CN110733629B - Flight control system guide device - Google Patents
Flight control system guide device Download PDFInfo
- Publication number
- CN110733629B CN110733629B CN201910970691.0A CN201910970691A CN110733629B CN 110733629 B CN110733629 B CN 110733629B CN 201910970691 A CN201910970691 A CN 201910970691A CN 110733629 B CN110733629 B CN 110733629B
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- CN
- China
- Prior art keywords
- guide
- flight control
- control system
- transmission rod
- base
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
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- 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)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The application provides a flight control system guide device, the device includes transfer line, guide base 1, leading wheel 2 and locking device, wherein: the guide piece base 1 is a flat plate provided with at least one perforation, a transmission rod of the flight control system penetrates through the perforation of the guide piece base 1, at least three guide wheels 2 are arranged on the first surface of the guide piece base 1 and surround the outer wall of the transmission rod, and the guide wheels 2 are fixed on the guide piece base 1 through a locking device.
Description
Technical Field
The invention relates to the field of aircraft flight control systems, in particular to a guide device of a flight control system.
Background
The guide means are support means for the drive rod of the hard control system of the aircraft. The mechanical handling system has also undergone its development during the last thirty years. The main factors contributing to its development are the elastic deformation, clearance, friction and weight requirements of the system. Due to the simple construction and the low weight of the soft steering system, it is used in aircraft in the first place. Over time, designers have found that it is a serious maneuver delay phenomenon, which is unsuitable for fighters with high mobility requirements and aircraft performing special tasks, and hard maneuver systems with drive levers as the main components have emerged. Such a guide arrangement may be used to support the drive rod when the hard drive system is not required to switch direction in a longer line, shortening the effective length of the drive rod when it is compressed.
Disclosure of Invention
The invention provides a novel flight control system transmission rod support piece for an aircraft, and provides a reliable and adjustable transmission mechanical movement device for a hard control system;
the application provides a flight control system guide device, the device includes transfer line, guide base 1, leading wheel 2 and locking device, wherein:
the guide piece base 1 is a flat plate provided with at least one perforation, a transmission rod of the flight control system penetrates through the perforation of the guide piece base 1, at least three guide wheels 2 are arranged on the first surface of the guide piece base 1 and surround the outer wall of the transmission rod, and the guide wheels 2 are fixed on the guide piece base 1 through a locking device.
Optionally, the locking means comprises a centering bolt 3, a locking washer 4, a nut 5, a bearing 6 and a cotter pin 7.
Optionally, the aligning bolt 3 sequentially passes through the guide wheel 2, the bearing 6 and the nut 5 and is locked by the locking washer 4 and the cotter pin 7.
Optionally, the outer ring of the guide wheel 2 is coated with an aluminum shell.
Optionally, the guide base 1 is a machined part.
Optionally, a boss is provided on the second face of the guide base 1, said boss being used to attach the flight control system guide device to the aircraft structure.
Optionally, the number of the transmission rods is three.
Optionally, three guide wheels 2 are arranged on the outer wall of each transmission rod.
The invention provides a novel flight control system transmission rod support piece for an aircraft. The beneficial effects are that the installation or transmission links of the control rocker arm, the bearing, the support and the like are reduced, so that the short and direct line is realized, the transmission links are minimum, and the adverse effects caused by the nonlinearity of the motion transmission of the system are fully reduced.
Drawings
FIG. 1 is a schematic view of a configuration of a flight control system guide apparatus provided by the present invention;
wherein: the guide piece base 1, the guide wheel 2, the aligning bolt 3, the locking gasket 4, the nut 5, the bearing 6 and the cotter pin 7.
Detailed Description
The invention discloses a novel guide piece device of a flight control system, which is a transmission rod support piece of the flight control system and comprises the following components: the guide piece comprises a guide piece base 1, a guide wheel 2, a centering bolt 3, a locking gasket 4, a nut 5, a bearing 6 and a cotter pin 7; the three-hole guide piece device is supported by rollers (guide wheels 2) of which the outer rings are coated with aluminum shells by 9 rolling bearings 6, each three rollers 2 supports a pull rod, and three transmission rods are supported by nine rollers; the guide piece base 1 is an machined piece, and a boss is arranged at a fixing bolt hole of the guide piece base for enabling the bottom surface of the support to be attached to an airplane structure; an inner hole of the guide wheel 2 is provided with a centering bolt 3, a locking gasket 4 at the centering bolt 3 is not locked before installation and debugging, and is locked after being adjusted by an upper control system; after the guide wheel 2, the aligning bolt 3, the nut 5 and the cotter pin 7 are assembled on the base, the rotation is flexible, and other cotter pins 7 are locked according to HB0-2-A except for the locking gasket 4; the device can conveniently adjust the gap between the guide wheel 2 and the transmission rod by adjusting the aligning bolt 3, thereby ensuring that the control system moves stably and exactly.
The invention will be further described with reference to the accompanying drawings.
The embodiment of the invention provides a novel guide device of a flight control system, which comprises a guide base 1, a guide wheel 2, a centering bolt 3, a locking gasket 4, a nut 5, a bearing 6 and a cotter pin 7. The method comprises the following steps:
in the concrete implementation, after the guide wheel 2 of the press bearing 6 is assembled on the base 1, the rotation is flexible, and other cotter pins except the locking gasket 4 are locked according to HB 0-2-A;
in the concrete implementation, each group of guide wheels 2 is provided with a aligning bolt 3, a locking gasket 4 at the aligning bolt 3 is not locked for delivery, and the guide wheels are locked after being installed and adjusted by an upper operating system;
in the concrete implementation, after the guide wheel 2 is installed, checking the GAP between the guide wheel and the guide wheel by using a process pipe or rod with the same diameter as the transmission rod, wherein the GAP between the guide wheel and the pull rod at each aligning bolt is required to meet the gap= (0.15-0.5) mm, and the rest guide wheels cannot excessively grind the pipe body;
the guide piece device of the flight control system provided by the embodiment of the invention can conveniently adjust the gap between the guide wheel and the transmission rod by adjusting the aligning bolt, thereby ensuring that the control system moves stably and exactly;
while the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, and such modifications and changes are intended to be included within the scope of the invention.
Claims (4)
1. A flight control system guide device, characterized in that the device comprises a transmission rod, a guide base (1), a guide wheel (2) and a locking device, wherein:
the guide piece base (1) is a flat plate provided with at least one perforation, a transmission rod of the flight control system penetrates through the perforation of the guide piece base (1), three guide wheels (2) are arranged on the first surface of the guide piece base (1) around the outer wall of the transmission rod, and the guide wheels (2) are fixed on the guide piece base (1) through a locking device;
each group of guide wheels (2) is provided with a aligning bolt (3), a locking gasket (4) at the aligning bolt (3) is not locked for delivery, and the guide wheels are locked after the upper operating system is installed and adjusted; after the guide wheel (2) is installed, checking the GAP between the guide wheel and the transmission rod by using a process pipe or rod with the same diameter as the transmission rod, wherein the GAP between the guide wheel and the transmission rod at each aligning bolt is required to meet the gap= (0.15-0.5) mm;
the locking device comprises a aligning bolt (3), a locking gasket (4), a nut (5), a bearing (6) and a cotter pin (7);
the aligning bolt (3) sequentially passes through the guide wheel (2), the bearing (6) and the nut (5) and is locked by the locking gasket (4) and the cotter pin (7);
a boss is arranged on the second surface of the guide piece base (1), and the boss is used for installing and attaching the flight control system guide piece device to an airplane structure.
2. The device according to claim 1, characterized in that the outer ring of the guide wheel (2) is wrapped around an aluminium housing.
3. The device according to claim 1, characterized in that the guide base (1) is a machined part.
4. The apparatus of claim 1 wherein the number of drive links that can be supported simultaneously in a parallel flight control triaxial main system line is three.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910970691.0A CN110733629B (en) | 2019-10-12 | 2019-10-12 | Flight control system guide device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910970691.0A CN110733629B (en) | 2019-10-12 | 2019-10-12 | Flight control system guide device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110733629A CN110733629A (en) | 2020-01-31 |
| CN110733629B true CN110733629B (en) | 2023-05-23 |
Family
ID=69268815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910970691.0A Active CN110733629B (en) | 2019-10-12 | 2019-10-12 | Flight control system guide device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110733629B (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB558935A (en) * | 1942-11-05 | 1944-01-27 | Blackburn Aircraft Ltd | Improvements in and relating to bearing supports for axially movable rods |
| GB618596A (en) * | 1946-01-28 | 1949-02-24 | Thomas Linford Marshall | Improvements in or relating to bearings for control tubes or rods |
| CN103496445A (en) * | 2013-09-26 | 2014-01-08 | 西安庆安电气控制有限责任公司 | Automatically-lockable tension regulator |
| CN104309805B (en) * | 2014-08-26 | 2017-07-07 | 中国直升机设计研究所 | A kind of PH phasemeter manipulated for helicopter flight |
| CN104908062B (en) * | 2015-06-09 | 2017-04-05 | 中国石油大学(华东) | Moveable industrial robot fixing device |
| CN208861517U (en) * | 2018-05-22 | 2019-05-14 | 珠海高斯科技有限公司 | Flight simulator and its manipulation load device |
| CN109533293A (en) * | 2018-11-15 | 2019-03-29 | 中国直升机设计研究所 | A kind of pull rod guiding mechanism for helicopter flight manipulation |
| CN109649640B (en) * | 2018-12-25 | 2020-12-11 | 北京青云航空仪表有限公司 | Friction damping device for accelerator platform |
-
2019
- 2019-10-12 CN CN201910970691.0A patent/CN110733629B/en active Active
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| Publication number | Publication date |
|---|---|
| CN110733629A (en) | 2020-01-31 |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221024 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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