Rocket flight attitude control device

Abstract

The invention relates to the technical field of rocket flight attitude control, in particular to a rocket flight attitude control device which comprises a first regulation and control structure, a second regulation and control structure and a pneumatic transmission structure, the first regulation and control structure and the second regulation and control structure are the same in structure and are fixedly connected, and the pneumatic transmission structure is fixedly connected with the first regulation and control structure. The center of the first regulation and control structure and the center of the second regulation and control structure are fixedly connected with a pneumatic transmission structure, and the pneumatic transmission structure communicates with the first regulation and control structure and the second regulation and control structure through pipelines; the pneumatic transmission structure is used for guiding air, so that air in the first air tank and the second air tank is guided into the grid air injection seat; and the second regulation and control structure is used for posture regulation work, and a telescopic regulation and control rod and a telescopic sleeve control the ball rod to rotate through a hinged end shaft and an external ring sleeve. Through the arrangement of the structure, the rocket flight attitude adjustment work is facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket flight attitude control, in particular to a rocket flight attitude control device. Background Art

[0002] The rocket's flight attitude control device is a grid rudder, which is a pneumatically controlled device. The grid rudder controls the rocket's flight attitude and landing accuracy by utilizing the thrust of different sizes and directions generated by the airflow acting on the rudder surface. Specifically, the grid rudder is close to the side wall of the rocket when the rocket is launched to avoid affecting the main mission; in the re-entry phase, it needs to be deployed and locked with the rudder shaft. Driven by the servo steering gear and transmission mechanism, it deflects according to the instructions issued by the control system, completing a series of actions such as unlocking-deployment-locking-transmission, thereby controlling the rocket's flight attitude and landing accuracy.

[0003] According to Chinese patent publication number CN119223102A, a sounding rocket axial attitude stabilization control device based on a momentum wheel group is disclosed, which belongs to the field of aerospace equipment technology. The device includes a nine-axis attitude sensor, a high-precision barometer, a first-order servo momentum wheel, a second-order servo momentum wheel and a core controller. The nine-axis attitude sensor, high-precision barometer and core controller are integrated in an aluminum packaging box and connected to the momentum wheel group through aviation plug-in cables. Through the fusion calculation of sensor data, the feedback output is applied to the momentum control wheel group, and the momentum control wheel group outputs the corresponding target torque to achieve stable control of the axial attitude of the aircraft. It has rapid response capability and the advantages of low energy consumption and low deadweight structure, which enhances the accuracy and stability of the aircraft attitude control. By utilizing the advantages of electrical energy storage, the system does not need to be equipped with a pressure tank, achieving a lightweight design, while improving the compactness of the rocket body and the attitude control efficiency.

[0004] At present, the existing rocket flight attitude control device and the above-mentioned case are not convenient for multi-dimensional control when in use, and the structure has poor stability during control. Therefore, improvements are made to address the above problems. Summary of the Invention

[0005] In view of the problems in the prior art, the present invention provides a rocket flight attitude control device.

[0006] The technical solution adopted by the present invention to solve the technical problem is: a rocket flight attitude control device includes a first control structure, a second control structure and a pneumatic transmission structure, the first control structure and the second control structure have the same structure, the first control structure and the second control structure are fixedly connected, the pneumatic transmission structure is fixedly connected to the center of the first control structure and the second control structure, and the pneumatic transmission structure is connected to the first control structure and the second control structure through a pipeline;

[0007] The pneumatic transmission structure is used for gas guiding so that the gas in the first gas tank and the second gas tank is introduced into the grid jet seat;

[0008] The second control structure is used for posture adjustment. The telescopic control rod and telescopic sleeve control the rotation of the ball club through the hinged end shaft and the external ring sleeve, and the electrically controlled telescopic pin rack can limit the ball club. Therefore, under the drive of the stepper motor, the rotation shaft, the docking ball seat, the ball club, the grid jet seat, and the external frame are controlled to rotate and adjust on the external ring sleeve through the bearing ring, and the spring buffer rod, the first buffer damping rod, the adjustment displacement frame, and the second buffer damping rod in the stable combination mechanism are used for shock protection of the stepper motor.

[0009] Specifically, the pneumatic transmission structure includes a first gas tank, a docking longitudinal pipe and a second gas tank. The lower end of the first gas tank is connected to the docking longitudinal pipe, the lower end of the docking longitudinal pipe is connected to the second gas tank, and a control valve seat is provided on the outer periphery of the second gas tank. The second gas tank is connected to the connecting gas pipe through the control valve seat.

[0010] Specifically, the second control structure includes a butt hinge shaft, an outer shell and a telescopic control rod. The butt hinge shaft is fixedly connected to the outer shell, and a telescopic control rod is hingedly provided on the butt hinge shaft. The lower end of the telescopic control rod is telescopically connected to a telescopic sleeve, and the lower end of the outer shell is fixedly connected to the flight control component.

[0011] Specifically, the flight control component includes a first control mechanism, a stabilizing combination mechanism, an adaptor seat and a second control mechanism. The stabilizing combination mechanism is fixedly installed on the upper end of the adaptor seat, the first control mechanism is installed at one end of the stabilizing combination mechanism, and the second control mechanism is installed at the other end of the stabilizing combination mechanism.

[0012] Specifically, the stabilizing combination mechanism includes a fixed sleeve, an adapting connecting shaft, a supporting collar, a first longitudinal rod, a spring buffer rod, a second longitudinal rod, a first buffer damping rod, an adjusting displacement frame and a second buffer damping rod. The side end of the fixed sleeve is fixedly connected to the adapting connecting shaft, the second buffer damping rod is fixedly mounted on the fixed sleeve, the adjusting displacement frame is elastically connected to the second buffer damping rod, the front end of the adjusting displacement frame is elastically connected to the first buffer damping rod, the side end of the adjusting displacement frame is fixed with the second longitudinal rod, the side end of the second longitudinal rod is hingedly provided with a spring buffer rod, the side end of the spring buffer rod is hingedly set to the first longitudinal rod, and the first longitudinal rod is fixedly welded to the supporting collar.

[0013] Specifically, the second regulating mechanism includes a stepping motor, a rotating shaft, a docking ball seat, an electrically controlled telescopic pin holder, a ball rod, an articulated end shaft, a grid jet seat, an external frame, a bearing ring and an external ring sleeve. The side end of the stepping motor is driven and connected to the rotating shaft, and the side end of the rotating shaft is fixedly connected to the docking ball seat. The electrically controlled telescopic pin holder is installed on the docking ball seat. The electrically controlled telescopic pin holder controls the position limit of the ball rod. The side end of the ball rod is fixedly connected to the external frame. The grid jet seat is installed on the external frame. The outer periphery of the side end of the external frame is fixedly connected to the bearing ring. The bearing ring is rotatably connected in the external ring sleeve. The external ring sleeve is fixedly connected to the articulated end shaft. The structural setting of the pneumatic transmission structure facilitates pneumatic regulation. The first gas tank and the second gas tank are connected through a docking longitudinal pipe, which can conduct gas, thereby controlling the direction of gas. Adjustment, the second gas tank is connected with the connecting air pipe through the control valve seat, and the connecting air pipe is connected with the adapter seat, the side end of the adapter seat is connected with the grid jet seat through the pipe body, and the bottom of the grid jet seat is provided with a nozzle for pneumatic spraying to change the overall structural position, and the stepper motor can control the rotation of the docking ball seat through the rotating shaft, and the docking ball seat is connected with the ball rod limit by the electric control telescopic pin rack, so as to control the grid jet seat, the external frame, and the bearing ring to rotate and adjust around the external ring sleeve, and can adjust the position in multiple directions, and the electric control telescopic pin rack can be retracted by electric control to cancel the limit with the ball rod. At this time, the telescopic control rod and the telescopic sleeve can control the displacement of the hinged end shaft, act on the bearing ring and the external ring sleeve, so that the grid jet seat and the external frame rotate around the center of the ball rod and the electric control telescopic pin rack to change the overall tilt position.

[0014] Specifically, the upper end of the hinged end shaft is hinged to the telescopic sleeve, the fixed sleeve frame, the adapter connecting shaft and the adapter sleeve are fixedly connected, and the support sleeve ring is fixedly sleeved to the stepping motor.

[0015] Specifically, the rotating shaft and the adapter socket are set through, the docking hinge shaft is hingedly matched with the hinge end shaft through a telescopic control rod and a telescopic sleeve, the grid jet seat is connected with the adapter socket through a pipe body, and the upper end of the adapter socket is connected with the connecting air pipe.

[0016] Specifically, the side end of the adapting connecting shaft is fixedly connected to the stepping motor, the docking ball seat is used for rotation adjustment of the ball rod, and the top of the docking ball seat is provided with a groove body distributed longitudinally of the ball rod.

[0017] Specifically, the first regulating structure and the second regulating structure are staggered, and adjustments in four directions are performed through the first regulating structure and the second regulating structure. The first buffer damping rod is fixedly connected to the adapter socket.

[0018] Beneficial effects of the present invention:

[0019] 1. The present invention facilitates pneumatic control work through the structural setting of the pneumatic transmission structure. The first gas tank and the second gas tank are connected by a docking longitudinal pipe, which can transmit gas, thereby adjusting the direction of gas control. The second gas tank is connected to the connecting air pipe through the control valve seat, and the connecting air pipe is connected to the adapter seat. The side end of the adapter seat is connected to the grid jet seat through the pipe body. The bottom of the grid jet seat is provided with a nozzle for pneumatic spraying to change the overall structural position. The stepping motor can control the rotation of the docking ball seat through the rotating shaft. The docking ball seat is connected to the ball rod limit by an electrically controlled telescopic pin rack, thereby controlling the grid jet seat, the external frame, and the bearing ring to rotate and adjust around the external ring sleeve, and can adjust the position in multiple directions. The electrically controlled telescopic pin rack can be retracted by electric control to cancel the limit with the ball rod. At this time, the telescopic control rod and the telescopic sleeve can control the displacement of the hinged end shaft, act on the bearing ring and the external ring sleeve, so that the grid jet seat and the external frame rotate around the center of the ball rod and the electrically controlled telescopic pin rack to change the overall tilt position.

[0020] Second, the present invention is used for shock-absorbing protection of stepper motors through the structural setting of a stable combination mechanism. The support collar is fixedly sleeved on the stepper motor, and the upper end of the support collar is fixed to the first longitudinal rod. A spring buffer rod is hingedly arranged on the first longitudinal rod to transmit stress. At the same time, the spring buffer rod is hingedly arranged on the adjustment displacement frame through the second longitudinal rod, and the adjustment displacement frame is buffered on the first buffer damping rod and the second buffer damping rod, thereby improving the protection of the stepper motor and performing shock-absorbing treatment on the stepper motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be further described below with reference to the accompanying drawings and examples.

[0022] Figure 1 This is a schematic diagram of the three-dimensional structure of the main body of the present invention from the front perspective;

[0023] Figure 2 This is a split diagram of the main body of the present invention;

[0024] Figure 3 A perspective view of the pneumatic transmission structure of the present invention;

[0025] Figure 4 is a three-dimensional diagram of the second regulating structure in the present invention;

[0026] Figure 5 This is a split diagram of the second regulatory structure in the present invention;

[0027] Figure 6 A perspective view of the flight control component of the present invention;

[0028] Figure 7 It is a three-dimensional structural diagram of the stable combination mechanism of the present invention;

[0029] Figure 8 It is a three-dimensional structural diagram of the second regulating mechanism in the present invention.

[0030] In the figure: 1-first regulating structure, 2-second regulating structure, 3-pneumatic transmission structure, 4-first gas tank, 5-docking longitudinal pipe, 6-second gas tank, 7-control valve seat, 8-connecting air pipe, 9-docking hinge shaft, 10-housing, 11-telescopic regulating rod, 12-telescopic sleeve, 13-flight regulating component, 14-first regulating mechanism, 15-stabilizing combination mechanism, 16-adapting sleeve, 17-second regulating mechanism, 18-fixing sleeve, 19-adapting connecting shaft, 20-supporting collar, 21-first longitudinal rod, 22-spring buffer rod, 23-second longitudinal rod, 24-first buffer damping rod, 25-adjusting displacement frame, 26-second buffer damping rod, 27-stepping motor, 28-rotating shaft, 29-docking ball seat, 30-electrically controlled telescopic pin frame, 31-ball rod, 32-articulated end shaft, 33-grid jet seat, 34-external frame, 35-bearing ring, 36-external ring sleeve. DETAILED DESCRIPTION

[0031] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0032] The present invention will be further described below with reference to the accompanying drawings.

[0033] Example

[0034] like Figure 1-8 As shown, a rocket flight attitude control device of the present invention includes a first regulating structure 1, a second regulating structure 2 and a pneumatic transmission structure 3. The first regulating structure 1 and the second regulating structure 2 have the same structure and are fixedly connected to each other. The pneumatic transmission structure 3 is fixedly connected to the centers of the first regulating structure 1 and the second regulating structure 2, and the pneumatic transmission structure 3 is connected to the first regulating structure 1 and the second regulating structure 2 through a pipeline.

[0035] The pneumatic transmission structure 3 is used for gas guiding so that the gas in the first gas tank 4 and the second gas tank 6 is introduced into the grid jet seat 33;

[0036] The second control structure 2 is used for posture adjustment. The telescopic control rod 11 and the telescopic sleeve 12 control the rotation of the ball rod 31 through the hinged end shaft 32 and the external ring sleeve 36, and the electrically controlled telescopic pin rack 30 can limit the ball rod 31. Therefore, under the drive of the stepper motor 27, the rotation shaft 28, the docking ball seat 29, the ball rod 31, the grid jet seat 33, and the external rack 34 are controlled to rotate and adjust on the external ring sleeve 36 through the bearing ring 35, and the spring buffer rod 22, the first buffer damping rod 24, the adjustment displacement rack 25, and the second buffer damping rod 26 in the stabilizing combination mechanism 15 are used for shock protection of the stepper motor 27.

[0037] The pneumatic transmission structure 3 includes a first gas tank 4, a docking longitudinal pipe 5 and a second gas tank 6. The lower end of the first gas tank 4 is connected to the docking longitudinal pipe 5, and the lower end of the docking longitudinal pipe 5 is connected to the second gas tank 6. A control valve seat 7 is provided on the outer periphery of the second gas tank 6. The second gas tank 6 is connected to the connecting air pipe 8 through the control valve seat 7. The first regulating structure 1 and the second regulating structure 2 are staggered. The top view shows that the four grid jet seats 33 are located in four directions, so that multi-directional position adjustment can be performed. The gas in the first gas tank 4, the docking longitudinal pipe 5 and the second gas tank 6 can be conducted and guided to the connecting air pipe 8 through the control valve seat 7. The connecting air pipe 8 is connected to the adapter seat 16, and the adapter seat 16 is connected to the grid jet seat 33 through the tube body. The jet is sprayed through the nozzle at the lower end of the grid jet seat 33 to perform position adjustment.

[0038] The second control structure 2 includes a butt hinge shaft 9, an outer shell 10 and a telescopic control rod 11. The butt hinge shaft 9 is fixedly connected to the outer shell 10. The telescopic control rod 11 is hingedly provided on the butt hinge shaft 9. The lower end of the telescopic control rod 11 is telescopically connected to a telescopic sleeve 12. The lower end of the outer shell 10 is fixedly connected to the flight control component 13.

[0039] The flight control component 13 includes a first control mechanism 14, a stabilizing combination mechanism 15, an adapting socket 16 and a second control mechanism 17. The stabilizing combination mechanism 15 is fixedly installed on the upper end of the adapting socket 16. The first control mechanism 14 is installed at one end of the stabilizing combination mechanism 15, and the second control mechanism 17 is installed at the other end of the stabilizing combination mechanism 15.

[0040] The stabilizing assembly mechanism 15 includes a fixed sleeve 18, an adapting connecting shaft 19, a supporting collar 20, a first longitudinal rod 21, a spring buffer rod 22, a second longitudinal rod 23, a first buffer damping rod 24, an adjusting displacement frame 25 and a second buffer damping rod 26. The side end of the fixed sleeve 18 is fixedly connected with the adapting connecting shaft 19, the second buffer damping rod 26 is fixedly mounted on the fixed sleeve 18, the second buffer damping rod 26 is elastically connected with the adjusting displacement frame 25, the front end of the adjusting displacement frame 25 is elastically connected with the first buffer damping rod 24, the side end of the adjusting displacement frame 25 is fixed with a second longitudinal rod 23, the side end of the second longitudinal rod 23 is hinged with a spring buffer rod 22, the side end of the spring buffer rod 22 is hinged with the first longitudinal rod 21, and the first The longitudinal rod 21 is fixedly welded to the support collar 20, and the stepper motor 27 is limited by the support collar 20. The support collar 20 is hinged to the spring buffer rod 22 through the first longitudinal rod 21, and the side end of the spring buffer rod 22 is hinged to the second longitudinal rod 23. When the stepper motor 27 vibrates, the stress can be transmitted through the spring buffer rod 22 and part of the stress can be absorbed at the same time. Then the force is transmitted to the adjustment displacement frame 25. The adjustment displacement frame 25 can move between the first buffer damping rod 24 and the second buffer damping rod 26 to absorb excess stress. The fixed sleeve 18 and the adapter connecting shaft 19 are fixed on the adapter sleeve 16, and the adapter connecting shaft 19 is fixedly connected to the stepper motor 27 to perform support and protection.

[0041] The second regulating mechanism 17 includes a stepping motor 27, a rotating shaft 28, a docking ball seat 29, an electrically controlled telescopic pin holder 30, a ball rod 31, a hinged end shaft 32, a grid jet seat 33, an external frame 34, a bearing ring 35 and an external ring sleeve 36. The side end of the stepping motor 27 is driven and connected to the rotating shaft 28. The side end of the rotating shaft 28 is fixedly connected to the docking ball seat 29. The electrically controlled telescopic pin holder 30 is installed on the docking ball seat 29. The electrically controlled telescopic pin holder 30 controls the limit of the ball rod 31. The side end of the ball rod 31 is fixedly connected to the external The frame 34 is provided with a grid jet seat 33 on the external frame 34, and the outer periphery of the side end of the external frame 34 is fixedly connected with a bearing ring 35, which is rotatably connected in the external ring sleeve 36, and the external ring sleeve 36 is fixedly connected with a hinged end shaft 32. The first regulating structure 1, the second regulating structure 2, and the pneumatic transmission structure 3 are fixedly set. When the rocket reaches the specified position, the telescopic regulating rod 11 and the telescopic sleeve 12 are regulated at this time. By telescopic control, the position of the hinged end shaft 32 and the external ring sleeve 36 is changed. When the ball rod 31 is in the horizontal state, the extension of the ball rod 31 can be controlled by the electric telescopic pin holder 30 to limit the locking of the ball rod 31, so that the electric telescopic pin holder 30, the docking ball seat 29 and the ball rod 31 are fixed as a whole. The upper end of the telescopic control rod 11 is hinged to the docking hinge shaft 9, which can change the angle when it is extended and retracted, so that the grid jet seat 33 and the external frame 34 reach the horizontal position, and the stepper motor 27 can be started. The stepper motor 27 controls The rotating shaft 28 rotates, driving the docking ball seat 29 to rotate accordingly, and the docking ball seat 29 is limitedly connected to the ball rod 31 through the electrically controlled telescopic pin bracket 30, so that the grid jet seat 33 and the external frame 34 rotate under the drive of the stepper motor 27, so that the external frame 34 drives the bearing ring 35 to rotate on the external ring sleeve 36. At this time, the grid jet seat 33 and the external frame 34 rotate around the axis of the external ring sleeve 36, controlling the position of the grid jet seat 33 so that the grid jet seat 33 reaches the specified position.

[0042] The upper end of the hinged end shaft 32 is hinged to the telescopic sleeve 12 , the fixed sleeve frame 18 and the adapting connecting shaft 19 are fixedly connected to the adapting sleeve 16 , and the supporting collar 20 is fixedly sleeved to the stepping motor 27 .

[0043] The rotating shaft 28 is connected to the adapter socket 16, and the hinge shaft 9 is hingedly matched with the hinge end shaft 32 through the telescopic control rod 11 and the telescopic sleeve 12. The grid jet seat 33 is connected to the adapter socket 16 through the pipe body, and the upper end of the adapter socket 16 is connected to the connecting air pipe 8.

[0044] The side end of the adapter connecting shaft 19 is fixedly connected to the stepping motor 27, and the docking ball seat 29 is used for rotation adjustment of the ball rod 31, and the top of the docking ball seat 29 is provided with a groove body in which the ball rod 31 is longitudinally distributed.

[0045] The first regulating structure 1 and the second regulating structure 2 are staggered, and adjustments in four directions are performed through the first regulating structure 1 and the second regulating structure 2 . The first buffer damping rod 24 is fixedly connected to the adapting seat 16 .

[0046] The working principle is as follows: when in use, the first regulating structure 1, the second regulating structure 2, and the pneumatic transmission structure 3 are fixedly arranged. When the rocket reaches the designated position, the telescopic regulating rod 11 and the telescopic sleeve 12 are regulated at this time. By telescopic control, the positions of the hinge end shaft 32 and the external ring sleeve 36 are changed. At this time, the ball rod 31 is not locked with the electrically controlled telescopic pin holder 30. When the ball rod 31 is in a horizontal state, the extension can be controlled by the electrically controlled telescopic pin holder 30 to limit the ball rod 31, so that the electrically controlled telescopic pin holder 30, the docking ball seat 29, and the ball rod 31 are fixed as a whole. The upper end of the telescopic regulating rod 11 is hinged to the docking hinge shaft 9, and can change its angle when telescoping, so that the grid jet seat 33 and the external frame 34 reach the horizontal position.

[0047] Afterwards, the stepper motor 27 can be started, and the stepper motor 27 controls the rotation of the rotating shaft 28, driving the docking ball seat 29 to rotate accordingly, and the docking ball seat 29 is connected to the ball rod 31 through the electrically controlled telescopic pin bracket 30, so that the grid jet seat 33 and the external frame 34 rotate under the drive of the stepper motor 27, so that the external frame 34 drives the bearing ring 35 to rotate on the external ring sleeve 36. At this time, the grid jet seat 33 and the external frame 34 rotate around the axis of the external ring sleeve 36, controlling the position of the grid jet seat 33, so that the grid jet seat 33 reaches the specified position;

[0048] Among them, the stepping motor 27 is limited by the support collar 20, and the support collar 20 is hinged to the spring buffer rod 22 through the first longitudinal rod 21. The side end of the spring buffer rod 22 is hinged to the second longitudinal rod 23. When the stepping motor 27 vibrates, the stress can be transmitted through the spring buffer rod 22 and part of the stress is absorbed at the same time. Then the force is transmitted to the adjustment displacement frame 25. The adjustment displacement frame 25 can move between the first buffer damping rod 24 and the second buffer damping rod 26 to absorb the excess stress. The fixed sleeve 18 and the adapting connecting shaft 19 are fixed on the adapting sleeve 16, and the adapting connecting shaft 19 is fixedly connected to the stepping motor 27 to perform support and protection work;

[0049] The first regulating structure 1 and the second regulating structure 2 are staggered, and the positions of the four grid jet seats 33 are in four directions when viewed from above, so that multi-directional position adjustment can be performed. The gas in the first gas tank 4, the docking longitudinal pipe 5, and the second gas tank 6 can be conducted and guided to the connecting air pipe 8 through the control valve seat 7. The connecting air pipe 8 is connected to the adapter seat 16, and the adapter seat 16 is connected to the grid jet seat 33 through the pipe body. The jet is sprayed through the nozzle at the lower end of the grid jet seat 33 to perform position adjustment and complete the work.

[0050] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A rocket flight attitude control device, characterized by: The invention comprises a first regulating structure (1), a second regulating structure (2) and a pneumatic transmission structure (3), wherein the first regulating structure (1) and the second regulating structure (2) have the same structure, the first regulating structure (1) and the second regulating structure (2) are fixedly connected, the centers of the first regulating structure (1) and the second regulating structure (2) are fixedly connected with the pneumatic transmission structure (3), and the pneumatic transmission structure (3) is connected to the first regulating structure (1) and the second regulating structure (2) through a pipeline; The pneumatic transmission structure (3) is used for gas guiding so that the gas in the first gas tank (4) and the second gas tank (6) is introduced into the grid jet seat (33); The second regulating structure (2) is used for posture adjustment. The telescopic regulating rod (11) and the telescopic sleeve (12) control the rotation of the ball rod (31) through the hinged end shaft (32) and the external ring sleeve (36), and the electrically controlled telescopic pin frame (30) can limit the position of the ball rod (31). Therefore, under the drive of the stepping motor (27), the rotating shaft (28), the docking ball seat (29), the ball rod (31), the grid jet seat (33), and the external frame (34) are controlled to rotate and adjust on the external ring sleeve (36) through the bearing ring (35), and the spring buffer rod (22), the first buffer damping rod (24), the adjustment displacement frame (25), and the second buffer damping rod (26) in the stabilizing combination mechanism (15) are used for shock protection of the stepping motor (27).

2. A rocket flight attitude control device according to claim 1, characterized in that: The pneumatic transmission structure (3) comprises a first gas tank (4), a docking longitudinal pipe (5) and a second gas tank (6); the lower end of the first gas tank (4) is connected to the docking longitudinal pipe (5); the lower end of the docking longitudinal pipe (5) is connected to the second gas tank (6); a control valve seat (7) is provided on the outer periphery of the second gas tank (6); and the second gas tank (6) is connected to the connecting gas pipe (8) via the control valve seat (7).

3. A rocket flight attitude control device according to claim 2, characterized in that: The second control structure (2) comprises a butt hinge shaft (9), a housing (10) and a telescopic control rod (11); the housing (10) is fixedly connected to the butt hinge shaft (9); the butt hinge shaft (9) is hingedly provided with a telescopic control rod (11); the lower end of the telescopic control rod (11) is telescopically connected to a telescopic sleeve (12); and the lower end of the housing (10) is fixedly connected to a flight control component (13).

4. A rocket flight attitude control device according to claim 3, characterized in that: The flight control component (13) comprises a first control mechanism (14), a stabilizing combination mechanism (15), an adapting seat (16) and a second control mechanism (17); the stabilizing combination mechanism (15) is fixedly mounted on the upper end of the adapting seat (16); one end of the stabilizing combination mechanism (15) is limitedly mounted with the first control mechanism (14); the other end of the stabilizing combination mechanism (15) is limitedly mounted with the second control mechanism (17).

5. A rocket flight attitude control device according to claim 4, characterized in that: The stabilizing assembly mechanism (15) comprises a fixed sleeve (18), an adapting connecting shaft (19), a supporting collar (20), a first longitudinal rod (21), a spring buffer rod (22), a second longitudinal rod (23), a first buffer damping rod (24), an adjusting displacement frame (25) and a second buffer damping rod (26). The side end of the fixed sleeve (18) is fixedly connected to the adapting connecting shaft (19), the second buffer damping rod (26) is fixedly mounted on the fixed sleeve (18), the adjusting displacement frame (25) is elastically connected to the second buffer damping rod (26), the front end of the adjusting displacement frame (25) is elastically connected to the first buffer damping rod (24), the side end of the adjusting displacement frame (25) is fixedly provided with the second longitudinal rod (23), the side end of the second longitudinal rod (23) is hingedly provided with the spring buffer rod (22), the side end of the spring buffer rod (22) is hingedly arranged with the first longitudinal rod (21), and the first longitudinal rod (21) is fixedly welded to the supporting collar (20).

6. A rocket flight attitude control device according to claim 5, characterized in that: The second regulating mechanism (17) comprises a stepping motor (27), a rotating shaft (28), a docking ball seat (29), an electrically controlled telescopic pin holder (30), a ball rod (31), a hinged end shaft (32), a grid jet seat (33), an external frame (34), a bearing ring (35) and an external ring sleeve (36), wherein the side end of the stepping motor (27) is drivingly connected to the rotating shaft (28), the side end of the rotating shaft (28) is fixedly connected to the docking ball seat (29), and the docking ball seat (29) is equipped with an electric-controlled telescopic pin frame (30), which controls the position limit of the ball rod (31). The side end of the ball rod (31) is fixedly connected to an external frame (34), and a grid jet seat (33) is installed on the external frame (34). The outer periphery of the side end of the external frame (34) is fixedly connected to a bearing ring (35), and the bearing ring (35) is rotatably connected in an external ring sleeve (36). The external ring sleeve (36) is fixedly connected to a hinged end shaft (32).

7. A rocket flight attitude control device according to claim 6, characterized in that: The upper end of the hinged end shaft (32) is hingedly connected to the telescopic sleeve (12), the fixed sleeve frame (18), the adapting connecting shaft (19) and the adapting sleeve (16) are fixedly connected, and the supporting collar (20) is fixedly sleeved to the stepping motor (27).

8. A rocket flight attitude control device according to claim 7, characterized in that: The rotating shaft (28) is connected to the adapting seat (16), the butt hinge shaft (9) is hingedly matched with the hinge end shaft (32) through the telescopic regulating rod (11) and the telescopic sleeve (12), the grid jet seat (33) is connected to the adapting seat (16) through the pipe body, and the upper end of the adapting seat (16) is connected to the communicating air pipe (8).

9. The rocket flight attitude control device according to claim 8, characterized in that: The side end of the adapting connecting shaft (19) is fixedly connected to the stepping motor (27), the docking ball seat (29) is used for rotation adjustment of the ball rod (31), and the top of the docking ball seat (29) is provided with a groove body distributed longitudinally of the ball rod (31).

10. The rocket flight attitude control device according to claim 9, characterized in that: The first regulating structure (1) and the second regulating structure (2) are staggered, and four directions of adjustment are performed through the first regulating structure (1) and the second regulating structure (2). The first buffer damping rod (24) is fixedly connected to the adapting seat (16).

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