torque etc.) measure outside, can also carry out vision simulation simulation and
Brake control strategy research.
The wind load simulated loading system includes four sets of hydraulic loading systems, and flight simulator both sides are designed with two
Hydraulic loading system, truly simulates Lateral Wind, can simulate maximum crosswind load for 7 grades, can on a large scale examine aircraft to slide
Race process is influenceed by crosswind load.
The hydraulic loading system includes fixed ear base, axle, hydraulic cylinder, force snesor, effect ear mount, and fixed ear base is by liquid
Pressure system is fixed on framework, and effect ear mount is acted on flight simulator, control system control hydraulic cylinder extension, and by power
Sensor real-time detection acts on the size of the active force on flight simulator, realizes the real-time precise control of loading force.
The framework is the mounting platform of hydraulic loading system, including crossbeam, vertical beam are welded using van-type floor,
And it is designed with reinforcing rib structure, it is ensured that the requirement of intensity and toughness.
The runway simulation system is made up of three sets of motion simulators, often covers motion simulator and is independently placed in flight mould
Intend device wheel lower section, by Action of Gravity Field, flight simulator wheel is reliably pressed in motion simulator；The motion simulation
Device includes simulation runway, motor, driven pulley, inertia disc, nut, driving wheel, support frame, and motor drives driving wheel to rotate, and
Runway motion is driven, the translational speed of runway is controlled by controlled motor rotating speed, so that true simulated flight device is in sliding race process
In wheel speed, the side of driven pulley is designed with inertia disc, and reliably fixed with nut, by changing inertia disc mode come mould
Intend the load of unmanned plane linear inertia；In view of existing type and its subsequent expansion, running speed is determined in 0~300km/h.
The wheel center of the flight simulator back two is designed with angular encoder, real-time detection flight simulator
Course angle.
The simulation runway can lay different materials on analog orbit surface according to actual needs, simulate Different climate
Runway attachment coefficient under the conditions of (sleet, greasy weather gas).
The present invention can slide race process and carry out total factor simulation and emulation to takeoff and landing, fed back by course and braked
Power closed-loop control, and optimal landing cunning race control strategy and method can be given.
The platform also includes control system, with to test parameters on-line real time monitoring, the emulation of panorama simulation animation and boat
To correction Real Time Control Function, and comprehensive assessment is carried out to unmanned plane landing cunning race performance by on-line analysis assessment optimization software
And analysis, it is that the design of type aircraft Landing Gear System, the design of sliding race control rate and whole machine inertia are distributed rationally and provides important reason
By, emulation and test basis.
The present invention can be designed and the optimization of whole machine inertia for active service or the design of type Aircraft landing gear system, sliding control rate of running is ground
Configuration provides early stage theory, emulation and test basis.Solution can only study its control strategy in the sliding race stage of taking a flight test at this stage
Problem, and then outfield cunning race experimentation cost and risk is greatly reduced.
Brief description of the drawings
Fig. 1 is that race performance synthesis verification platform axonometric drawing 1 is slided in the takeoff and landing of an implementation method of the invention；
Fig. 2 is that race performance synthesis verification platform axonometric drawing 2 is slided in the takeoff and landing of an implementation method of the invention；
Fig. 3 is that race performance synthesis verification platform top view is slided in the takeoff and landing of an implementation method of the invention；
Fig. 4 is that race performance synthesis verification platform left view is slided in the takeoff and landing of an implementation method of the invention；
Fig. 5 is that the gimbal axis survey of race performance synthesis verification platform is slided in the takeoff and landing of an implementation method of the invention
Figure；
Fig. 6 is that race performance synthesis verification platform framework main view is slided in the takeoff and landing of an implementation method of the invention
Figure；
Fig. 7 is that race performance synthesis verification platform hydraulic loaded dress is slided in the takeoff and landing of an implementation method of the invention
Put axonometric drawing；
Fig. 8 is that race performance synthesis verification platform Aircraft Simulator is slided in the takeoff and landing of an implementation method of the invention
And motion simulator front view；
Fig. 9 is that race performance synthesis verification platform Aircraft Simulator is slided in the takeoff and landing of an implementation method of the invention
And motion simulator axonometric drawing 1；
Figure 10 is that race performance synthesis verification platform plane simulation is slided in the takeoff and landing of an implementation method of the invention
Device and motion simulator axonometric drawing 2；
Figure 11 is that the verification platform motion simulation of race performance synthesis is slided in the takeoff and landing of an implementation method of the invention
Device axonometric drawing；
In figure：1st, framework；2nd, Aircraft Simulator；3rd, motion simulator；4th, ground；5th, hydraulic loading device；6th, crossbeam；
7th, vertical beam；8th, reinforcement；9th, fixed ear base；10th, axle；11st, hydraulic cylinder；12nd, force snesor；13rd, ear mount is acted on；14th, brake system
System；15th, aircraft wheel；16th, runway is simulated；17th, motor；18th, driven pulley；19th, inertia disc；20th, nut；21st, driving wheel；22nd, prop up
Support.
Specific embodiment
Describe in detail below in conjunction with the accompanying drawings according to the embodiment of the present invention.
As shown in figure 1, magnetostrictive actuator includes：It is comprehensive race performance to be slided it is an object of the invention to provide a kind of takeoff and landing
Verification platform is closed, the simulation of collection airplane inertial, load simulated crosswind, sliding speed simulation, runway state simulation and brake are controlled in
The very strong all-around test stand of the versatility of one, it is possible to achieve the simulation of race process total factor and test assessment are slided in takeoff and landing.
Therefore, the present invention provides a kind of takeoff and landing slides race performance synthesis verification platform, including：Aircraft simulation system,
Undercarriage wheel system, brake system, crosswind simulated loading system, runway simulation system and TT＆C simulation system etc..It is described to fly
Row device simulation system includes flight simulator 2, balancing weight, hydraulic loading system 5, and the weight according to real aircraft is with barycenter position
Put, position and quantity by balancing weight in change of flight simulator 2, the centroid position of simulated flight, adjusted according to centroid position
The fixed position of whole hydraulic loading system 5 and stretching for hydraulic cylinder 11, gravitational load is carried out in centroid position, and true simulation flies
The weight and centroid position of machine, true simulation airframe inertial properties；The undercarriage wheel and brake simulation system 14
Can be simulated using real aircraft undercarriage or approximation system；Crosswind simulated loading system can be according to actual crosswind loading spectrum
Side force is carried out by four sets of hydraulic loading systems 5 and side force square is simulated；Runway simulation system is not only able to simulation aircraft and slides race speed
Degree and aircraft equivalent inertia, can also be by surface attachment material simulation runway environment；TT＆C simulation system is except to various property
Outside energy parameter (running speed, course heading, loading force, brake torque etc.) is measured, vision simulation mould can also be carried out
Fit brake control strategy research.
The wind load simulated loading system includes four sets of hydraulic loading systems 5, and flight simulator both sides are designed with two
Individual hydraulic loading system 5, truly simulates Lateral Wind, can simulate maximum crosswind load for 7 grades, can on a large scale examine aircraft
Sliding race process is influenceed by crosswind load.
The hydraulic loading system includes fixed ear base 9, axle 10, hydraulic cylinder 11, force snesor 12, effect ear mount 13, Gu
Determine ear mount 9 hydraulic system is fixed on framework 1, on flight simulator 2, control system controls hydraulic pressure for effect ear mount effect 9
Cylinder 11 is stretched, and the size of the active force on flight simulator is acted on by the real-time detection of force snesor 12, realizes loading force
Real-time precise control.
The framework 1 is the mounting platform of hydraulic loading system, including crossbeam 6, vertical beam 7, using the welding of van-type floor
Into, and it is designed with reinforcing rib structure, it is ensured that the requirement of intensity and toughness.
The runway simulation system is made up of three sets of motion simulators 3, often covers motion simulator 3 and is independently placed in flight
The lower section of simulator wheel 15, by Action of Gravity Field, flight simulator wheel 15 is reliably pressed in motion simulator 3；It is described
Motion simulator 3 includes simulation runway 16, motor 17, driven pulley 18, inertia disc 19, nut 20, driving wheel 21, support frame
22, motor 17 drives driving wheel 21 to rotate, and drives runway 16 to move, and the movement of runway 16 is controlled by the rotating speed of controlled motor 17
Speed, so that true simulated flight device 2 is sliding the wheel speed during running, the side of driven pulley 16 is designed with inertia disc 19,
And it is reliable fixed with nut 20, the load of unmanned plane linear inertia is simulated by changing the mode of inertia disc 19；In view of existing machine
Type and its subsequent expansion, running speed are determined in 0~300km/h.
The center of wheel 15 of the flight simulator back two is designed with angular encoder, real-time detection flight simulator
Course angle.
The simulation runway 16 can lay different materials on analog orbit surface according to actual needs, simulate different gas
Wait the runway attachment coefficient under the conditions of (sleet, greasy weather gas).
The present invention can slide race process and carry out total factor simulation and emulation to takeoff and landing, fed back by course and braked
Power closed-loop control, and optimal landing cunning race control strategy and method can be given.
The platform also includes control system, with to test parameters on-line real time monitoring, the emulation of panorama simulation animation and boat
To correction Real Time Control Function, and comprehensive assessment is carried out to unmanned plane landing cunning race performance by on-line analysis assessment optimization software
And analysis, it is that the design of type aircraft Landing Gear System, the design of sliding race control rate and whole machine inertia are distributed rationally and provides important reason
By, emulation and test basis.
The working method that an illustrative embodiments for running performance synthesis verification platform are slided in takeoff and landing is as follows, it is also possible to
Other modes work.
Organism parameter first according to actual tested aircraft is entered by counterweight mode to the weight and barycenter of flight simulator 2
Row regulation, then Cross Wind Force is simulated by lateral force loading device 5, by being arranged in the midpoint of two trailing wheel of flight simulator 15 position
The angular encoder put carrys out survey aircraft course angle, used as the feedback signal of brake correction closed-loop control.Start runway simulation dress
3 are put, that is, is arranged in the runway under three wheels to simulate takeoff and landing speed and equivalent inertia, control system is according to course
The change at angle carries out brake weight closed-loop control, and the dynamic vision panorama emulation display on simulation computer in real time.By measuring,
Monitoring, emulation and control process analysis system slide race performance and carry out comprehensive assessment and evaluation to the landing of tested unmanned plane, and can
Provide optimal landing and slide race control strategy and method.
The present invention can be designed and the optimization of whole machine inertia for active service or the design of type Aircraft landing gear system, sliding control rate of running is ground
Configuration provides early stage theory, emulation and test basis.Solution can only study its control strategy in the sliding race stage of taking a flight test at this stage
Problem, and then outfield cunning race experimentation cost and risk is greatly reduced.
The above, specific embodiment only of the invention, but protection scope of the present invention is not limited thereto, and it is any
Those familiar with the art the invention discloses technical scope in, change or replacement can be readily occurred in, should all contain
Cover within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (7)
1. a kind of takeoff and landing are slided and run performance synthesis verification platform, it is characterised in that including：Aircraft simulation system, undercarriage
Wheel system, brake system, crosswind simulated loading system, runway simulation system and TT＆C simulation system；
The aircraft simulation system includes flight simulator, balancing weight, hydraulic loading system, weight according to real aircraft with
Centroid position, position and quantity by balancing 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 stretching for hydraulic cylinder, carry out gravitational load, very in centroid position
The weight and centroid position of real simulation aircraft, true simulation airframe inertial properties；
Crosswind simulated loading system can carry out side force and side force square according to actual crosswind loading spectrum by four sets of hydraulic loading systems
Simulation；
Runway simulation system is not only able to simulate aircraft running speed and aircraft equivalent inertia, can also be by surface attachment material
Simulation runway environment；
TT＆C simulation system can also enter in addition to being measured to running speed, course heading, loading force and brake torque
Row vision simulation is simulated and brake control strategy research.
2. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that wind load simulation adds
Loading system includes four sets of hydraulic loading systems, and flight simulator both sides are designed with two hydraulic loading systems, true analog side
To wind load, maximum crosswind load can be simulated for 7 grades, can on a large scale examine aircraft to slide race process is influenceed by crosswind load.
3. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that the hydraulic loaded
System includes fixed ear base, axle, hydraulic cylinder, force snesor, effect ear mount, and be fixed on hydraulic system on framework by fixed ear base,
Effect ear mount is acted on flight simulator, control system control hydraulic cylinder extension, and is acted on by force snesor real-time detection
The size of the active force on flight simulator, realizes the real-time precise control of loading force.
4. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that the runway simulation
System is made up of three sets of motion simulators, often covers motion simulator and is independently placed in flight simulator wheel lower section, by weight
Power is acted on, and flight simulator wheel is reliably pressed in motion simulator；The motion simulator includes simulation runway, electricity
Machine, driven pulley, inertia disc, nut, driving wheel, support frame, motor drive driving wheel to rotate, and drive runway to move, by control
Motor speed processed controls the translational speed of runway, so that wheel speed of the true simulated flight device during sliding race, driven pulley
Side be designed with inertia disc, it is and reliably fixed with nut, unmanned plane linear inertia is simulated by changing inertia disc mode and is born
Carry；In view of existing type and its subsequent expansion, running speed is determined in 0~300km/h.
5. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that the flight simulation
The wheel center of device back two is designed with angular encoder, and the course angle of real-time detection flight simulator is fed back by course
Brake weight closed-loop control is carried out, and optimal landing can be provided to slide race control strategy and method.
6. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that simulation runway can be with
According to actual needs, in simulation runway surface laying different materials, the runway attachment coefficient under the conditions of simulation Different climate.
7. takeoff and landing according to claim 1 are slided and run performance synthesis verification platform, it is characterised in that TT＆C simulation system
With Real Time Control Function of being rectified a deviation to test parameters on-line real time monitoring, the emulation of panorama simulation animation and course, and by online
Analysis and evaluation optimization software slides race performance to unmanned plane landing and carries out comprehensive assessment and analysis.
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Families Citing this family (10)
| 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 |
| CN107215480B (en) * | 2017-05-23 | 2019-04-19 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN107521720B (en) * | 2017-07-14 | 2020-11-13 | 中国飞行试验研究院 | Method for determining green color band for takeoff of transport plane |
| 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 |
| CN110550233B (en) * | 2019-09-12 | 2021-09-07 | 中国商用飞机有限责任公司 | Automatic adjusting method and system for airplane front wheel turning |
| 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 |
| 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 |
| 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 |
| CN114638181B (en) * | 2022-05-18 | 2022-09-20 | 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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| DE3002581C2 (en) * | 1980-01-25 | 1981-11-19 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | System for testing the landing process of aircraft |
| CN102589840B (en) * | 2012-01-12 | 2014-04-16 | 清华大学 | Vertical or short-distance takeoff and landing aircraft ground effect test system |
| CN103287587B (en) * | 2013-06-17 | 2015-10-07 | 西北工业大学 | A kind of vertical take-off and landing aircraft (VTOL aircraft) ground simulated flight test platform |
| CN204078085U (en) * | 2014-07-10 | 2015-01-07 | 中国商用飞机有限责任公司 | Aircraft floor motion simulator |
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Effective date of registration: 20201028 Address after: Room 301, building 25, District 11, Nanjing International Commodity City, No. 2, Qinlu Avenue, Lukou street, Jiangning District, Nanjing City, Jiangsu Province (Jiangning Development Zone) Patentee after: Jiangsu Changfeng Aviation Technology Co., Ltd Address before: 362000, Quanzhou, Fujian province Yongchun County, China Town, Peng Village No. 8 Patentee before: Pan Baoying |