A fin control mechanism with variable transmission angle

Abstract

The present invention provides a tail control mechanism with a variable transmission angle, which relates to the field of aviation. It includes a tilt shaft, a tilt rocker arm, a cross control rocker arm, a Y-shaped adapter, a tilt actuator, and a deflection actuator. The tilt shaft is supported on the front and rear fuselage frames, and the tilt shaft is fixedly connected to the starting end of the tilt rocker arm. Driven by the tilt actuator, the tilt shaft and the tilt rocker arm rotate around the tail tilt axis. The deflection actuator is connected to the cross control rocker arm, and the cross control rocker arm is rotatably connected to a support fixed on the fuselage frame and can rotate around the rocker arm axis of the cross control rocker arm. The cross control rocker arm and the Y-shaped adapter are hinged together by a connecting shaft. The Y-shaped adapter is connected to the tail through hinge points on the tail main beam and the tail beam partition.

Description

Technical Field

[0001] The present invention relates to the field of aviation, and is mainly used for a full-motion V-tail control mechanism of an intelligent variant aircraft. Background Art

[0002] The tail is a critical component mounted at the rear of an aircraft, providing stability and control. Traditional fighter jets are typically equipped with both a horizontal stabilizer and a vertical stabilizer. The horizontal stabilizer helps restore the aircraft to its original attitude when subjected to various disturbances (such as gusts of wind) and deviates from its original position, thus ensuring longitudinal stability. The horizontal stabilizer also serves as a crucial trim control surface, used to achieve longitudinal trim and provide the control torque for maneuvers such as pitch and roll. The vertical stabilizer also performs a similar function, ensuring directional stability.

[0003] In current engineering applications, there is a lack of mechanisms that can realize a fully moving V-tail, and the mechanisms are also relatively complex. Summary of the Invention

[0004] The purpose of the present invention is to provide a fully movable tail fin control system capable of solving the tilt and yaw motion of the V-tail. This control system not only realizes the tilt and yaw motion of the V-tail, but also reduces the space requirement of the mechanism and improves the flight performance of the aircraft.

[0005] The technical solution of the present invention:

[0006] A tail wing control mechanism with a variable transmission angle comprises a tilting shaft, a tilting rocker arm, a cross control rocker arm, a Y-shaped adapter frame, a tilting actuator cylinder and a deflection actuator cylinder.

[0007] One end of the tilt shaft is connected to the ear piece on the tail main beam through two ear pieces, so that it rotates around the tail deflection axis. The other end of the tilt shaft is supported on the front and rear fuselage frames, and the tilt shaft is fixedly connected to the starting end of the tilt rocker arm. The tilt shaft and the tilt rocker arm rotate around the tail tilt axis under the drive of the tilt actuator. The tail control mechanism with variable transmission angle also includes a supporting rocker arm, a locking strut, a rocker arm connector, and a folding locking strut. The end of the tilt rocker arm is hinged to the rocker arm connector. The supporting rocker arm and the folding locking strut are connected to the same hinge shaft, and are connected to the rocker arm connector through a hinge shaft. The folding locking strut is hinged to the locking strut.

[0008] The deflection actuator is connected to a cross-steering rocker arm, which is pivotally connected to a support fixed to the fuselage frame and can rotate about its rocker axis. The cross-steering rocker arm is hinged to the Y-shaped adapter via a connecting shaft. The Y-shaped adapter is connected to the tail wing via hinge points on the tail wing main beam and the tail boom bulkhead.

[0009] The variable-angle tail control mechanism's tilting motion is achieved by the tilt actuator pushing the tilt rocker arm, which in turn drives the main tilt axis. At the two extremes of the V-tail's tilting motion, 0° and 50°, the tilt axis is locked in place by a folding locking strut, supporting rocker arm, and rocker arm connector.

[0010] The variable-angle tail control mechanism's yaw mechanism (basically the same as that of a cross-articulated universal joint) operates by rotating the cross-arm around its axis. The yaw actuator then rotates the cross-arm around its axis, causing the tail yaw axis to move around the tilt axis as the tail pitch angle changes. By leveraging the intersecting point of the tail pitch and yaw axes, a Y-shaped adapter is used to connect the tail main beam and the cross-arm, enabling yaw control at any tail pitch angle.

[0011] The advantages of this invention include: The variable transmission angle tail wing control mechanism requires minimal space for its layout. The addition of a support rocker arm and locking strut for the auxiliary tilt support significantly reduces the performance requirements of the tilt actuator, thereby reducing the overall system weight. The related components also offer excellent manufacturing processability. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 Schematic diagram of the composition of the tail wing control mechanism with variable transmission angle.

[0013] Figure 2 Schematic diagram of the composition of the tail wing control mechanism with variable transmission angle.

[0014] Figure 3 Schematic diagram of the composition of the tail wing control mechanism with variable transmission angle.

[0015] Figure 4 Schematic diagram of the tilting motion process.

[0016] Figure 5 It is the axis related to the deflection movement of the tail wing control mechanism with variable transmission angle.

[0017] Figure 6 It is the deflection motion process of the tail wing control mechanism with variable transmission angle (tilt angle 0°).

[0018] Figure 7 The deflection motion process of the tail wing control mechanism with variable transmission angle (inclination angle 50°).

[0019] Figure 8 It is the tilting axis.

[0020] Figure 9 For the tilting rocker arm.

[0021] Figure 10 To support the rocker arm.

[0022] Figure 11 Lock the struts for folding.

[0023] Figure 12 To lock the strut.

[0024] Figure 13 It is a cross-control rocker arm.

[0025] Figure 14 It is a Y-shaped adapter.

[0026] In the figure: 1 tilt axis, 2 tilt rocker arm, 3 tail wing main beam, 4 tail wing side rib, 5 deflection actuator, 6 support rocker arm, 7 folding locking strut, 8 tilt actuator, 9 cross control rocker arm, 10 Y-shaped adapter frame, 11 rocker arm connector, 12 tail wing tilt axis, 13 tail wing deflection axis, 14 cross rocker arm hinge axis, 15 locking strut. DETAILED DESCRIPTION

[0027] A tail wing control mechanism with variable transmission angle, comprising a tilt shaft 1, a tilt rocker arm 2, a cross control rocker arm 9, a Y-shaped adapter 10, a tilt actuator 8, a deflection actuator 5, a support rocker arm 6, a locking strut 15, a rocker arm connector 11, a folding locking strut 7, etc. Figure 1 、 Figure 2 and Figure 3 As shown in .

[0028] One end of the tilt shaft 1 is connected to the ear piece on the tail main beam 3 through two ears, so that it rotates around the tail deflection axis. The other end of the tilt shaft 1 passes through and is supported on the front and rear fuselage frames, and the starting end of the tilt rocker arm 5 is fixed on the tilt shaft 1 between the front and rear fuselage frames. The tilt shaft 1 and the tilt rocker arm 2 rotate around the tail tilt axis under the drive of the tilt actuator 8. The tilt rocker arm 2 is hinged to the lower end of the tilt actuator 8 near the end, and the upper end of the tilt actuator 8 is rotationally connected to the fixed connection structure on the fuselage; the end of the tilt rocker arm 2 is hinged to one end of the rocker arm connector 11. One end of the support rocker arm 6 and one end of the folding locking strut 7 are connected to the same hinge shaft, and are connected to the other end of the rocker arm connector 11 through a hinge shaft. The other end of the supporting rocker arm 6 is rotatably connected to the fixed connection structure on the fuselage; the other end of the folding locking strut 7 is hinged to one end of the locking strut 15, and the other end of the locking strut 15 is rotatably connected to the fixed connection structure on the fuselage.

[0029] One end of the deflection actuator 5 is fixed to the fuselage, with its axis parallel to the axis of the main tilt axis 1. The telescopic end of the deflection actuator 5 is pivotally connected to the tab at the upper end of the cross-control rocker 9. The rocker shaft in the middle of the cross-control rocker 9 is pivotally connected to a support fixed to the fuselage frame, allowing it to rotate around the rocker shaft of the cross-control rocker 9 when driven by the deflection actuator 5. The upper and lower ends of the cross-control rocker 9 are respectively hinged to a Y-shaped adapter 10 via connecting shafts. The Y-shaped adapter 10 is connected to the tail wing via hinge points on the tail wing main beam 3 and the tail beam bulkhead.

[0030] The variable-angle tail control mechanism's tilting motion is achieved by the tilt actuator 8, which drives the tilt rocker arm 2, driving the tilt axis 1. At the two extreme positions of the V-tail's tilting motion, 0° and 50°, the tilt axis 1 is locked in place by a folding locking strut 7, supporting rocker arm 6, and rocker arm connector 11.

[0031] The yaw motion principle of the variable-angle tail control mechanism is essentially the same as that of a cross-articulated universal joint. The yaw actuator 5 rotates the cross-control rocker 9, causing the tail yaw axis to move about the tail tilt axis as the tail pitch angle changes. Taking advantage of the fact that the tail tilt axis and the tail yaw axis intersect at a single point in space, a Y-shaped adapter is used to connect the tail main beam 3 and the cross-control rocker 9, enabling yaw control at any tail pitch angle.

[0032] The deflection motion process of the tail wing control mechanism with variable transmission angle is as follows when the tail wing inclination angle is 0° Figure 6 The deflection motion process of the suspended articulated full-motion V-tail mechanism is as follows when the tail tilt angle is 50°: Figure 7 As shown in .

Claims

1. A tail wing control mechanism with variable transmission angle, characterized in that: It includes a tilting shaft, a tilting rocker arm, a cross-control rocker arm, a Y-shaped adapter, a tilting actuator and a yaw actuator; One end of the tilt shaft is connected to the lugs on the tail main beam through two lugs, thereby rotating around the tail deflection axis; the other end of the tilt shaft is supported on the front and rear fuselage frames, and the tilt shaft is fixedly connected to the starting end of the tilt rocker arm; the tilt shaft and the tilt rocker arm rotate around the tail tilt axis under the drive of the tilt actuator; The deflection actuator is connected to the cross-control rocker arm, which is rotatably connected to a support fixed to the fuselage frame and can rotate around the rocker arm axis of the cross-control rocker arm. The cross-control rocker arm is hinged to the Y-shaped adapter frame through a connecting shaft. The Y-shaped adapter frame is connected to the tail wing through hinge points on the tail wing main beam and the tail beam bulkhead. One end of the tilting shaft is connected to the lugs on the tail wing main beam through two lugs, so that it rotates around the tail wing deflection axis; the other end of the tilting shaft passes through and is supported on the front and rear fuselage frames, and the starting end of the tilting rocker arm is sleeved and fixed on the tilting shaft between the front and rear fuselage frames; the tilting shaft and the tilting rocker arm rotate around the tail wing tilt axis under the drive of the tilt actuator cylinder; the tilting rocker arm is hinged to the lower end of the tilt actuator cylinder near the end, and the upper end of the tilt actuator cylinder is rotatably connected to the fixed connection structure on the fuselage; the very end of the tilting rocker arm is hinged to one end of the rocker arm connector; one end of the supporting rocker arm and one end of the folding locking strut are connected to the same hinge shaft, and are connected to the other end of the rocker arm connector through a hinge shaft; the other end of the supporting rocker arm is rotatably connected to the fixed connection structure on the fuselage; the other end of the folding locking strut is hinged to one end of the locking strut, and the other end of the locking strut is rotatably connected to the fixed connection structure on the fuselage; One end of the deflection actuator is fixed on the fuselage, and the direction of its axis is parallel to the direction of the axis of the tilt axis; the telescopic end of the deflection actuator is rotatably connected to the ear piece at the upper end of the cross-control rocker arm; the rocker shaft in the middle of the cross-control rocker arm is rotatably connected to the support fixed on the fuselage frame, and the cross-control rocker arm can rotate around the rocker shaft of the cross-control rocker arm under the drive of the deflection actuator; the upper and lower ends of the cross-control rocker arm are respectively hinged to the Y-shaped adapter frame through the connecting shaft; the Y-shaped adapter frame is connected to the tail wing through the hinge points on the tail wing main beam and the tail beam partition.

2. The tail wing control mechanism with variable transmission angle according to claim 1, characterized in that: The tail wing control mechanism with variable transmission angle also includes a supporting rocker arm, a locking strut, a rocker arm connector, and a folding locking strut; the end of the tilting rocker arm is hinged to the rocker arm connector; the supporting rocker arm and the folding locking strut are connected to the same hinge shaft and are connected to the rocker arm connector through the hinge shaft; the folding locking strut is hinged to the locking strut.

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