CN113815844B - Electric control type tail boom retraction system of airplane and control method - Google Patents
Electric control type tail boom retraction system of airplane and control method Download PDFInfo
- Publication number
- CN113815844B CN113815844B CN202111124176.4A CN202111124176A CN113815844B CN 113815844 B CN113815844 B CN 113815844B CN 202111124176 A CN202111124176 A CN 202111124176A CN 113815844 B CN113815844 B CN 113815844B
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- tail
- support
- tail support
- boom
- valve
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
- B64C25/28—Control or locking systems therefor with indicating or warning devices
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The application belongs to the technical field of retraction of an aircraft tail boom, and particularly relates to an electric control type retraction system and a control method of the aircraft tail boom. The system comprises: the tail support comprises a left tail support and a right tail support, the left tail support and the right tail support are arranged at the rear lower part of the machine body, and the left tail support and the right tail support are provided with a hydraulic actuating cylinder and a tail support upper lock; the tail boom control panel is provided with a tail boom control switch, a tail boom inclination indicator lamp and a tail boom locking indicator lamp; the control valve comprises a tail stay receiving and discharging magnetic valve, a tail stay telescopic electromagnetic valve and a tail stay upper lock manual valve, wherein the tail stay receiving and discharging magnetic valve is respectively and electrically connected with a tail stay control switch, the tail stay upper lock manual valve and the landing gear wheel load signal acquisition module, and the tail stay telescopic electromagnetic valve is electrically connected with the hydraulic actuator; the micro-motion electric gate comprises a tail support inclined micro-motion electric gate and a tail support shortened micro-motion electric gate; and the tail support control module of the rear 2 electromechanical secondary power distribution device is used for supplying power to the tail support control switch, the control valve and the micro-motion electric valve.
Description
Technical Field
The application belongs to the technical field of retraction of an aircraft tail boom, and particularly relates to an electric control type retraction system and a control method of the aircraft tail boom.
Background
Tail boom is an important component of the aircraft structure, and relates to the safety of the aircraft in air flight and the safety of the unit and ground loading. The fault mode of the airplane tail boom is mainly as follows: the system cannot be put down or put up, faults are indicated, control failure, human misoperation and the like, and the faults directly affect the reliability of the tail boom system.
In the prior art, a hydraulic electromagnetic valve for controlling a tail stay system cannot supply power for a long time, is easy to break power when the tail stay is put down, cannot maintain pressure, and generates a naturally falling fault. And the left and right tail boom switches are independent, so that the left and right tail boom control is asynchronous.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide an electric control type tail boom retraction system and a control method for an aircraft, which are used for solving at least one problem existing in the prior art.
The technical scheme of the application is as follows:
the first aspect of the application provides an aircraft electrically controlled tail boom retraction system, comprising:
the tail support comprises a left tail support and a right tail support, the left tail support and the right tail support are arranged at the rear lower part of the machine body, and the left tail support and the right tail support are respectively provided with a hydraulic actuator cylinder and a tail support upper lock;
the tail boom control panel is provided with a tail boom control switch, a tail boom inclination indicator lamp and a tail boom locking indicator lamp;
the control valve comprises a tail stay retraction magnetic valve, a tail stay telescopic electromagnetic valve and a tail stay upper lock manual valve, wherein the tail stay retraction magnetic valve is respectively and electrically connected with the tail stay control switch, the tail stay upper lock manual valve and the landing gear wheel load signal acquisition module, and the tail stay telescopic electromagnetic valve is electrically connected with the hydraulic actuating cylinder;
the micro-motion electric door comprises a tail support inclined micro-motion electric door and a tail support shortened micro-motion electric door, the tail support inclined micro-motion electric door is respectively and electrically connected with the tail support receiving and releasing magnetic valve and the tail support telescopic electromagnetic valve, and the tail support shortened micro-motion electric door is respectively and electrically connected with the tail support receiving and releasing magnetic valve and the tail support telescopic electromagnetic valve;
and the tail support control module of the rear 2 electromechanical secondary power distribution device is used for supplying power to the tail support control switch, the control valve and the micro-motion electric valve.
In at least one embodiment of the present application, the hydraulic rams of the left tail boom and the right tail boom are each powered by a hydraulic energy system.
In at least one embodiment of the application, the tail boom control switch adopts a 3-position switch with a protective cover for pulling the neutral position of the belt up and down.
The second aspect of the application provides an aircraft electric control type tail boom retraction control method, which is based on the aircraft electric control type tail boom retraction system, and comprises the following steps:
the tail stay laying-down process comprises the following steps: when the tail support receiving and releasing magnetic valve synchronously receives a tail support control switch release signal, a tail support upper lock manual valve opening signal and a landing gear wheel load signal, the tail support receiving and releasing magnetic valve releases and energizes, when the tail support receiving and releasing magnetic valve releases in place, the tail support tilting micro-motion switch triggers, controls the tail support telescopic electromagnetic valve to open, the hydraulic actuating cylinder controls the tail support to synchronously extend the left tail support and the right tail support,
when the hydraulic pressure reaches 21 megapascals, the tail boom is put down, and the manual tail boom control switch is turned back to neutral; or alternatively, the first and second heat exchangers may be,
when the prop inclination of the hydraulic actuator cylinder is larger than 7 degrees, the tail support inclination inching electric gate sends an alarm signal to the tail support control panel, the tail support control panel alarms through the tail support inclination indicator lamp, and the direct manual tail support control switch is reset to be neutral;
the tail support is folded and is put up: opening the tail boom control switch, electrifying the tail boom telescopic electromagnetic valve, triggering the tail boom to shorten the micro-motion electric valve, controlling the tail boom to retract and discharge the electromagnetic valve to retract and electrify, controlling the left tail boom and the right tail boom to retract synchronously by the hydraulic actuator cylinder, locking the tail boom upper lock manual valve, opening the tail boom locking indicator lamp of the tail boom control panel, and directly and manually resetting the tail boom control switch.
The application has at least the following beneficial technical effects:
the electric control type tail boom retraction system for the aircraft can realize the consistency of the operation of the electric valve with the same function in the retraction process of the tail boom under the condition of not changing the use of the tail boom, simultaneously ensure the continuous power-off of the hydraulic electromagnetic valve and the retraction of the oil return tail boom of the hydraulic system in the retraction process of the tail boom, and effectively avoid the failure of the loading process of the tail boom and the safe ground loading.
Drawings
FIG. 1 is a schematic diagram of an electronically controlled tail boom retraction system for an aircraft in accordance with one embodiment of the present application;
fig. 2 is a flowchart of an aircraft electric control type tail boom retraction control method according to an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 2.
The first aspect of the application provides an aircraft electric control type tail boom retraction system, which comprises: the tail stay, tail stay control panel, control valve, micro-gap electric door and back 2 electromechanical secondary distribution device tail stay control module.
Specifically, the tail support comprises a left tail support and a right tail support, the left tail support and the right tail support are arranged at the rear lower part of the machine body, and the left tail support and the right tail support are provided with a hydraulic actuating cylinder and a tail support upper lock; the tail boom control panel is provided with a tail boom control switch, a tail boom inclination indicator lamp and a tail boom locking indicator lamp; the control valve comprises a tail stay receiving and discharging magnetic valve, a tail stay telescopic electromagnetic valve and a tail stay upper lock manual valve, wherein the tail stay receiving and discharging magnetic valve is respectively and electrically connected with a tail stay control switch, the tail stay upper lock manual valve and the landing gear wheel load signal acquisition module, and the tail stay telescopic electromagnetic valve is electrically connected with the hydraulic actuator; the tail support tilting micro-electric valve is respectively electrically connected with the tail support receiving and discharging magnetic valve and the tail support telescopic electromagnetic valve; the tail support control module of the rear 2 electromechanical secondary power distribution device is used for supplying power to a tail support control switch, a control valve and a micro-switch.
According to the electric control type tail boom retraction system for the aircraft, retraction and extension of the tail boom are controlled by the hydraulic control system, the tail boom hydraulic control system works by a single hydraulic control system, and the left tail boom and the right tail boom are supplied with pressure by a No. 1 hydraulic energy system. The tail boom control switch is not provided with an automatic rebound function and is required to be disconnected by manual operation. The tail support control switch selects a 3-position switch with a protective cover for pulling the belt up and down to a neutral position, and the manual electric control hydraulic control actuating cylinder is used for opening and releasing left and right tail supports. The left tail support and the right tail support are retracted and extended together, and the position indication of the tail support is sent by a hard wire signal. The control and position display signals are separated as far as possible from the power distribution, so that the position display function is prevented from being affected under the condition that a control circuit fails, and the control and display have own power distribution and are not affected each other. Preferably, warning information is provided at two places of the cockpit and the cargo hold.
Based on the above-mentioned electric control type tail boom retraction system of the aircraft, the second aspect of the application provides an electric control type tail boom retraction control method of the aircraft, comprising the following steps:
the tail stay laying-down process comprises the following steps: when the tail support receiving and releasing magnetic valve synchronously receives a tail support control switch release signal, a tail support upper lock manual valve opening signal and a landing gear wheel load signal, the tail support receiving and releasing magnetic valve releases and energizes, when the tail support receiving and releasing magnetic valve releases in place, the tail support tilting micro-motion switch triggers, controls the tail support telescopic electromagnetic valve to open, the hydraulic actuating cylinder controls the tail support to synchronously extend the left tail support and the right tail support,
when the hydraulic pressure reaches 21 megapascals, the tail boom is put down, and the manual tail boom control switch is turned back to neutral; or alternatively, the first and second heat exchangers may be,
when the prop inclination of the hydraulic actuator cylinder is larger than 7 degrees, the tail support inclination inching electric gate sends an alarm signal to the tail support control panel, the tail support control panel alarms through the tail support inclination indicator lamp, and the direct manual tail support control switch is reset to be neutral;
the tail support is folded and is put up: opening the tail boom control switch, electrifying the tail boom telescopic electromagnetic valve, triggering the tail boom to shorten the micro-motion electric valve, controlling the tail boom to retract and discharge the electromagnetic valve to retract and electrify, controlling the left tail boom and the right tail boom to retract synchronously by the hydraulic actuator cylinder, locking the tail boom upper lock manual valve, opening the tail boom locking indicator lamp of the tail boom control panel, and directly and manually resetting the tail boom control switch.
According to the electric control type tail boom retraction system and the control method of the aircraft, manual control is responsible for sending out instructions to drive the electromagnetic valve to move. The control structure electric door is normally put down and taken up. In order to meet the control task with high requirements, the functions of controlling and indicating separate power distribution, increasing in-place monitoring of the electric valve, continuously and continuously uninterrupted power of the hydraulic electromagnetic valve are adopted to finish the retraction and extension of the tail boom, meanwhile, the fault information of the electric valve is acquired and judged through computers with mutual redundancy, the relay logic is adopted to control the hydraulic electromagnetic valve to work, and the reliability of tail boom control is effectively improved. Under the condition that the tail boom is not changed, the consistency of the operation of the electric gate with the same function in the tail boom retraction process can be realized, meanwhile, the phenomena of continuous power failure of the hydraulic electromagnetic valve and the retraction of the oil return tail boom of the hydraulic system in the tail boom retraction process are ensured, and the failure in the tail boom loading process and the safe ground loading are effectively avoided.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. An aircraft electronic control type tail boom retraction system, which is characterized by comprising:
the tail support comprises a left tail support and a right tail support, the left tail support and the right tail support are arranged at the rear lower part of the machine body, and the left tail support and the right tail support are respectively provided with a hydraulic actuator cylinder and a tail support upper lock;
the tail boom control panel is provided with a tail boom control switch, a tail boom inclination indicator lamp and a tail boom locking indicator lamp;
the control valve comprises a tail stay retraction magnetic valve, a tail stay telescopic electromagnetic valve and a tail stay upper lock manual valve, wherein the tail stay retraction magnetic valve is respectively and electrically connected with the tail stay control switch, the tail stay upper lock manual valve and the landing gear wheel load signal acquisition module, and the tail stay telescopic electromagnetic valve is electrically connected with the hydraulic actuating cylinder;
the micro-motion electric door comprises a tail support inclined micro-motion electric door and a tail support shortened micro-motion electric door, the tail support inclined micro-motion electric door is respectively and electrically connected with the tail support receiving and releasing magnetic valve and the tail support telescopic electromagnetic valve, and the tail support shortened micro-motion electric door is respectively and electrically connected with the tail support receiving and releasing magnetic valve and the tail support telescopic electromagnetic valve;
and the tail support control module of the rear 2 electromechanical secondary power distribution device is used for supplying power to the tail support control switch, the control valve and the micro-motion electric valve.
2. The aircraft electrically controlled tail boom retraction system according to claim 1 wherein the hydraulic rams of the left tail boom and the right tail boom are both powered by a hydraulic energy system.
3. The aircraft electrically controlled tail boom retraction system according to claim 1 wherein the tail boom control switch is a 3-position switch with a protective cover to pull the neutral position up and down.
4. An aircraft electronic control type tail boom retraction control method based on the aircraft electronic control type tail boom retraction system of claim 3, comprising the following steps:
the tail stay laying-down process comprises the following steps: when the tail support receiving and releasing magnetic valve synchronously receives a tail support control switch release signal, a tail support upper lock manual valve opening signal and a landing gear wheel load signal, the tail support receiving and releasing magnetic valve releases and energizes, when the tail support receiving and releasing magnetic valve releases in place, the tail support tilting micro-motion switch triggers, controls the tail support telescopic electromagnetic valve to open, the hydraulic actuating cylinder controls the tail support to synchronously extend the left tail support and the right tail support,
when the hydraulic pressure reaches 21 megapascals, the tail boom is put down, and the manual tail boom control switch is turned back to neutral; or alternatively, the first and second heat exchangers may be,
when the prop inclination of the hydraulic actuator cylinder is larger than 7 degrees, the tail support inclination inching electric gate sends an alarm signal to the tail support control panel, the tail support control panel alarms through the tail support inclination indicator lamp, and the direct manual tail support control switch is reset to be neutral;
the tail support is folded and is put up: opening the tail boom control switch, electrifying the tail boom telescopic electromagnetic valve, triggering the tail boom to shorten the micro-motion electric valve, controlling the tail boom to retract and discharge the electromagnetic valve to retract and electrify, controlling the left tail boom and the right tail boom to retract synchronously by the hydraulic actuator cylinder, locking the tail boom upper lock manual valve, opening the tail boom locking indicator lamp of the tail boom control panel, and directly and manually resetting the tail boom control switch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111124176.4A CN113815844B (en) | 2021-09-24 | 2021-09-24 | Electric control type tail boom retraction system of airplane and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111124176.4A CN113815844B (en) | 2021-09-24 | 2021-09-24 | Electric control type tail boom retraction system of airplane and control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113815844A CN113815844A (en) | 2021-12-21 |
| CN113815844B true CN113815844B (en) | 2023-09-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111124176.4A Active CN113815844B (en) | 2021-09-24 | 2021-09-24 | Electric control type tail boom retraction system of airplane and control method |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB548916A (en) * | 1941-05-10 | 1942-10-29 | Percival Aircraft Ltd | Improvements in and relating to mechanism for releasably locking a pivoted member in one or more positions, particularly applicable to retractable undercarriages for aircraft |
| CN102060104A (en) * | 2010-11-19 | 2011-05-18 | 陕西飞机工业（集团）有限公司 | Micro-switch assembly |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN106762880A (en) * | 2016-12-28 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane tail pillar hydraulic pressure folding and unfolding control system |
| CN213892878U (en) * | 2020-08-31 | 2021-08-06 | 上海航空电器有限公司 | Aircraft landing gear operating switch structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11433993B2 (en) * | 2019-11-07 | 2022-09-06 | Goodrich Corporation | Electromechanical actuator pump |
-
2021
- 2021-09-24 CN CN202111124176.4A patent/CN113815844B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB548916A (en) * | 1941-05-10 | 1942-10-29 | Percival Aircraft Ltd | Improvements in and relating to mechanism for releasably locking a pivoted member in one or more positions, particularly applicable to retractable undercarriages for aircraft |
| CN102060104A (en) * | 2010-11-19 | 2011-05-18 | 陕西飞机工业（集团）有限公司 | Micro-switch assembly |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN106762880A (en) * | 2016-12-28 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane tail pillar hydraulic pressure folding and unfolding control system |
| CN213892878U (en) * | 2020-08-31 | 2021-08-06 | 上海航空电器有限公司 | Aircraft landing gear operating switch structure |
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| Publication number | Publication date |
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| CN113815844A (en) | 2021-12-21 |
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