CN107499499A - The plane lease of function during a kind of band machinery returns - Google Patents
The plane lease of function during a kind of band machinery returns Download PDFInfo
- Publication number
- CN107499499A CN107499499A CN201710597244.6A CN201710597244A CN107499499A CN 107499499 A CN107499499 A CN 107499499A CN 201710597244 A CN201710597244 A CN 201710597244A CN 107499499 A CN107499499 A CN 107499499A
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- Prior art keywords
- actuator
- machinery
- return
- neutral mechanism
- mechanical return
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The plane lease of function in being returned the invention discloses a kind of band machinery, belong to plane lease technical field, including actuator controller (1), the actuator (2) with mechanical return to neutral mechanism, machinery return middle bar (3) and bearing (4).Actuator is arranged on the vertical fin back rest, and bar (3) one end is connected with actuator during machinery returns, and other end is connected with bearing (4), and bearing (4) is arranged on rudder face.Under fax mode, actuator controller (1) reception is converted to output order after the instruction from flight control computer and is sent to actuator, the instruction campaign of actuator response actuator controller (1) and then driving control surface deflection, now the mechanical return to neutral mechanism in actuator is in suspended state, is not responding to the instruction of actuator reception.After middle mode is returned by Flying by wire mode conversion for machinery, the mechanical return to neutral mechanism in actuator is started working, and bar drives rudder face to return to neutral position the feedback of rudder face position in being returned by machinery.
Description
Technical field
The invention belongs to plane lease technical field, and in particular to the aircraft start system of function during a kind of band machinery returns
System.
Background technology
Aircraft in any normal trim position in-flight, pitching, rolling, driftage should all show it is certain in returning, especially
It is after control system corresponding to certain rudder face fails, and in order to reduce the influence after the thrashing as far as possible, typically requires the rudder
During face is returned.The functional configuration of realization and plane lease in rudder face time is closely related.In the prior art, in general rudder face returns
In be all to be realized by fax mechanism, but Flying by wire failure after, can to machinery return in have an impact.
The content of the invention
The present invention proposes the plane lease of function during a kind of band machinery returns, set in actuator return to neutral mechanism and
Machinery returns middle interface, and by the connection realization of bar in being returned with machinery and being indirectly connected with for rudder face, bar is to rudder in being returned by machinery
The feedback of face position, so as to form a closed-loop control system, in the machinery time for realizing rudder face.When control system has fax mould
State is transformed into during machinery returns after mode, and mechanical return to neutral mechanism is started working, and the feedback according to bar in mechanical return to rudder face position,
Actuator motion is controlled, so as to drive rudder face to return to neutral position.
The plane lease of function includes actuator controller, the work with mechanical return to neutral mechanism during the present invention returns with machinery
By cable connection between bar and bearing during dynamic device, machinery return, actuator controller and actuator with mechanical return to neutral mechanism,
Actuator with mechanical return to neutral mechanism is arranged on the vertical fin back rest, bar one end and the actuator with mechanical return to neutral mechanism during machinery returns
Connection, other end are connected with bearing, and bearing is fixedly mounted on rudder face, and the actuator with mechanical return to neutral mechanism has fax control
Mode during molding state is returned with machinery,
Under the Flying by wire mode, actuator controller reception is converted to output after the instruction from flight control computer and referred to
Order is sent to the actuator with mechanical return to neutral mechanism, and actuator responds the instruction campaign of actuator controller and then drives rudder face inclined
Turn, the mechanical return to neutral mechanism in actuator now with mechanical return to neutral mechanism is in suspended state, is not responding to mechanical Hui Zhongji
The instruction that the actuator of structure receives；
During the machinery returns under mode, the mechanical return to neutral mechanism being connected with the actuator with mechanical return to neutral mechanism starts work
Make, and rudder face position is fed back into the actuator with mechanical return to neutral mechanism, rudder face is driven by the actuator with mechanical return to neutral mechanism
Return to neutral position.
Preferably, the actuator of the band machinery return to neutral mechanism configures for electrical dual-redundancy.
Preferably, bar is adjustable length pull bar during the machinery returns.
Preferably, during the machinery returns bar include the Part I that is connected with rudder face and with mechanical return to neutral mechanism
The Part II of actuator connection, the Part I are spirally connected with the Part II.
The present invention meets returning for aircraft rudder surface by setting mechanical return to neutral mechanism and machinery to return middle interface in actuator
Middle demand；Bar is arranged to the pull bar of adjustable in length during machinery is returned, and counteracts caused by design, production and alignment error by mistake
Difference is accumulative, meets installation and debugging and the adjustment demand of system in machinery time.System in being returned this process simplify the machinery of aircraft, is carried
High rudder face return in reliability, ensure that Flight Safety.
Brief description of the drawings
Fig. 1 is the Organization Chart of a preferred embodiment of the plane lease of function in being returned according to the present invention with machinery.
Wherein, 1 is actuator controller, and 2 be the actuator with mechanical return to neutral mechanism, and 3 return middle bar for machinery, and 4 be bearing.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
Part of the embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
The present invention proposes a kind of plane lease of function during band machinery returns, as shown in figure 1, being controlled including actuator
Bar and bearing during device, the actuator with mechanical return to neutral mechanism, machinery return, actuator controller and the work with mechanical return to neutral mechanism
By cable connection between dynamic device, the actuator with mechanical return to neutral mechanism is arranged on the vertical fin back rest, during machinery returns bar one end with
Actuator connection with mechanical return to neutral mechanism, other end are connected with bearing, and bearing is fixedly mounted on rudder face, during band machinery returns
There is the actuator of mechanism Flying by wire mode to return middle mode with machinery,
Under the Flying by wire mode, actuator controller reception is converted to output after the instruction from flight control computer and referred to
Order is sent to the actuator with mechanical return to neutral mechanism, and actuator responds the instruction campaign of actuator controller and then drives rudder face inclined
Turn, the mechanical return to neutral mechanism in actuator now with mechanical return to neutral mechanism is in suspended state, is not responding to mechanical Hui Zhongji
The instruction that the actuator of structure receives；
During the machinery returns under mode, the mechanical return to neutral mechanism being connected with the actuator with mechanical return to neutral mechanism starts work
Make, and rudder face position is fed back into the actuator with mechanical return to neutral mechanism, rudder face is driven by the actuator with mechanical return to neutral mechanism
Return to neutral position.
In the present embodiment, the actuator of the band machinery return to neutral mechanism configures for electrical dual-redundancy.
In the present embodiment, bar is adjustable length pull bar during the machinery returns, to adapt to design, produce and alignment error institute band
The deviation accumulation come, meet that machinery returns the adjustment demand of middle system.
In the present embodiment, during the machinery returns bar include the Part I that is connected with rudder face and with mechanical return to neutral mechanism
Actuator connection Part II, the Part I is spirally connected with the Part II.Regulation is rotated against by two parts
The length of bar during machinery returns, it is to be understood that two end sets that Part I and Part II are located remotely from each other have rotation
Mechanism, miscellaneous equipment is connected by rotating mechanism, when regulation machinery returns middle pole length, to ensure bearing and mechanical Hui Zhongji
The stabilization of structure.
The present embodiment by mechanical return to neutral mechanism is set in actuator and machinery return in interface, and by the interface with having
Bar connection during the machinery of adjustable in length returns, then be connected to by bar in machinery time on the bearing for being fixed on rudder face, so as to be formed
Control system during the machinery of one closed loop returns.After mode during control system has fax mode conversion to be returned to machinery, machinery returns
Middle mechanism starts working, and the feedback according to bar in machinery time to rudder face position, control actuator motion, so as to drive rudder face to return
To neutral position.This method comprises the following steps：
The first step：Design the actuator with mechanical return to neutral mechanism；
Second step：Bar and the bearing being connected with rudder face during design machinery returns；
3rd step：Establish the linear system of system during machinery returns and be adjusted according to design requirement, determine actuator, machine respectively
The installation site of bar and bearing during tool returns；
4th step：The installation and debugging of system during machinery returns are carried out according to design and calculating.
5th step：Time middle function and performance of system in being returned after the completion of debugging by experimental test machinery, if meeting to require
Then show that the machinery returns middle system success.
The present invention meets returning for aircraft rudder surface by setting mechanical return to neutral mechanism and machinery to return middle interface in actuator
Middle demand；Bar is arranged to the pull bar of adjustable in length during machinery is returned, and counteracts caused by design, production and alignment error by mistake
Difference is accumulative, meets installation and debugging and the adjustment demand of system in machinery time.System in being returned this process simplify the machinery of aircraft, is carried
High rudder face return in reliability, ensure that Flight Safety.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (4)
- A kind of 1. plane lease of function during band machinery returns, it is characterised in that：Including actuator controller (1), band machinery Bar (3) and bearing (4) during the actuator (2) of return to neutral mechanism, machinery return, actuator controller (1) with mechanical return to neutral mechanism Actuator (2) between by cable connection, the actuator (2) with mechanical return to neutral mechanism be arranged on the vertical fin back rest on, machinery return Middle bar (3) one end is connected with the actuator (2) with mechanical return to neutral mechanism, and other end is connected with bearing (4), and bearing (4) is fixed On rudder face, there is the actuator (2) with mechanical return to neutral mechanism Flying by wire mode to return middle mode with machinery,Under the Flying by wire mode, actuator controller (1) reception is converted to output after the instruction from flight control computer and referred to Order is sent to the actuator (2) with mechanical return to neutral mechanism, the instruction campaign and then drive of actuator (2) response actuator controller (1) Dynamic control surface deflection, the mechanical return to neutral mechanism in actuator (2) now with mechanical return to neutral mechanism are in suspended state, are not responding to band The instruction that the actuator (2) of mechanical return to neutral mechanism receives；During the machinery returns under mode, the mechanical return to neutral mechanism being connected with the actuator (2) with mechanical return to neutral mechanism is started working, And rudder face position is fed back into the actuator (2) with mechanical return to neutral mechanism, rudder is driven by the actuator (2) with mechanical return to neutral mechanism Face returns to neutral position.
- 2. the plane lease as claimed in claim 1 for flying function in being returned with machinery, it is characterised in that：The band machinery returns The actuator (2) of middle mechanism configures for electrical dual-redundancy.
- 3. the plane lease as claimed in claim 1 that middle function is returned with machinery, it is characterised in that：Bar during the machinery returns (3) it is adjustable length pull bar.
- The plane lease of function during 4. the band machinery described in claim 3 returns, it is characterised in that：Bar during the machinery returns (3) Part I being connected with rudder face and the Part II being connected with the actuator (2) with mechanical return to neutral mechanism are included, it is described Part I is spirally connected with the Part II.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710597244.6A CN107499499B (en) | 2017-07-20 | 2017-07-20 | Airplane actuating system with mechanical centering function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710597244.6A CN107499499B (en) | 2017-07-20 | 2017-07-20 | Airplane actuating system with mechanical centering function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107499499A true CN107499499A (en) | 2017-12-22 |
| CN107499499B CN107499499B (en) | 2021-01-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710597244.6A Active CN107499499B (en) | 2017-07-20 | 2017-07-20 | Airplane actuating system with mechanical centering function |
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| CN (1) | CN107499499B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109596155A (en) * | 2018-11-07 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | The synchronous device for detecting multiple sensors |
| CN112697389A (en) * | 2020-12-02 | 2021-04-23 | 哈尔滨工程大学 | Automatic angle changing device for closed-loop control surface and control method thereof |
| CN113401332A (en) * | 2021-06-16 | 2021-09-17 | 北京中航智科技有限公司 | Working mode conversion device and centering device |
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| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN104787304A (en) * | 2015-04-27 | 2015-07-22 | 中国航天空气动力技术研究院 | Connecting rod mechanism of unmanned aircraft rudder system |
| CN105523170A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft control system with terminal neutral-position-pulling-back mechanism |
| CN105523171A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Hybrid transverse control system for large aircraft |
| CN105523174A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator |
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Patent Citations (6)
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| CN102239083A (en) * | 2008-12-04 | 2011-11-09 | 空中客车运作有限公司 | Aircraft directional control and stabilizing surface |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN105523170A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft control system with terminal neutral-position-pulling-back mechanism |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109596155A (en) * | 2018-11-07 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | The synchronous device for detecting multiple sensors |
| CN109596155B (en) * | 2018-11-07 | 2021-02-09 | 中国航空工业集团公司西安飞机设计研究所 | Device for synchronously detecting multiple sensors |
| CN112697389A (en) * | 2020-12-02 | 2021-04-23 | 哈尔滨工程大学 | Automatic angle changing device for closed-loop control surface and control method thereof |
| CN112697389B (en) * | 2020-12-02 | 2024-05-14 | 哈尔滨工程大学 | Automatic angle changing device for closed-loop control surface and control method thereof |
| CN113401332A (en) * | 2021-06-16 | 2021-09-17 | 北京中航智科技有限公司 | Working mode conversion device and centering device |
| CN113401332B (en) * | 2021-06-16 | 2023-03-10 | 北京中航智科技有限公司 | Working mode conversion device and centering device |
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| Publication number | Publication date |
|---|---|
| CN107499499B (en) | 2021-01-08 |
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