Transverse control device for control surface of airplane
By adopting a lateral arrangement structure of angular rocker arms and levers on the aircraft control surfaces, the transmission angle is optimized, solving the problem of limited space and large deflection angle in the design of control surfaces for small and medium-sized aircraft. This achieves the requirement of large deflection angle of control surfaces in a confined space, reduces actuator load, increases control torque, and ensures aircraft safety.
Patent Information
- Application Number
- CN202423215916.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-25
- Publication Date
- 2025-12-23
- Estimated Expiration
- 2034-12-25
AI Technical Summary
Existing aircraft control surface actuators are difficult to arrange in small and medium-sized aircraft where space is limited and large deflection angles are required. This leads to an increase in actuator length, which fails to meet control torque requirements and affects aircraft safety.
It adopts a transverse arrangement structure of angular rocker arm and tie rod. The angular rocker arm is hinged to the control surface, and the control surface is deflected by the tie rod. The connection point of the angular rocker arm with the rocker arm bracket, actuator, and tie rod is adjustable, and the transmission angle is optimized to reduce the size of the actuator and the load.
It achieves a control surface arrangement that meets the requirements of large deflection angles in a confined design space, reduces actuator load, reduces structural weight, increases control torque, and ensures aircraft safety.
Smart Images
Figure CN223702935U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application belongs to the technical field of aircraft control surface structure, and particularly relates to a horizontal control device of an aircraft control surface. BACKGROUND
[0002] The aircraft control surface is generally controlled by an actuator to realize the up and down deflection of the control surface, thereby providing the aircraft with rolling, yawing and pitching maneuver. The current aircraft control surface actuator is arranged longitudinally, that is, the actuator axis is arranged in a plane parallel to the rotation plane of the aircraft control surface, one end of the actuator is hinged to the aircraft 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 aircraft structure is narrow, and the suspension and control structure of the control surface is difficult to design. Considering the case of engine failure, the control surface is required to have a larger up and down deflection angle to provide sufficient control moment for the aircraft to ensure the safety of the aircraft. The stroke of the actuator is further lengthened, which leads to a significant increase in the length of the actuator, and the current arrangement form of the control surface actuator cannot be realized. SUMMARY
[0004] In order to solve the above problems, the present application provides a horizontal control device of an aircraft control surface, comprising:
[0005] an angle rocker, an actuator, a pull rod and a control surface.
[0006] The middle part of the angle rocker is hinged to the aircraft body, one end of the angle rocker is hinged to the output shaft of the actuator, the other end of the angle rocker 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 aircraft body. The extension of the actuator drives the rotation of the angle rocker, and the angle rocker drives the swing of the control surface through the pull rod. The rotation axis of the angle rocker (1) is perpendicular to the rotation axis of the control surface (13).
[0007] Preferably, the angle rocker is divided into a first rocker and a second rocker by a hinge hole hinged to the aircraft body, and the included angle between the first rocker and the second rocker is adapted to the transmission angle of the actuator and the angle rocker, so that the transmission angle of the actuator and the angle rocker is optimal under the conditions of considering the neutral, up and down deflection of the control surface, that is, the force transmission efficiency is the highest.
[0008] Preferably, the included angle between the first rocker and the second rocker is adapted to the transmission angle of the angle rocker and the pull rod, so that the transmission angle of the angle rocker and the pull rod is optimal under the conditions of considering the neutral, up and down deflection of the control surface, and the force transmission efficiency is the highest.
[0009] Preferably, the first rocker and the second rocker are of a split structure, and the included angle between the first rocker and the second rocker 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 a plurality of positioning holes distributed circumferentially around the hinge center, and a 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 a plurality of connecting holes along the length direction, which can be used to adjust the length and proportion relationship of the first rocker arm and the second rocker arm, and control the movement speed and load size relationship of the actuator and the pull rod in the deflection of the control surface.
[0012] Preferably, the hinge point of the first rocker arm and the second rocker arm and the hinge point of the angular rocker arm and the machine body are coaxial.
[0013] Preferably, the middle part of the angular rocker arm is connected to a rocker arm support fixed to the machine body by a pin shaft.
[0014] Preferably, the control surface is connected to the suspension support by a connecting bolt, and the control surface can be deflected up and down around the axis of the connecting bolt.
[0015] Preferably, the angular rocker arm rotates counterclockwise to push the control surface downward by the pull rod, and when the actuator is retracted from the initial state to pull the angular rocker arm, the angular rocker arm rotates clockwise to pull the control surface upward by the pull rod. The hinge point of the angular rocker arm (1) and the pull rod (5) and the hinge point of the angular rocker arm (1) and the machine body both have joint bearings.
[0016] The advantages of the present application include: first, the aircraft control surface using the lateral control device can meet the control surface control suspension arrangement requirements under the conditions of small design space and large deflection angle; the relative position relationship of the connection points of the angular rocker arm and the rocker arm support, the connection points of the angular rocker arm and the actuator, and the connection points of the angular rocker arm and the pull rod 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 structure weight; second, the angular rocker arm with adjustable included angle can be adjusted to adapt to various assembly spaces to achieve the optimal transmission angle. BRIEF DESCRIPTION OF DRAWINGS
[0017] Figure 1 is a schematic view of an aircraft control surface lateral control device according to an embodiment of the present application;
[0018] Among them: angular rocker arm-1, rocker arm support-2, pin shaft-3, actuator-4, pull rod-5, actuator connecting support-6, suspension support-7, connecting bolt-8, connecting bolt-9, connecting bolt-10, connecting bolt-11, connecting bolt-12 and control surface-13.
[0019] Figure 2A schematic diagram of an upper deflection of a control surface of a lateral control device of an aircraft control surface according to an embodiment of the application;
[0020] Figure 3 A schematic diagram of a lower deflection of a control surface of a lateral control device of an aircraft control surface according to an embodiment of the application.
[0021] Figure 4 A schematic diagram of an angular rocker arm according to an embodiment of the application. DETAILED DESCRIPTION
[0022] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.
[0023] In addition, it should be further noted that, unless otherwise explicitly specified and limited, the terms such as "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the terms in the present application according to the specific circumstances.
[0024] As Figures 1-4As shown, the aircraft control surface lateral control device can include: an angle-shaped rocker arm 1, a rocker arm support 2, a pin shaft 3, an actuator 4, a pull rod 5, an actuator connecting support 6, a suspension support arm 7, connecting bolts 8, 9, 10, 11, 12, and a control surface 13. The angle-shaped rocker arm is connected to the rocker arm support 2 fixed to the aircraft structure by the pin shaft 3, and the angle-shaped rocker arm 1 can rotate clockwise or counterclockwise around the axis of the pin shaft 3. One end of the angle-shaped rocker arm 1 is hingedly connected to the pull rod 5 by the connecting bolt 8, and the other end is hingedly connected to the actuator 4 by the connecting bolt 9. The pull rod 5 is hingedly connected to the control surface 13 by the connecting bolt 10. The actuator 4 is hingedly connected to the actuator connecting support 6 by the connecting bolt 12. The control surface 13 is connected to the suspension support arm 7 by the connecting bolt 11, and the control surface 13 can deflect up and down around the axis of the connecting bolt 11. The rotation axis of the angle-shaped rocker arm 1 is perpendicular to the rotation axis of the control surface 13, so that the angle-shaped rocker arm 1, the rocker arm support 2, the pin shaft 3, the actuator 4, the pull rod 5, the actuator connecting support 6, and the suspension support arm 7 are arranged laterally, i.e., in a plane perpendicular to the movement plane of the control surface 13, thereby reducing the longitudinal space requirement.
[0025] In some embodiments, the connection points of the angle-shaped rocker arm 1 and the rocker arm support 2, the connection points of the angle-shaped rocker arm 1 and the actuator 4, and the connection points of the angle-shaped rocker arm 1 and the pull rod 5 can be on a straight line.
[0026] In some embodiments, the first rocker arm and the second rocker arm are in a split structure, and the included angle between the first rocker arm and the second rocker arm is adjustable. The included angle between the first rocker arm and the second rocker arm is adapted to the transmission angle of the actuator 4 and the angle-shaped rocker arm 1, so that the transmission angle of the actuator 4 and the angle-shaped rocker arm 1 is minimized. The included angle between the first rocker arm and the second rocker arm is adapted to the transmission angle of the angle-shaped rocker arm 1 and the pull rod 5, so that the transmission angle of the angle-shaped rocker arm 1 and the pull rod 5 is minimized.
[0027] In an embodiment in which the first rocker arm and the second rocker arm are in a split structure with an adjustable included angle, the first rocker arm and the second rocker arm are hingedly connected. The first rocker arm and the second rocker arm have a plurality of positioning holes circumferentially distributed around the hinge center. A 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.
[0028] In another embodiment in which the first rocker arm and the second rocker arm are in a split structure with an adjustable included angle, the first rocker arm and the second rocker arm are both in a split combined structure and have a plurality of connection holes along the length direction. The connection holes 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 4 and the pull rod 5 in the deflection of the control surface.
[0029] The angle-shaped rocker arm with an adjustable included angle can be adapted to various assembly spaces to achieve the optimal transmission angle.
[0030] Through a large number of calculation analysis and test, the result proves that the aircraft control surface adopting the transverse control device can meet the control surface control suspension arrangement requirement under the condition of narrow design space and large deflection angle requirement; the relative position relationship of the three connection points of the connecting point of the angle rocker and the rocker support, the connecting point of the angle rocker and the actuator and the connecting point of the angle rocker and the pull rod can be designed according to the situation, the load on the actuator can be effectively reduced, the size of the actuator is reduced, and the purpose of reducing the structure weight is achieved.
[0031] The above merely provides a specific implementation of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A lateral control device for aircraft control surfaces, characterized in that, include: Angle rocker arm (1), actuator (4), lever (5), control surface (13); The angular rocker arm (1) is hinged to the machine body in the middle. One end of the rocker arm (1) 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. The angular rocker arm (1) pulls the control surface (13) to swing through the pull rod (5). The axis of rotation of the angular rocker arm (1) is perpendicular to the axis of rotation of the control surface (13).
2. The aircraft control surface lateral control device as described in 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 on the machine body. The included 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 the maximum force transmission efficiency while taking into account the neutral, upward and downward states of the control surface.
3. The aircraft control surface lateral control device as described in claim 1, characterized in that, The angle between the first rocker arm and the second rocker arm is adapted to the transmission angle of the angular rocker arm (1) and the pull rod (5), so that the transmission angle of the angular rocker arm (1) and the pull rod (5) achieves the maximum force transmission efficiency while taking into account the neutral, upward and downward states of the control surface.
4. The aircraft control surface lateral control device as described in claim 3, characterized in that, The first rocker arm and the second rocker arm are separate structures, and the angle between them is adjustable.
5. The aircraft control surface lateral control device as described in 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 multiple positioning holes distributed circumferentially 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 as described in claim 4, characterized in that, Both the first rocker arm and the second rocker arm are separate assembly structures and have multiple connection holes along their length. They can be used to adjust the length and proportional relationship of the first rocker arm and the second rocker arm, and to control the speed and load relationship of the actuator (4) and the lever (5) during the deflection of the control surface.
7. The aircraft control surface lateral control device as described in claim 5, characterized in that, The hinge point of the first rocker arm and the second rocker arm and the hinge point of the angle rocker arm (1) are coaxial with the hinge point of the machine body.
8. The aircraft control surface lateral control device as described in claim 1, characterized in that, The middle part of the angular rocker arm (1) is connected to the rocker arm bracket (2) fixed to the machine body by a pin (3).
9. The aircraft control surface lateral control device as described in claim 1, characterized in that, 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).
10. The aircraft control surface lateral control device as described in claim 1, characterized in that, The angular rocker arm (1) rotates counterclockwise and pushes the control surface (13) 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 and pulls the control surface (13) upward through the pull rod (5).
11. The aircraft control surface lateral control device as described in claim 1, characterized in that, The hinge joints between the angular rocker arm (1) and the pull rod (5) and between the angular rocker arm (1) and the machine body are equipped with spherical bearings.