CN205010480U - Unmanned aerial vehicle undercarriage composite control system - Google Patents
Unmanned aerial vehicle undercarriage composite control system Download PDFInfo
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- CN205010480U CN205010480U CN201520553736.1U CN201520553736U CN205010480U CN 205010480 U CN205010480 U CN 205010480U CN 201520553736 U CN201520553736 U CN 201520553736U CN 205010480 U CN205010480 U CN 205010480U
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Abstract
The utility model relates to an unmanned aerial vehicle undercarriage composite control system divide into electric subtotal atmospheric pressure part, the pneumatic circuit comprises two gas cylinders and two atmospheric pressure solenoid valves, electric system includes front wheel turn power amplification actuator, atmospheric pressure solenoid valve, baroceptor, undercarriage position sensor, brake power amplification actuator, undercarriage composite control unit component, the pneumatic circuit includes that pneumatic circuit main entrance and pneumatic circuit are equipped with the passageway, forms pressure system main entrance by first gas cylinder and second atmospheric pressure solenoid valve, forms the pneumatic circuit by second gas cylinder and second atmospheric pressure solenoid valve and is equipped with the passageway, first atmospheric pressure solenoid valve and second atmospheric pressure solenoid valve be two remaining atmospheric pressure solenoid valves. The utility model discloses two remainings configurations are taked in high security, electric and atmospheric pressure part, and arbitrary electric or atmospheric pressure component breaks down in the system, all can use the stand -by power source or switch over to alternate channel work, and each item function of impact systems has not been guaranteed undercarriage system homoenergetic under any single trouble and has normally been worked. The utility model discloses simplify the rise and fall constitution of function of aircraft, alleviateed aircraft weight.
Description
Technical field
This patent relates to a kind of unmanned plane alighting gear complex control system, specifically the front master of unmanned aerial vehicle rise hatch door and gear down, the complex control system of Nose Wheel Steering and main wheel brake function, this system be a kind of all can ensure under any single failure the hatch door of unmanned plane in descent with gear down, Nose Wheel Steering effectively and reliably stops the security ststem of grounding machine.
Background technology
Because unmanned plane itself has lightweight, the feature such as fuel economy good, attack time short and maintainability is good again, along with domestic and international unmanned plane is in the use in each field, unmanned plane increases increasingly to alighting gear complex control system reliability and safety.
The System's composition of electric brake and Nose Wheel Steering is respectively described in " aircraft electric braking high-voltage drive design and research " and in September, 2013 " machine science and technology " in " aircraft all electric Nose Wheel Steering system and Optimization analyses " two literary compositions in June, 2012 " micromotor ", but after all lacking the system failure, the ability of remaining reconstruct, electric system is the higher system of aircraft's failure ratio normally, so the reliability and safety of said system is lower.
Summary of the invention
Completely independent and occur for solving undercarriage control, Nose Wheel Steering and brake in existing unmanned plane Landing Gear System: it is many that system forms product, use working medium is different, overall weight weight, reliability and safety low wait deficiency, the present invention proposes a kind of alighting gear complex control system.
The present invention includes pressure system and electric system: described pressure system is made up of two gas cylinders and two air pressure electromagnetic valve, described electric system comprises Nose Wheel Steering power gain actuator, air pressure electromagnetic valve, baroceptor, landing gear position sensor, brake power amplifies actuator, alighting gear Comprehensive Control unit forms.
Described pressure system comprises pressure system main channel and pressure system for passage, forms pressing system main channel, form pressure system for passage by the second gas cylinder and the second air pressure electromagnetic valve by the first gas cylinder and the second air pressure electromagnetic valve; The first described air pressure electromagnetic valve and the second air pressure electromagnetic valve are two remaining air pressure electromagnetic valve.
Described electric system comprises electric main channel and electrically for passage, by aircraft main power source, aircraft emergency battery, two remaining Nose Wheel Steering power gain actuator, two remaining landing gear position sensor, two redundance flight control systems computing machine, two remaining alighting gear Comprehensive Control unit, the left brake power of two remaining amplifies actuator, the amplification of two remaining right brake power actuator, two remaining first air pressure electromagnetic valve, two remaining second air pressure electromagnetic valve, two remaining first baroceptor and two remaining second baroceptor form.
The electric part of alighting gear complex control system comprises Nose Wheel Steering power gain actuator, air pressure electromagnetic valve, baroceptor, landing gear position sensor, brake power amplification actuator, alighting gear Comprehensive Control unit, the two redundancy design of above-mentioned electric part, defines the primary channel of electric part.
Landing gear control system air pressure part comprises active and standby gas cylinder and reducing valve composition.
The first passage of the first winding that the electric main channel of the above unmanned plane comprises the first winding of each Nose Wheel Steering power gain actuator and primary importance sensor, the first coil of the first air pressure electromagnetic valve, the first coil of the second air pressure electromagnetic valve, the first passage of the first baroceptor, the first passage of the second baroceptor, the first passage of landing gear position sensor, brake power amplify actuator and primary importance sensor, alighting gear Comprehensive Control unit.When connecting above-mentioned electric part main channel.The primary importance sensor of Nose Wheel Steering power gain actuator is connected with the first passage input interface of alighting gear Comprehensive Control unit, the first passage of landing gear position sensor is connected with the first passage input interface of alighting gear Comprehensive Control unit, the primary importance sensor that brake power amplifies actuator is connected with the first passage input interface of alighting gear Comprehensive Control unit, the first passage of the first baroceptor is connected with the first passage input interface of alighting gear Comprehensive Control unit, the first passage of the second baroceptor is connected with the first passage input interface of alighting gear Comprehensive Control unit.First winding of Nose Wheel Steering power gain actuator is connected with the first passage output interface of alighting gear Comprehensive Control unit, first coil of the first air pressure electromagnetic valve is connected with the main channel output interface of alighting gear Comprehensive Control unit, first coil of the second air pressure electromagnetic valve is connected with the first passage output interface of alighting gear Comprehensive Control unit, and the first winding that brake power amplifies actuator is connected with the first passage output interface of alighting gear Comprehensive Control unit.
The above unmanned plane electrically standby passage comprises the second winding and the second place sensor of each Nose Wheel Steering power gain actuator, second coil of the first air pressure electromagnetic valve, second coil of the second air pressure electromagnetic valve, the second channel of the first baroceptor, the second channel of the second baroceptor, the second channel of landing gear position sensor, brake power amplifies the second winding and the second place sensor of actuator, the second channel of alighting gear Comprehensive Control unit, when connecting above-mentioned electric part second channel, the second channel input interface of the second place sensor of Nose Wheel Steering power gain actuator with alighting gear Comprehensive Control unit is connected, the second channel of landing gear position sensor is connected with the second channel input interface of alighting gear Comprehensive Control unit, brake power amplifies the second place sensor of actuator and is connected with the standby second input interface of alighting gear Comprehensive Control unit, second of Nose Wheel Steering power gain actuator is connected for the second channel output interface of winding with alighting gear Comprehensive Control unit, second coil of the first air pressure electromagnetic valve is connected with the second channel output interface of alighting gear Comprehensive Control unit, second coil of the second air pressure electromagnetic valve is connected with the second channel output interface of alighting gear Comprehensive Control unit, the second winding that brake power amplifies actuator is connected with the second channel output interface of alighting gear Comprehensive Control unit.
The air pressure part of described unmanned plane landing gear control system connects as follows: the first gas cylinder voltage supply mouth is connected with the first air pressure electromagnetic valve input port, second gas cylinder is connected with the second air pressure electromagnetic valve input port, first and second air pressure electromagnetic valve delivery port is in parallel, is connected with unmanned plane nose-gear and the pressurized strut of main landing gear compartment door lock.
Unmanned plane is in descent, control command is opened by bus transmission aircraft door and alighting gear by UAV flight control, after alighting gear Comprehensive Control unit receives order, open the first air pressure electromagnetic valve, air pressure is by cabin door lock pressurized strut main before electromagnetic valve effect aircraft, there is displacement in front main cabin door lock pressurized strut, open front MLG Door and lock, simultaneously, main cabin door lock pressurized strut triggers coordination valve on unmanned plane, air pressure is put down by main landing gear before main landing gear uplock effect before coordination valve effect aircraft, whether alighting gear Comprehensive Control unit detects hatch door and alighting gear by baroceptor and two remaining hatch door and landing gear position sensor and puts down and put in place.
After landing, send Nose Wheel Steering and braking commands by UAV flight control by bus, alighting gear Comprehensive Control unit amplifies actuator by Nose Wheel Steering power gain actuator and brake power and completes corresponding Nose Wheel Steering and brake operation unmanned plane.
Of the present inventionly electrically all take pair redundant configurations with air pressure part, ensure that Landing Gear System all can normally work under any single failure.Specifically: system is active and standby pair of gas cylinder mode for letting the source of the gas of cabin door and alighting gear fly away, system power supply adopts is that aircraft main power source of boarding a plane is in parallel with emergency battery two-way simultaneously to alighting gear Comprehensive Control unit power supply mode; System control component-Comprehensive Control unit adopts independently primary channel mode, hot spare mode of operation; The acquisition instruction path of system-independently obtained by Comprehensive Control cell main-slave passage; System sensing element-baroceptor, hatch door and landing gear position sensor, Nose Wheel Steering power gain actuator position transduser, brake power amplify actuator position transduser and all have employed redundancy design, simultaneously for Comprehensive Control unit provides signal; System power element-air pressure electromagnetic valve, Nose Wheel Steering power gain actuator winding, brake power amplify actuator winding and all take two redundancy design, accept Comprehensive Control unit master or standby passage control.
This invention takes the fault handling strategy of high security, both ensure that the various functions of unmanned aerial vehicle landing gear control system, in turn simplify the composition of aircraft takeoffs and landings function, alleviate aircraft weight, thus largely improve the safety of unmanned aerial vehicle landing process.Specifically: in system arbitrary electrically or gas-pressure component break down, all can use stand-by power source or switch to alternate channel work, not the various functions of influential system, concrete analysis is in table 1.
Table 1
Accompanying drawing explanation
Fig. 1 is alighting gear complex control system block diagram.In figure:
1. aircraft main power source; 2. aircraft emergency battery; 3. Nose Wheel Steering power gain actuator; 4. landing gear position sensor; 5. flight-control computer; 6. alighting gear Comprehensive Control unit; 7. left brake power amplifies actuator; 8. right brake power amplifies actuator; 9. aircraft off front wheel; 10. the left main wheel of aircraft; The right main wheel of 11. aircraft; 12. first gas cylinders; 13. second gas cylinders; 14. first air pressure electromagnetic valve; 15. second air pressure electromagnetic valve; Cabin door lock pressurized strut is played before 16.; 17. left masters play cabin door lock pressurized strut; 18. right masters play cabin door lock pressurized strut; 19. nose-gear lock pressurized struts; 20. left main lock pressurized struts; 21. starboard main landing gear lock pressurized struts; 22. first baroceptor; 23. second baroceptor; 24. aircraft the near front wheels.
Detailed description of the invention
The present embodiment is certain unmanned plane alighting gear complex control system, comprises two remaining pressure system and two remaining electric system.
Described pair of remaining pressure system is made up of two gas cylinders and two air pressure electromagnetic valve.
Described pair of remaining electric system comprises Nose Wheel Steering power gain actuator, air pressure electromagnetic valve, baroceptor, landing gear position sensor, brake power amplification actuator, alighting gear Comprehensive Control unit composition, defines the primary channel of this electric part.
Two gas cylinders in described pair of remaining pressure system are the first gas cylinder 12 and the second gas cylinder 13, two air pressure electromagnetic valve is respectively the first air pressure electromagnetic valve 14 and the second air pressure electromagnetic valve 15 respectively.The first described air pressure electromagnetic valve 14 and the second air pressure electromagnetic valve 15 all adopt two remaining air pressure electromagnetic valve.
The standby passage of the main channel of pressure system and pressure system is had in described pair of remaining pressure system.
The main channel of described pressure system is made up of the first gas cylinder 12 and the first air pressure electromagnetic valve 14, and the standby passage of described pressure system is made up of the second gas cylinder 13 and the second air pressure electromagnetic valve 15.
During connection, one end of described first gas cylinder 12 is connected by pipeline with the input port of the first baroceptor 22, and the other end of described first gas cylinder 12 is connected by pipeline with the input port of the first air pressure electromagnetic valve 14, defines the main channel of pressure system.One end of described second gas cylinder 13 is connected by pipeline with the input port of the second baroceptor 23, and the other end of described second gas cylinder 13 is connected by pipeline with the input port of the second air pressure electromagnetic valve 15, defines the standby passage of pressure system.The delivery port of described first air pressure electromagnetic valve 14 is in parallel with the delivery port of the second air pressure electromagnetic valve 15.
Described pair of remaining electric system comprises aircraft main power source 1, aircraft emergency battery 2, Nose Wheel Steering power gain actuator 3, landing gear position sensor 4, flight-control computer 5, alighting gear Comprehensive Control unit 6, left brake power amplification actuator 7, right brake power amplification actuator 8, first air pressure electromagnetic valve 14, second air pressure electromagnetic valve 15, first baroceptor 22 and the second baroceptor 23.Described Nose Wheel Steering power gain actuator 3, landing gear position sensor 4, flight-control computer 5, alighting gear Comprehensive Control unit 6, left brake power amplify actuator 7, right brake power amplifies actuator 8, first air pressure electromagnetic valve 14, second air pressure electromagnetic valve 15, first baroceptor 22 and the second baroceptor 23 all adopts two remaining.
The electric main channel of unmanned plane landing gear control system and unmanned plane landing gear control system electrically standby passage is had in described pair of remaining electric system, wherein:
The described electric main channel of unmanned plane landing gear control system is by the first winding in described Nose Wheel Steering power gain actuator 3 and primary importance sensor, first coil of the first air pressure electromagnetic valve 14, the first passage of the first baroceptor 22, the first passage of the second baroceptor 23, the first passage of landing gear position sensor 4, the first winding in left brake power amplification actuator 7 and primary importance sensor, the first winding in right brake power amplification actuator 8 and primary importance sensor, the first passage composition of alighting gear Comprehensive Control unit 6.
When the electric main channel of the described unmanned plane landing gear control system of connection, by parallel with aircraft emergency battery 2 for described aircraft main power source 1.The output interface of this aircraft main power source is connected with the first passage input interface of alighting gear Comprehensive Control unit 6; The bus of flight-control computer 5 is connected with the first passage input interface of described alighting gear Comprehensive Control unit; The primary importance sensor of Nose Wheel Steering power gain actuator 3 is connected with the first passage input interface of alighting gear Comprehensive Control unit 6; The first passage of landing gear position sensor 4 is connected with the first passage input interface of alighting gear Comprehensive Control unit 6; The primary importance sensor that left brake power amplifies actuator 7 is connected with the first passage input interface of alighting gear Comprehensive Control unit 6 respectively with the primary importance sensor that right brake power amplifies actuator 8; The first passage of the first baroceptor 22 is connected with the first passage input interface of described alighting gear Comprehensive Control unit 6 respectively with the first passage of the second baroceptor 15; First winding of Nose Wheel Steering power gain actuator 3 is connected with the first passage output interface of alighting gear Comprehensive Control unit 6; First coil of the first air pressure electromagnetic valve 14 is connected with the first passage output interface of described alighting gear Comprehensive Control unit 6 respectively with the first coil of the second air pressure electromagnetic valve 15; The first winding that left brake power amplifies actuator 7 is connected with the first passage output interface of described alighting gear Comprehensive Control unit respectively with the first winding that right brake power amplifies actuator 8.
The electric standby passage of described unmanned plane landing gear control system is by the second winding in described Nose Wheel Steering power gain actuator 3 and second place sensor, second coil of the first air pressure electromagnetic valve 14, the second channel of the first baroceptor 22, the second channel of the second baroceptor 23, the second channel of landing gear position sensor 4, the second winding in left brake power amplification actuator 7 and second place sensor, the second winding in right brake power amplification actuator 8 and second place sensor, the second channel composition of alighting gear Comprehensive Control unit 6.
When connecting described unmanned plane landing gear control system electrically for passage, by parallel with aircraft emergency battery 2 for described aircraft main power source 1.The output interface of this aircraft emergency battery 2 is connected with the second channel input interface of alighting gear Comprehensive Control unit 6; The bus of flight-control computer 5 is connected with the second channel input interface of described alighting gear Comprehensive Control unit; The second place sensor of Nose Wheel Steering power gain actuator 3 is connected with the second channel input interface of alighting gear Comprehensive Control unit 6; The second channel of landing gear position sensor 4 is connected with the second channel input interface of alighting gear Comprehensive Control unit 6; The second place sensor that left brake power amplifies actuator 7 is connected with the second channel input interface of alighting gear Comprehensive Control unit 6 respectively with the second place sensor that right brake power amplifies actuator 8; The second channel of the first baroceptor 22 is connected with the second channel input interface of described alighting gear Comprehensive Control unit 6 respectively with the second channel of the second baroceptor 15; Second winding of Nose Wheel Steering power gain actuator 3 is connected with the second channel output interface of alighting gear Comprehensive Control unit 6; Second coil of the first air pressure electromagnetic valve 14 is connected with the second channel output interface of described alighting gear Comprehensive Control unit 6 respectively with the second coil of the second air pressure electromagnetic valve 15; The second winding that left brake power amplifies actuator 7 is connected with the second channel output interface of described alighting gear Comprehensive Control unit respectively with the second winding that right brake power amplifies actuator 8.
During work, aircraft door and gear down instruction is sent by bus by UAV flight control 5, after alighting gear Comprehensive Control unit 6 main channel receives instruction, open the first air pressure electromagnetic valve 14, the air pressure of the first gas cylinder 12 makes a front cabin door lock pressurized strut 16 by the first air pressure electromagnetic valve 14, left master plays cabin door lock pressurized strut 17, right master plays cabin door lock pressurized strut 18, the pressurized strut 19 of nose-gear lock, left main lock pressurized strut 20 is locked pressurized strut 21 with starboard main landing gear and is opened, complete putting down of unmanned plane hatch door and alighting gear, alighting gear Comprehensive Control unit 6 is by the state of monitoring landing gear position sensor 4, whether acquisition unmanned plane hatch door and alighting gear put down the information put in place, when there is alighting gear Comprehensive Control unit 6 main channel fault, first gas cylinder 12 is revealed, the standby passage enabling alighting gear Comprehensive Control unit 6 during the first following situation of coil fault of the first air pressure electromagnetic valve 14 is taken over main channel and is carried out work, another for ensureing system operational security, by closedown first air pressure electromagnetic valve 14.
After UAV Landing, flight control computer 5 sends Nose Wheel Steering and brake instruction by bus, after alighting gear Comprehensive Control unit 6 main channel receives instruction, Nose Wheel Steering power gain actuator 3 is driven to complete the handling maneuver of aircraft off front wheel 9 and aircraft the near front wheel 24 according to the position transduser of Nose Wheel Steering power gain actuator 3.And the position transduser of actuator 8 is amplified according to left brake power amplification actuator 7 and right brake power, complete the brake operation of the left main wheel of aircraft 10 and the right main wheel 11 of aircraft.When there is alighting gear Comprehensive Control unit 6 main channel fault, the primary importance sensor of Nose Wheel Steering power gain actuator 3 or the first winding failure, left brake power amplifies primary importance sensor or first winding failure of actuator 7, the standby passage enabling alighting gear Comprehensive Control unit 6 when right brake power amplifies primary importance sensor or the first winding failure situation of actuator 8 is taken over main channel and is carried out work, another for ensureing system operational security, primary importance sensor or first winding of Nose Wheel Steering power gain actuator 3 will be disconnected, left brake power amplifies the primary importance sensor of actuator 7 or the first winding and right brake power and amplifies the primary importance sensor of actuator 8 or the power supply of the first winding.
When adopting the present embodiment, the fault handling strategy of system ensemble: for the various failure modes that aircraft may occur, system ensemble takes fault handling strategy, to guarantee the safety of system, specifically in table 2.
Table 2
Claims (6)
1. a unmanned plane alighting gear complex control system, comprise pressure system and electric system: described pressure system is made up of two gas cylinders and two air pressure electromagnetic valve, described electric system comprises Nose Wheel Steering power gain actuator, air pressure electromagnetic valve, baroceptor, landing gear position sensor, brake power amplifies actuator, alighting gear Comprehensive Control unit forms; It is characterized in that:
Described pressure system comprises pressure system main channel and pressure system for passage, forms pressing system main channel, form pressure system for passage by the second gas cylinder and the second air pressure electromagnetic valve by the first gas cylinder and the second air pressure electromagnetic valve; The first described air pressure electromagnetic valve and the second air pressure electromagnetic valve are two remaining air pressure electromagnetic valve,
Described electric system comprises electric main channel and electrically for passage, by aircraft main power source, aircraft emergency battery, two remaining Nose Wheel Steering power gain actuator, two remaining landing gear position sensor, two redundance flight control systems computing machine, two remaining alighting gear Comprehensive Control unit, the left brake power of two remaining amplifies actuator, the amplification of two remaining right brake power actuator, two remaining first air pressure electromagnetic valve, two remaining second air pressure electromagnetic valve, two remaining first baroceptor and two remaining second baroceptor form.
2. a kind of unmanned plane alighting gear complex control system as claimed in claim 1, it is characterized in that, when connecting described pressure system, one end of described first gas cylinder is connected by pipeline with the input port of the first baroceptor, the other end of described first gas cylinder is connected by pipeline with the input port of the first air pressure electromagnetic valve, define the main channel of pressure system, one end of described second gas cylinder is connected by pipeline with the input port of the second baroceptor, the other end of described second gas cylinder is connected by pipeline with the input port of the second air pressure electromagnetic valve, define the standby passage of pressure system, the delivery port of described first air pressure electromagnetic valve is in parallel with the delivery port of the second air pressure electromagnetic valve.
3. a kind of unmanned plane alighting gear complex control system as claimed in claim 1, it is characterized in that, the described electric main channel of unmanned plane landing gear control system is by the first winding in described Nose Wheel Steering power gain actuator and primary importance sensor, first coil of the first air pressure electromagnetic valve, the first passage of the first baroceptor, the first passage of the second baroceptor, the first passage of landing gear position sensor, the first winding in left brake power amplification actuator and primary importance sensor, the first winding in right brake power amplification actuator and primary importance sensor, the first passage composition of alighting gear Comprehensive Control unit.
4. a kind of unmanned plane alighting gear complex control system as claimed in claim 1, it is characterized in that, the electric standby passage of described unmanned plane landing gear control system is by the second winding in described Nose Wheel Steering power gain actuator and second place sensor, second coil of the first air pressure electromagnetic valve, the second channel of the first baroceptor, the second channel of the second baroceptor, the second channel of landing gear position sensor 4, the second winding in left brake power amplification actuator and second place sensor, the second winding in right brake power amplification actuator and second place sensor, the second channel composition of alighting gear Comprehensive Control unit.
5. a kind of unmanned plane alighting gear complex control system as claimed in claim 3, it is characterized in that, when the electric main channel of the described unmanned plane landing gear control system of connection, the first passage input interface of the alighting gear Comprehensive Control unit in the described electric main channel of unmanned plane landing gear control system is connected with the output interface of aircraft main power source; The bus of flight-control computer is connected with the first passage input interface of described alighting gear Comprehensive Control unit; The primary importance sensor of Nose Wheel Steering power gain actuator is connected with the first passage input interface of alighting gear Comprehensive Control unit; The first passage of landing gear position sensor is connected with the first passage input interface of alighting gear Comprehensive Control unit; The primary importance sensor that left brake power amplifies actuator is connected with the first passage input interface of alighting gear Comprehensive Control unit respectively with the primary importance sensor that right brake power amplifies actuator; The first passage of the first baroceptor and the first passage of the second baroceptor are connected with the first passage input interface of described alighting gear Comprehensive Control unit respectively; First winding of Nose Wheel Steering power gain actuator is connected with the first passage output interface of alighting gear Comprehensive Control unit; First coil of the first air pressure electromagnetic valve and the first coil of the second air pressure electromagnetic valve are connected with the first passage output interface of described alighting gear Comprehensive Control unit respectively; The first winding that left brake power amplifies actuator is connected with the first passage output interface of described alighting gear Comprehensive Control unit respectively with the first winding that right brake power amplifies actuator.
6. a kind of unmanned plane alighting gear complex control system as claimed in claim 4, it is characterized in that, when connecting described unmanned plane landing gear control system electrically for passage, by in parallel with aircraft emergency battery for described aircraft main power source, the output interface of this aircraft emergency battery is connected with the second channel input interface of alighting gear Comprehensive Control unit; The bus of flight-control computer is connected with the second channel input interface of described alighting gear Comprehensive Control unit; The second place sensor of Nose Wheel Steering power gain actuator is connected with the second channel input interface of alighting gear Comprehensive Control unit; The second channel of landing gear position sensor is connected with the second channel input interface of alighting gear Comprehensive Control unit; The second place sensor that left brake power amplifies actuator is connected with the second channel input interface of alighting gear Comprehensive Control unit respectively with the second place sensor that right brake power amplifies actuator; The second channel of the first baroceptor and the second channel of the second baroceptor are connected with the second channel input interface of described alighting gear Comprehensive Control unit respectively; Second winding of Nose Wheel Steering power gain actuator is connected with the second channel output interface of alighting gear Comprehensive Control unit; Second coil of the first air pressure electromagnetic valve and the second coil of the second air pressure electromagnetic valve are connected with the second channel output interface of described alighting gear Comprehensive Control unit respectively; The second winding that left brake power amplifies actuator is connected with the second channel output interface of described alighting gear Comprehensive Control unit respectively with the second winding that right brake power amplifies actuator.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107074351A (en) * | 2016-09-30 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Control method, device and the unmanned vehicle of unmanned plane |
| CN109343335A (en) * | 2018-11-05 | 2019-02-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hatch door redundance control system |
| CN110632863A (en) * | 2018-06-25 | 2019-12-31 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle data transmission method and device |
| CN111619791A (en) * | 2019-02-28 | 2020-09-04 | 空中客车营运有限公司 | Landing gear system operation |
| CN112407257A (en) * | 2020-12-04 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
| CN113665797A (en) * | 2021-08-30 | 2021-11-19 | 西安微电子技术研究所 | Electrical and pneumatic heterogeneous redundant undercarriage retractable actuator cylinder of unmanned aerial vehicle and working method |
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2015
- 2015-07-28 CN CN201520553736.1U patent/CN205010480U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107074351A (en) * | 2016-09-30 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Control method, device and the unmanned vehicle of unmanned plane |
| CN110632863A (en) * | 2018-06-25 | 2019-12-31 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle data transmission method and device |
| CN110632863B (en) * | 2018-06-25 | 2021-03-30 | 北京京东尚科信息技术有限公司 | Unmanned aerial vehicle data transmission method and device |
| CN109343335A (en) * | 2018-11-05 | 2019-02-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hatch door redundance control system |
| CN111619791A (en) * | 2019-02-28 | 2020-09-04 | 空中客车营运有限公司 | Landing gear system operation |
| CN112407257A (en) * | 2020-12-04 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
| CN112407257B (en) * | 2020-12-04 | 2021-06-22 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
| CN113665797A (en) * | 2021-08-30 | 2021-11-19 | 西安微电子技术研究所 | Electrical and pneumatic heterogeneous redundant undercarriage retractable actuator cylinder of unmanned aerial vehicle and working method |
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