Missile wing unfolding mechanism with variable sweepback angle

Abstract

The invention discloses a missile wing unfolding mechanism with variable sweepback angles. The missile wing unfolding mechanism comprises a cam sliding block, a gas actuator cylinder mounting seat, a linear motor, an actuator cylinder sliding rail, a cam sliding rail, a rack, a gear right missile wing, a gear left missile wing and a roller. Missile wings are unfolded through the actuator cylinder-rack-gear, the unfolding angle of the missile wings is adjustable through the motor-cam mechanism, and the functions of synchronous unfolding of the missile wings, storage and transportation of hair in a small space and adjustment of the sweepback angle according to requirements can be met at the same time. The device is simple and reliable in structure and convenient to maintain.

Description

Technical Field

[0001] The invention relates to a missile wing deployment mechanism, in particular to a missile wing deployment mechanism design with a variable sweep angle at any time. Background Art

[0002] With the rapid development of loitering ammunition, higher requirements are placed on the cost-effectiveness of loitering ammunition. At the same time, with the improvement of engine performance, the flight speed of ammunition is getting faster and faster, which also brings a series of requirements on fuel consumption, flight speed, etc.

[0003] The deployment mechanism of existing cruise missiles usually uses a gas actuator as a driving energy source to achieve a single actuation deployment, and the final position is locked by a locking pin to ensure the flight stability of the missile body. Its wing sweep angle is fixed and the aerodynamic configuration parameters are single, so it can only achieve flight within a small range of speed envelope by adjusting the rudder, and cannot meet the requirements of adapting to a larger speed range. In particular, it is difficult to meet the comprehensive functional requirements of existing large cruise munitions for high-speed penetration and low-speed cruise.

[0004] Therefore, there is an urgent need for a new type of wing deployment mechanism that can meet the needs of storage, transportation and launch in a small space, and at the same time can adjust the sweep angle at any time according to the task during the mission execution, and is compatible with high and low speed switching. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and provide a wing deployment mechanism with a variable sweep angle at any time, which can simultaneously meet the functions of small-space storage, transportation and launch, and the sweep angle can be adjusted at any time according to needs during the execution of the mission. The structure is simple and reliable, easy to maintain, the two wings have good synchronization, and are easy to implement, while meeting the needs of low-speed cruising flight with a small sweep angle and high-speed penetration with a large sweep angle.

[0006] The technical solution of the present invention is: a wing deployment mechanism with a variable sweep angle, comprising a cam slider, a gas actuator mounting seat, a linear motor, an actuator slide rail, a cam slide rail, a rack, a gear right wing, a gear left wing 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 both fixedly mounted on the projectile body, and the gas actuator is fixedly mounted on the gas actuator mounting seat; a wheel shaft is provided at the bottom of the gas actuator mounting seat, a curved groove is provided on the cam slider, and the roller is mounted on the wheel shaft A cam mechanism is installed in the curved groove, and the pull rod of the linear motor is fixedly connected to 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 cylinder mounting seat to move forward and backward; the roots of the right and left wing of the gear are symmetrically installed on the projectile body through the rotating axis respectively, and the roots of the right and left wing of the gear are provided with gears for meshing with one end of the rack, and the other end of the rack is fixedly connected to the gas actuator cylinder mounting seat, and the movement of the gas actuator cylinder mounting seat drives the right and left wing of the gear to expand or close.

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

[0008] Furthermore, the sweep angle adjustment angle Δα satisfies the relationship R chilun Δα=ΔS 电机 ·f 凸轮 , where R chilun is the turning radius of the wing gear, f 凸轮 is the function of the longitudinal displacement determined by the curve where the curved groove is located with respect to the lateral displacement, ΔS 电机 It is the lateral displacement of the cam slider pulled by the linear motor; the turning radius of the elastic wing gear is the distance between the meshing point of the right elastic wing of the gear or the left elastic wing of the gear and the rack and the center of the rotating axis.

[0009] Preferably, the cam mechanism is a linear cam with a slope angle of β. 凸轮 =tanβ.

[0010] Furthermore, the actuator slide rail is arranged in a direction parallel to the axis of the projectile body, and the cam slide rail is arranged in a direction perpendicular to the axis of the projectile body.

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

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

[0013] (B) After receiving the deployment command, the gas actuator on the actuator mounting seat works to push the rack to move, and then the gear right wing and the gear left wing are pushed to deploy synchronously through the meshing size, so that the wing can be deployed at a small angle, and the missile body has an initial sweep angle;

[0014] (C) When the deployment angle of the wing needs to be increased, 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 backward along the actuator slide rail through the cam mechanism, driving the rack to move backward together, and then the gear right wing and the gear left wing are further deployed through the meshing size to increase the sweep angle of the projectile;

[0015] (D) When the deployment angle of the wing needs to be reduced, the linear motor is controlled to reverse and 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 with the gas actuator mounting seat, and then the gear right wing and the gear left wing are retracted through the meshing size to reduce the sweep angle of the projectile.

[0016] The advantages of the present invention compared with the prior art are:

[0017] (1) The present invention uses a gas actuator to realize the initial wing deployment, which can ensure the reliability and short-time requirements of the wing deployment;

[0018] (2) The present invention uses a gear rack as a transmission mechanism for the deployment of the missile wings, which ensures the synchronization of the deployment of the left and right missile wings, ensures that the forces on the two missile wings are consistent during the deployment process, and can also ensure the stability of the missile body's rolling attitude during the deployment process;

[0019] (3) The present invention achieves amplification of the driving torque through the motor reducer mechanism, thereby reducing the power consumption requirement of the motor;

[0020] (4) The present invention uses a cam mechanism and a gear rack mechanism to realize the adjustment of the swept angle of the missile wing, which can ensure that the flight posture of the missile body is stable and reliable during the adjustment process of the missile wing angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the folded state of the upper deployment mechanism of the present invention;

[0022] Figure 2 It is a schematic diagram of the large-angle swept state of the missile deployment mechanism of the present invention;

[0023] Figure 3 It is a schematic diagram of the small-angle swept state of the missile deployment mechanism of the present invention;

[0024] Figure 4 Schematic diagram of the actuator cylinder-rack-pinion wing (a) and cam mechanism (b) of the deployment mechanism on the bomb of the present invention;

[0025] Figure 5 It is a schematic diagram of the sweep angle adjustment process of the missile deployment mechanism of the present invention. DETAILED DESCRIPTION

[0026] like Figure 1 , Figure 4 As shown in (b), the wing deployment mechanism of the present invention mainly comprises a projectile 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 gear right wing 8, a gear left wing 9 and a roller 10.

[0027] The installation method is as follows: the gear left wing 9 and the gear right wing 8 are installed on the rotary shaft of the projectile body 1 and are respectively meshed with the rack 7; the rack 7 is fixedly connected to the gas actuator, the gas actuator is installed on the gas actuator mounting seat 3, and the gas actuator mounting seat 3 is installed in the actuator slide rail 5, wherein the actuator slide rail 5 is fixedly connected to the projectile body 1 to provide axial sliding support for the actuator mounting seat 3, and the rack 7 is extended axially by the pushing actuation of the gas actuator, so that the gear left wing 9 and the gear right wing 8 are simultaneously deployed in place, as shown in FIG. Figure 4 (a) As shown. The wheel shaft of the actuator mounting seat 3 passes through the roller 10 and 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, wherein the cam slide rail 6 is fixedly connected to the elastic body 1, as shown in FIG. Figure 4 (b) As shown. The linear motor 4 is fixedly connected to the 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 roller 10 rolls in the curved groove of the cam slider 2 to convert the horizontal movement into the axial forward movement of the actuator mounting seat 3, thereby driving the rack 7 to drive the gear right wing 8 and the gear left wing 9 to swing in the folding direction through the gear, as shown in FIG. Figure 5 As shown, the sweep angle is changed from a small sweep angle to a low-speed cruise state (such as Figure 3 As shown) is adjusted to a high-speed penetration state with a large sweep angle (as shown Figure 2 shown).

[0028] When the mission requirement is adjusted from high-speed penetration to slow cruising, it is only necessary to reverse the linear motor 4 and push the cam slider 2 to move to the left to adjust the sweep angle from large to small and realize the state conversion, thus completing the system installation.

[0029] like Figure 5 As shown, the sweep angle of the wing is set to α, where the sweep angle in state 1 is α1, the sweep angle in state 2 is α2, ΔS 电机is the lateral displacement of the cam slider 2 pulled by the linear motor 4. In order to simply describe the motion relationship of the present invention, the cam in the present invention adopts the simplest linear curve cam, whose slope angle is β, and its curve function is f 凸轮 =tanβ. In order to achieve better transmission efficiency and force conditions, the cam curve can be designed according to the actual situation. When the wing is adjusted from state 1 to state 2, the sweep angle adjustment angle Δα=α1-α2, Δα and the linear motor movement distance ΔS 电机 The relationship is:

[0030] R chilun Δα=ΔS 电机 tanβ

[0031] Where R chilun It is the gyration radius of the wing gear, that is, the distance between the meshing point of the wing gear and the rack 7 and the gyration center of the wing.

[0032] The motion mode of the mechanism of the present invention is described below. The initial state is as follows: Figure 1 As shown, the right gear wing 8 and the left gear wing 9 are completely folded in the envelope of the missile body, realizing the storage, transportation and launch requirements of the missile body 1. When the missile body 1 is launched from the frame and meets the deployment requirements, the system issues a deployment command, and the gas cylinder on the gas cylinder mounting seat 3 works, pushing the rack 7 through the meshing size to synchronously push the gear wings 8 and 9 to deploy, as shown in FIG. Figure 4 As shown in (a), the state is Figure 2 As shown, the small angle deployment of the wing is realized. At this time, the aerodynamic shape is in a small swept state, which meets the requirements of fast penetration with a large swept angle. After reaching the predetermined area, the linear motor 4 pulls the cam slider 2 to move rightward along the cam guide rail 6, as shown in FIG. Figure 5 As shown, 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 curve groove, driving the rack 7 to move backward together, and then further expands the gear right wing 8 and the gear left wing 9 through the meshing size to increase the sweep angle. Figure 3 As shown, the low-speed cruising requirements of the projectile are met.

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

[0034] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A wing deployment mechanism with a variable sweep angle, characterized in that: The invention comprises 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 gear wing (8), a left gear wing (9) and a roller (10); the gas actuator mounting seat (3) is mounted on the actuator slide rail (5), the cam slider (2) is mounted on the cam slide rail (6), the actuator slide rail (5) and the cam slide rail (6) are both fixedly mounted on the projectile (1), and the gas actuator is fixedly mounted on the gas actuator mounting seat (3); a wheel shaft is provided at the bottom of the gas actuator mounting seat (3), a curved groove is provided on the cam slider (2), and the roller (10) is mounted on the curved groove via the wheel shaft A 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 the cam mechanism drives the gas actuator cylinder mounting seat (3) to move forward and backward; the roots of the right gear wing (8) and the left gear wing (9) are symmetrically installed on the projectile body (1) through the rotating axis, and 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), and the other end of the rack (7) is fixedly connected to the gas actuator cylinder mounting seat (3), and the movement of the gas actuator cylinder mounting seat (3) drives the right gear wing (8) and the left gear wing (9) to expand or close.

2. The variable sweep angle wing deployment mechanism according to claim 1, characterized in that: The deployment angle range of the gear right wing (8) and the gear left 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 is the turning radius of the wing gear, f 凸轮 is the function of the longitudinal displacement determined by the curve where the curved groove is located with respect to the lateral displacement, ΔS 电机 The lateral displacement of the cam slider (2) driven by the linear motor (4); the rotation radius of the elastic wing gear is the distance between the meshing point of the right elastic wing (8) or the left elastic wing (9) of the gear and the rack (7) and the center of the rotation axis.

4. The variable sweep angle wing deployment mechanism according to claim 3, characterized in that: The cam mechanism is a linear curve cam with a slope 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 actuating cylinder slide rail (5) is arranged in a direction parallel to the axis of the projectile body.

7. The 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 body.

8. A method for controlling a missile body by using the variable sweep angle missile wing deployment mechanism according to claim 1, characterized in that include: (A) completely folding the gear right wing (8) and the gear left wing (9) into the envelope of the projectile body; (B) After receiving the deployment command, the gas actuator on the actuator mounting seat (3) works to push the rack (7) to move, and then the gear right wing (8) and the gear left wing (9) are synchronously pushed to deploy through the meshing size, so that the wings can be deployed at a small angle, and the missile body has an initial sweep angle; (C) When the deployment angle of the wing needs to be increased, the linear motor (4) is controlled to pull the cam slider (2) to move rightward along the cam guide rail (6), and 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, driving the rack (7) to move backward together, and then the gear right wing (8) and the gear left wing (9) are further deployed through the meshing size, thereby increasing the sweep angle of the projectile; (D) When it is necessary to reduce the deployment angle of the wing, the linear motor (4) is controlled to reverse, and the cam slider (2) is pulled to move leftward along the cam guide 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, and the rack (7) moves forward together with the gas actuator mounting seat (3), and then the gear right wing (8) and the gear left wing (9) are retracted through the meshing size to reduce the sweep angle of the projectile.

Images