CN105000172A - Launch and recovery electrical control system of aircraft landing gear - Google Patents
Launch and recovery electrical control system of aircraft landing gear Download PDFInfo
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- CN105000172A CN105000172A CN201510445292.4A CN201510445292A CN105000172A CN 105000172 A CN105000172 A CN 105000172A CN 201510445292 A CN201510445292 A CN 201510445292A CN 105000172 A CN105000172 A CN 105000172A
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Abstract
The invention discloses a launch and recovery electrical control system of an aircraft landing gear. The launch and recovery electrical control system comprises a landing gear control switch, a displayer, a plurality of position sensors, a mechanical and electrical management computer, a power driving device, a landing gear hydro-electric valve, a guard board hydro-electric valve, a landing gear mechanism and a guard board mechanism. After the mechanical and electrical management computer receives a launch and recovery instruction of the control switch of the landing gear, and corresponding control signals are output to the power driving device according to logistics by collecting feedback signals of position sensors mounted on the landing gear mechanism and the guard board mechanism, so that the landing gear hydro-electric valve and the guard board hydro-electric valve are controlled to be reversed, and normal launch and recovery of the landing gear mechanism and the guard board mechanism are achieved; and meanwhile, the mechanical and electrical management computer monitors the states of the landing gear and the state of guard boards in real time, and the position states and failure alarm information are sent to the displayer. The development cost of an aircraft is effectively reduced, and the development period is effectively shortened; and the monitoring on the states and failures of the launch and recovery system of the landing gear is reinforced, and the maintenance of the system is greatly improved.
Description
Technical field
The present invention relates to a kind of undercarriage holding electric control system.
Background technology
In home-built aircraft, undercarriage control electrical control mostly still adopts a large amount of relays to build control logic and realizes.Not only control logic is simple, single, and not enough to Landing Gear System condition monitoring, and fault detect rate is low, and maintainability is poor.If Variation control condition, also need the cost (increase the development cost of aircraft, extend the lead time) costed a lot of money.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
In order to overcome the drawback of undercarriage folding and unfolding traditional control method, particularly controlled condition changes the shortcoming of (or injection) difficulty, the technical issues that need to address of the present invention are to provide a kind of undercarriage holding electric control system, Import computer technology realizes computer management and control to Landing Gear System, and devise electrically backup blow the gear down circuit (for cutting off computer control circuit when computer failure, drop), and then improve reliability, the maintainability of system, save the development cost of aircraft, shorten the lead time.
For solving technical matters of the present invention, the technical solution used in the present invention is:
Undercarriage holding electric control system, it comprises landing-gear actuation switch, telltale, some position transdusers, Electromechanical Management computing machine, power driving device, alighting gear liquid electricity valve, backplate liquid electricity valve, landing gear mechanism and backplate mechanism, described landing gear mechanism and backplate mechanism are all provided with some position transdusers, after described Electromechanical Management computing machine receives the folding and unfolding instruction of landing-gear actuation switch, landing gear mechanism is arranged on by gathering, position sensor feedback signal in backplate mechanism, logically export corresponding control signal to power driving device, and then control alighting gear liquid electricity valve and the commutation of backplate liquid electricity valve, realize the normal folding and unfolding of landing gear mechanism and backplate mechanism, Electromechanical Management computing machine is in real time to alighting gear and backplate monitoring state simultaneously, telltale is sent by its location status and fault warning information.
Described power driving device is by Power supply.
Wherein, alighting gear and backplate are not mechanical linkage, and landing gear mechanism and backplate mechanism independently of one another, have independently hydraulic control circuit.By alighting gear liquid electricity valve commutation control alighting gear receipts on put down, by backplate liquid electricity valve commutation control backplate receipts on put down.
Undercarriage control electric control system electric control circuit is divided into Normal Takeoff and Landing frame folding and unfolding control circuit and backup blow the gear down control circuit.Electric backup blow the gear down circuit is used for cutting off computer control circuit when computer failure, drop.
Beneficial effect of the present invention: due to Import computer technology, complicated logic is more easily realized to the control of landing-gear system, the boundary limitation conditions such as aircraft flight height, speed, attitude can be introduced, and the change of control logic also becomes simple, significantly reduce the development cost of aircraft and shorten the lead time, strengthen the state to landing-gear system and failure monitoring, significantly improve the maintainability of system.
Accompanying drawing explanation
Fig. 1 is the electric control theory block diagram of landing-gear system of the present invention.
Fig. 2 is normal gear up computer controlled block diagram.
Fig. 3 is normal blow the gear down computer controlled block diagram.
1, landing-gear actuation switch, 2, telltale, 3, Electromechanical Management computing machine, 4, power driving device, 5, power supply, 6, alighting gear liquid electricity valve, 7, backplate liquid electricity valve, 8, landing gear mechanism, 9, backplate mechanism, 10, position transduser.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
Undercarriage holding electric control system of the present invention, it comprises landing-gear actuation switch 1, telltale 2, some position transdusers 10, Electromechanical Management computing machine 3, power driving device 4, alighting gear liquid electricity valve 6, backplate liquid electricity valve 7, landing gear mechanism 8 and backplate mechanism 9, landing gear mechanism 8 and backplate mechanism 9 are all provided with some position transdusers 10, Electromechanical Management computing machine 3 is by gathering the feedback signal of each position sensor 10, and then judge that the state of alighting gear and backplate is (in receipts, put down or other position), after Electromechanical Management computing machine 3 receives the folding and unfolding instruction of landing-gear actuation switch 1, landing gear mechanism 8 is arranged on by gathering, position sensor feedback signal in backplate mechanism 9, (aircraft flight height can be introduced according to set control logic, speed, the boundary limitation conditions such as attitude) export corresponding control signal to power driving device 4, power driving device 4 is powered by power supply 5, and then control alighting gear liquid electricity valve 6 and backplate liquid electricity valve 7 commutates, realize the normal folding and unfolding of Landing Gear System, Electromechanical Management computing machine 3 is in real time to alighting gear and backplate monitoring state simultaneously, telltale 2 is sent by its location status and fault warning information.
Undercarriage holding electric control system electric control circuit is divided into Normal Takeoff and Landing frame folding and unfolding control circuit and backup blow the gear down control circuit, electric backup blow the gear down circuit is used for cutting off computer control circuit when computer failure, drop.
1) Normal Takeoff and Landing frame folding and unfolding control circuit
The normal folding and unfolding of Landing Gear System is controlled by action landing-gear actuation switch 1, Electromechanical Management computing machine 3 completes the management such as collection, record, self-inspection, logic output control of landing-gear system signal, is arranged on the multifunction display in passenger cabin, approaching signal box for showing undercarriage control position and fault/status information.
After Electromechanical Management computing machine 3 receives the folding and unfolding instruction of landing-gear actuation switch 1, by gathering the position sensor feedback signal be arranged on alighting gear, backplate, logically export corresponding control signal to power driving device 4, and then control alighting gear liquid electricity valve 6 and backplate liquid electricity valve 7 commutates, realize the normal folding and unfolding of Landing Gear System.Electromechanical Management computing machine 3 is in real time to alighting gear and backplate monitoring state simultaneously, telltale is sent by its location status and fault warning information, after power driving device 4 receives Electromechanical Management computing machine 3 control signal, control alighting gear liquid electricity valve 6, backplate liquid electricity valve 7 commutates, realize the normal folding and unfolding of landing gear mechanism 8 and backplate mechanism 9.
A., during normal gear up, being controlled (by Fig. 2) by Electromechanical Management computing machine 3, alighting gear backplate all opens-> alighting gear all packs up-and > backplate packs up.
B., during normal blow the gear down, being controlled (by Fig. 3) by Electromechanical Management computing machine 3, alighting gear backplate all opens-> alighting gear all puts down-and > backplate packs up.
2) blow the gear down control circuit is backed up
When normal operation of landing gear electric control circuit (or Electromechanical Management computing machine) breaks down, by electrically backing up blow the gear down switch cutoff Electromechanical Management computer logic control circuit, drop.
Claims (2)
1. undercarriage holding electric control system, it is characterized in that: it comprises landing-gear actuation switch, telltale, some position transdusers, Electromechanical Management computing machine, power driving device, alighting gear liquid electricity valve, backplate liquid electricity valve, landing gear mechanism and backplate mechanism, described landing gear mechanism and backplate mechanism are all provided with some position transdusers, after described Electromechanical Management computing machine receives the folding and unfolding instruction of landing-gear actuation switch, landing gear mechanism is arranged on by gathering, position sensor feedback signal in backplate mechanism, logically export corresponding control signal to power driving device, and then control alighting gear liquid electricity valve and the commutation of backplate liquid electricity valve, realize the normal folding and unfolding of landing gear mechanism and backplate mechanism, Electromechanical Management computing machine is in real time to alighting gear and backplate monitoring state simultaneously, telltale is sent by its location status and fault warning information.
2. undercarriage holding electric control system according to claim 1, is characterized in that: described power driving device is by Power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510445292.4A CN105000172A (en) | 2015-07-27 | 2015-07-27 | Launch and recovery electrical control system of aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510445292.4A CN105000172A (en) | 2015-07-27 | 2015-07-27 | Launch and recovery electrical control system of aircraft landing gear |
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| Publication Number | Publication Date |
|---|---|
| CN105000172A true CN105000172A (en) | 2015-10-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201510445292.4A Pending CN105000172A (en) | 2015-07-27 | 2015-07-27 | Launch and recovery electrical control system of aircraft landing gear |
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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 |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
| CN109353491A (en) * | 2018-09-11 | 2019-02-19 | 陕西千山航空电子有限责任公司 | A kind of airborne computer cockpit handle instruction identification method |
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
| CN110844124A (en) * | 2019-11-11 | 2020-02-28 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN116176832A (en) * | 2023-05-04 | 2023-05-30 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
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| CN202226056U (en) * | 2011-08-15 | 2012-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Control system for front landing gear |
| CN103072687A (en) * | 2011-10-26 | 2013-05-01 | 尤洛考普特公司 | Landing gear, an aircraft, and a method implemented by landing gear |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
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2015
- 2015-07-27 CN CN201510445292.4A patent/CN105000172A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN202226056U (en) * | 2011-08-15 | 2012-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Control system for front landing gear |
| CN103072687A (en) * | 2011-10-26 | 2013-05-01 | 尤洛考普特公司 | Landing gear, an aircraft, and a method implemented by landing gear |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
Cited By (9)
| 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 |
| CN107450307A (en) * | 2017-08-30 | 2017-12-08 | 陕西千山航空电子有限责任公司 | A kind of double remaining control methods of undercarriage of Electromechanical Management computer |
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
| CN109353491A (en) * | 2018-09-11 | 2019-02-19 | 陕西千山航空电子有限责任公司 | A kind of airborne computer cockpit handle instruction identification method |
| CN109353491B (en) * | 2018-09-11 | 2022-08-23 | 陕西千山航空电子有限责任公司 | Airborne computer cockpit handle instruction identification method |
| CN110844124A (en) * | 2019-11-11 | 2020-02-28 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN110844124B (en) * | 2019-11-11 | 2021-09-03 | 中国运载火箭技术研究院 | Reusable carrier landing gear control system and control method |
| CN116176832A (en) * | 2023-05-04 | 2023-05-30 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
| CN116176832B (en) * | 2023-05-04 | 2023-10-24 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
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Application publication date: 20151028 |
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