Variable sweep wing deployment mechanism

Abstract

The variable sweep angle missile wing unfolding mechanism comprises a cam slider, a gas actuating cylinder mounting seat, a linear motor, an actuating cylinder sliding rail, a cam sliding rail, a rack, a right gear missile wing, a left gear missile wing and a roller. The invention realizes the unfolding of the missile wing through the actuating cylinder-rack-gear, and realizes the adjustable unfolding angle of the missile wing through the motor-cam mechanism, which can simultaneously satisfy the functions of synchronous unfolding of the missile wing, storage and transportation in small space, and adjustment of the sweep angle according to requirements. The invention has simple and reliable structure and is convenient to maintain.

Description

TECHNICAL FIELD

[0001] The present application relates to a missile wing unfolding mechanism, in particular to a missile wing unfolding mechanism with variable sweepback angle. BACKGROUND

[0002] With the rapid development of cruise missile, higher requirements are put forward for the cost-effectiveness ratio of cruise missile. At the same time, with the improvement of engine performance, the flight speed of the missile is getting faster and faster, which brings a series of requirements for fuel consumption and flight speed.

[0003] The existing cruise missile unfolding mechanism usually uses a gas actuator cylinder as a driving energy source to realize single-time actuation and unfolding, and uses a locking pin to lock at the end to ensure the stability of the missile body in flight. The sweepback angle of the missile wing is fixed, and the aerodynamic configuration parameters are single, so it can only realize flight within a small range of speed envelope by adjusting the rudder, and cannot meet the requirements of large speed range adaptation. Especially it is difficult to meet the comprehensive functional requirements of high-speed penetration and low-speed cruise of existing large cruise missiles.

[0004] Therefore, there is an urgent need for a new type of missile wing unfolding mechanism that can meet the requirements of small space storage and launch, and can realize the adjustment of sweepback angle at any time during task execution according to the task, and the switching requirements of high and low speed. SUMMARY

[0005] The technical problem solved by the present application is to overcome the shortcomings of the prior art and provide a missile wing unfolding mechanism with variable sweepback angle at any time, which can meet the requirements of small space storage and launch, and the sweepback angle can be adjusted at any time according to the requirements during task execution. The structure is simple and reliable, easy to maintain, the synchronization of the two wings is good, easy to realize, and it can meet the requirements of small sweepback angle low-speed cruise flight and large sweepback high-speed penetration at the same time.

[0006] The technical solution of the present application is: a variable sweep angle missile wing unfolding mechanism, comprising a cam slider, a gas actuator mounting seat, a linear motor, an actuator slide rail, a cam slide rail, a rack, a right wing gear, a left wing gear and a roller; the gas actuator mounting seat is mounted on the actuator slide rail, the cam slider is mounted on the cam slide rail, the actuator slide rail and the cam slide rail are fixedly installed on the missile body, and the gas actuator is fixedly installed on the gas actuator mounting seat; the bottom of the gas actuator mounting seat is provided with an axle, the cam slider is provided with a curved groove, the roller is installed in the curved groove through the axle to form a cam mechanism, the pull rod of the linear motor is fixedly connected with the cam slider, the rotation of the linear motor drives the movement of the cam slider, and then the cam mechanism drives the gas actuator mounting seat to move forward and backward; the roots of the right wing gear and the left wing gear are symmetrically installed on the missile body through a rotary shaft, the roots of the right wing gear and the left wing gear are provided with gears for meshing with one end of the rack, the other end of the rack is fixedly connected with the gas actuator mounting seat, and the movement of the gas actuator mounting seat drives the right wing gear and the left wing gear to unfold or fold.

[0007] Further, the unfolding angle range of the right wing gear and the left wing gear determines the adjustment range of the sweep angle adjustment angle Δα.

[0008] Further, the sweep angle adjustment angle Δα satisfies the relationship R chilun ·Δα=ΔS 电机 ·f 凸轮 , wherein R chilun is the rotary radius of the wing gear, f 凸轮 is a function of the longitudinal displacement with respect to the transverse displacement determined by the curve where the curved groove is located, ΔS 电机 is the transverse displacement of the linear motor pulling the cam slider to move; the rotary radius of the wing gear is the distance between the meshing position of the right wing gear or the left wing gear and the rack and the center of the rotary shaft.

[0009] Preferably, the cam mechanism is a one-time curve cam, and the slope angle is β. f 凸轮 =tanβ.

[0010] Further, the actuator slide rail is arranged in a direction parallel to the axis of the missile body. The cam slide rail is arranged in a direction perpendicular to the axis of the missile body.

[0011] A method for controlling a missile body by using a variable sweep angle missile wing unfolding mechanism, comprising:

[0012] (A) folding the right wing gear and the left wing gear completely into the missile body envelope;

[0013] (B) After receiving the unfolding instruction, the gas actuator on the actuator mounting seat works to push the rack to move, and then the right wing and the left wing are pushed to unfold synchronously through the meshing size, so that the wings are unfolded at a small angle, and the missile body has an initial sweepback angle;

[0014] (C) When it is necessary to increase the unfolding angle of the wings, the linear motor is controlled to pull the cam slider to move rightward along the cam guide rail, the cam slider pushes the gas actuator mounting seat to continue to move rearward along the actuator slide rail through the cam mechanism, drives the rack to move rearward, and then the right wing and the left wing are further unfolded through the meshing size, so that the sweepback angle of the missile body is increased;

[0015] (D) When it is necessary to reduce the unfolding angle of the wings, the linear motor is reversed, the cam slider is pulled to move leftward along the cam guide rail, the cam slider drives the gas actuator mounting seat to move forward along the actuator slide rail through the cam mechanism, the rack moves forward together with the gas actuator mounting seat, and then the right wing and the left wing are folded through the meshing size, so that the sweepback angle of the missile body is reduced.

[0016] Compared with the prior art, the present application has the following advantages:

[0017] (1) The present application uses a gas actuator to unfold the wings for the first time, which can ensure the reliability and short-time requirement of wing unfolding;

[0018] (2) The present application uses a gear and rack as a transmission mechanism for wing unfolding, which ensures the synchronization of left and right wing unfolding, ensures that the two wings are subjected to consistent force during unfolding, and ensures the stability of the rolling attitude of the missile body during unfolding;

[0019] (3) The present application realizes the amplification of driving torque through a motor reducer mechanism, which reduces the power consumption requirement of the motor;

[0020] (4) The present application uses a cam mechanism and a gear and rack mechanism to realize the adjustment of the sweepback angle of the wings, which can ensure the stability and reliability of the flight attitude of the missile body during the adjustment of the sweepback angle of the wings. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a schematic view of the folding state of the unfolding mechanism on the missile of the present application;

[0022] Figure 2 It is a schematic view of the large-angle sweepback state of the unfolding mechanism on the missile of the present application;

[0023] Figure 3 It is a schematic view of the small-angle sweepback state of the unfolding mechanism on the missile of the present application;

[0024] Figure 4 It is a schematic view of the actuator-rack-gear wing (a) and the cam mechanism (b) of the unfolding mechanism on the missile of the present application;

[0025] Figure 5 Figure 1 is a schematic diagram of the adjustment process of the rear-swept angle of the missile wing unfolding mechanism of the present application. DETAILED DESCRIPTION

[0026] As shown in Figure 1 , Figure 4 (b), the system components of the missile wing unfolding mechanism of the present application mainly include a missile body 1, a cam slider 2, a gas actuator mounting seat 3, a linear motor 4, an actuator slide rail 5, a cam slide rail 6, a rack 7, a right wing gear 8, a left wing gear 9, and a roller 10.

[0027] The installation mode is as follows: the left wing gear 9 and the right wing gear 8 are installed on the rotating shaft of the missile body 1 and are in meshing installation with the rack 7, respectively; the rack 7 is fixedly connected with a gas actuator, which is mounted on the gas actuator mounting seat 3, and the gas actuator mounting seat 3 is installed in the actuator slide rail 5, which is fixedly connected to the missile body 1, thereby providing axial sliding support for the gas actuator mounting seat 3; the gas actuator is pushed to actuate the rack 7 to extend along the axial direction, thereby achieving the simultaneous unfolding of the left wing gear 9 and the right wing gear 8 to the position, as shown in Figure 4 (a). The wheel shaft of the actuator mounting seat 3 is installed in the curved groove of the cam slider 2 to complete the installation of the cam mechanism; the cam slider 2 is installed in the cam slide rail 6, which is fixedly connected to the missile body 1, as shown in Figure 4 (b). The linear motor 4 is installed and fixedly connected to the missile body 1, and the pull rod of the linear motor 4 is fixedly connected to the cam slider 2; the linear motor 4 pulls the cam slider 2 to move horizontally to the right, and the horizontal movement is converted into the axial forward movement of the actuator mounting seat 3 through the rolling of the roller 10 in the curved groove of the cam slider 2, thereby driving the rack 7 to swing the right wing gear 8 and the left wing gear 9 in the folding direction through the gear, as shown in Figure 5 , thereby achieving the adjustment of the rear-swept angle from the small rear-swept angle low-speed cruising state (as shown in Figure 3 ) to the large rear-swept angle high-speed penetration state (as shown in Figure 2 ).

[0028] When the task requirement is adjusted from high-speed penetration to slow-speed cruising, the linear motor 4 is only needed to be reversed to push the cam slider 2 to move to the left, thereby achieving the adjustment of the rear-swept angle from large to small, realizing the state conversion, and thus completing the system installation.

[0029] As shown in Figure 5 , the rear-swept angle of the missile wing is set as α, wherein the rear-swept angle in state 1 is α1, the rear-swept angle in state 2 is α2, and ΔS 电机The transverse movement displacement of the cam slider 2 is pulled by the linear motor 4. In order to simply describe the motion relationship of the present application, the cam in the present application adopts the simplest one curve cam, and the slope angle is β, and the curve function is f 凸轮 =tanβ. In order to realize the better transmission efficiency and force condition, the cam curve can be designed according to the actual situation. When the wing is adjusted from state 1 to state 2, the sweepback angle adjustment angle Δα=α1-α2, and the relationship between Δα and the linear motor motion distance ΔS 电机 is:

[0030] R chilun ·Δα=ΔS 电机 ·tanβ

[0031] Wherein R chilun is the rotation radius of the wing gear, that is, the distance between the meshing position of the wing gear and the rack 7 and the rotation center of the wing.

[0032] The motion mode of the mechanism of the present application is introduced below. The initial state is shown in Figure 1 , the right wing gear 8 and the left wing gear 9 are completely folded in the body envelope, realizing the storage and transportation requirements of the body 1. When the body 1 is launched off the rack to achieve the deployment requirement, the system issues a deployment command, and the gas actuator cylinder on the gas actuator cylinder mounting seat 3 works to push the rack 7 through the meshing size to synchronously push the wing gears 8 and 9 to deploy, as shown in Figure 4 (a), at this time, the state is shown in Figure 2 , realizing the small angle deployment of the wing, and the aerodynamic configuration is in the small sweepback state, meeting the rapid penetration requirement of the large sweepback angle. When reaching the predetermined area, the linear motor 4 pulls the cam slider 2 to move along the cam rail 6 to the right, as shown in Figure 5 , the cam slider 2 pushes the gas actuator cylinder mounting seat 3 to continue to move along the actuator cylinder slide rail 5 to the rear, driving the rack 7 to move to the rear, and then through the meshing size, the right wing gear 8 and the left wing gear 9 are further deployed to increase the sweepback angle, and the state is shown in Figure 3 , meeting the low-speed cruising requirement of the body.

[0033] When the body 1 needs to penetrate again at high speed, the linear motor 4 is reversed to push the cam slider 2, and the cam slider 2 drives the gas actuator cylinder mounting seat 3 to move along the actuator cylinder slide rail 5 to the front, and the rack 7 moves forward with the gas actuator cylinder mounting seat 3, so that the body can be converted into the high-speed penetration state.

[0034] The contents not described in detail in the specification of the present application are the known technology of those skilled in the art.

Claims

1. A variable sweep angle missile wing deployment mechanism, characterized in that: The system includes a cam slider (2), a gas actuator mounting base (3), a linear motor (4), an actuator slide rail (5), a cam slide rail (6), a rack (7), a right gear wing (8), a left gear wing (9), and a roller (10). The gas actuator mounting base (3) is mounted on the actuator slide rail (5), the cam slider (2) is mounted on the cam slide rail (6), and both the actuator slide rail (5) and the cam slide rail (6) are fixedly mounted on the projectile (1). The gas actuator is fixedly mounted on the gas actuator mounting base (3). The bottom of the gas actuator mounting base (3) is provided with an axle, the cam slider (2) is provided with a curved groove, and the roller (10) is mounted on the curved groove through the axle. The cam mechanism is formed in the middle. The pull rod of the linear motor (4) is fixedly connected to the cam slider (2). The rotation of the linear motor (4) drives the movement of the cam slider (2), and then drives the gas actuator cylinder mounting seat (3) to move back and forth through the cam mechanism. The roots of the right gear wing (8) and the left gear wing (9) are respectively symmetrically mounted on the projectile body (1) through the rotary shaft. The roots of the right gear wing (8) and the left gear wing (9) are provided with gears for meshing with one end of the rack (7). The other end of the rack (7) is fixedly connected to the gas actuator cylinder mounting seat (3). The movement of the gas actuator cylinder mounting seat (3) drives the right gear wing (8) and the left gear wing (9) to unfold or close.

2. The variable sweep angle wing deployment mechanism according to claim 1, characterized in that: The deployment angle range of the right gear wing (8) and the left gear wing (9) determines the adjustment range of the sweep angle adjustment angle Δα.

3. The variable sweep angle wing deployment mechanism according to claim 2, characterized in that: The sweep angle adjustment angle Δα satisfies the relationship R chilun ·Δα=ΔS 电机 ·f 凸轮 , where R chilun f is the radius of rotation of the wing gear. 凸轮 ΔS is a function of the longitudinal displacement determined by the curve containing the groove, with respect to the lateral displacement. 电机 The lateral displacement of the cam slider (2) pulled by the linear motor (4) is the distance between the center of the rotating shaft and the meshing point of the right wing (8) or left wing (9) of the gear and the rack (7).

4. The variable sweep angle wing deployment mechanism according to claim 3, characterized in that: The cam mechanism is a single-curve cam with a ramp angle of β.

5. The variable sweep angle wing deployment mechanism according to claim 4, characterized in that: The f 凸轮 =tanβ.

6. The variable sweep angle wing deployment mechanism according to claim 1, characterized in that: The actuator slide rail (5) is arranged in a direction parallel to the axis of the projectile.

7. A variable sweep angle wing deployment mechanism according to claim 5, characterized in that: The cam slide rail (6) is arranged in a direction perpendicular to the axis of the projectile.

8. A method for controlling a projectile using the variable sweep angle wing deployment mechanism as described in claim 1, characterized in that... include: (A) Fold the right gear wing (8) and the left gear wing (9) completely into the envelope of the projectile body; (B) After receiving the deployment command, the gas actuator on the actuator mounting base (3) works, pushing the rack (7) to move, and then pushing the right gear wing (8) and the left gear wing (9) to deploy synchronously through the meshing size, so as to realize the small angle deployment of the wings and the missile body has an initial sweep angle. (C) When it is necessary to increase the deployment angle of the missile wings, control the linear motor (4) to pull the cam slider (2) to move to the right along the cam slide rail (6). The cam slider (2) pushes the gas actuator mounting seat (3) to continue to move backward along the actuator slide rail (5) through the cam mechanism, which drives the rack (7) to move backward together. Then, through the meshing size, the right gear missile wing (8) and the left gear missile wing (9) are further deployed to increase the sweep angle of the missile body. (D) When it is necessary to reduce the deployment angle of the missile wings, control the linear motor (4) to reverse and pull the cam slider (2) to move to the left along the cam slide rail (6). The cam slider (2) drives the gas actuator mounting seat (3) to move forward along the actuator slide rail (5) through the cam mechanism. The rack (7) moves forward together with the gas actuator mounting seat (3), and then retracts the right wing (8) and the left wing (9) of the gear through the meshing size, thereby reducing the sweep angle of the missile body.

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