Airplane control surface lock mechanism

Abstract

The utility model discloses an aircraft control surface lock mechanism. Comprising a lock groove support (1), a rocker arm (2) and a lock mechanism (3), one end of the rocker arm (2) is fixedly connected with the control surface tubular shaft (8), one end of the control surface tubular shaft (8) is fixedly connected with the control surface (9), the other end of the control surface tubular shaft (8) is rotatably connected with the support (4), and the support (4) is fixedly connected with the airplane structure II (7); the other end of the rocker arm (2) is hinged with the pull rod (5); the lock groove support (1) is fixedly arranged on the waist portion of the rocker arm (2), and a lock hole (10) is formed in the lock groove support (1). The lock mechanism (3) is fixedly installed on the airplane structure I (6) through a fastener, and a lock pin (11) of the lock mechanism (3) can be inserted into the lock hole (10). According to the utility model, the control surface can be indirectly locked outside the control surface; in the unlocking state, the lock groove support can move along with the control surface tubular shaft, and the maneuvering performance of the aircraft is not affected.

Description

Technical Field

[0001] The utility model belongs to the technical field of flight control system design and relates to an aircraft control surface locking mechanism. Background Art

[0002] When the aircraft is parked on the ground, the pilot operates the control switch to drive the rudder lock to work, extend the lock tongue, and directly lock the rudder (wing) surface to prevent the rudder from swinging and damaging the transmission mechanism of the rudder surface and the control system when the wind blows. However, the installation space of the rudder lock of most aircraft is limited, and the rudder lock cannot directly lock the rudder surface. Summary of the invention

[0003] The purpose of the utility model is to provide an aircraft rudder surface locking mechanism. The utility model can indirectly lock the rudder surface outside the rudder surface; in the unlocked state, the lock slot support can also move with the rudder surface tube axis without affecting the aircraft control performance.

[0004] Technical solution. An aircraft rudder locking mechanism comprises a locking groove support, a rocker arm, and a locking mechanism; one end of the rocker arm is fixedly connected to the rudder tube shaft, one end of the rudder tube shaft is fixedly connected to the rudder, the other end of the rudder tube shaft is rotatably connected to the bracket, and the bracket is fixedly connected to the aircraft structure II; the other end of the rocker arm is hinged to the pull rod; the locking groove support is fixedly arranged at the waist of the rocker arm, and a locking hole is arranged on the locking groove support; the locking mechanism is fixedly installed on the aircraft structure I through a fastener, and a locking pin of the locking mechanism can be inserted into the locking hole.

[0005] In the aforementioned aircraft rudder surface locking mechanism, the locking hole is in the shape of a cone hole.

[0006] In the aforementioned aircraft control surface locking mechanism, a guide lip is provided at the edge of the opening of the locking hole.

[0007] In the aforementioned aircraft control surface locking mechanism, a circular chamfer is provided between the hole and the guide lip.

[0008] In the aforementioned aircraft control surface locking mechanism, the guide lip extends a guide arc along the deflection direction of the rocker arm, and the center of the guide arc coincides with the rotation axis of the rocker arm.

[0009] In the aforementioned aircraft control surface locking mechanism, the lock hole is 13 mm deep.

[0010] Beneficial Effects

[0011] The aircraft rudder lock mechanism provided by the utility model can, on the one hand, indirectly lock the rudder outside the rudder; on the other hand, in the unlocked state, the lock slot support can move with the rudder tube axis without affecting the aircraft's control performance. In addition, the utility model has a simple structure, low implementation difficulty, short development cycle, convenient installation and adjustment, good maintainability, and can be installed in different areas according to needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of the overall structure of the aircraft rudder lock mechanism;

[0013] Figure 2 It is a schematic diagram of the partial structure of the aircraft control surface locking mechanism;

[0014] Figure 3 It is a schematic diagram of the lock slot support structure.

[0015] Figure numerals: 1-locking groove support, 2-rocker arm, 3-locking mechanism, 4-bracket, 5-pull rod, 6-aircraft structure I, 7-aircraft structure II, 8-rudder tube axis, 9-rudder, 10-locking hole, 11-locking pin, 12-guide lip, 13-arc chamfer, 14-guide arc. DETAILED DESCRIPTION

[0016] Combined with the accompanying drawings, the utility model is described in detail:

[0017] Embodiment 1. An aircraft control surface locking mechanism, comprising: Figure 1-3 As shown, it includes a lock slot support 1, a rocker arm 2, and a lock mechanism 3; one end of the rocker arm 2 is fixedly connected to the rudder surface tube shaft 8, one end of the rudder surface tube shaft 8 is fixedly connected to the rudder surface 9, the other end of the rudder surface tube shaft 8 is rotatably connected to the bracket 4, and the bracket 4 is fixedly connected to the aircraft structure II 7; the other end of the rocker arm 2 is hinged to the pull rod 5; the lock slot support 1 is fixedly arranged at the waist of the rocker arm 2, and a lock hole 10 is arranged on the lock slot support 1; the lock mechanism 3 is fixedly installed on the aircraft structure I 6 through a fastener, and a lock pin 11 of the lock mechanism 3 can be inserted into the lock hole 10.

[0018] When the aircraft control system rod moves, the control system drives the rocker arm 2 to rotate through the pull rod 5, and then drives the control surface tube shaft 8 to rotate through the rocker arm 2, and finally drives the control surface 9 to deflect. When the control surface 9 deflects downward to the limit position, the lock pin 11 of the lock mechanism 3 is aligned with the lock hole 10 of the lock slot support 1. At this time, the lock mechanism 3 drives the lock pin 11 to insert into the lock hole 10. Since the lock mechanism 3 is fixedly connected to the aircraft structure Ⅰ6, the rotation of the rocker arm 2 is restricted, so the control surface 9 stops rotating and remains in the current position.

[0019] The aforementioned locking hole 10 is in a tapered shape, so that the locking pin 11 can slide into the locking hole 10 along the tapered surface.

[0020] The edge of the aforementioned lock hole 10 is provided with a guide lip 12; the guide lip 12 extends a guide arc 14 along the deflection direction of the rocker arm 2, and the center of the guide arc 14 coincides with the rotation axis of the rocker arm 2. Through this structure, even if the lock pin 11 is not aligned with the lock hole 10 when extended, the lock pin 11 can be moved along the guide lip 12 or the guide arc 14 into the lock hole 10 by operating the system rod to complete the aircraft control surface locking function.

[0021] A circular chamfer 13 is provided between the aforementioned hole and the guide lip 12 to facilitate the locking pin 11 to slide into the locking hole 10 .

[0022] The aforementioned lock hole 10 is 13 mm deep.

Claims

1. An aircraft control surface locking mechanism, characterized in that: The invention comprises a locking groove support (1), a rocker arm (2), and a locking mechanism (3); one end of the rocker arm (2) is fixedly connected to a rudder tube shaft (8), one end of the rudder tube shaft (8) is fixedly connected to a rudder (9), the other end of the rudder tube shaft (8) is rotatably connected to a bracket (4), and the bracket (4) is fixedly connected to an aircraft structure II (7); the other end of the rocker arm (2) is hinged to a pull rod (5); the locking groove support (1) is fixedly arranged at the waist of the rocker arm (2), and a locking hole (10) is arranged on the locking groove support (1); the locking mechanism (3) is fixedly installed on the aircraft structure I (6) via a fastener, and a locking pin (11) of the locking mechanism (3) can be inserted into the locking hole (10).

2. The aircraft control surface locking mechanism according to claim 1, characterized in that: The lock hole (10) is in the shape of a cone hole.

3. The aircraft control surface locking mechanism according to claim 1, characterized in that: The edge of the opening of the lock hole (10) is provided with a guide lip (12).

4. The aircraft control surface locking mechanism according to claim 3, characterized in that: A circular chamfer (13) is provided between the hole and the guide lip (12).

5. The aircraft control surface locking mechanism according to claim 3, characterized in that: The guide lip (12) extends a guide arc (14) along the deflection direction of the rocker arm (2), and the center of the guide arc (14) coincides with the rotation axis of the rocker arm (2).

6. The aircraft control surface locking mechanism according to claim 1, characterized in that: The lock hole (10) is 13 mm deep.

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