Solid rocket engine flap structure attitude adjusting structure and method

Abstract

The invention relates to the technical field of aerospace attitude and orbit control power, in particular to a solid rocket engine flap structure attitude adjusting structure and method.The adjusting structure comprises a spoiler and further comprises a connecting rod mechanism and a driving mechanism; the spoiler is in transmission connection with the driving mechanism through the connecting rod mechanism; the driving mechanism drives the connecting rod mechanism to drive the spoiler to deflect by a certain angle. The thrust deflection angle is controlled by controlling the deflection angle of the spoiler, and vector control over the thrust of the engine is achieved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace attitude and orbit control power technology, and in particular to a solid rocket engine flap structure attitude adjustment structure and method. Background Art

[0002] At present, countries around the world have stepped up their exploration of space and launched hundreds of satellites. At the same time, this has also led to the generation of more space debris. This poses a high risk to satellites in orbit. Once a satellite collides with other satellites or space debris, it will cause catastrophic damage to the satellite and make it unable to continue to work normally. Therefore, the satellite needs to be controlled to leave the orbit, which requires an active propulsion system to achieve this by lowering the orbit perigee to below 120 kilometers to ensure re-entry into the atmosphere.

[0003] In this specific application, TVC performance is critical because a misoriented satellite may not set the correct orbit and may leave the satellite in an ordinary operational orbit instead of entering a graveyard orbit or a lower orbit, increasing the possibility of collision with operational spacecraft and creating space debris. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a solid rocket engine flap structure attitude adjustment structure and method. Compared with other solutions, the flap structure can reduce the potential mass of the entire system, only move the flap instead of the entire engine, the operability is stronger and there is no need to produce a specific model of engine, which is more economical.

[0005] The first object of the present invention is to provide a solid rocket engine flap structure attitude adjustment structure, including a spoiler, characterized in that it also includes a connecting rod mechanism and a driving mechanism; The spoiler is transmission-connected to the driving mechanism via the connecting rod mechanism; The driving mechanism drives the connecting rod mechanism to drive the spoiler to deflect a certain angle.

[0006] Preferably, the connecting rod mechanism comprises a first connecting rod and a second connecting rod connected in sequence. One end of the first connecting rod away from the second connecting rod is connected to the spoiler; One end of the second connecting rod away from the first connecting rod is transmission-connected to the driving mechanism; A shaft body is passed through the connection between the first connecting rod and the second connecting rod. The shaft body is rotatably connected to the connection, and both ends of the shaft body are fixed to the solid rocket shell through connecting parts.

[0007] Preferably, the connecting rod mechanism is connected to the driving mechanism via a gear transmission mechanism, and the gear transmission mechanism comprises: A first gear fixedly connected to one end of the second connecting rod away from the first connecting rod, and a second gear sleeved on the output shaft of the driving mechanism; The first gear meshes with the second gear; The output shaft of the driving mechanism rotates to drive the second gear to rotate, and at the same time drives the first gear to rotate around the shaft; When the first gear rotates, the spoiler connected by the connecting rod mechanism is deflected by a certain angle.

[0008] Preferably, the drive mechanism is fixed to the solid rocket casing.

[0009] Preferably, the connecting rod mechanism comprises two groups of first connecting rods and second connecting rods connected in sequence, each group comprising: One end of the first connecting rod away from the second connecting rod is connected to the spoiler; one end of the second connecting rod away from the first connecting rod is transmission-connected to the driving mechanism; In the two groups, the connection between the first connecting rod and the second connecting rod is provided with a common shaft body; The shaft body is rotatably connected to the connection point in each group, and the two ends of the shaft body are fixed to the solid rocket shell through connecting pieces.

[0010] Preferably, the driving mechanism is a stepping motor.

[0011] The second object of the present invention is to provide a solid rocket engine flap structure attitude adjustment method, using the solid rocket engine flap structure attitude adjustment structure, comprising: After receiving the required change in angle of the spoiler, the driving mechanism rotates a corresponding angle, and drives the spoiler to deflect a certain angle through the connecting rod mechanism.

[0012] The third object of the present invention is to provide an application of an adjustment structure in a spacecraft.

[0013] The present invention has at least the following beneficial effects: The present invention provides a solid rocket engine flap structure attitude adjustment structure and method. The adjustment structure controls the deflection angle of the thrust by controlling the deflection angle of the spoiler, thereby realizing vector control of the engine thrust.

[0014] The present invention is different from other attitude adjustment systems and has a simple structure. It does not require the design of a new solid rocket engine power system. Thrust control can be achieved by simply installing the flap structure outside the engine, thus saving costs.

[0015] Combining the flap structure with the solid rocket engine power system and the pulse ignition of the solid rocket engine can provide the satellite with high thrust for a short period of time, enabling the satellite to quickly avoid obstacles and change orbits. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Overall schematic diagram of the solid rocket motor flap structure system.

[0017] Figure 2 Right view of the solid rocket motor flap structure system. DETAILED DESCRIPTION

[0018] In order to illustrate the technical means and effects adopted by the present invention to achieve the predetermined purpose of the invention, the following is a detailed description in conjunction with embodiments.

[0019] The purpose of the present invention is to provide a method for adjusting the attitude of a flap structure of a solid rocket engine. The method comprises a spoiler, a connecting rod mechanism, a gear transmission mechanism, a stepping motor, and a solid rocket engine power system. The spoiler, the connecting rod mechanism, the gear transmission mechanism, and the stepping motor constitute a flap structure. The spoiler is fixed on the connecting rod mechanism and then connected to the gear mechanism, and the stepping motor can control the spoiler.

[0020] To achieve the above purpose, see Figure 1~2 As shown, the present invention provides a solid rocket engine flap structure attitude adjustment structure, including a spoiler 2, a connecting rod mechanism 3 and a driving mechanism; The spoiler 2 is connected to the driving mechanism through the connecting rod mechanism 3; the driving mechanism drives the connecting rod mechanism 3 to drive the spoiler 2 to deflect a certain angle.

[0021] The present invention controls the deflection angle of the thrust by controlling the deflection angle of the spoiler, thereby realizing vector control of the thrust of the engine.

[0022] In order to realize the transmission connection between the spoiler 2 and the driving mechanism through the connecting rod mechanism 3, the connecting rod mechanism 3 is provided to include a first connecting rod 31 and a second connecting rod 32 which are connected in sequence; wherein, one end of the first connecting rod 31 away from the second connecting rod 32 is connected to the spoiler 2; one end of the second connecting rod 32 away from the first connecting rod 31 is transmission connected to the driving mechanism; a shaft body 34 is provided at the connection between the first connecting rod 31 and the second connecting rod 32, the shaft body 34 is rotationally connected to the connection, and both ends of the shaft body 34 are fixed to the solid rocket shell through a connecting piece. To this end, the second connecting rod 32 of the connecting rod mechanism 3 and the first connecting rod 31 which are connected to the connecting rod 3 are driven to rotate by the driving mechanism, so as to realize the deflection of the spoiler 2 by a certain angle.

[0023] In order to realize the transmission connection, the connecting rod mechanism 3 is connected to the driving mechanism through a gear transmission mechanism, and the gear transmission mechanism includes: a first gear 33 fixedly connected to the end of the second connecting rod 32 away from the first connecting rod 31, and a second gear 13 sleeved on the output shaft of the driving mechanism; the first gear 33 is meshed with the second gear 13; the second gear 13 is driven to rotate by the output shaft of the driving mechanism, and the first gear 33 is driven to rotate around the shaft body 34; while the first gear 33 rotates, the spoiler 2 connected through the connecting rod mechanism 3 is deflected by a certain angle. To this end, the spoiler 2 is further connected to the driving mechanism through the connecting rod mechanism 3.

[0024] It should be noted that the driving mechanism is fixed to the solid rocket shell, and the two ends of the shaft 34 are fixed to the solid rocket shell through connecting parts. For this reason, when the connecting rod mechanism is driven by the driving mechanism, the second connecting rod and the first connecting rod rotate around the shaft 34, mainly utilizing the lever principle, that is, applying force to the end of the second connecting rod away from the first connecting rod, so that the end of the first connecting rod connected to the spoiler can be rotated around the shaft 34, so that the spoiler is deflected by a certain angle.

[0025] In order to stabilize the deflection of the spoiler, the connecting rod mechanism 3 is provided to include two groups of first connecting rods 31 and second connecting rods 32 connected in sequence, each group including: One end of the first connecting rod 31 away from the second connecting rod 32 is connected to the spoiler 2; one end of the second connecting rod 32 away from the first connecting rod 31 is transmission-connected to the driving mechanism; In the two groups, the connection between the first connecting rod 31 and the second connecting rod 32 is penetrated by a common shaft 34; The shaft body 34 is rotatably connected to the connection in each group, and both ends of the shaft body 34 are fixed to the solid rocket shell through a connecting piece. It should be noted that the first connecting rod 31 and the second connecting rod 32 of the two groups connected in sequence are arranged in parallel.

[0026] At the same time, each group of connecting rod mechanisms 3 is connected to the driving mechanism through a gear transmission mechanism. The gear transmission mechanism of each group includes: a first gear 33 fixedly connected to the end of the second connecting rod 32 away from the first connecting rod 31, and a second gear 13 sleeved on the output shaft of the driving mechanism; the first gear 33 is meshed with the second gear 13; it should be noted that two second gears 13 are sleeved on the output shaft of the driving mechanism.

[0027] The output shaft of the driving mechanism rotates to drive the two second gears 13 to rotate, and at the same time drives the two first gears 33 to rotate around the shaft 34; while the two first gears 33 rotate, the spoiler 2 connected by the connecting rod mechanism 3 is deflected by a certain angle. In order to ensure the stability of the two first gears 33, a connecting piece is provided between the two first gears 33, so that the two first gears 33 can move simultaneously.

[0028] In this embodiment, the driving mechanism is a stepping motor.

[0029] The present invention provides a solid rocket engine flap structure attitude adjustment method, which adopts the above-mentioned solid rocket engine flap structure attitude adjustment structure, comprising: After receiving the required change in angle of the spoiler, the driving mechanism rotates the corresponding angle, and drives the spoiler 2 to deflect a certain angle through the connecting rod mechanism 3.

[0030] The invention provides an application of an adjustment structure in a spacecraft.

[0031] Among them, the working process of the solid rocket engine flap structure is as follows: When the spacecraft needs to avoid obstacles and change its trajectory quickly in space, the flap system is activated to calculate the angle of each spoiler. The stepper motor rotor rotates to the corresponding angle. The gear transmission mechanism and the connecting rod mechanism can control the spoiler to deflect to a certain angle. Then the solid rocket engine is ignited, and the engine generates a short-term high thrust. The gas is ejected from the nozzle and passes through the spoiler. The gas direction is deflected and the thrust is also deflected, so the spacecraft can achieve rapid obstacle avoidance and rapid trajectory change.

[0032] In summary, the present invention can be directly installed outside the solid rocket engine, and the stepper motor can control the gear to rotate to a specific angle. Through the gear transmission mechanism and the connecting rod mechanism, the spoiler can be controlled to deflect to a desired angle. The gas is ejected from the nozzle and passes through the spoiler, and the airflow is deflected, thereby deflecting the thrust generated by the engine, achieving the purpose of controlling its attitude, and thus realizing the deorbit of the satellite.

[0033] The spoiler is mainly used to change the thrust direction and is connected to the stepper motor through a connecting rod mechanism and a gear transmission mechanism. The connecting rod mechanism connects the spoiler and the gear transmission mechanism to transmit power.

[0034] The gear transmission mechanism uses a gear pair to transmit the power from the stepper motor.

[0035] The stepper motor can convert the electrical pulse signal into the corresponding angular displacement or linear displacement. Each time a pulse signal is input, the rotor rotates an angle or moves forward one step. The output angular displacement or linear displacement is proportional to the number of input pulses, and the speed is proportional to the pulse frequency. Therefore, the stepper motor can be used to control the deflection angle of the spoiler, and then control the engine thrust.

[0036] The solid rocket engine power system can provide short-term thrust for the satellite, and combined with the flap structure, it can achieve rapid orbit changes of the satellite.

[0037] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A solid rocket engine flap structure attitude adjustment structure, comprising a spoiler (2), characterized in that: It also includes a connecting rod mechanism (3) and a driving mechanism; The spoiler (2) is transmission-connected to the driving mechanism via the connecting rod mechanism (3); The driving mechanism drives the connecting rod mechanism (3) to drive the spoiler (2) to deflect by a certain angle.

2. The solid rocket engine flap structure attitude adjustment structure according to claim 1, characterized in that: The connecting rod mechanism (3) comprises a first connecting rod (31) and a second connecting rod (32) which are connected in sequence. One end of the first connecting rod (31) away from the second connecting rod (32) is connected to the spoiler (2); One end of the second connecting rod (32) away from the first connecting rod (31) is transmission-connected to the driving mechanism; A shaft body (34) is provided at the connection point between the first connecting rod (31) and the second connecting rod (32), the shaft body (34) is rotatably connected to the connection point, and both ends of the shaft body (34) are fixed to the solid rocket casing via connecting pieces.

3. The solid rocket engine flap structure attitude adjustment structure according to claim 2, characterized in that: The connecting rod mechanism (3) is connected to the driving mechanism via a gear transmission mechanism, and the gear transmission mechanism comprises: A first gear (33) fixedly connected to one end of the second connecting rod (32) away from the first connecting rod (31), and a second gear (13) sleeved on the output shaft of the driving mechanism; The first gear (33) meshes with the second gear (13); The output shaft of the driving mechanism rotates to drive the second gear (13) to rotate, and at the same time drives the first gear (33) to rotate around the shaft (34); When the first gear (33) rotates, the spoiler (2) connected via the connecting rod mechanism (3) is deflected by a certain angle.

4. The solid rocket engine flap structure attitude adjustment structure according to claim 3, characterized in that: The driving mechanism is fixed on the solid rocket casing.

5. The solid rocket engine flap structure attitude adjustment structure according to claim 2, characterized in that: The connecting rod mechanism (3) comprises two groups of first connecting rods (31) and second connecting rods (32) which are connected in sequence, and each group comprises: One end of the first connecting rod (31) away from the second connecting rod (32) is connected to the spoiler (2); and one end of the second connecting rod (32) away from the first connecting rod (31) is transmission-connected to the driving mechanism; In the two groups, a common shaft (34) is provided at the connection point between the first connecting rod (31) and the second connecting rod (32); The shaft body (34) is rotatably connected to the connection point in each group, and both ends of the shaft body (34) are fixed to the solid rocket shell through connecting pieces.

6. The solid rocket engine flap structure attitude adjustment structure according to claim 1, characterized in that: The driving mechanism is a stepping motor.

7. A method for adjusting the attitude of a flap structure of a solid rocket engine, characterized in that: The solid rocket engine flap structure attitude adjustment structure according to claim 1 comprises: After receiving the required change in angle of the spoiler, the driving mechanism rotates to a corresponding angle, and drives the spoiler (2) to deflect to a certain angle through the connecting rod mechanism (3).

8. Use of the regulating structure according to any one of claims 1 to 6 in a spacecraft.

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