CN105523170A - Aircraft control system with terminal neutral-position-pulling-back mechanism - Google Patents
Aircraft control system with terminal neutral-position-pulling-back mechanism Download PDFInfo
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- CN105523170A CN105523170A CN201410508214.XA CN201410508214A CN105523170A CN 105523170 A CN105523170 A CN 105523170A CN 201410508214 A CN201410508214 A CN 201410508214A CN 105523170 A CN105523170 A CN 105523170A
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Abstract
The invention relates to an aircraft control system with a terminal neutral-position-pulling-back mechanism, and belongs to the field of control system design in the aircraft design field. The aircraft control system with the terminal neutral-position-pulling-back mechanism comprises a control device, a transmission mechanism, a terminal rocker arm and a neutral-position-pulling-back mechanism, wherein the control device is connected to the terminal rocker arm through the transmission mechanism, the terminal rocker arm is connected to a control surface through the transmission mechanism, the neutral-position-pulling-back mechanism comprises a stretching rod, a cylinder, springs, fixed baffles and movable baffles, the stretching rod penetrates through a terminal head blocking sheet, the two groups of the movable baffles and the springs are placed between the terminal head blocking sheet and a middle blocking sheet, one end of the neutral-position-pulling-back mechanism is hinged to an aircraft fixation member, and the other end is hinged to one joint of the terminal rocker arm through the stretching rod. According to the present invention, the pre-loaded spring neutral-position-pulling-back mechanism is arranged on the terminal end of the control system, such that the aircraft control surface has the good neutral-position-pulling-back performance, the problem that the reduced mechanical system rigidity and the insufficient manufacturing precision cause the large mechanical system dead zone is solved, the design difficulty and the manufacturing cost of the system are substantially reduced, and the flight safety is improved.
Description
Technical field
The invention belongs to the maneuvering system design field of field of airplane design, be specifically related to the flight control system with end item.
Background technology
In the mechanical manoeuvring system of aircraft, in the mechanical transfer of especially longer distance (being greater than 30m), distortion in frequent mechanical transmission mechanism, and gap can affect the performance of maneuvering system, as increased the manipulation dead band of system, when operating control rests on center position, rudder face still have angle, problems is the vice proper in mechanical system, and can not overcome, impact can only be reduced, as adopted increase system stiffness, increase the accuracy of manufacture of system unit, but this can increase the weight of aircraft undoubtedly, become geometric relationship to increase the manufacturing cost of aircraft simultaneously.Find through flight validation, insufficient rigidity and the gap of mechanical system are large, time operating control to neutral position is come to the safety effects main source of aircraft, rudder face still has angle, for this problem, can, by arranging certain device at aircraft rudder surface end, back segment maneuvering system be forced to retract neutral position, thus when can realize operating control without input, rudder face is also without drift angle.
Summary of the invention
The object of the invention is: the maneuvering system that a kind of end of tape Hui Zhong mechanism is provided, when realizing operating control neutrality by Hui Zhong mechanism, rudder face also gets back to center position, thus improves the performance of maneuvering system, improve flight safety, reduce pilot control tired.
Technical scheme of the present invention is: a kind of flight control system of end of tape Hui Zhong mechanism, comprise operating control, transmission device, end rocking arm and Hui Zhong mechanism, operating control is connected with end rocking arm by transmission device, end rocking arm is connected with rudder face by transmission device, Hui Zhong mechanism one end and aircraft fixed parts hinged, the other end is hinged by a joint of expansion link and end rocking arm, Hui Zhong mechanism comprises expansion link and cylindrical shell, cylindrical shell one end is closed, the other end is provided with termination catch, middle inside place is provided with middle part catch, expansion link is from left to right successively through the termination catch of cylindrical shell, and the left side fixed dam in cylindrical shell, left side shifting board, spring, right side shifting board, right side fixed dam, left side fixed dam is fixed in the middle part of expansion link, for the stop tab of left side shifting board, right side fixed dam is fixed on the right-hand member of expansion link, for the stop tab of right side shifting board, the termination catch of cylindrical shell is spacing to left side shifting board, middle part catch is spacing to right side shifting board, spring has certain pre compressed magnitude in an initial condition, pre compressed magnitude is determined by the distance of termination catch and middle part catch.
The spring of described Hui Zhong mechanism by organizing rigidity difference more, and the elastic element that drift is different is nested to be combined.
Transmission device local is the mechanism that cable wire and pulley form.
The beneficial effect that the present invention produces: the flight control system of a kind of end of tape Hui Zhong of the present invention mechanism, by arranging at maneuvering system end, there is preloading spring Hui Zhong mechanism, what realize aircraft rudder surface has good time neutrality, for reducing the large problem in mechanical system dead band that mechanical system rigidity and accuracy of manufacture deficiency causes, greatly reduce design difficulty and the manufacturing cost of system, improve flight safety.Return middle mechanism structure simple simultaneously, achieve the function with power in preloading, Double-directional back with same group of spring, and can realize back middle power change gradient function by cluster spring, there is very high actual value
Accompanying drawing explanation
Fig. 1 is the flight control system of a kind of end of tape Hui Zhong of the present invention mechanism;
Fig. 2 is the structure principle chart of Hui Zhong mechanism of the present invention;
Wherein, catch in the middle part of shifting board, 407-termination catch, 408-on the right side of fixed dam, 406-on the right side of shifting board, 405-on the left of fixed dam, 404-on the left of 1-operating control, 2-transmission device, 3-end rocking arm, 4-Hui Zhong mechanism, 5-rudder face, 401-cylindrical shell, 402-expansion link, 403-.
Detailed description of the invention
Below in conjunction with Figure of description, the present invention is described in further detail, refers to Fig. 1 and Fig. 2.
A kind of aircraft evelvator maneuvering system of end of tape Hui Zhong mechanism, comprise operating control, transmission device, end rocking arm and Hui Zhong mechanism, operating control is connected with end rocking arm by transmission device, end rocking arm is connected with elevating rudder rudder face by transmission device, Hui Zhong mechanism one end and aircraft fixed parts hinged, the other end is hinged by a joint of expansion link and end rocking arm, Hui Zhong mechanism comprises expansion link and cylindrical shell, cylindrical shell one end is closed, the other end is provided with termination catch, middle inside place is provided with middle part catch, expansion link is from left to right successively through the termination catch of cylindrical shell, and the left side fixed dam in cylindrical shell, left side shifting board, spring, right side shifting board, right side fixed dam, left side fixed dam is fixed in the middle part of expansion link, for the stop tab of left side shifting board, right side fixed dam is fixed on the right-hand member of expansion link, for the stop tab of right side shifting board, the termination catch of cylindrical shell is spacing to left side shifting board, middle part catch is spacing to right side shifting board, spring has certain pre compressed magnitude in an initial condition, pre compressed magnitude is determined by the distance of termination catch and middle part catch.When chaufeur is handled operating control, drive end rocking arm by transmission device and final driving elevating rudder rudder face, have application force to Hui Zhong mechanism simultaneously; When chaufeur stops handling operating control, operating control is back to center position, if now rudder face is not back to neutrality, the counter spring force of Hui Zhong mechanism will drive end rocking arm, make rudder face be back to neutrality.
The spring of described Hui Zhong mechanism is different by two groups of rigidity, the cylindrically coiled spring composition that drift is different, two groups of cylindrically coiled springs are placed on expansion link with one heart, the cylindrically coiled spring drift that wherein rigidity is large is longer than the distance of two shifting boards, the cylindrically coiled spring drift that rigidity is little is shorter than the distance of two shifting boards, in an initial condition, when having pulling force on the auricle of expansion link, pulling force is passed to the shifting board of fitting with middle part catch by the fixed dam fixed with expansion link termination, pulling force is passed to cylindrically coiled spring by shifting board, when pulling force is greater than the preload force of cylindrically coiled spring, just the cylindrically coiled spring that compression stiffness is large is started, when the distance of two groups of shifting boards is reduced to the drift being less than the less cylindrically coiled spring of rigidity, the cylindrically coiled spring that rigidity is less just starts to be compressed, thus the integral rigidity realizing Hui Zhongji changes, when having pressure on the auricle of expansion link, pressure is passed to the shifting board of fitting with termination catch by the fixed dam be connected with in the middle part of expansion link, pulling force is passed to cylindrically coiled spring by shifting board, when pressure is greater than the preload force of cylindrically coiled spring, just the cylindrically coiled spring that compression stiffness is large is started, when the distance of two groups of shifting boards is reduced to the drift being less than the less cylindrically coiled spring of rigidity, the cylindrically coiled spring that rigidity is less just starts to be compressed, thus the integral rigidity realizing Hui Zhongji changes, when system stop motion, if the cylindrically coiled spring of Hui Zhong mechanism is still compressed by two groups of active blades, and the outer face size of two groups of active blades is when being less than the inner end surface size of fixing catch and middle part catch, by the impact of cylindrically coiled spring counter-force, position when two groups of active catch sector-meetings are finally returned to Hui Zhong mechanism initial condition by the effect of cylindrically coiled spring power, thus by expansion link, the end of maneuvering system is retracted center position, thus during the manipulation realizing rudder face returns.
In elevator-control system in the present embodiment, described transmission device local is the flexible control mechanism that cable wire and pulley form.
Claims (3)
1. the flight control system of an end of tape Hui Zhong mechanism, it is characterized in that: comprise operating control, transmission device, end rocking arm and Hui Zhong mechanism, operating control is connected with end rocking arm by transmission device, end rocking arm is connected with rudder face by transmission device, Hui Zhong mechanism one end and aircraft fixed parts hinged, the other end is hinged by a joint of expansion link and end rocking arm, Hui Zhong mechanism comprises expansion link and cylindrical shell, cylindrical shell one end is closed, the other end is provided with termination catch, middle inside place is provided with middle part catch, expansion link is from left to right successively through the termination catch of cylindrical shell, and the left side fixed dam in cylindrical shell, left side shifting board, spring, right side shifting board, right side fixed dam, left side fixed dam is fixed in the middle part of expansion link, for the stop tab of left side shifting board, right side fixed dam is fixed on the right-hand member of expansion link, for the stop tab of right side shifting board, the termination catch of cylindrical shell is spacing to left side shifting board, middle part catch is spacing to right side shifting board, spring has certain pre compressed magnitude in an initial condition, pre compressed magnitude is determined by the distance of termination catch and middle part catch.
2. the flight control system of a kind of end of tape Hui Zhong mechanism as claimed in claim 1, is characterized in that: the spring of described Hui Zhong mechanism by organizing rigidity difference more, and the elastic element that drift is different is nested to be combined.
3. the flight control system of a kind of end of tape Hui Zhong mechanism as claimed in claim 1, is characterized in that: transmission device local is the mechanism that cable wire and pulley form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508214.XA CN105523170B (en) | 2014-09-28 | 2014-09-28 | A kind of flight control system of end of tape return to neutral mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508214.XA CN105523170B (en) | 2014-09-28 | 2014-09-28 | A kind of flight control system of end of tape return to neutral mechanism |
Publications (2)
| Publication Number | Publication Date |
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| CN105523170A true CN105523170A (en) | 2016-04-27 |
| CN105523170B CN105523170B (en) | 2018-04-03 |
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| CN201410508214.XA Active CN105523170B (en) | 2014-09-28 | 2014-09-28 | A kind of flight control system of end of tape return to neutral mechanism |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499499A (en) * | 2017-07-20 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | The plane lease of function during a kind of band machinery returns |
| CN108154748A (en) * | 2018-02-08 | 2018-06-12 | 哈尔滨莱特兄弟飞行技术有限公司 | A kind of rocker actuator for simulating big aircraft |
| CN108609199A (en) * | 2018-06-23 | 2018-10-02 | 中电科芜湖钻石飞机制造有限公司 | Applied to the limiting tool in flight control system assembling process |
| 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 |
| CN114368473A (en) * | 2022-02-09 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Push-pull control soft rope of airplane |
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| GB722842A (en) * | 1952-06-12 | 1955-02-02 | Northrop Aircraft Inc | Aileron, flap, and dive brake |
| KR20050028715A (en) * | 2003-09-19 | 2005-03-23 | 한국항공우주산업 주식회사 | Centering spring apparatus |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499499A (en) * | 2017-07-20 | 2017-12-22 | 中国航空工业集团公司西安飞机设计研究所 | The plane lease of function during a kind of band machinery returns |
| CN108154748A (en) * | 2018-02-08 | 2018-06-12 | 哈尔滨莱特兄弟飞行技术有限公司 | A kind of rocker actuator for simulating big aircraft |
| CN108154748B (en) * | 2018-02-08 | 2023-12-08 | 哈尔滨莱特兄弟飞行技术有限公司 | Rocker device for simulating large aircraft |
| CN108609199A (en) * | 2018-06-23 | 2018-10-02 | 中电科芜湖钻石飞机制造有限公司 | Applied to the limiting tool in flight control system assembling process |
| CN108609199B (en) * | 2018-06-23 | 2024-03-15 | 中电科芜湖钻石飞机制造有限公司 | Limiting tool applied to assembly process of airplane control system |
| 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 |
| CN114368473A (en) * | 2022-02-09 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Push-pull control soft rope of airplane |
| CN114368473B (en) * | 2022-02-09 | 2024-04-12 | 中国航空工业集团公司西安飞机设计研究所 | Push-pull control soft rope for airplane |
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|---|---|
| CN105523170B (en) | 2018-04-03 |
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