CN105620732A - Undercarriage extension and retraction system - Google Patents
Undercarriage extension and retraction system Download PDFInfo
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- CN105620732A CN105620732A CN201410708266.1A CN201410708266A CN105620732A CN 105620732 A CN105620732 A CN 105620732A CN 201410708266 A CN201410708266 A CN 201410708266A CN 105620732 A CN105620732 A CN 105620732A
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- undercarriage
- motor
- extension
- retraction
- backplate
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Abstract
The invention discloses an undercarriage extension and retraction system and relates to the field of undercarriage extension and retraction of airplanes. The undercarriage extension and retraction system comprises a flight control computer and three subsystems. The flight control computer is in RS485 communication with the subsystems. The three subsystems are the main undercarriage left extension and retraction subsystem, the main undercarriage right extension and retraction subsystem and the front undercarriage extension and retraction subsystem. The main undercarriage left extension and retraction subsystem is used for controlling extension and retraction of a left undercarriage and a guard board. The main undercarriage right extension and retraction subsystem is used for controlling extension and retraction of a right undercarriage and a guard board. The front undercarriage extension and retraction subsystem is used for controlling extension and retraction of a front undercarriage and a guard board. Each subsystem is composed of a controller, an undercarriage motor, a guard board motor, motor drivers and a disconnecting switch, wherein the undercarriage motor is used for controlling extension and retraction of the corresponding undercarriage, the guard board motor is used for controlling extension and retraction of the corresponding guard board and the number of the motor drivers is equal to the sum of the motor numbers. The undercarriage extension and retraction system is small in size and low in weight; the execution efficiency for extending and retracting the undercarriages is high, and the energy consumption is low; the operating speed for extending and retracting the undercarriages is controllable; a standby motor can be switched on after a single motor breaks down, so that the safety performance is high.
Description
Technical field
The present invention relates to the undercarriage of a kind of aircraft, be specifically related to the folding and unfolding technology of undercarriage.
Background technology
At present, domestic and international aircraft operation of landing gear mainly adopts hydraulic system folding and unfolding and the emergent folding and unfolding of cold gas system to put, and hydraulic system folding and unfolding has the disadvantage that (1) uses the hydraulic drive requirement to safeguarding high, and working oil to remain cleaning; (2) the Hydraulic Elements accuracy of manufacture is required height, complex process, relatively costly; (3) Hydraulic Elements maintenance is more complicated, and need to have higher technical merit; (4) work medium with oil, there is disaster hidden-trouble at work surface; (5) transmission efficiency is low.
Summary of the invention
It is an object of the invention to for above-mentioned prior art not enough, it is provided that a kind of efficiency is high, the electric lifting device frame extension and retraction system consuming energy few.
In order to reach above-mentioned technique effect, the present invention takes techniques below scheme: a kind of landing-gear system, and it includes 1 flight control computer and 3 subsystems, adopts RS485 to communicate between described flight control computer and subsystem. Described 3 subsystems are led left extension and retraction system, led right extension and retraction system and front extension and retraction system respectively, described master plays left extension and retraction system for controlling the folding and unfolding of left side undercarriage and backplate, having led right extension and retraction system for controlling the folding and unfolding of the right undercarriage and backplate, front extension and retraction system is for controlling the folding and unfolding of front undercarriage and backplate. Described subsystem by 1 controller, control the undercarriage motor of corresponding undercarriage control, control the backplate motor of the corresponding backplate folding and unfolding motor driver identical with number of motors summation and location switch composition. Described control edge is provided with put in place signaling interface end and rate signal interface end, is provided with the first dsp board and the second dsp board inside controller, and the first dsp board is used for controlling undercarriage motor, it is achieved the folding and unfolding of corresponding undercarriage; Second dsp board is used for controlling backplate motor, it is achieved the folding and unfolding of corresponding backplate; A-road-through letter it is provided with between described first dsp board and the second dsp board.
The quantity of above-mentioned each subsystem correspondence undercarriage motor is 2, including the standby motor of undercarriage mair motor and undercarriage; The quantity of backplate motor is 2, including the standby motor of backplate mair motor and backplate.
The present invention compared with prior art, has following beneficial effect: system bulk is little, lightweight; Operation of landing gear execution efficiency is high, and power consumption is few; Operation of landing gear operating rate is controlled; After single motor breaks down, switching to standby motor, after location switch lost efficacy, can move the judgement of distance according to rate signal, therefore security performance is high.
Accompanying drawing explanation
Fig. 1 is the topology diagram of the present invention;
Fig. 2 is principles of the invention figure.
Detailed description of the invention
Below in conjunction with embodiments of the invention, the invention will be further elaborated.
Embodiment:
As it is shown in figure 1, a kind of landing-gear system, it includes 1 flight control computer and 3 subsystems, adopts RS485 to communicate between flight control computer with subsystem, and discrete magnitude is as the RS485 backup communicated simultaneously. 3 subsystems are led left extension and retraction system 01, led right extension and retraction system 02 and front extension and retraction system 03 respectively. Having led left extension and retraction system 01 for controlling the folding and unfolding of left side undercarriage and backplate, led right extension and retraction system 02 for controlling the folding and unfolding of the right undercarriage and backplate, front extension and retraction system 03 is for controlling the folding and unfolding of front undercarriage and backplate. Above-mentioned subsystem is by the identical motor driver of 1 controller undercarriage motor corresponding with controller, backplate motor and number of motors summation and location switch composition. The quantity of undercarriage motor is 2, including the standby motor of undercarriage mair motor and undercarriage; The quantity of backplate motor is 2, including the standby motor of backplate mair motor and backplate.
As in figure 2 it is shown, control edge is provided with put in place signaling interface end and rate signal interface end, puts signal in place and rate signal is coupled with on corresponding interface end. The first dsp board and the second dsp board it is provided with, i.e. DSP1 plate and DSP2 plate inside controller. DSP1 plate is used for controlling undercarriage motor, it is achieved the folding and unfolding of corresponding undercarriage, and DSP2 plate is used for controlling backplate motor, it is achieved the folding and unfolding of corresponding backplate. A-road-through letter it is provided with, it is achieved signal interface end obtained is transmitted separately to two boards card between DSP1 plate and DSP2 plate.
Above-mentioned landing-gear system can realize carrying out the function of normal or emergent operation of landing gear and backplate thereof according to flying control instruction, and concrete function is as follows:
Receive flight control computer by the RS485 normal operation of landing gear instruction sent;
Receive flight control computer by the RS485 landing-gear emergency extension instruction sent;
To flight control computer feedback system duty;
Feed back undercarriage to flight control computer to put in place signal;
When RS485 breaks down and cannot communicate, it is possible to obtained by discrete magnitude form and fly control operation of landing gear and backplate instruction thereof;
When RS485 breaks down and cannot communicate, it is possible to put in place by discrete magnitude form feedback whether all undercarriages and backplate folding and unfolding all;
Each motor is realized 2 �� 4 controls by controller, improves and controls security of system.
Realize above-mentioned functions, specifically comprise the following steps that
Flight control computer send out " normal blow the gear down and backplate " instruction to front controller, led left controller, led right controller;
The front controller that rises drives apron plate mair motor, puts apron plate. Lead left controller and driven left backplate mair motor, put left backplate. Lead right controller and driven right backplate mair motor, put right backplate. Three above action carries out simultaneously.
A front backplate puts down after putting in place, plays a backplate and put down signal extremely front the controller that put in place before feedback. Having led after left backplate puts down and put in place, feedback lead left backplate and has been put down the signal that puts in place and extremely led left controller. Having led after right backplate puts down and put in place, feedback lead right backplate and has been put down the signal that puts in place and extremely led right controller.
The front controller that rises drives nose-gear mair motor, puts nose-gear. Lead left controller to drive and led a left side and fall frame mair motor, put and led a left side and fall frame. Lead right controller to drive and led the right side and fall frame mair motor, put and led the right side and fall frame. Three above action carries out simultaneously, and in the course of the work, feedback speed signal is correspondence controller extremely for all motors;
Nose-gear puts down after putting in place, rises and put down signal extremely front the controller that put in place before feedback. Having led a left side and fallen after frame puts down and put in place, feedback lead a left side and has been put down the signal controller extremely from left to right that puts in place. Having led the right side and fallen after frame puts down and put in place, feedback lead the right side and has been put down the signal controller extremely from right to left that puts in place.
Before play controller, lead left controller, led the right controller each undercarriage of feedback and backplate puts down the signal that puts in place to flight control computer.
After RS485 communication failure (continually attempting to 3 times shake hands), flight control computer provides undercarriage instruction extremely front controller by discrete magnitude, instruction is forwarded to by a front controller have been led left controller and has led right controller, led a left side put in place signal, led the right side fall frame put in place signal by having led left controller, led right controller and reached before play controller, front rising before the signal that puts in place reaches plays controller, all signals that put in place are done logical operations, then operation result is reached flight control computer. In the case, flight control computer does not repartition " normal blow the gear down ", " landing-gear emergency extension " instruction, controller normal blow the gear down program is first carried out, if it fails, perform landing-gear emergency extension program again.
Each dsp board all can drive 4 motors of correspondence, and between two pieces of dsp boards, design has a-road-through to believe, passes the information such as self duty mutually. After one piece of dsp board breaks down wherein, automatically switch to another block dsp board and control.
System of the present invention, after single motor breaks down, is switched to standby motor, carries out normal operation; When programmed decision location switch lost efficacy, move the judgement of distance according to the rate signal collected, improve the security performance of whole system.
Claims (2)
1. a landing-gear system, it is characterised in that: it includes 1 flight control computer and 3 subsystems, adopts RS485 to communicate between described flight control computer and subsystem; Described 3 subsystems are led left extension and retraction system (01), led right extension and retraction system (02) and front extension and retraction system (03) respectively, described master plays left extension and retraction system (01) for controlling the folding and unfolding of left side undercarriage and backplate, having led right extension and retraction system (02) for controlling the folding and unfolding of the right undercarriage and backplate, front extension and retraction system (03) is for controlling the folding and unfolding of front undercarriage and backplate; Described subsystem is by the identical motor driver of 1 controller undercarriage motor corresponding with controller, backplate motor and number of motors summation and location switch composition; Described control edge is provided with put in place signaling interface end and rate signal interface end, the first dsp board and the second dsp board it is provided with inside controller, first dsp board is used for controlling undercarriage motor, realize the folding and unfolding of corresponding undercarriage, second dsp board is used for controlling backplate motor, realize the folding and unfolding of corresponding backplate, between described first dsp board and the second dsp board, be provided with a-road-through letter.
2. a kind of landing-gear system according to claim 1, it is characterised in that: the quantity of described undercarriage motor is 2, including the standby motor of undercarriage mair motor and undercarriage; The quantity of backplate motor is 2, including the standby motor of backplate mair motor and backplate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410708266.1A CN105620732A (en) | 2014-11-28 | 2014-11-28 | Undercarriage extension and retraction system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410708266.1A CN105620732A (en) | 2014-11-28 | 2014-11-28 | Undercarriage extension and retraction system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620732A true CN105620732A (en) | 2016-06-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410708266.1A Pending CN105620732A (en) | 2014-11-28 | 2014-11-28 | Undercarriage extension and retraction system |
Country Status (1)
| Country | Link |
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| CN (1) | CN105620732A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109733594A (en) * | 2019-03-06 | 2019-05-10 | 成都飞机工业（集团）有限责任公司 | A kind of cold air operation of landing gear system and its method of rising and falling |
| CN110626493A (en) * | 2019-10-30 | 2019-12-31 | 中航通飞华南飞机工业有限公司 | Electric retraction control system based on large aircraft landing gear |
| CN112441221A (en) * | 2020-12-04 | 2021-03-05 | 中航飞机起落架有限责任公司 | Dual-redundancy undercarriage backup and placing device |
-
2014
- 2014-11-28 CN CN201410708266.1A patent/CN105620732A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109733594A (en) * | 2019-03-06 | 2019-05-10 | 成都飞机工业（集团）有限责任公司 | A kind of cold air operation of landing gear system and its method of rising and falling |
| CN110626493A (en) * | 2019-10-30 | 2019-12-31 | 中航通飞华南飞机工业有限公司 | Electric retraction control system based on large aircraft landing gear |
| CN112441221A (en) * | 2020-12-04 | 2021-03-05 | 中航飞机起落架有限责任公司 | Dual-redundancy undercarriage backup and placing device |
| CN112441221B (en) * | 2020-12-04 | 2022-11-11 | 中航飞机起落架有限责任公司 | Dual-redundancy undercarriage backup and placing device |
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| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |