Airplane rocker arm support assembly

Abstract

The utility model discloses an aircraft rocker arm support assembly. Comprising a support, a rocker arm, an input pull rod and an output pull rod, and the support is fixed to an aircraft structure and hinged to the position, close to the top, of the rocker arm; the input pull rod is hinged to the position, close to the middle, of the rocker arm, and the output pull rod is hinged to the position, close to the bottom, of the rocker arm. The connecting line of the hinge point close to the top and the hinge point close to the middle of the rocker is perpendicular to the axis of the input pull rod. A connecting line of a hinge point close to the top and a hinge point close to the bottom of the rocker arm is vertical to the axis of the output pull rod; hinge points, close to the top, the middle and the bottom, of the rocker arms are non-collinear. The utility model provides a method for quickly and accurately assembling the aircraft rocker arm support assembly and the pull rod, can prevent the pull rod and the rocker arm from being not connected in place, improves the error prevention capability of an aircraft system, and obtains an accurate control surface deflection angle.

Description

Technical Field

[0001] The utility model belongs to the technical field of flight control system design and relates to an aircraft rocker arm support assembly. Background Art

[0002] The aircraft control system is to transmit the pilot's control instructions, drive the control surface, and control the aircraft's flight attitude. According to the source of the instructions, it can be divided into manual control (which can be divided into main control system and auxiliary control system) and automatic control system. Among them, the main control system controls the aircraft's elevator, aileron and rudder control mechanism through the joystick / plate and pedals to control the aircraft's flight trajectory and attitude. As an important functional system of the aircraft, the design of the main control system is crucial, and it directly affects the flight safety of the aircraft.

[0003] Mechanical control systems generally include driver control devices, transmission devices, servo actuators, and artificial sense and trim devices. Rocker arm support components and tie rods are typical transmission devices, which are mainly used to transmit the driver's instructions and displacements. They are important components of mechanical control systems, and the length of the rocker arm directly affects the system transmission ratio.

[0004] If the rocker arm support assembly is connected incorrectly to the tie rod, it will not only affect the neutral position of the control system, but also affect the transmission ratio of the rudder control system, which will bring potential safety hazards to the aircraft flight. Therefore, it is very important to strictly control the accuracy of the connection between the aircraft's rocker arm and the tie rod. Summary of the invention

[0005] The purpose of the utility model is to provide an aircraft rocker arm support assembly. The utility model can provide an aircraft rocker arm support assembly and a method for quickly and accurately assembling a tie rod, which can prevent the tie rod rocker arm from being improperly connected, improve the error-proofing capability of the aircraft system, and obtain an accurate rudder surface deflection angle.

[0006] Technical solution. An aircraft rocker arm support assembly includes a support, a rocker arm, an input tie rod and an output tie rod, wherein the support is fixed to the aircraft structure, and the support is hinged to the position of the rocker arm near the top; the input tie rod and the output tie rod are arranged on both sides of the rocker arm, the input tie rod is hinged to the position of the rocker arm near the middle, and the output tie rod is hinged to the position of the rocker arm near the bottom; the line connecting the hinge point near the top of the rocker arm and the hinge point near the middle is perpendicular to the axis of the input tie rod; the line connecting the hinge point near the top of the rocker arm and the hinge point near the bottom is perpendicular to the axis of the output tie rod; the hinge points near the top, middle and bottom of the rocker arm are not collinear.

[0007] In the aforementioned aircraft rocker arm support assembly, the outer side of the rocker arm gradually becomes thinner from the middle to the bottom.

[0008] In the aforementioned aircraft rocker arm support assembly, the end of the bottom of the rocker arm is provided with a semicircular protrusion (6) protruding toward the rear of the aircraft.

[0009] In the aforementioned aircraft rocker arm support assembly, a groove is provided in the middle of the rocker arm, and the groove is a blind hole structure. After the input pull rod is inserted into the groove, it is hinged to the rocker arm.

[0010] In the aforementioned aircraft rocker arm support assembly, a notch is provided at the bottom of the rocker arm, and the output tie rod is inserted into the notch and is hinged to the rocker arm.

[0011] In the aforementioned aircraft rocker arm support assembly, the support is symmetrical along its own horizontal center plane, and the hinge point between the rocker arm and the support is on the horizontal center plane.

[0012] Beneficial Effects

[0013] The utility model provides an aircraft rocker arm support assembly, which can provide an aircraft rocker arm support assembly and a fast and accurate assembly method of a tie rod, can prevent the tie rod rocker arm from being incompletely connected, improve the error prevention capability of the aircraft system, and obtain an accurate rudder surface deflection angle. The utility model has a simple structure, low implementation difficulty, a short development cycle, convenient installation and adjustment, and good maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is the installation diagram of the aircraft rocker arm support assembly;

[0015] Figure 2 It is a three-dimensional diagram of the rocker arm;

[0016] Figure 3 This is a three-dimensional diagram of the support. DETAILED DESCRIPTION

[0017] Combined with the accompanying drawings, the utility model is described in detail:

[0018] Embodiment 1. An aircraft rocker arm support assembly, comprising: Figure 1-3 As shown, it includes a support 1, a rocker arm 2, an input rod 3 and an output rod 4, the support 1 is fixed on the aircraft structure 5, the support 1 is hinged to the rocker arm 2 near the top; the input rod 3 and the output rod 4 are arranged on both sides of the rocker arm 2, the input rod 3 is hinged to the rocker arm 2 near the middle, and the output rod 4 is hinged to the rocker arm 2 near the bottom; the line connecting the hinge point near the top and the hinge point near the middle of the rocker arm 2 is perpendicular to the axis of the input rod 3; the line connecting the hinge point near the top and the hinge point near the bottom of the rocker arm 2 is perpendicular to the axis of the output rod 4; the hinge points of the rocker arm 2 near the top, the middle and the bottom are not collinear.

[0019] The outer side of the aforementioned rocker arm 2 tapers gradually from the middle to the bottom, which is used to indicate the installation direction of the rocker arm to prevent reverse installation up and down.

[0020] The end of the bottom of the aforementioned rocker arm 2 is provided with a semicircular protrusion (6) protruding toward the rear of the aircraft, which is also used to indicate the installation direction of the rocker arm to prevent reverse installation.

[0021] The middle of the aforementioned rocker arm 2 is provided with a groove, which is a blind hole structure, and the input pull rod 3 is inserted into the groove and hinged with the rocker arm 2. The blind hole structure can prevent the output pull rod 4 from being inserted into the middle of the rocker arm 2, thereby preventing mis-assembly.

[0022] The bottom of the aforementioned rocker arm 2 is provided with a notch, and the output pull rod 4 is hinged to the rocker arm 2 after being inserted into the notch.

[0023] The aforementioned support 1 is symmetrical along its own horizontal center plane, and the hinge point between the rocker arm 2 and the support 1 is located on the horizontal center plane.

[0024] The rocker arm 2 is connected to the support 1 by bolts, and the rocker arm 2 can rotate around a central axis of the support 1. The support 1 is fixed to the aircraft structure 5 by bolts. When the aircraft control system lever (disc) or pedal moves, the input rod 3 moves forward and backward, driving the rocker arm 2 to swing forward and backward, and the rocker arm 2 drives the output rod 4 to move forward and backward.

Claims

1. An aircraft rocker arm support assembly, characterized in that: The invention comprises a support (1), a rocker arm (2), an input tie rod (3) and an output tie rod (4), wherein the support (1) is fixed on an aircraft structure (5), and the support (1) is hinged to a position near the top of the rocker arm (2); the input tie rod (3) and the output tie rod (4) are arranged on both sides of the rocker arm (2), the input tie rod (3) is hinged to a position near the middle of the rocker arm (2), and the output tie rod (4) is hinged to a position near the bottom of the rocker arm (2); a line connecting a hinge point near the top of the rocker arm (2) and a hinge point near the middle is perpendicular to the axis of the input tie rod (3); a line connecting a hinge point near the top of the rocker arm (2) and a hinge point near the bottom is perpendicular to the axis of the output tie rod (4); and hinge points near the top, middle and bottom of the rocker arm (2) are not collinear.

2. The aircraft rocker arm support assembly according to claim 1, characterized in that: The outer side of the rocker arm (2) gradually tapers from the middle to the bottom.

3. The aircraft rocker arm support assembly according to claim 1, characterized in that: The end of the bottom of the rocker arm (2) is provided with a semicircular protrusion (6) protruding toward the rear of the aircraft.

4. The aircraft rocker arm support assembly according to claim 1, characterized in that: A groove is provided in the middle of the rocker arm (2), and the groove is a blind hole structure. After the input pull rod (3) is inserted into the groove, it is hinged to the rocker arm (2).

5. The aircraft rocker arm support assembly according to claim 1, characterized in that: A notch is provided at the bottom of the rocker arm (2), and the output pull rod (4) is hinged to the rocker arm (2) after being inserted into the notch.

6. The aircraft rocker arm support assembly according to claim 1, characterized in that: The support (1) is symmetrical along its own horizontal center plane, and the hinge point between the rocker arm (2) and the support (1) is located on the horizontal center plane.

Images