CN108216683B - Unlocking method for fault protection device of rotary actuator - Google Patents
Unlocking method for fault protection device of rotary actuator Download PDFInfo
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- CN108216683B CN108216683B CN201711293815.3A CN201711293815A CN108216683B CN 108216683 B CN108216683 B CN 108216683B CN 201711293815 A CN201711293815 A CN 201711293815A CN 108216683 B CN108216683 B CN 108216683B
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- rotary actuator
- maintenance
- protection device
- fault protection
- unlocking
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Safety Devices In Control Systems (AREA)
Abstract
The invention belongs to the control surface control technology of an aircraft, and relates to an unlocking method for a fault protection device of a rotary actuator. The invention realizes the maintenance function of the rotary actuator: in the maintenance equipment, designing a maintenance mode or a maintenance instruction for unlocking a fault protection device of the rotary actuator; meanwhile, the mutual influence of the maintenance function and other maintenance functions is avoided. By using the unlocking method, the maintenance efficiency of the control surface of the aircraft can be greatly improved.
Description
Technical Field
The invention belongs to the control surface control technology of an aircraft, and relates to an unlocking method for a fault protection device of a rotary actuator.
Background
The rotary actuator is characterized in that the control surface can rotate for 0-360 degrees in a small installation space. In practice, however, the range of deflection of the control surfaces must be limited to protect the safety of the airframe structure. Therefore, rotary actuators are generally provided with failsafe devices for limiting the mechanical travel and protecting the control surfaces from damage such as distortion.
If the failsafe device is switched on due to a fault or for some other reason, the leading-edge flap can still not be deflected normally after the failsafe if this electrical signal is present all the time, so that an unlocking operation of the failsafe device is necessary. In the conventional unlocking process of the leading edge flap, a maintainer manually pulls a transmission shaft of the leading edge flap or a maintenance device writes a long control command one by one so as to achieve the purpose of unlocking the fault protection device. The process is time-consuming and labor-consuming, and has higher requirements on the operation skills of maintenance personnel, so that a quick unlocking mode is needed on a maintenance site to improve the maintenance efficiency.
Disclosure of Invention
The purpose of the invention is: aiming at a typical rotary actuator (such as a leading edge flap driving device) as a research object, a quick and effective unlocking method of a fault protection device is realized, so that the maintenance difficulty is reduced, and the efficiency is improved.
The technical scheme of the invention is as follows: an unlocking method for a fault protection device of a rotary actuator comprises the following steps:
a) realizing maintenance function of rotary actuator
1) In the maintenance equipment, designing a maintenance mode or a maintenance instruction for unlocking a fault protection device of the rotary actuator; meanwhile, the mutual influence of the maintenance function and other maintenance functions is avoided;
2) in the control part of the rotary actuator, the maintenance mode or the maintenance instruction and the corresponding safety interlocking condition are used for enabling the unlocking function of the fault protection device of the rotary actuator;
b) unlocking step of fault protection device of rotary actuator
1) After the unlocking function of the fault protection device of the rotary actuator is enabled, the operation of a monitor for monitoring the state of the fault protection device is forbidden; after exiting the unlock function, the disabled monitor should be re-enabled;
2) resetting the rotary actuator to ensure that the control loop of the drive device of the rotary actuator works normally;
3) acquiring a deflection position signal of a current rotary actuator to be unlocked, caching the deflection position signal, and assuming that the deflection position signal is X;
4) outputting a position instruction of X + m for the rotary actuator to be unlocked, and outputting a position instruction of X-m for the rotary actuator to be unlocked after T time; the value of m is the minimum skewness of the fault protection device which can be separated from the locking state; the value of T is m/minimum deflection rate of the rotary actuator;
5) and (4) exiting the unlocking function, resetting the control loop of the rotary actuator again, and confirming the normal deflection of the rotary actuator.
In the unlocking process of the fault protection device of the rotary actuator, a row of safety protection measures need to be designed so as to avoid accidental damage:
1. using the linkage conditions of software and hardware, and immediately quitting the unlocking function when the safety linkage conditions are not met;
2. during the unlocking process, the position command of the rotary actuator needs to be limited, namely, the allowable rotary actuator command range cannot be exceeded.
The invention has the beneficial effects that: by using the unlocking method, the maintenance efficiency can be greatly improved. Taking the leading edge flap unlocking operation on two types of aircraft as an example, a comparison is made: in case external conditions are all ready: the method comprises the steps that when a person skilled in operation and maintenance of equipment is needed for unlocking the leading edge flap of the A-type airplane, the locked position is judged, then a position instruction needed for unlocking is calculated, and finally more than 10 commands are input to ensure that the unlocking is successful within about 5 minutes; the leading edge flap of the B-type airplane is unlocked only by one maintenance person and clicking a button on the maintenance equipment twice, and the time does not exceed 20 s.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
Taking the leading edge flap actuator as an example, the control system actively disengages the leading edge flap from the locked state by using a maintenance device unified by the whole aircraft, or a maintenance device of the leading edge flap control system and a leading edge flap control part through a special maintenance mode. The specific technical content is as follows:
1. implementing specific leading edge flap actuator maintenance functions
1) In the maintenance equipment, designing a maintenance mode or a maintenance instruction for unlocking a fault protection device of the leading edge flap actuator; meanwhile, attention needs to be paid to avoid the mutual influence of the maintenance function and other maintenance functions;
2) in the leading edge flap control part, the unlocking function of the leading edge flap actuator fault protection device needs to be enabled by using the maintenance mode or the maintenance command and the corresponding safety interlocking condition;
2. unlocking step of leading edge flap actuator failsafe device
1) After enabling the unlocking function of the leading edge flap actuator fault protection device, disabling a portion of the fault monitors (monitors that are required to disable the fault protection device status) from operating; after exiting the unlock function, the disabled monitor should be re-enabled;
2) resetting the leading edge flap actuator to ensure that the leading edge flap control loop works normally;
3) obtaining a leading edge flap deflection position signal needing to be unlocked at present, caching the leading edge flap deflection position signal, and assuming that the value is X;
4) outputting a position instruction of X +5 degrees for the leading edge flap actuator to be unlocked, and outputting a position instruction of X-5 degrees for the leading edge flap actuator to be unlocked after 500 ms;
5) and exiting the unlocking function, resetting the leading edge flap control loop again and confirming the normal deflection of the leading edge flap.
In the unlocking of the leading-edge flap actuator failsafe, it is necessary to design a series of safety precautions in order to avoid accidental damage:
1. using the linkage conditions of software and hardware, and immediately quitting the unlocking function when the safety linkage conditions are not met;
2. in the unlocking process, the position instruction of the leading edge flap actuator needs to be limited, namely the allowable instruction range of the leading edge flap actuator cannot be exceeded;
3. after entering the maintenance mode, the system operating conditions differ from normal conditions, so it is necessary to note whether all signals used by the leading edge flap control loop during the unlocking process correspond to the actual conditions.
The unlocking method is already applied to leading edge flap actuators of certain airplanes, improves maintenance efficiency and is widely praised.
Claims (4)
1. A method of unlocking a rotary actuator fault protection device, the method comprising:
a) realizing maintenance function of rotary actuator
1) In the maintenance equipment, designing a maintenance mode or a maintenance instruction for unlocking a fault protection device of the rotary actuator; meanwhile, the mutual influence of the maintenance function and other maintenance functions is avoided;
2) in the control part of the rotary actuator, the maintenance mode or the maintenance instruction and the corresponding safety interlocking condition are used for enabling the unlocking function of the fault protection device of the rotary actuator;
b) unlocking step of fault protection device of rotary actuator
1) After the unlocking function of the fault protection device of the rotary actuator is enabled, the operation of a monitor for monitoring the state of the fault protection device is forbidden; after exiting the unlock function, the disabled monitor should be re-enabled;
2) resetting the rotary actuator to ensure that the control loop of the drive device of the rotary actuator works normally;
3) acquiring a deflection position signal of a current rotary actuator to be unlocked, caching the deflection position signal, and assuming that the deflection position signal is X;
4) outputting a position instruction of X + m for the rotary actuator to be unlocked, and outputting a position instruction of X-m for the rotary actuator to be unlocked after T time; the value of m is the minimum skewness of the fault protection device which can be separated from the locking state; the value of T is m/minimum deflection rate of the rotary actuator;
5) and (4) exiting the unlocking function, resetting the control loop of the rotary actuator again, and confirming the normal deflection of the rotary actuator.
2. The method of claim 1, wherein the method further comprises: the rotary actuator is a leading edge flap actuator.
3. The method of claim 1, wherein the method further comprises: and m is 5 degrees.
4. The method of claim 1, wherein the method further comprises: and T is 500 ms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711293815.3A CN108216683B (en) | 2017-12-08 | 2017-12-08 | Unlocking method for fault protection device of rotary actuator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711293815.3A CN108216683B (en) | 2017-12-08 | 2017-12-08 | Unlocking method for fault protection device of rotary actuator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108216683A CN108216683A (en) | 2018-06-29 |
| CN108216683B true CN108216683B (en) | 2021-05-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711293815.3A Active CN108216683B (en) | 2017-12-08 | 2017-12-08 | Unlocking method for fault protection device of rotary actuator |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112046776A (en) * | 2020-09-07 | 2020-12-08 | 中国航空工业集团公司成都飞机设计研究所 | Ground comprehensive warning method for unmanned aerial vehicle |
Citations (6)
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|---|---|---|---|---|
| CN101909992A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | System for actuating at least one regulating flap of an aircraft and a method for checking the system. |
| EP3050796A1 (en) * | 2015-01-29 | 2016-08-03 | Airbus Operations GmbH | Method for adjusting the play in a high-lift system of an aircraft |
| EP3096037A1 (en) * | 2015-05-22 | 2016-11-23 | Goodrich Actuation Systems SAS | Actuator drive disconnection system |
| CN106184812A (en) * | 2016-08-17 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of aircraft handling rudder face automatic zero-setting method |
| CN106347708A (en) * | 2015-07-16 | 2017-01-25 | 波音公司 | Method and system for controlling automated operations on a workpiece |
| CN106564614A (en) * | 2016-11-01 | 2017-04-19 | 广州飞机维修工程有限公司 | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10053237B2 (en) * | 2016-05-20 | 2018-08-21 | The Boeing Company | Track roller failure detection systems and methods |
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2017
- 2017-12-08 CN CN201711293815.3A patent/CN108216683B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101909992A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | System for actuating at least one regulating flap of an aircraft and a method for checking the system. |
| EP3050796A1 (en) * | 2015-01-29 | 2016-08-03 | Airbus Operations GmbH | Method for adjusting the play in a high-lift system of an aircraft |
| EP3096037A1 (en) * | 2015-05-22 | 2016-11-23 | Goodrich Actuation Systems SAS | Actuator drive disconnection system |
| CN106347708A (en) * | 2015-07-16 | 2017-01-25 | 波音公司 | Method and system for controlling automated operations on a workpiece |
| CN106184812A (en) * | 2016-08-17 | 2016-12-07 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of aircraft handling rudder face automatic zero-setting method |
| CN106564614A (en) * | 2016-11-01 | 2017-04-19 | 广州飞机维修工程有限公司 | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock |
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| Publication number | Publication date |
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| CN108216683A (en) | 2018-06-29 |
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