CN206946224U - A kind of Landing Gear System control law synthesis verification platform - Google Patents
A kind of Landing Gear System control law synthesis verification platform Download PDFInfo
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- CN206946224U CN206946224U CN201720839773.8U CN201720839773U CN206946224U CN 206946224 U CN206946224 U CN 206946224U CN 201720839773 U CN201720839773 U CN 201720839773U CN 206946224 U CN206946224 U CN 206946224U
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Abstract
The utility model discloses a kind of Landing Gear System control law synthesis verification platform, belongs to aircraft takeoffs and landings frame control system technical field.Manipulation shows that computer is connected by cable with the side ports of Ethernet one with data acquisition computer, observing and controlling and master control management computer, three-dimensional live instrument, and another side ports of Ethernet are connected with multiple undercarriage subsystem replicating machines and aircraft total simulation machine respectively；Bus detection is connected with multiple undercarriage subsystem replicating machines, aircraft total simulation machine respectively with analysis computer, its signal can be detected and analyzed；Multiple undercarriage subsystem replicating machines and aircraft total simulation machine are connected with each other by Reflective memory network and can to carry out real time data interactive and shared；Multiple undercarriage subsystem replicating machine and aircraft total simulation machines are connected by signal adaptation unit with equipment in kind respectively；Landing Gear System control law synthesis verification platform can carry out Digital Simulation and HWIL simulation to Landing Gear System.The utility model can not only realize the l-G simulation test of undercarriage subsystem, additionally it is possible to realize the influence of Comprehensive Control l-G simulation test and Landing Gear System to aircraft between subsystem.
Description
Technical field
The utility model belongs to aircraft takeoffs and landings frame control system technical field, and in particular to a kind of Landing Gear System control law
Comprehensive verification platform.
Background technology
The security incident of aircraft more than 50% occurs not only to have good fly in takeoff and landing stage, aircraft at present
Row characteristic, should also have good ground handling characteristic, landing gear control system control law is mainly imitative by numeral at this stage
Very inertia test table is verified with subsystem testing stand；
Aircraft floor is a complicated multi-body system when running, and aircraft dynamics side is established using traditional Digital Simulation
The method that journey solves is taken time and effort, and generally for simulated effect is ensured, a large amount of simplification have been carried out to model, such as reduces fuselage
Freedom of motion, or motion of each wheel etc. is replaced with the motion of non-resilient support quality point, these are for multi-wheeled bogie
Formula aircraft, it can not truly study the respective stressing conditions of wheel.
Inertia test table is tested considerably complicated to brake process simulation system, and inertia wheel surface can not simulate truly well
Runway unevenness, smoothness；Limited by structural strength and space, be difficult to carry out the wheel with multi-wheeled bogie on testing stand
Wheels-locked testing.
Utility model content
The purpose of this utility model：In order to solve the above problems, the utility model proposes a kind of control of Landing Gear System
Comprehensive verification platform is restrained, airframe six degrees of freedom model and Landing gear model is established by building vector analysis, builds and rise and fall
Frame system control law synthesis verifies software and hardware integrated platform, considers landing-gear system, Nose Wheel Steering system, wheel and stops
Car system control law and the ground influence on aircraft entirety.
The technical solution of the utility model:A kind of Landing Gear System control law synthesis verification platform, it is characterised in that bag
Include：Multiple undercarriage subsystem replicating machines, aircraft total simulation machine, manipulation and data acquisition computer, observing and controlling and master control management
Computer, three-dimensional live-instrument show computer and bus detection and analysis computer；
The manipulation shows computer with data acquisition computer, observing and controlling and master control management computer, three-dimensional live-instrument
It is connected by cable with the side ports of Ethernet one, another side ports of Ethernet are imitated with the multiple undercarriage subsystem respectively
Prototype and the connection of aircraft total simulation machine；
The bus detection connects with multiple undercarriage subsystem replicating machines, aircraft total simulation machine respectively with analysis computer
Connect, its signal can be detected and analyzed；
The multiple undercarriage subsystem replicating machine and aircraft total simulation machine are connected with each other by Reflective memory network and energy
It is interactive and shared enough to carry out real time data；
The multiple undercarriage subsystem replicating machine and aircraft total simulation machine passes through signal adaptation unit and material object respectively
Equipment connects；
The Landing Gear System control law synthesis verification platform can carry out Digital Simulation and half material object to Landing Gear System
Emulation.
Preferably, the undercarriage subsystem replicating machine be separately operable undercarriage control control law and external drive model,
Brake control law and external drive model, Nose Wheel Steering control law and external drive model.
Preferably, the multiple undercarriage emulation subsystem is respectively that landing-gear system replicating machine, brake system are imitated
Prototype, Nose Wheel Steering system emulation machine.
Preferably, the bus detection and analysis computer are to multiple undercarriage subsystem replicating machines and aircraft total simulation
1553B and Arinc429 bus signals in machine are detected and analyzed.
Preferably, the signal adaptation unit is signal condition/transfer box, under HWIL simulation pattern, real equipment
It is connected with multiple undercarriage subsystem replicating machines and aircraft total simulation machine by signal condition/transfer box, interface can be realized
Matching and signal transmission.
Preferably, the manipulation receives the control instruction of flight stick and flight pin rudder with data acquisition computer, leads to
Cross Ethernet to be distributed in multiple undercarriage subsystem replicating machine and aircraft total simulation machines, handle control, throttle can be realized
Control and the function of flight pin rudder pedal.
Preferably, observing and controlling establishes undercarriage simulation model with master control management computer, and automatically generates configuration processor download
Into multiple undercarriage subsystem replicating machines, undercarriage subsystem replicating machine is monitored and managed.
Preferably, the three-dimensional live-instrument shows that computer is received by Ethernet and comes from multiple undercarriage subsystems
The data of replicating machine, aircraft total simulation machine, the posture of undercarriage is showed.
The advantageous effects of technical solutions of the utility model：A kind of Landing Gear System control law synthesis of the utility model is tested
Platform is demonstrate,proved, is realized using multidisciplinary simulation software joint modeling comprising landing gear mechanism multi-body Dynamics Model, aircraft body
The multidisciplinary complex model of model, Landing Gear System control law and external drive model, in combination with Ethernet and real-time simulation
Machine carries out Digital Simulation and semi-physical simulation, the application of real-time simulation machine to Landing Gear System can not need simplified model with regard to energy
Enough realize the requirement of real-time of aircraft, ensure that the integrality of model, and can by the real-time status of aircraft by high speed with
Too net transmits in real time carries out Dynamic Announce into computer.The utility model can not only realize that undercarriage point is
The l-G simulation test of system, additionally it is possible to realize the influence of Comprehensive Control l-G simulation test and Landing Gear System to aircraft between subsystem.
Brief description of the drawings
Fig. 1 is that a kind of numeral of a preferred embodiment of Landing Gear System control law synthesis verification platform of the utility model is imitated
True structure composition schematic diagram；
Fig. 2 is a kind of half material object of a preferred embodiment of Landing Gear System control law synthesis verification platform of the utility model
Simulation architecture composition schematic diagram.
Embodiment
Landing Gear System is mainly by three undercarriage control subsystem, brake subsystem, Nose Wheel Steering subsystem subsystems
Composition, Landing Gear System comprehensive verification platform are mainly to verify that three system control laws and Landing Gear System are overall to aircraft
Influence.
A kind of Landing Gear System control law synthesis verification platform, including：Multiple undercarriage subsystem replicating machines, aircraft are overall
Replicating machine, manipulation and data acquisition computer, observing and controlling and master control management computer, three-dimensional live-instrument show computer and total
Line detects and analysis computer；
In the present embodiment, multiple undercarriages emulation subsystems are respectively that landing-gear system replicating machine, brake system are imitated
Prototype, Nose Wheel Steering system emulation machine；
Landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine are separately operable undercarriage
Folding and unfolding control law and external drive model, brake control law and external drive model, Nose Wheel Steering control law and external drive mould
Type；
Aircraft total simulation owner will run aircraft body motion calculation model and undercarriage multi-body Dynamics Model.
Manipulation is made up of with data acquisition computer a Windows main frame, and the main frame receives flight stick and flight
The various control instructions of pin rudder, the various control commands of user are transmitted to multiple undercarriage subsystem replicating machines by Ethernet and flown
In machine total simulation machine, the function of handle control, Throttle Opening Control and flight pin rudder pedal can be achieved；
Observing and controlling is based on windows platform with master control management computer, is set up using Matlab/Simulink, AMESim
Fall frame folding and unfolding, brake and Nose Wheel Steering simulation model, simulation model can automatically generate executable program, and download to
Real time execution in VxWorks target machine.Passed through using SimCreator main control softwares and the aobvious control components of SimViewer patterned
Mode realizes the monitoring to replicating machine, completes the management function to real-time target machine.
Three-dimensional live-instrument shows that computer is made up of 1 Windows main frame, is received by Ethernet and comes from multiple
Fall frame subsystem replicating machine, the data of aircraft total simulation machine, run there is the aircraft that undercarriage participates in slide, take off and land
Process is shown, and instrument shows that instrument display interface mainly related to undercarriage control state and flying instruments are shown
Interface.
Bus detection is connected with analysis computer with multiple undercarriage subsystem replicating machines and aircraft total simulation machine, is passed through
Dedicated bus test software BUSTOOLS is run to realize in multiple undercarriage subsystem replicating machines and aircraft total simulation machine
1553B and Arinc429 bus signals are detected and analyzed.
Landing Gear System control law synthesis verification platform can carry out Digital Simulation and HWIL simulation to Landing Gear System.
Digital Simulation pattern：
Manipulation receives the various control instructions of flight stick and aircraft pin rudder with data acquisition computer, passes through Ethernet
Various user's control commands are transmitted to landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine
And aircraft total simulation machine；
Observing and controlling and master control management computer by undercarriage control, brake and Nose Wheel Steering simulation model generate code by with
It is too off the net to be loaded onto landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine and aircraft totality
Run in replicating machine, instructed with reference to the aircraft handling manipulated and data acquisition computer is assigned, run Landing Gear System and aircraft
Ontology model, at the same it is interactive and shared using reflective memory progress real time data between replicating machine；
Landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine and aircraft are totally imitative
Result is transmitted to three-dimensional vision-instrument display computer, by the posture of undercarriage by Ethernet after prototype resolves operation
Showed；
Bus is detected with analysis computer in real time in multiple undercarriage subsystem replicating machines and aircraft total simulation machine
1553B and Arinc429 bus signals are detected and analyzed.
HWIL simulation pattern：
HWIL simulation pattern is to carry out half material object with the crosslinking of real undercarriage equipment on the basis of Digital Simulation pattern
Emulation；
Because real computer equipment interface and the simulation model interface inside replicating machine are inconsistent, so needing to set up
Corresponding signal adaptation unit, realize that the Interface Matching of real equipment and emulator and signal transmit by cable, it is real half
Under thing simulation model, what Controlling model was run is the control law of real equipment, and aircraft totality and undercarriage kinetic model are still transported
Row is in aircraft body replicating machine.
Manipulation receives the various control instructions of flight stick and aircraft pin rudder with data acquisition computer, passes through Ethernet
Various user's control commands are transmitted to landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine
And aircraft total simulation machine；
Observing and controlling and master control management computer by undercarriage control, brake and Nose Wheel Steering simulation model generate code by with
It is too off the net to be loaded onto landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine and aircraft totality
Run in replicating machine, by the Interface Matching of cable and signal adaptation unit by control command and external drive signal transmit to rise
Fall in frame system actual computer；
In the present embodiment, signal adaptation unit is preferably signal condition/transfer box, under HWIL simulation pattern, truly
Equipment is connected with multiple undercarriage subsystem replicating machines and aircraft total simulation machine by signal condition/transfer box, can be realized
Interface Matching and signal transmission.
Result is transmitted to three-dimensional vision-instrument by Ethernet after the resolving operation of landing-gear system actual computer shows
Show computer, the posture of undercarriage is showed.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model
The spirit and scope of technical scheme.
Claims (8)
- A kind of 1. Landing Gear System control law synthesis verification platform, it is characterised in that including：Multiple undercarriage subsystem emulation Machine, aircraft total simulation machine, manipulation and data acquisition computer, observing and controlling and master control management computer, three-dimensional live-instrument are shown Computer and bus detection and analysis computer；The manipulation shows that computer passes through with data acquisition computer, observing and controlling and master control management computer, three-dimensional live-instrument Cable is connected with the side ports of Ethernet one, another side ports of Ethernet respectively with the multiple undercarriage subsystem replicating machine And aircraft total simulation machine connection；The bus detection is connected with multiple undercarriage subsystem replicating machines, aircraft total simulation machine respectively with analysis computer, Its signal can be detected and analyzed；The multiple undercarriage subsystem replicating machine and aircraft total simulation machine are connected with each other and can entered by Reflective memory network Row real time data is interactive and shared；The multiple undercarriage subsystem replicating machine and aircraft total simulation machine passes through signal adaptation unit and equipment in kind respectively Connection；The Landing Gear System control law synthesis verification platform can carry out Digital Simulation and HWIL simulation to Landing Gear System.
- 2. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：The undercarriage divides System replicating machine is separately operable undercarriage control control law and external drive model, brake control law and external drive model, front-wheel Turning control law and external drive model.
- 3. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：The multiple undercarriage It is respectively landing-gear system replicating machine, brake system replicating machine, Nose Wheel Steering system emulation machine to emulate subsystem.
- 4. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：Bus detection with Analysis computer is to 1553B the and Arinc429 bus signals in multiple undercarriage subsystem replicating machines and aircraft total simulation machine Detected and analyzed.
- 5. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：The signal adaptation list Member is signal condition/transfer box, under HWIL simulation pattern, real equipment and multiple undercarriage subsystem replicating machines and aircraft Total simulation machine is connected by signal condition/transfer box, can realize Interface Matching and signal transmission.
- 6. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：The manipulation and data Collecting computer receives the control instruction of flight stick and flight pin rudder, and multiple undercarriage subsystems are distributed to by Ethernet In replicating machine and aircraft total simulation machine, the function of handle control, Throttle Opening Control and flight pin rudder pedal can be realized.
- 7. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：Observing and controlling and master control management Computer establishes undercarriage simulation model, and automatically generates configuration processor and be downloaded to multiple undercarriage subsystem replicating machines In, undercarriage subsystem replicating machine is monitored and managed.
- 8. Landing Gear System control law synthesis verification platform as claimed in claim 1, it is characterised in that：The three-dimensional live- Instrument shows that computer receives the data from multiple undercarriage subsystem replicating machines, aircraft total simulation machine by Ethernet, The posture of undercarriage is showed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201720839773.8U CN206946224U (en) | 2017-07-12 | 2017-07-12 | A kind of Landing Gear System control law synthesis verification platform |
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| CN201720839773.8U CN206946224U (en) | 2017-07-12 | 2017-07-12 | A kind of Landing Gear System control law synthesis verification platform |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111942616A (en) * | 2020-08-24 | 2020-11-17 | 北京特种机械研究所 | 1553B bus type falling frame test equipment and method |
-
2017
- 2017-07-12 CN CN201720839773.8U patent/CN206946224U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111942616A (en) * | 2020-08-24 | 2020-11-17 | 北京特种机械研究所 | 1553B bus type falling frame test equipment and method |
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