Transverse control device for control surface of airplane

Abstract

The invention belongs to the technical field of aircraft control surface structures, and particularly relates to an aircraft control surface transverse control device which comprises an angle rocker arm, an actuator, a pull rod and a control surface. One end of the angle-shaped rocker arm is hinged to an output shaft of the actuator, the other end of the angle-shaped rocker arm is hinged to the pull rod, the pull rod is hinged to the upper end of the control surface, and the lower end of the control surface is hinged to the machine body; the actuator stretches out and draws back to drive the angle-shaped rocker arm to rotate, and the angle-shaped rocker arm pulls the control surface to swing through the pull rod. The aircraft control surface adopting the transverse control device can meet the control suspension arrangement requirements of the control surface under the conditions that the design space is narrow and the deflection angle is large.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft control surface structures, and in particular relates to a lateral control device for an aircraft control surface. Background Art

[0002] Aircraft control surfaces are generally controlled by actuators to achieve the up and down deflection function of the control surfaces, thereby providing roll, yaw and pitch maneuvers for aircraft flight. Currently, existing aircraft control surface actuators are all arranged longitudinally, that is, the actuation axis of the actuator is arranged in a plane parallel to the rotation plane of the aircraft control surface, one end of the actuator is hinged to the fuselage structure, and the other end is hinged to the control joint of the control surface.

[0003] However, for small and medium-sized aircraft, the design space between the control surface and the fuselage structure is narrow, and the control surface suspension and control structure design are relatively difficult. Considering the event of an engine failure, the control surface is required to have a larger up and down deflection angle to provide the aircraft with sufficient control torque to ensure the safety of the aircraft. The stroke of the actuator will be further lengthened, resulting in a significant increase in the length of the actuator, which cannot be achieved with the existing control surface actuator arrangement. Summary of the invention

[0004] In order to solve the above problems, the present application provides an aircraft control surface lateral control device, comprising:

[0005] Angle rocker arms, actuators, tie rods, control surfaces;

[0006] The middle part of the angular rocker arm is hinged on the machine body, one end of which is hinged on the output shaft of the actuator, and the other end is hinged on the pull rod, the pull rod is hinged on the upper end of the control surface, and the lower end of the control surface is hinged on the machine body; the actuator's extension and retraction drives the angular rocker arm to rotate, and the angular rocker arm pulls the control surface to swing through the pull rod. The rotation axis of the angular rocker arm (1) is perpendicular to the rotation axis of the control surface (13).

[0007] Preferably, the angular rocker arm is divided into a first rocker arm and a second rocker arm by a hinge hole hinged on the body, and the angle between the first rocker arm and the second rocker arm is adapted to the transmission angle between the actuator and the angular rocker arm, so that the transmission angle between the actuator and the angular rocker arm reaches the optimal state while taking into account the neutral, upward and downward deflection of the control surface, that is, the force transmission efficiency is the highest.

[0008] Preferably, the angle between the first rocker arm and the second rocker arm is adapted to the transmission angle of the angle rocker arm and the pull rod, so that the transmission angle of the angle rocker arm and the pull rod reaches the optimal state while taking into account the neutral, upward and downward deflection of the control surface, and the force transmission efficiency is the highest.

[0009] Preferably, the first rocker arm and the second rocker arm are separate structures, and the angle between them is adjustable.

[0010] Preferably, the first rocker arm and the second rocker arm are connected by a hinge, and the first rocker arm and the second rocker arm have multiple positioning holes distributed circumferentially around the hinge center, and the positioning pin passes through the positioning holes of the first rocker arm and the second rocker arm to fix the first rocker arm and the second rocker arm at a preset angle.

[0011] Preferably, the first rocker arm and the second rocker arm are both split combined structures and have multiple connecting holes along the length direction, which can be used to adjust the length and proportional relationship of the first rocker arm and the second rocker arm, and to control the movement speed and load size relationship of the actuator and the pull rod during the deflection of the control surface.

[0012] Preferably, the hinge point between the first rocker arm and the second rocker arm and the hinge point between the angle rocker arm and the machine body are coaxial.

[0013] Preferably, the middle portion of the angle rocker arm is connected to a rocker arm bracket fixed to the machine body by a pin.

[0014] Preferably, the aircraft control surface lateral control device according to claim 1 is characterized in that:

[0015] Preferably, the control surface is connected to the suspension arm by connecting bolts, and the control surface can deflect up and down around the axis of the connecting bolts.

[0016] Preferably, the angle rocker arm rotates counterclockwise, and the control surface is pushed downward by the pull rod, and when the actuator retracts from the initial state to pull the angle rocker arm, the angle rocker arm rotates clockwise, and the control surface is pulled upward by the pull rod. The hinged joints between the angle rocker arm (1) and the pull rod (5) and the hinged joints between the angle rocker arm (1) and the machine body are both provided with joint bearings.

[0017] The advantages of the present application include: first, the aircraft control surface using the lateral control device can meet the control surface control suspension layout requirements under a narrow design space and a large deflection angle requirement; the connection points of the angle rocker arm and the rocker arm bracket, the connection points of the angle rocker arm and the actuator, and the connection points of the angle rocker arm and the pull rod, the relative position relationship of these three connection points can be designed according to the situation, which can effectively reduce the load on the actuator, reduce the size of the actuator, and achieve the purpose of reducing the weight of the structure; secondly, the use of an angle rocker arm with an adjustable angle can adapt to and adjust various assembly spaces to achieve the optimal transmission angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of a lateral control device for an aircraft control surface according to an embodiment of the present invention;

[0019] Among them: angle rocker arm-1, rocker arm bracket-2, pin shaft-3, actuator-4, pull rod-5, actuator connecting bracket-6, suspension arm-7, connecting bolt-8, connecting bolt-9, connecting bolt-10, connecting bolt-11, connecting bolt-12 and control surface-13.

[0020] Figure 2 A schematic diagram of a control surface of a lateral control device for an aircraft control surface according to an embodiment of the present invention;

[0021] Figure 3 A schematic diagram of a control surface downward deflection of a lateral control device for an aircraft control surface according to an embodiment of the present invention.

[0022] Figure 4 Schematic diagram of an angular rocker arm according to an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0024] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0025] like Figure 1-Figure 4As shown, a lateral control device for an aircraft control surface may include: an angle rocker arm 1, a rocker arm bracket 2, a pin shaft 3, an actuator 4, a tie rod 5, an actuator connecting bracket 6, a suspension arm 7, a connecting bolt 8, a connecting bolt 9, a connecting bolt 10, a connecting bolt 11, a connecting bolt 12 and a control surface 13, etc. Among them: the angle rocker arm is connected to the rocker arm bracket 2 fixed to the body structure by a pin shaft 3, the angle rocker arm 1 can rotate clockwise or counterclockwise around the axis of the pin shaft 3, one end of the angle rocker arm 1 is hingedly connected to the tie rod 5 by a connecting bolt 8, and the other end is hingedly connected to the actuator 4 by a connecting bolt 9, the tie rod 5 is hingedly connected to the control surface 13 by a connecting bolt 10, the actuator 4 is hingedly connected to the actuator connecting bracket 6 by a connecting bolt 12, the control surface 13 is connected to the suspension arm 7 by a connecting bolt 11, and the control surface 13 can deflect up and down around the axis of the connecting bolt 11. Among them, the rotating axis of the angle rocker arm 1 is perpendicular to the rotating axis of the control surface 13, so that the angle rocker arm 1, rocker arm bracket 2, pin shaft 3, actuator 4, pull rod 5, actuator connecting bracket 6, and suspension arm 7 are arranged horizontally, that is, they are in a plane perpendicular to the movement plane of the control surface 13, reducing the longitudinal space requirement.

[0026] In some embodiments, the connection point between the angle rocker arm 1 and the rocker arm bracket 2, the connection point between the angle rocker arm 1 and the actuator 4, and the connection point between the angle rocker arm 1 and the pull rod 5 can be on a straight line.

[0027] In some embodiments, the first rocker arm and the second rocker arm are split structures, and the angle between them is adjustable. The angle between the first rocker arm and the second rocker arm is adapted to the transmission angle between the actuator 4 and the angle rocker arm 1, so that the transmission angle between the actuator 4 and the angle rocker arm 1 is minimized. The angle between the first rocker arm and the second rocker arm is adapted to the transmission angle between the angle rocker arm 1 and the pull rod 5, so that the transmission angle between the angle rocker arm 1 and the pull rod 5 is minimized.

[0028] In an embodiment in which the first rocker arm and the second rocker arm are split structures with an adjustable angle, the first rocker arm and the second rocker arm are connected by a hinge, and the first rocker arm and the second rocker arm have multiple positioning holes distributed circumferentially around the hinge center, and the positioning pins pass through the positioning holes of the first rocker arm and the second rocker arm to fix the first rocker arm and the second rocker arm at a preset angle.

[0029] In some other embodiments in which the first rocker arm and the second rocker arm are split structures with adjustable angles, the first rocker arm and the second rocker arm are both split combined structures and have multiple connecting holes along the length direction, which can be used to adjust the length and proportional relationship of the first rocker arm and the second rocker arm, and are used to control the movement speed and load size relationship of the actuator (4) and the pull rod (5) during the deflection of the control surface.

[0030] The angle-type rocker arm with adjustable angle can be adapted to various assembly spaces to achieve the optimal transmission angle.

[0031] After a large amount of calculation analysis and experiments, the results show that the aircraft control surface using this lateral control device can meet the control surface control suspension layout requirements under the conditions of narrow design space and large deflection angle requirements; the connection points of the angle rocker arm and the rocker arm bracket, the connection points of the angle rocker arm and the actuator, and the connection points of the angle rocker arm and the pull rod, the relative position relationship of these three connection points can be designed according to the situation, which can effectively reduce the load on the actuator, reduce the size of the actuator, and achieve the purpose of reducing the weight of the structure.

[0032] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A lateral control device for an aircraft control surface, characterized in that: include: Angle rocker arm (1), actuator (4), tie rod (5), control surface (13); The middle part of the angular rocker arm (1) is hinged on the machine body, one end of which is hinged to the output shaft of the actuator (4), and the other end is hinged to the pull rod (5), the pull rod (5) is hinged to the upper end of the control surface (13), and the lower end of the control surface (13) is hinged to the machine body; the extension and retraction of the actuator (4) drives the angular rocker arm (1) to rotate, and the angular rocker arm (1) pulls the control surface (13) to swing through the pull rod (5), wherein the rotation axis of the angular rocker arm (1) is perpendicular to the rotation axis of the control surface (13).

2. The aircraft control surface lateral control device according to claim 1, characterized in that: in, The angle rocker arm (1) is divided into a first rocker arm and a second rocker arm by a hinge hole hinged on the machine body, and the angle between the first rocker arm and the second rocker arm is adapted to the transmission angle between the actuator (4) and the angle rocker arm (1), so that the transmission angle between the actuator (4) and the angle rocker arm (1) achieves maximum force transmission efficiency while taking into account the control surface neutral, upward deflection and downward deflection states.

3. The aircraft control surface lateral control device according to claim 1, characterized in that: The included angle between the first rocker arm and the second rocker arm is adapted to the transmission angle between the angle rocker arm (1) and the pull rod (5), so that the transmission angle between the angle rocker arm (1) and the pull rod (5) achieves maximum force transmission efficiency while taking into account the neutral, upward and downward deflection states of the control surface.

4. The aircraft control surface lateral control device according to claim 3, characterized in that: The first rocker arm and the second rocker arm are split structures, and the angle between them is adjustable.

5. The aircraft control surface lateral control device according to claim 4, characterized in that: The first rocker arm and the second rocker arm are connected by a hinge. The first rocker arm and the second rocker arm have a plurality of circumferentially distributed positioning holes around the hinge center. The positioning pin passes through the positioning holes of the first rocker arm and the second rocker arm to fix the first rocker arm and the second rocker arm at a preset angle.

6. The aircraft control surface lateral control device according to claim 4, characterized in that: The first rocker arm and the second rocker arm are both split assembly structures and have a plurality of connection holes along the length direction, which can be used to adjust the length and proportional relationship of the first rocker arm and the second rocker arm, and are used to control the movement speed and load size relationship of the actuator (4) and the pull rod (5) during the deflection of the control surface.

7. The aircraft control surface lateral control device according to claim 5, characterized in that: The hinge point between the first rocker arm and the second rocker arm and the hinge point between the angle rocker arm (1) and the machine body are coaxial.

8. The aircraft control surface lateral control device according to claim 1, characterized in that: The middle part of the angle rocker arm (1) is connected to a rocker arm bracket (2) fixed to the machine body by means of a pin shaft (3).

9. The aircraft control surface lateral control device according to claim 1, characterized in that: The control surface (13) is connected to the suspension support arm (7) by means of a connecting bolt (11), and the control surface (13) can deflect upward and downward around the axis of the connecting bolt (11).

10. The aircraft control surface lateral control device according to claim 1, characterized in that: The angular rocker arm (1) rotates counterclockwise, pushing the control surface (13) to deflect downward through the pull rod (5); when the actuator (4) retracts from the initial state to pull the angular rocker arm (1), the angular rocker arm (1) rotates clockwise, pulling the control surface (13) to deflect upward through the pull rod (5).

11. The aircraft control surface lateral control device according to claim 1, characterized in that: The hinged joints between the angle rocker arm (1) and the pull rod (5) and the hinged joints between the angle rocker arm (1) and the machine body are both provided with joint bearings.

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