CN112977804B - Control surface lock - Google Patents
Control surface lock Download PDFInfo
- Publication number
- CN112977804B CN112977804B CN202110324530.1A CN202110324530A CN112977804B CN 112977804 B CN112977804 B CN 112977804B CN 202110324530 A CN202110324530 A CN 202110324530A CN 112977804 B CN112977804 B CN 112977804B
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- lock
- control surface
- pull rod
- groove
- 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
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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
- B64C9/02—Mounting or supporting thereof
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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
Abstract
The invention belongs to the technical field of airplane control systems, and discloses a control surface lock, which comprises: the device comprises a rocker arm, a pull rod, a lock groove rocker arm, a bracket and a lock mechanism; the upper end of the rocker arm is connected with the elevator rudder pipe shaft and can rotate along with the elevator rudder pipe shaft; the lower end of the rocker arm is connected with the right end of the pull rod; the rocker arm can rotate around the right end of the pull rod; the left end of the pull rod is connected with the lower end of the lock groove rocker arm; the left end of the pull rod can rotate around the lower end of the lock groove rocker arm; the bracket is fixed on the airplane structure; two lugs are arranged on the bracket; the two lugs are connected through a connecting shaft, and the upper end of the locking groove rocker arm is connected with the double lug connecting shaft; the lock groove rocker arm can rotate around the connecting shaft; the movable end of the lock groove rocker arm is provided with a lock groove; the lock mechanism is fixed on the aircraft structure, the lock mechanism is provided with a lock tongue, the lock tongue is telescopic, and the lock tongue is used for locking the lock groove rocker arm with the lock groove in a matching mode so as to lock the control surface. The device is simple in structure and can adapt to installation in different areas.
Description
Technical Field
The invention belongs to the technical field of airplane control systems, and particularly relates to a rudder surface lock of an airplane control system.
Background
When the airplane is in a ground shutdown state, a driver operates the control switch to drive the rudder surface lock to work, the lock pin is extended out, and the rudder (wing) surface is directly locked, so that the situation that the rudder surface swings to damage the rudder surface and a transmission mechanism of an operating system during wind blowing is avoided. The existing aircraft rudder surface lock cannot directly lock the rudder surface due to the limited installation space.
Disclosure of Invention
The invention overcomes the defects in the prior art and provides a control surface brake conversion mechanism.
A control surface lock comprising: rocker arm 7, pull rod 10, lock groove rocker arm 11, bracket 14 and lock mechanism 16; the upper end of the rocker arm is connected with the elevator rudder pipe shaft and can rotate along with the elevator rudder pipe shaft; the lower end of the rocker arm is connected with the right end of the pull rod; the rocker arm can rotate around the right end of the pull rod; the left end of the pull rod is connected with the lower end of the lock groove rocker arm; the left end of the pull rod can rotate around the lower end of the lock groove rocker arm;
the bracket is fixed on the aircraft structure 6; two lugs are arranged on the bracket; the two lugs are connected through a connecting shaft, and the upper end of the locking groove rocker arm is connected with the double-lug connecting shaft; the locking groove rocker arm can rotate around the connecting shaft; the movable end of the lock groove rocker arm is provided with a lock groove; the lock mechanism is fixed on the aircraft structure 6, the lock mechanism is provided with a lock tongue, the lock tongue is telescopic, and the lock tongue is used for locking the lock groove rocker arm with the lock groove in a matching mode so as to lock the control surface.
Furthermore, the four points are connected in sequence to form a parallelogram.
Furthermore, the end face of the movable end of the locking groove rocker arm, provided with the locking groove, is arc-shaped.
Furthermore, the end face of the movable end of the locking groove rocker arm, which is provided with the locking groove, is in a circular arc shape with the connecting shaft as the circle center.
Further, the extension line of the lock mechanism lock tongue passes through the connecting shaft.
Furthermore, an adjustable joint is arranged at one end of the pull rod, and the length of the pull rod can be adjusted by adjusting the adjustable joint.
Further, when the control surface is in a neutral position, the included angle between the lock groove rocker arm and the vertical direction is 0-15 degrees.
Further, when the control surface is in the neutral position, the included angle between the lock groove rocker arm and the vertical direction is 15 degrees.
Compared with the prior art, the invention has the beneficial effects that: the invention relates to a control surface locking mechanism of an operating system, which can indirectly lock a control surface outside the control surface on one hand. On the other hand, in the unlocking state, the control surface lock mechanism can move along with the control surface tubular shaft, and the control performance of the airplane is not influenced.
Drawings
FIG. 1 is a schematic view of the control surface lock structure;
FIG. 2 is an enlarged view of the control surface lock;
in the figure: 1 elevator, 2 elevator tube shaft, 3 main control system rocker arms, 4 elevator tube shaft brackets, 5 main control system transmission rods, 6 airplane structures, 7 rocker arms, 8 bolts, 9 bolts, 10 pull rods, 11 locking groove rocker arms, 12 bolts, 13 bolts, 14 brackets, 15 bolts, 16 locking mechanisms and 17 bolts.
Detailed Description
As shown in fig. 1 and 2, the rudder surface lock consists of a pull rod 10, a lock groove rocker arm 11, a rocker arm 7 and a bracket 14. The upper end of the rocker arm 7 is connected with the elevator pipe shaft 2 and can rotate along with the elevator pipe shaft; the lower end of the rocker arm 7 is connected with the right end of the pull rod 10; the rocker arm 7 can rotate around the right end of the pull rod 10; the left end of the pull rod 10 is connected with the lower end of the locking groove rocker arm 11; the left end of the pull rod 10 can rotate around the lower end of the lock groove rocker arm 11;
the bracket 14 is fixed to the aircraft structure 6; two ears are arranged on the bracket 14; the two lugs are connected through a connecting shaft, and the upper end of the locking groove rocker arm 11 is connected with the double lug connecting shaft; the locking groove rocker arm 11 can rotate around a connecting shaft; the movable end of the locking groove rocker arm is provided with a locking groove; the lock mechanism 16 is fixed on the aircraft structure 6, the lock mechanism is provided with a lock tongue, the lock tongue is telescopic, and the lock tongue is used for locking the lock groove rocker arm with the lock groove in a matching mode so as to lock the control surface.
An adjustable joint is arranged at one end of the pull rod 10 to adjust the length of the pull rod.
The end face of the movable end of the locking groove rocker arm 11, which is provided with the locking groove, is in a circular arc shape with the connecting shaft as the center of a circle.
The extension line of the lock mechanism lock tongue passes through the connecting shaft.
When the control surface is in a neutral position, the included angle between the lock groove rocker arm and the vertical direction is 0-15 degrees.
Preferably, when the control surface is in neutral position, the angle between the lock groove rocker arm and the vertical direction is 15 degrees.
The pull rod 10, the rocker arm 7 and the lock groove rocker arm 11 form three sides of a parallelogram.
Rocker arm 7 links firmly with elevator hollow shaft 2 through the fastener, and pull rod 10 one end is connected with rocker arm 7 through the fastener, and the other end passes through the fastener and links to each other with lock groove rocker arm 11, and lock groove rocker arm 11 passes through the fastener and is connected with support 14, and rudder face lock all passes through fastener fixed mounting on the aircraft frame web with the support.
When the control system rod (disc) or the pedals of the airplane move, the control system drives the elevator tubular shaft 2 to rotate, the rocker arm 7 drives the pull rod 10 to move, the pull rod 10 drives the lock groove rocker arm 11 to rotate, the rotation angle of the lock groove rocker arm 11 of the control system is equal to the rotation angle of the elevator tubular shaft 2, and when the control surface lock pin extends into the groove of the lock groove rocker arm 11, the control surface is locked and connected on the airplane body, so that the rotation of the rocker arm is limited, the control surface stops rotating and is kept at the current position. When the control surface lock pin extends out in time, the lock pin is not aligned with the notch of the rocker arm, and when the control system lever (disc) or the pedal moves, the lock pin slides into the lock groove along the arc surface of the rocker arm of the lock groove. The locking function of the control system is completed.
When the ground is stopped and braked, the rudder and the ailerons are locked at a neutral position, and at the same time, the pedal plate and the steering wheel are in the neutral position. In order to avoid the aircraft rising in the presence of strong winds, the elevator 1 is locked in the lower limit position. At this time, the steering column should be in the front limit position.
Claims (8)
1. A control surface lock is characterized in that: the control surface lock includes: the device comprises a rocker arm (7), a pull rod (10), a lock groove rocker arm (11), a bracket (14) and a lock mechanism (16);
the upper end of the rocker arm is connected with the elevator rudder pipe shaft and can rotate along with the elevator rudder pipe shaft;
the lower end of the rocker arm is connected with one end of a pull rod; the rocker arm can rotate around one end of the pull rod;
the other end of the pull rod is connected with the lower end of the lock groove rocker arm; the other end of the pull rod can rotate around the lower end of the lock groove rocker arm;
the support is fixed on the aircraft structure (6); two lugs are arranged on the bracket; the two lugs are connected through a connecting shaft, and the upper end of the locking groove rocker arm is connected with the connecting shaft; the locking groove rocker arm can rotate around the connecting shaft;
the movable end of the locking groove rocker arm is provided with a locking groove;
the lock mechanism is fixed on an airplane structure (6), a lock tongue is arranged on the lock mechanism and is telescopic, and the lock tongue is used for locking the lock groove rocker arm in a matched mode with the lock groove to lock the control surface.
2. Control surface lock according to claim 1, characterized in that: the connecting point of the locking groove rocker arm and the support, the connecting point of the pull rod and the locking groove rocker arm, the connecting point of the pull rod and the rocker arm, and the connecting point of the rocker arm and the elevator are connected in sequence, and a graph formed by connecting the four points is a parallelogram.
3. Control surface lock according to claim 1, characterized in that: the end face of the movable end of the locking groove rocker arm, provided with the locking groove, is arc-shaped.
4. Control surface lock according to claim 3, characterized in that: the end face of the movable end of the locking groove rocker arm, which is provided with the locking groove, is in a circular arc shape with the connecting shaft as the circle center.
5. Control surface lock according to claim 4, characterized in that: the extension line of the lock mechanism lock tongue passes through the connecting shaft.
6. Control surface lock according to claim 2, characterized in that: one end of the pull rod is provided with an adjustable joint, and the length of the pull rod can be adjusted by adjusting the adjustable joint.
7. Control surface lock according to claim 1, characterized in that: when the control surface is in a neutral position, the included angle between the lock groove rocker arm and the vertical direction is 0-15 degrees.
8. Control surface lock according to claim 7, characterized in that: when the control surface is in the neutral position, the included angle between the lock groove rocker arm and the vertical direction is 15 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110324530.1A CN112977804B (en) | 2021-03-26 | 2021-03-26 | Control surface lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110324530.1A CN112977804B (en) | 2021-03-26 | 2021-03-26 | Control surface lock |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112977804A CN112977804A (en) | 2021-06-18 |
| CN112977804B true CN112977804B (en) | 2023-03-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110324530.1A Active CN112977804B (en) | 2021-03-26 | 2021-03-26 | Control surface lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112977804B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2763094C1 (en) * | 2021-07-30 | 2021-12-27 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Mechanism for actuating control surfaces |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101559831A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Multi-functional bird collision resistant ventilation window |
| EP2578347A2 (en) * | 2011-10-06 | 2013-04-10 | Airbus Operations GmbH | Joining device for connecting structural components for an aircraft |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB566583A (en) * | 1943-05-29 | 1945-01-04 | Short Brothers Rochester & Bedford Ltd | A new or improved means for ensuring that aircraft controls are unlocked before the aircraft takes off |
| FR2855496B1 (en) * | 2003-05-27 | 2006-09-22 | Snecma Moteurs | REAR SUSPENSION OF AIRCRAFT ENGINE WITH PUSH REPEAT |
| CN202783776U (en) * | 2012-08-13 | 2013-03-13 | 湖南山河科技股份有限公司 | Spring centering and positioning mechanism for rudder of light aircraft |
| CN206737652U (en) * | 2017-05-04 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft emergency hatch handle mechanism |
| US10808808B2 (en) * | 2017-05-05 | 2020-10-20 | Sierra Nevada Corporation | Expanding pin assembly controlled by actuator for locking and unlocking mechanical joint |
| CN208576722U (en) * | 2018-06-29 | 2019-03-05 | 长沙市云智航科技有限公司 | A kind of component that verts for more rotor flying vehicles |
| CN211810196U (en) * | 2019-11-29 | 2020-10-30 | 西安京东天鸿科技有限公司 | Locking device and aircraft |
-
2021
- 2021-03-26 CN CN202110324530.1A patent/CN112977804B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101559831A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Multi-functional bird collision resistant ventilation window |
| EP2578347A2 (en) * | 2011-10-06 | 2013-04-10 | Airbus Operations GmbH | Joining device for connecting structural components for an aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112977804A (en) | 2021-06-18 |
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