CN110217383B - Hard steering system for steering front wheel by aircraft foot - Google Patents
Hard steering system for steering front wheel by aircraft foot Download PDFInfo
- Publication number
- CN110217383B CN110217383B CN201910547429.5A CN201910547429A CN110217383B CN 110217383 B CN110217383 B CN 110217383B CN 201910547429 A CN201910547429 A CN 201910547429A CN 110217383 B CN110217383 B CN 110217383B
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- CN
- China
- Prior art keywords
- pull rod
- rocker arm
- steering
- front wheel
- spring pull
- Prior art date
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- 230000000694 effects Effects 0.000 claims description 4
- 238000002955 isolation Methods 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 230000035945 sensitivity Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
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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)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention belongs to the field of airplane aviation, and relates to a pedal-operated front wheel turning hard-type operating system. Comprises a spring pull rod, an operating rocker arm, a triangular rocker arm, a pull rod and a rudder plate valve rocker arm; the control rocker arm is provided with a bulge, a connecting hole is formed in the bulge, one end, provided with a single lug, of the spring pull rod is connected with the single lug of the triangular rocker arm through the connecting hole by adopting a bolt, the other end, provided with double lugs, of the spring pull rod is connected with the single lug of the triangular rocker arm, one end, provided with double lugs, of the triangular rocker arm is connected with the pull rod, and the other end of the pull rod is connected with the rudder plate valve rocker arm. The idle stroke of the control system can be reduced, and the control accuracy is improved. On the other hand, the anti-fault working capacity of the system is improved by adopting the spring pull rod, so that the safety of the aircraft is ensured.
Description
Technical Field
The invention belongs to the field of airplane control, relates to an airplane front wheel turning control system, and particularly relates to a pedal-operated front wheel turning hard control system.
Background
Currently, there are two input modes for mechanical feedback control systems: the hand steering front wheel turns and the foot pedal steering front wheel turns.
When the ground slides at a low speed and turns at a large angle, the front wheels are controlled to rotate by the hand wheel mechanism, and when the ground takes off and lands, the front wheels are rectified by the rudder plate mechanism.
Front wheel steering systems are typically designed with soft drive mechanisms. The signal is transmitted to the turn input rocker arm (rudder plate mechanism) through a wire rope, drum, pulley, and the like. Since the steel cable is woven from steel wires, it can only withstand tensile forces and not compressive forces. Therefore, when the steel cable is pulled, the steel cable is easily stretched to generate an elastic gap. Too large an elastic gap of the wire rope deteriorates the sensitivity of the steering system.
Disclosure of Invention
The invention overcomes the defects of large idle stroke and poor maneuvering sensitivity of the maneuvering system in the prior art, and provides the transmission system with high safety and excellent comprehensive performance.
Technical proposal
The hard steering system for steering the front wheel of the aircraft foot comprises a spring pull rod 3, a steering rocker arm 4, a triangular rocker arm 5, a pull rod 2 and a rudder plate valve rocker arm 1; the control rocker arm 4 is provided with a bulge, a connecting hole is formed in the bulge, one end, provided with a single lug, of the spring pull rod 3 is connected with the connecting hole through a bolt, the other end, provided with double lugs, of the spring pull rod 3 is connected with the single lug of the triangular rocker arm 5, one end, provided with double lugs, of the triangular rocker arm 5 is connected with the pull rod 2, and the other end of the pull rod 2 is connected with the rudder plate valve rocker arm 1.
The end, connected with the control rocker arm 4, of the spring pull rod 3 is provided with a bearing, friction force is reduced, and the spring pull rod 3 is provided with a pretightening force, so that fault isolation effect is achieved.
The middle of the bulge on the control rocker arm 4 is provided with a groove, so that the weight reduction effect is achieved.
The single ear end of the triangular rocker arm 5 is provided with a bearing, so that the rotation is flexible and friction force is reduced.
The rotating shaft end on the triangular rocker arm 5 is connected with the support through a bolt, and the rotating shaft end is provided with a bearing, so that the rotating is flexible and friction force is reduced. The support is fixed to the aircraft structure.
One end of the pull rod 2 connected with the triangular rocker arm 5 is provided with a bearing, so that the pull rod can flexibly rotate to reduce friction force.
The single lug end of the triangular rocker arm 5 is provided with an inclination angle design, and the inclination angle is set according to the inclination angle between the spring pull rod 3 and the plane of the aircraft structure frame during installation.
The single lug of the triangular rocker arm 5 is parallel to the axis of the spring pull rod 3.
The rudder plate valve rocker arm 1 controls the opening and closing of a hydraulic system slide valve through rotation.
The lengths of the pull rod 2 and the spring pull rod 3 are adjustable, and the adjustable ends are locked through the stop gaskets to play a loosening role.
Technical effects
Compared with the prior art, the invention has the beneficial effects that: the invention relates to a hard steering line system for steering front wheels of aircraft feet. On the one hand, the idle stroke of the control system can be reduced, and the control accuracy is improved. On the other hand, the anti-fault working capacity of the system is improved by adopting the spring pull rod, so that the safety of the aircraft is ensured.
Drawings
FIG. 1 is a diagram of a steering string design of the present invention;
wherein 1, a rudder plate valve rocker arm 2, a pull rod 3, a spring pull rod 4, a rudder control rocker arm 5 and a triangular rocker arm
FIG. 2 is a front view of a triangular rocker arm of the present invention;
FIG. 3 is a top view of a triangular rocker arm of the present invention;
fig. 4 is a schematic view of a pilot rocker arm of the present invention.
Detailed Description
The invention is described in further detail below with reference to the attached drawings and detailed description: referring to fig. 1, a hard steering line system design for steering front wheels of an aircraft foot is provided in the present embodiment.
The steering rocker arm (4) moves along with the steering line system of the rudder when the rudder is steered by foot steering, the steering rocker arm (4) drives the spring pull rod (3) to move up and down, the spring pull rod (3) drives the triangular rocker arm (5) to rotate, the rudder plate valve rocker arm (1) deflects through the pull rod (2), the opening and closing of the slide valve are controlled, the hydraulic system works, and the purpose of steering the front wheel is achieved.
The steering wheel is rotated by pedaling the steering wheel pedal, at the moment, the spring of the spring pull rod (3) is not deformed, the length of the spring pull rod (3) is unchanged, and the steering wheel and the front wheel work cooperatively. When the rudder plate valve fails and is blocked, the pedal is stepped on, the length of the spring pull rod is changed, and the normal operation of the rudder is not affected. In the aerial steering rudder, the rudder plate valve is followed (at the moment, the front wheel steering hydraulic system is not operated), and the rudder can deflect normally.
Claims (9)
1. The utility model provides an aircraft foot controls front wheel hard control system of turning, control slide valve's opening and closing realizes pedal and controls front wheel turn, its characterized in that: comprises a spring pull rod (3), an operating rocker arm (4), a triangular rocker arm (5), a pull rod (2) and a rudder plate valve rocker arm (1); the control rocker arm (4) is provided with a bulge, a connecting hole is formed in the bulge, one end, with a single lug, of the spring pull rod (3) is connected with the connecting hole through a bolt, the other end, with double lugs, of the spring pull rod (3) is connected with the single lug of the triangular rocker arm (5), one end, with double lugs, of the triangular rocker arm (5) is connected with the pull rod (2), and the other end of the pull rod (2) is connected with the rudder plate valve rocker arm (1); the single lug end of the triangular rocker arm (5) is provided with an inclination angle design, and the inclination angle is set according to the inclination angle between the spring pull rod (3) and the plane of the aircraft structure frame when the spring pull rod is installed; the steering arm (4) in the steering system is crosslinked with a steering wheel front section hard steering line system, when the steering wheel is steered by pedaling, the steering arm (4) moves along with the steering line system, the steering arm (4) drives the spring pull rod (3) to move up and down, the spring pull rod (3) drives the triangular rocker arm (5) to rotate, the steering plate valve rocker arm (1) deflects through the pull rod (2) to control the opening and closing of the sliding valve, the hydraulic system works, the purpose of front wheel steering is achieved, the steering pedal bends the front wheel, at the moment, the spring of the spring pull rod (3) is not deformed, the length of the spring pull rod (3) is unchanged, the steering wheel and the front wheel work in a coordinated manner, when the steering plate valve is jammed due to faults, the pedaling, the length of the spring pull rod is changed, normal work of the steering wheel is not affected, the steering wheel is steered in an air, the steering plate valve moves along, at the moment, the front wheel steering hydraulic system does not work, and the steering valve can normally deflect.
2. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: one end of the spring pull rod (3) connected with the control rocker arm (4) is provided with a bearing, friction force is reduced, and the spring pull rod (3) is provided with a pretightening force, so that fault isolation effect is achieved.
3. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: a groove is arranged in the middle of the bulge on the control rocker arm (4) to play a role in reducing weight.
4. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: the single ear end of the triangular rocker arm (5) is provided with a bearing, so that the rotation is flexible and friction force is reduced.
5. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: the rotating shaft end on the triangular rocker arm (5) is connected with the support through a bolt, the bearing is arranged at the rotating shaft end, the rotating is flexible, the friction force is reduced, and the support is fixed on an airplane structure.
6. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: one end of the pull rod (2) connected with the triangular rocker arm (5) is provided with a bearing, so that the rotation is flexible and friction force is reduced.
7. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: the single lug of the triangular rocker arm (5) is parallel to the axis of the spring pull rod (3).
8. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: the rudder plate valve rocker arm (1) controls the opening and closing of a slide valve of the hydraulic system through rotation.
9. An aircraft foot-operated front wheel turning hard steering system according to claim 1, wherein: the lengths of the pull rod (2) and the spring pull rod (3) are adjustable, and the adjustable ends are locked through the stop gaskets to play a loosening role.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547429.5A CN110217383B (en) | 2019-06-24 | 2019-06-24 | Hard steering system for steering front wheel by aircraft foot |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910547429.5A CN110217383B (en) | 2019-06-24 | 2019-06-24 | Hard steering system for steering front wheel by aircraft foot |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110217383A CN110217383A (en) | 2019-09-10 |
| CN110217383B true CN110217383B (en) | 2023-06-23 |
Family
ID=67814617
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910547429.5A Active CN110217383B (en) | 2019-06-24 | 2019-06-24 | Hard steering system for steering front wheel by aircraft foot |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110217383B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111572757B (en) * | 2020-05-09 | 2023-03-14 | 陕西飞机工业（集团）有限公司 | Method for designing driving mechanism of follow-up control surface of aircraft rudder |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2517692A1 (en) * | 1974-04-26 | 1975-11-13 | Deere & Co | VEHICLE STEERING |
| CN203780509U (en) * | 2014-02-20 | 2014-08-20 | 高邮市迅达工程机械集团有限公司 | Auxiliary braking device for chassis of engineering vehicle |
| CN105460225A (en) * | 2015-11-26 | 2016-04-06 | 庆安集团有限公司 | Fault isolation mechanism for elevating rudders |
| CN208233348U (en) * | 2018-05-02 | 2018-12-14 | 西安翔安测控设备有限责任公司 | A kind of unmanned plane during flying steerable system |
| CN109229345A (en) * | 2018-09-25 | 2019-01-18 | 陕西飞机工业（集团）有限公司 | A kind of aircraft foot operating mechanism of anti-error brake |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB523663A (en) * | 1938-12-08 | 1940-07-19 | George Herbert Dowty | Improvements relating to aircraft landing gear |
| FR1020859A (en) * | 1949-06-02 | 1953-02-11 | Hobson Ltd H M | Servomotor or similar hydraulic actuating device applicable in particular to aircraft control surfaces |
| GB760225A (en) * | 1953-06-04 | 1956-10-31 | Northrop Aircraft Inc | Improvements in or relating to aircraft control systems |
| NL217349A (en) * | 1956-07-27 | |||
| JP2617448B2 (en) * | 1986-05-28 | 1997-06-04 | 三菱重工業株式会社 | Aircraft human-powered steering system |
| JPH1148077A (en) * | 1997-08-01 | 1999-02-23 | Asahi Seiki Mfg Co Ltd | Tool operating device |
| US9162706B2 (en) * | 2010-03-23 | 2015-10-20 | Cataldo Proia | Self-tracking system for the rear axles of trucks |
| CN202481306U (en) * | 2012-03-09 | 2012-10-10 | 陕西飞机工业（集团）有限公司 | Airplane foot control brake mechanism |
| CN203350054U (en) * | 2013-01-05 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test device of actuator rear flight control mechanical control system |
| CN203228767U (en) * | 2013-04-27 | 2013-10-09 | 六安市金安区生产力促进中心 | Fixed whirly elastic forklift pedal |
| CN106184714B (en) * | 2015-04-29 | 2018-07-24 | 陕西飞机工业（集团）有限公司 | A kind of load of aircraft control surface and drift angle limits device |
| CN106741870B (en) * | 2016-11-30 | 2019-03-26 | 中国直升机设计研究所 | A kind of cockpit steerable system and method |
| CN108001671B (en) * | 2017-11-08 | 2019-11-15 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of aircraft nose wheel turning actuator |
| CN109625084A (en) * | 2019-01-16 | 2019-04-16 | 杭州米氪科技有限公司 | Differential type non-steering wheels Follow-up steering mechanism |
-
2019
- 2019-06-24 CN CN201910547429.5A patent/CN110217383B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2517692A1 (en) * | 1974-04-26 | 1975-11-13 | Deere & Co | VEHICLE STEERING |
| CN203780509U (en) * | 2014-02-20 | 2014-08-20 | 高邮市迅达工程机械集团有限公司 | Auxiliary braking device for chassis of engineering vehicle |
| CN105460225A (en) * | 2015-11-26 | 2016-04-06 | 庆安集团有限公司 | Fault isolation mechanism for elevating rudders |
| CN208233348U (en) * | 2018-05-02 | 2018-12-14 | 西安翔安测控设备有限责任公司 | A kind of unmanned plane during flying steerable system |
| CN109229345A (en) * | 2018-09-25 | 2019-01-18 | 陕西飞机工业（集团）有限公司 | A kind of aircraft foot operating mechanism of anti-error brake |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110217383A (en) | 2019-09-10 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |