CN102621899B - Method for opening thrust-reversing system of power device of aircraft - Google Patents
Method for opening thrust-reversing system of power device of aircraft Download PDFInfo
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- CN102621899B CN102621899B CN201110348495.3A CN201110348495A CN102621899B CN 102621899 B CN102621899 B CN 102621899B CN 201110348495 A CN201110348495 A CN 201110348495A CN 102621899 B CN102621899 B CN 102621899B
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Abstract
The invention provides a method for opening a thrust-reversing system of a power device of an aircraft. The method comprises the following steps: providing a man-computer interaction interface of a flight motor-mounted maintenance system in a cockpit of the aircraft; setting a ground maintenance override software switch on the man-computer interaction interface; communicating the ground maintenance override software switch with at least one controller for realizing thrust-reversing control; and using the controller to receive a signal of the ground maintenance override software switch, and judging an actuator for controlling the thrust-reversing system through control logic according to the current state of an engine so as to open a thrust-reversing cover of the thrust-reversing system. According to the method disclosed by the invention, the function of the ground maintenance override switch of the thrust-reversing system is realized by adopting a soft switching way, the connection of hard wires is reduced, and the maintenance steps, the workload of ground service staff and maintenance tools are reduced.
Description
Technical field
The present invention relates to a kind of method of opening the anti-pushing system of aircraft power plant, especially, relate to the method for using the anti-pushing system of a kind of soft switch opens aircraft power plant when ground maintenance.
Background technology
The anti-pushing system of aircraft power plant, when doing ground maintenance, need to be opened the anti-cover that pushes away and carry out examination and maintenance.This just needs independent ground maintenance override (GMO) switch, makes THR REV not meeting the anti-cover that pushes away that just can open anti-pushing system under the normal anti-condition that pushes away steering logic, and facilitates the actuation mechanism of the anti-pushing system of ground service personnel inspection.
In the prior art, normally on the nacelle surface of engine, a physics hard switching is set, i.e. ground maintenance override (GMO) switch, it is the controller with engine by rigid line---and the full powers sub-controller FADEC that rations the power supply is connected.When ground crew backs down with instrument the hard switching that is located at nacelle surface, FADEC receives a hard signal, converts this hard signal to bus signals simultaneously and sends engine interface control unit---EICU to.According to the state of present engine, FADEC and EICU can carry out release to anti-pushing system.At this moment, the anti-cover that pushes away can be opened, and ground crew can carry out maintenance work.
Be not difficult to find out, such scheme needs ground crew to use some instrument firmly to back down hard switching generation analog control signal, just can release open the anti-cover that pushes away.Such scheme has not only increased electronic equipment and hardwire interface, and the step of maintenance is also more loaded down with trivial details, and ground crew's work load is also heavier.
Yet whole service aircrafts is all that the anti-cover that pushes away of taking this method to open the anti-pushing system of propulsion system carries out ground maintenance work at present, thereby can realize quickly and easily without any need for instrument the anti-method that pushes away cover of opening in the urgent need to a kind of.
Summary of the invention
Object of the present invention is just to provide the function of ground maintenance override (GMO) switch that a kind of convenient simple method realizes anti-pushing system.
In order to achieve the above object, the invention provides a kind of method that realizes the GMO switch of anti-pushing system with software switch, the method realizes by following scheme:
A method of opening the anti-pushing system of aircraft power plant, comprising: the human-computer interaction interface that the airborne maintenance system of aircraft cockpit avionics is provided; Ground maintenance override software switch is set on described human-computer interaction interface; Described ground maintenance override software switch is realized the anti-controller that pushes away control with at least one and is communicated by letter; Described controller receives after the signal of ground maintenance override software switch, and according to the state of present engine, the actuator that anti-pushing system is controlled in judgement through steering logic is to open the anti-cover that pushes away of anti-pushing system.
Preferably, described ground maintenance override software switch is communicated by letter by the anti-controller that pushes away control of data bus and described realization.
Preferably, described ground maintenance override software switch is arranged under the starting test function of described human-computer interaction interface.
By technique scheme, when aircraft need to carry out ground maintenance when work of anti-pushing system, can on the maintenance interface of engine, select the soft switch of GMO, switch command signal can be simultaneously transmission network by aircraft sent the anti-controller that pushes away control to.Complete the anti-controller that pushes away control and receive after switch command signal, can be according to the state of present engine, the actuator that anti-pushing system is controlled in judgement through steering logic is successively to anti-pushing system release, to complete the anti-work that pushes away cover of opening.
Here, opening the anti-order that pushes away cover is to complete by completing the anti-internal logic that pushes away the controller of control, by the anti-pushing system of the common release of at least one controller.The conclusion of safety analysis shows that this scheme can not affect the security of aircraft, does not have specific (special) requirements to the software level of airborne maintenance system yet.Therefore, the mode that realizes anti-pushing system ground maintenance override switching function with soft switch had both reduced rigid line connection, also reduced the step of safeguarding, ground crew's work load and maintenance tool, be also an important embodiment of civil aircraft system synthesis trend simultaneously.
Accompanying drawing explanation
More features of the present invention and advantage are by by understanding better the further description of embodiment below in conjunction with accompanying drawing.Wherein:
Fig. 1 is according to the module frame chart of a kind of embodiment of the inventive method;
Fig. 2 is the schematic diagram of the aircraft airborne maintenance system human-computer interaction interface of a kind of preferred implementation according to the present invention;
Fig. 3 is for realizing the module frame chart of the inventive method according to preferred implementation shown in Fig. 2.
Embodiment
First referring to Fig. 1, it shows according to the module frame chart of a kind of embodiment of the inventive method.According to the present invention, the human-computer interaction interface of safeguarding of a friendly engine can be set on the display screen of the airborne maintenance system of aircraft cockpit avionics, and a soft switch of GMO is set on maintenance interface.The soft switch of this GMO can be realized the anti-controller that pushes away control with at least one and pass through data bus communication, in Fig. 1, illustrate two such controllers, described controller can pass through electric interfaces (Electrical interface) and be electrically connected to the actuator (Actuation of Reverser Thrust) of anti-pushing system, thereby the command signal to the soft switch of GMO responds, the for example 3 road locks of opening anti-pushing system, complete the anti-work that pushes away cover of opening.
Preferably the soft switch of GMO is arranged under starting test (Initiated Test) function of human-computer interaction interface, as shown in Figure 2, original function under this function interface, such as safeguarding-send that reset switch (TLD Clean Switch), the reset switch that transfinites (Exceed Clean Switch) etc. still retain.By such setting, original starting test function is not disturbed, and due to the starting test person machine interactive interface of avionics aloft its function be repressed, this has just effectively been avoided the soft incorrect switching of GMO to cause the anti-risk that cover is opened that pushes away.
When the anti-pushing system of aircraft being carried out to ground maintenance work, as shown in Figure 3, in the situation that the soft switch of GMO is communicated by letter with EICU with two anti-controller FADEC that push away control of realization simultaneously, power on only need to FADEC and EICU, then on the human-computer interaction interface of airborne maintenance system, select the soft switch of GMO, switch command signal can be by avionics and propulsion system crosslinked data bus for example ARINC664 send FADEC to, crosslinked data bus that simultaneously can be by avionics and EICU for example ARINC429 sends EICU to.FADEC and EICU receive after switch command signal, can be according to the state of present engine (signals such as wheel load signal, air speed, N2), the 3 roads locks of opening successively anti-pushing system through the actuator of the anti-pushing system of steering logic judgement control, complete the anti-work that pushes away cover of opening.It should be understood that above-mentioned data bus ARINC664 and ARINC429 control in function and are all used in original aircraft, just additionally utilize its data function to realize the soft operation of GMO switch here, original bus functionality is had no effect.In addition,, by safety analysis, the solution of the present invention has identical level of security with conventional hard switching scheme.Comparatively speaking, the present invention does not need to use any instrument, only need on the human-computer interaction interface of the aircraft airborne maintenance system of driving cabin, select the soft switch of GMO, just can reach and open the anti-object that pushes away cover, operate more easy reliably.
Above-mentioned preferred implementation is exemplary has described the mode that the soft switch of GMO is communicated by letter with EICU with FADEC simultaneously, it should be understood that method of the present invention is equally applicable to the mode that the soft switch of GMO is only communicated by letter with a controller.For example GMO intercoms with engine controller FADEC mutually by data bus, and FADEC sends switch command signal to EICU by avionics network, then is realized and opened the anti-cover that pushes away by the judgement of EICU steering logic.This embodiment is favourable than prior art equally.
Technology contents of the present invention and technical characterstic disclose as above, yet are appreciated that under creative ideas of the present invention, and those skilled in the art can make various changes and improve above-mentioned embodiment, but all belongs to protection scope of the present invention.The description of above-mentioned embodiment is exemplary rather than restrictive, and protection scope of the present invention is determined by claim.
Claims (2)
1. a method of opening the anti-pushing system of aircraft power plant, comprising:
The human-computer interaction interface of the airborne maintenance system of aircraft cockpit avionics is provided;
Ground maintenance override software switch is set on described human-computer interaction interface;
Described ground maintenance override software switch is realized the anti-controller that pushes away control with at least one and is communicated by letter;
Described controller receives after the signal of ground maintenance override software switch, according to the state of present engine, through steering logic, judges that the actuator of controlling anti-pushing system is to open the anti-cover that pushes away of anti-pushing system,
Wherein, described ground maintenance override software switch is arranged under the starting test function of described human-computer interaction interface.
2. the method for opening the anti-pushing system of aircraft power plant according to claim 1, is characterized in that, described ground maintenance override software switch is communicated by letter by the anti-controller that pushes away control of data bus and described realization.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110348495.3A CN102621899B (en) | 2011-11-07 | 2011-11-07 | Method for opening thrust-reversing system of power device of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110348495.3A CN102621899B (en) | 2011-11-07 | 2011-11-07 | Method for opening thrust-reversing system of power device of aircraft |
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| Publication Number | Publication Date |
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| CN102621899A CN102621899A (en) | 2012-08-01 |
| CN102621899B true CN102621899B (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110348495.3A Active CN102621899B (en) | 2011-11-07 | 2011-11-07 | Method for opening thrust-reversing system of power device of aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113602507B (en) * | 2021-08-26 | 2022-08-02 | 中国商用飞机有限责任公司 | Automatic reverse control system and method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0843089A1 (en) * | 1996-11-14 | 1998-05-20 | Hispano-Suiza | Electric control system for a turbo jet thrust reverser |
| US6622963B1 (en) * | 2002-04-16 | 2003-09-23 | Honeywell International Inc. | System and method for controlling the movement of an aircraft engine cowl door |
| CN1521087A (en) * | 2002-10-25 | 2004-08-18 | �ŵ����-�������˹�� | Maintenance and inhibition plate for a thrust reverser |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| CN101784448A (en) * | 2007-08-20 | 2010-07-21 | 埃尔塞乐公司 | Device for controlling maintenance actuators of the cowlings of a turbojet engine nacelle |
| FR2956163A1 (en) * | 2010-02-10 | 2011-08-12 | Aircelle Sa | CONTROL SYSTEM OF AN AIRCRAFT |
-
2011
- 2011-11-07 CN CN201110348495.3A patent/CN102621899B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0843089A1 (en) * | 1996-11-14 | 1998-05-20 | Hispano-Suiza | Electric control system for a turbo jet thrust reverser |
| US6622963B1 (en) * | 2002-04-16 | 2003-09-23 | Honeywell International Inc. | System and method for controlling the movement of an aircraft engine cowl door |
| CN1521087A (en) * | 2002-10-25 | 2004-08-18 | �ŵ����-�������˹�� | Maintenance and inhibition plate for a thrust reverser |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| CN101784448A (en) * | 2007-08-20 | 2010-07-21 | 埃尔塞乐公司 | Device for controlling maintenance actuators of the cowlings of a turbojet engine nacelle |
| FR2956163A1 (en) * | 2010-02-10 | 2011-08-12 | Aircelle Sa | CONTROL SYSTEM OF AN AIRCRAFT |
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| CN102621899A (en) | 2012-08-01 |
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