A rudder surface deflection actuator with adjustable deflection angle

Abstract

The present invention discloses a deflection actuator for a rudder surface with adjustable deflection angle, comprising a rudder surface, a rudder shaft, a clamping claw, an eccentric cam, a motor, and a fixing seat. The rotation speed of the motor is changed by controlling a motor control signal, thereby changing the deflection frequency of the rudder surface, and the entire device does not need to be changed. In the present invention, the angle between the small cylinder on the eccentric cam and the plane is fixed, and the maximum deflection angle of the rudder surface can be changed by replacing the eccentric cam with different angles, thereby increasing the application range of the device, increasing the flexibility of use of the device, reducing the manufacturing difficulty, and making it more practical in engineering.

Description

Technical Field

[0001] The invention belongs to the technical field of high-speed wind tunnel test equipment, in particular to a rudder surface deflection execution device capable of adjusting a deflection angle. Background Art

[0002] For an aircraft to complete a turn, the pilot needs to make corresponding movements on the three axes of the aircraft to complete the turn. The aircraft's center of gravity is taken as the reference point, and three axes are divided, and the changes are made accordingly, namely pitch, roll, and yaw. The rotation of the nose / tail up and down with the fuselage's horizontal axis as the center is called pitch; the rotation of the wings up and down with the fuselage's longitudinal axis as the center is called roll; and the left and right rotation of the nose / tail with the fuselage's center of gravity vertical line as the center is called yaw.

[0003] Conventional aircraft move in space by coordinated movements of three axes. When the aircraft needs to pitch (climb or descend), the elevator moves up and down to disturb the airflow above and below the fuselage, generate a pitching moment, and change the up and down angle of the nose / tail. When the aircraft needs to roll (tilt), the ailerons behind the wings on both sides make opposite movements to change the lift of the wings on both sides, generate a rolling moment, and rotate the fuselage. When the aircraft needs to yaw (turn), the rudder turns left or right to disturb the airflow on the left and right of the fuselage, generate a yaw moment, and change the direction of the nose / tail. Through these three sets of control surfaces, the aircraft can turn in any direction. Of course, to complete a smooth turn, the pilot must operate these control surfaces at the same time to make the aircraft change direction on the same horizontal plane. The main control surfaces are composed of ailerons, elevators, and rudders. Every tiny parameter on the main control surfaces directly affects the flight attitude. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a rudder surface deflection execution device with adjustable deflection angle, which can accurately control the frequency of rudder surface deflection so that the rudder surface deflection can stabilize the rotation speed. At the same time, by replacing the deflection cam in the deflection execution device, the maximum angle of the rudder surface deflection can be changed, thereby increasing the application range of the device.

[0005] In order to achieve the above-mentioned invention object, the present invention adopts the following technical solutions:

[0006] A deflection actuator for a rudder surface with adjustable deflection angle comprises a rudder surface, a rudder shaft, a clamping claw, an eccentric cam, a motor and a fixing seat; the clamping claw is fixedly mounted on the fixing seat, and the eccentric cam is connected to the motor shaft of the motor; the rudder surface is mounted at the end of the rudder shaft; the clamping claw is fixedly connected to the rudder shaft; the clamping claw and the eccentric cam are constrained by line contact. The angle between the small cylinder on the eccentric cam and the plane is fixed, and there are multiple eccentric cams with different angles for replacement.

[0007] Furthermore, the eccentric cam is threadedly connected to the motor shaft.

[0008] Furthermore, the rudder surface and the rudder shaft are fixed using screws and nuts, and the rudder shaft and the claws are fixed using screws.

[0009] Furthermore, the rear half of the eccentric cam rotates synchronously with the motor shaft, and the small cylinder in the front half of the eccentric cam rotates around the same point.

[0010] Furthermore, the eccentric cam rotating shaft and the claw rotating shaft intersect at one point, and at the same time, the point around which the front half of the eccentric cam revolves is the intersection point.

[0011] Furthermore, the motor is fixed to the fixing seat by screws, and the motor is fixed on the fixing seat.

[0012] According to the above technical scheme, the working principle of the rudder surface deflection actuator is as follows: the entire device is driven by an inner rotor motor, and the motor center axis is the fixed axis of the device. The motor rotor housing is fixedly connected to the fixed seat, and the fixed frequency rotation of the rudder surface is achieved through the rotation of the inner rotor of the motor. An eccentric cam is connected to one end of the motor shaft, and the relative movement of the claw and the eccentric cam is used to achieve the swing of the claw around the fixed axis. The oscillation angle of the rudder surface can be adjusted by the offset distance between the eccentric cam and the central axis. Different eccentric distances can achieve corresponding fixed rudder surface oscillation angles, and the adjustment of its oscillation frequency can be achieved by changing the speed of the drive motor.

[0013] The rudder surface deflection actuator with adjustable deflection angle of the present invention has high stability, stable rudder surface deflection, stable maximum angle of rudder surface deflection, and constant frequency of rudder surface deflection. The rudder surface deflection actuator with adjustable deflection angle of the present invention is not only accurate and convenient to control, but also has the advantages of good rigidity and simple manufacturing, is not prone to force deformation, and has long-term reliability and stability. The mechanism for controlling the deflection of the rudder surface will not be ablated, has a long service life, has low requirements on the heat resistance of the material, and has high stability and reliability in long-term operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of an embodiment of a high-speed wind tunnel rotating model synchronous test mechanism of the present invention;

[0015] In the attached drawings: 1-rudder surface, 2-rudder shaft, 3-claw, 4-eccentric cam, 5-motor, 6-fixed seat. DETAILED DESCRIPTION

[0016] In conjunction with the accompanying drawings, a rudder surface deflection actuator with adjustable deflection angle proposed in the present invention is described in detail below. In the description of the present invention, it should be understood that the terms "left side", "right side", "upper part", "lower part", "bottom" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and "first", "second" and the like do not indicate the importance of the components, and therefore cannot be understood as limitations on the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the scope of protection of the present invention.

[0017] like Figure 1 As shown, the rudder surface deflection actuator with adjustable deflection angle of the present invention includes a rudder surface 1, a rotating shaft 2, a clamping claw 3, an eccentric cam 4, a motor 5, and a fixing seat 6.

[0018] The whole device is driven by an inner rotor motor 5, and the central axis of the motor is the fixed axis of the device. The housing of the motor 5 is fixedly connected to the fixed seat 6, and the fixed frequency rotation of the rudder surface 1 is realized by the rotation of the inner rotor of the motor 5. An eccentric cam 4 is connected to one end of the fixed axis, and the relative movement of the claw 3 and the eccentric cam 4 is used to realize the swing of the claw 3 around the rudder shaft 2. The oscillation angle of the rudder surface 1 can be adjusted by the offset distance between the eccentric cam 4 and the central axis. Different eccentric distances can achieve corresponding fixed oscillation angles of the rudder surface 1, and the adjustment of its oscillation frequency can be achieved by changing the rotation speed of the driving motor 6.

[0019] Based on the description of the preferred embodiments of the present invention, it should be clear that the present invention defined by the attached claims is not limited to the specific details set forth in the above description, and many obvious changes to the present invention that do not depart from the spirit or scope of the present invention may also achieve the purpose of the present invention.

Claims

1. A rudder surface deflection actuator with adjustable deflection angle, characterized in that: It includes a projectile model shell, a rudder surface, a rudder shaft, a claw, an eccentric cam, a motor and a support shaft; the motor is installed inside the projectile model shell, the end of the motor is fixed on the support shaft, and the eccentric cam is connected to the motor shaft of the motor; the rudder shaft is longitudinally inserted into the projectile model shell, and the rudder surface is installed at the end of the rudder shaft; the claw is located inside the projectile model shell, and the claw is fixedly connected to the rudder shaft; the claw and the eccentric cam are constrained by line contact; the angle between the small cylinder on the eccentric cam and the plane is fixed, and the eccentric cam is replaced by other eccentric cams, and the angle between the small cylinder of the other eccentric cam and the plane is different from that of the eccentric cam; the rear half of the eccentric cam rotates synchronously with the motor shaft, and the small cylinder of the front half of the eccentric cam rotates around the same point.

2. The rudder surface deflection actuator with adjustable deflection angle according to claim 1, characterized in that: The motor center axis is the fixed axis of the projectile model shell, and the motor shell is fixedly connected to the inner wall of the projectile model shell.

3. The rudder surface deflection actuator with adjustable deflection angle according to claim 1, characterized in that: The eccentric cam rotating shaft and the claw rotating shaft intersect at one point, and at the same time, the point around which the front half of the eccentric cam revolves is the point where the eccentric cam rotating shaft and the claw rotating shaft intersect.

4. The rudder surface deflection actuator with adjustable deflection angle according to claim 1, characterized in that: The frequency of the deflection of the rudder surface is the same as the frequency of the rotation of the shell of the missile model, and the two are synchronized.

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