A rotating servo thruster and attitude control system

Abstract

The application discloses a rotary servo thruster and an attitude control system, and belongs to the technical field of aircraft propulsion, which comprises a first connecting piece, a first accommodating ring and a second accommodating ring are provided side by side on the first connecting piece, a steering assembly is arranged in the first accommodating ring, and a driving assembly is arranged in the second accommodating ring, the steering assembly comprises a driving mechanism arranged along a first direction, and an output shaft of the driving mechanism is connected with a driving gear; the driving assembly comprises a first shell, the first shell is provided with a fuel inlet along a first direction and a fuel outlet along a second direction, an outer gear ring is arranged outside the first shell, and the driving gear is rotatably engaged with the outer gear ring. The rotary servo thruster in the application can correspondingly adjust the thrust direction and the thrust size of the rotary servo thruster, so that the attitude control of the aircraft is realized, the overall quality of the existing aircraft attitude control system is greatly reduced, the number of thrusters arranged is reduced, and the reliability of the attitude control is improved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft propulsion technology, specifically relating to a rotary servo thruster and attitude control system. Background Technology

[0002] Traditional aircraft attitude control systems rely on solenoid valves for on / off control. Traditional thrusters have a fixed jet direction. In order to control the pitch, yaw, and roll attitudes of the aircraft, it is usually necessary to arrange 6 or 8 sets of thrusters with different exhaust directions. By controlling the opening and closing of solenoid valves in different directions, different attitude control requirements can be achieved.

[0003] From a reliability model perspective, this arrangement of multiple thrusters in the control system is a multi-model series configuration, which limits the reliability of the attitude control system. Furthermore, the multiple thrusters significantly increase the weight of the entire attitude control system, making it difficult to improve its impulse-to-mass ratio. Additionally, the solenoid valves, through the switching of flow paths, must directly withstand the thermal environment of the combustion gases. To accommodate the operating temperature of the solenoid valves, the attitude control system can only use low-temperature propellants, further reducing the impulse-to-mass ratio and hindering aircraft propulsion. Summary of the Invention

[0004] In view of one or more of the above-mentioned defects or improvement needs of the prior art, the present invention provides a rotary servo thruster to solve the problem that existing aircraft need to be equipped with multiple sets of thrusters for attitude changes.

[0005] To achieve the above objectives, the present invention provides a rotary servo thruster, comprising: A first connector, wherein a first receiving ring and a second receiving ring are arranged side by side on the first connector; A steering component is fitted inside the first receiving ring, and a driving component is fitted inside the second receiving ring; The steering assembly is arranged along a first direction, and the steering assembly includes a drive mechanism arranged along the first direction, with a drive gear rotatably connected to the output shaft of the drive mechanism; The drive assembly includes a first housing, one end of which is provided with a fuel inlet along a first direction, and one end of which is provided with a fuel outlet along a second direction. An external gear ring is fitted around the outside of the first housing. The drive gear meshes with the external gear ring, and the first housing can rotate under the drive gear, so as to change the gas outlet direction of the fuel outlet.

[0006] As a further improvement of the present invention, the first connecting member includes a first sleeve, on which a second receiving ring is provided, the first housing is partially sleeved inside the first sleeve at one end facing the fuel inlet, and a sealing member is provided on the outer periphery of the first housing to seal the gap between the first housing and the first sleeve.

[0007] As a further improvement of the present invention, a first stepped hole and a second stepped hole are provided inside the first sleeve along the first direction. The sealing element is provided at the first stepped hole, and the rotating element is provided at the second stepped hole; The rotating component includes a bushing sleeved on the outer wall of the first housing. One end of the bushing abuts against the side wall of the outer gear ring along the first direction, and the other end is provided with a pressure screw. A rotating bearing is fitted around the outer circumference of the bushing, and the outer ring of the rotating bearing abuts against the inner wall of the second stepped hole.

[0008] As a further improvement of the present invention, one side of the rotating bearing along the first direction is flush with the end face of the first sleeve along the first direction, and a bearing cover is coaxially sleeved on the first housing. The bearing cover abuts against the rotating bearing and the end face of the first sleeve, and the bearing cover is threadedly connected to the first sleeve.

[0009] As a further improvement of the present invention, a limiting ring is also sleeved on the outer periphery of the first housing, the outer wall of the limiting ring abuts against the inner wall of the second stepped hole, and the side wall of the limiting ring along the first direction abuts against the stepped surface formed by the first stepped hole and the second stepped hole.

[0010] As a further improvement of the present invention, the first housing is arranged in a "┌" shape, and a first heat insulation layer is provided inside the first housing, which is wrapped around the inner wall of the first housing; a nozzle is connected to the end of the first housing facing the fuel outlet, and a second heat insulation layer is provided on the inner wall of the nozzle; a throat liner is provided at the junction of the first heat insulation layer and the second heat insulation layer, and the throat liner is threadedly connected to the inner wall of the nozzle.

[0011] As a further improvement of the present invention, a third heat insulation layer is provided at the end of the first housing facing the fuel inlet. The third heat insulation layer is arranged in a stepped manner at the end facing the first heat insulation layer. The third heat insulation layer extends into the first heat insulation layer in a first direction and abuts against the inner wall of the first housing in a second direction.

[0012] As a further improvement of the present invention, the sealing element includes a graphite sealing gasket and an isolation gasket stacked sequentially along a first direction.

[0013] As a further improvement of the present invention, the steering assembly and the drive assembly have a gap of 0.02mm to 0.05mm along the second direction, and the steering assembly and the drive assembly have a gap of 0.05mm to 0.1mm along the first direction.

[0014] This application also includes an attitude control system, which includes: A cover plate, which is radially symmetrically equipped with two rotary servo thrusters, and a gas generator is connected to the fuel inlet of the first housing. The gas generator is fitted with a gas generator bracket around its outer periphery, and the gas generator bracket is connected to the cover plate.

[0015] The aforementioned improved technical features can be combined with each other as long as they do not conflict with each other.

[0016] In summary, the beneficial effects of the above-described technical solutions conceived by this invention compared with the prior art include: (1) The rotary servo thruster of the present invention connects the steering assembly and the drive assembly through a first connector, and through the cooperation of the drive gear and the external gear ring, the steering assembly can drive the drive assembly to rotate. The rotation of the drive assembly causes its fuel outlet to change accordingly, thereby changing the thrust direction of the rotary servo thruster. When the rotary servo thruster is used to drive the aircraft for attitude control, the attitude control of the aircraft is achieved by adjusting the thrust direction and thrust magnitude of the rotary servo thruster accordingly. This greatly reduces the overall mass of the existing aircraft attitude control system, reduces the number of thrusters, and improves the reliability of attitude control.

[0017] (2) The rotary servo thruster of the present invention, by setting the first connecting member as a combination of a first sleeve and a first receiving ring, and sleeves the first housing of the drive assembly inside the first sleeve, enables the drive assembly to rotate stably within the first sleeve, thus ensuring that the thrust direction of the rotary servo thruster is stable and controllable. At the same time, a sealing element is also provided between the first sleeve and the first housing. By adjusting the tightness of the seal, the drive assembly can rotate reliably, and the smoothness of the thrust direction change of the thruster can be improved.

[0018] (3) The rotary servo thruster of the present invention ensures stable rotation between the first housing and the first sleeve by sleeved with bushing, pressure screw, rotating bearing, etc. on the outer wall of the first housing, ensuring stable adjustment of the thrust direction of the drive component, and realizing precise control of the thrust direction.

[0019] (4) The rotary servo thruster of the present invention arranges a first heat insulation layer and a third heat insulation layer inside the first housing, and the first heat insulation layer and the third heat insulation layer form three gap mating surfaces at the contact end face. It forms a triple gap in the radial, axial and radial directions inside the first housing, and forms air isolation through the gap to reduce the heat conducted by the gas to the first housing. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the rotary servo thruster in an embodiment of the present invention; Figure 2 This is a cross-sectional structural diagram of the rotary servo thruster in an embodiment of the present invention; Figure 3 This is a cross-sectional structural diagram of the first housing in an embodiment of the present invention; Figure 4 This is a cross-sectional structural diagram of the first sleeve in an embodiment of the present invention; Figure 5 This is a cross-sectional structural diagram of the sealing element in an embodiment of the present invention; Figure 6 This is a schematic diagram of the overall structure of the attitude control system in an embodiment of the present invention; Figure 7 This is a schematic diagram of the azimuth angle of the rotary servo thruster under different attitude control conditions in the attitude control system of this invention.

[0021] In all the accompanying drawings, the same reference numerals denote the same technical features, specifically: 1. First connecting member; 2. Drive mechanism; 3. Drive gear; 4. First housing; 5. External gear ring; 6. Fuel inlet; 7. Fuel outlet; 8. First sleeve; 9. Seal; 10. Bushing; 11. Pressure screw; 12. Rotary bearing; 13. Bearing cover; 14. Limiting ring; 15. First heat insulation layer; 16. Nozzle; 17. Second heat insulation layer; 18. Throat liner; 19. Third heat insulation layer; 20. Graphite sealing gasket; 21. Isolation gasket; 22. Cover plate; 23. Gas generator; 24. Gas generator bracket. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0023] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0025] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0026] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0027] Example: Please see Figures 1-7In a preferred embodiment of the present invention, the rotary servo thruster includes a first connector 1, on which a first receiving ring and a second receiving ring are arranged side by side. A steering component is fitted inside the first receiving ring, and a driving component is fitted inside the second receiving ring. The steering component is arranged along a first direction and includes a driving mechanism 2 arranged along the first direction, and a driving gear 3 is rotatably connected to the output shaft of the driving mechanism 2. The driving component includes a first housing 4, with a fuel inlet 6 at one end along the first direction and a fuel outlet 7 at one end along the second direction. An external gear ring 5 is also fitted outside the first housing 4, and the driving gear 3 rotatably meshes with the external gear ring 5, so that the first housing 4 can rotate under the drive of the driving gear 3, thereby changing the outlet direction of the fuel outlet 7, and thus realizing the change of the thrust direction of the rotary servo thruster.

[0028] The rotary servo thruster of this invention connects a steering assembly and a drive assembly via a first connector 1. Through the cooperation of a drive gear 3 and an external gear ring 5, the steering assembly drives the drive assembly to rotate. This rotation of the drive assembly causes a corresponding change in its fuel outlet 7, thereby altering the thrust direction of the rotary servo thruster. When this rotary servo thruster is used to propel an aircraft for attitude control, the attitude control is achieved by adjusting the thrust direction and magnitude of the rotary servo thruster. This significantly reduces the overall weight of existing aircraft attitude control systems, decreases the number of thrusters required, and improves the reliability of attitude control.

[0029] Preferably, the steering assembly and the first connector 1 are fixedly connected by threads to ensure that the steering force of the steering assembly is stably transmitted to the drive assembly.

[0030] Preferably, the first direction in this application is the axial direction of the first sleeve 8, and the second direction is any direction perpendicular to the plane containing the first direction.

[0031] Furthermore, as a preferred embodiment of the present invention, the first connecting member 1 in this application includes a first sleeve 8, and a second receiving ring is formed inside the first sleeve 8. The first housing 4 is fitted inside the first sleeve 8 at one end facing the fuel inlet 6, and a sealing member 9 is fitted around the outer periphery of the first housing 4, which seals the gap between the first housing 4 and the first sleeve 8. When the steering assembly drives the drive assembly to rotate, in order to ensure the stability and controllability of the thrust direction of the thruster, it is necessary to ensure that the first housing 4 does not swing arbitrarily in the plane perpendicular to the first direction, and that the direction of the fuel inlet 6 remains parallel to the first direction. The present application correspondingly provides a first sleeve 8, which wraps around the first housing 4, so that the first housing 4 rotates within the range limited by the first sleeve 8, avoiding the first housing 4 from shaking arbitrarily during rotation. At the same time, the sealing member 9 is used to fill the gap between the first housing 4 and the first sleeve 8, improve the fit between the first housing 4 and the first sleeve 8, and ensure that the first housing 4 rotates stably within the first sleeve 8.

[0032] Furthermore, as a preferred embodiment of the present invention, the first sleeve 8 in this application has a first stepped hole and a second stepped hole along the first direction; the first stepped hole is provided with the aforementioned sealing member 9, and the second stepped hole is provided with a rotating member. The rotating member specifically includes a bushing 10 sleeved on the outer wall of the first housing 4, one end of the bushing 10 abutting against the side wall of the outer gear ring 5 along the first direction, and the other end being provided with a pressure screw 11; simultaneously, a rotating bearing 12 is sleeved on the outer periphery of the bushing 10, and the outer ring of the rotating bearing 12 abuts against the inner wall of the second stepped hole. To achieve stable steering of the drive assembly, in addition to the rotational engagement between the drive gear 3 and the external gear, it is also necessary to ensure the stable rotation of the first housing 4 within the first sleeve 8. The design structure of the bushing 10 and the pressure screw 11 can prevent the rotating bearing 12 sleeved on the bushing 10 from displacing along the first direction. The rotation of the rotating bearing 12 achieves stable rotation of the first housing 4 and the first sleeve 8, thereby changing the thrust direction of the rotary servo thruster.

[0033] Furthermore, in a preferred embodiment of the present invention, one side of the rotating bearing 12 along the first direction is flush with the end face of the first sleeve 8 along the first direction. A bearing cover 13 is provided on the coaxial sleeve 10 of the first housing 4. The bearing cover 13 abuts against the end faces of the rotating bearing 12 and the first sleeve 8, and the bearing cover 13 and the first sleeve 8 are threadedly connected by screws. The threaded connection between the bearing cover 13 and the end face of the first sleeve 8 can further prevent the rotating bearing 12 from moving along the first direction, and at the same time can encapsulate the aforementioned sleeve 10, pressure screw 11, rotating bearing 12, etc., within the closed space formed by the bearing cover 13 and the first sleeve 8, ensuring the stable operation of the rotary servo thruster.

[0034] More preferably, in this application, a limiting ring 14 is also fitted around the outer periphery of the first housing 4. The outer wall of the limiting ring 14 abuts against the inner wall of the second stepped hole, and one end of the limiting ring 14 along the first direction abuts against the sealing member 9, while the other end abuts against the side wall of the bearing cover 13. The two ends of the limiting ring 14 along the first direction abut against the sealing member 9 and the side wall of the bearing cover 13, respectively, which can ensure the clamping force of the sealing member 9. The axial preload of the sealing member 9 can be adjusted by the limiting ring 14 clamping the sealing member 9.

[0035] Specifically, the sealing element 9 in this application includes a graphite sealing gasket 20 and an isolation gasket 21 stacked sequentially along a first direction. The isolation gasket 21 is an elastic gasket. By pressing the sealing gasket together with the limiting ring 14 along the first direction, the preload between the first housing 4 and the first sleeve 8 can be adjusted. The graphite sealing gasket 20 has good wear resistance, ensuring that the sealing element 9 can maintain a relatively constant preload when the first housing 4 and the first sleeve 8 rotate relative to each other. Preferably, the sealing element 9 in this application is formed by stacking multiple layers of graphite sealing gaskets 20 and multiple layers of isolation gaskets 21.

[0036] Further, as a preferred embodiment of the present invention, the first housing 4 in this application is arranged in a "┌" shape. A first heat insulation layer 15 is provided inside the first housing 4, the shape of which is the same as the shape of the internal flow channel of the first housing 4. The first heat insulation layer 15 wraps around the inner wall of the first housing 4. Simultaneously, a nozzle 16 is connected to one end of the first housing 4 facing the fuel outlet 7, and a second heat insulation layer 17 is provided on the inner wall of the nozzle 16. A throat liner 18 is provided at the junction of the first heat insulation layer 15 and the second heat insulation layer 17, and the throat liner 18 is threadedly connected to the inner wall of the nozzle 16. The design of the first heat insulation layer 15 and the second heat insulation layer 17 is used to achieve heat insulation and erosion resistance between the gas and the first housing 4. The throat liner 18 is used to compress the gas, improving the thrust of the rotary servo thruster. The first heat insulation layer 15 and the second heat insulation layer 17 are respectively molded with the first housing 4 and the nozzle 16, and the nozzle 16 and the first housing 4 are formed by electron beam welding.

[0037] More preferably, in this application, the end of the first housing 4 facing the fuel inlet 6 is further provided with a third heat insulation layer 19. The end of the third heat insulation layer 19 facing the first heat insulation layer 15 is arranged in a stepped manner, and the third heat insulation layer 19 extends into the first heat insulation layer 15 along the first direction. The first heat insulation layer 15 and the third heat insulation layer 19 form three clearance mating surfaces at their contact end faces. By forming a triple gap in the radial, axial and radial directions inside the first housing 4, air isolation is formed through the gaps to reduce the heat conducted by the fuel gas to the first housing 4.

[0038] More preferably, in this application, the first housing 4 and the first sleeve 8 have a gap of 0.02mm to 0.05mm along the second direction, and a gap of 0.05mm to 0.1mm along the first direction. This gap between the first housing 4 and the first sleeve 8 ensures that after the rotary servo thruster is subjected to pressure during operation, the first housing 4 can rotate normally within the first sleeve 8, thereby changing the thrust direction of the rotary servo thruster. Furthermore, after the rotary servo thruster is subjected to internal pressure during operation, the axial pressure will axially press the rotary bearing 12, and maintain the gap between the first sleeve 8 and the first housing 4 along the first direction at its maximum value, ensuring that sliding friction between the first sleeve 8 and the first housing 4 is eliminated during rotation.

[0039] Preferably, the transmission ratio between the drive gear 3 and the external gear ring 5 in this application is in the range of 3:1 to 10:1. A suitable transmission ratio is designed according to the power, speed and response speed of the drive mechanism 2 and the rotary servo thruster to ensure that the rotary servo thruster has both sufficient power and fast response speed.

[0040] This application also includes an attitude control system comprising a cover plate 22, on which two of the aforementioned rotary servo thrusters are arranged radially symmetrically. A gas generator 23 is connected to a first housing 4 at a fuel inlet 6. A gas generator bracket 24 is fitted around the outer periphery of the gas generator 23, and the gas generator bracket 24 is connected to the cover plate 22. The gas generator 23 provides gas power to the drive mechanism 2, and the gas generator bracket 24 is used to fix the gas generator 23.

[0041] Specifically, the cover plate 22 in this application is circular. With the center of cover plate 22 as the center of gravity, cover plate 22 is divided into four quadrants. One rotary servo thruster is positioned in the first quadrant at a 45° angle offset from the fourth quadrant, with a median azimuth angle of -45° and a rotation angle range of -180° to +90°. The other rotary servo thruster is positioned in the second quadrant at a 45° angle offset from the third quadrant, with a median azimuth angle of 135° and a rotation angle range of 0° to +270°. Through servo control of the rotary servo thrusters, pitch, yaw, and roll attitude control torques can be output as needed.

[0042] Specifically, the attitude control system employs the following control strategy: (1) One of the rotary servo thrusters has an azimuth angle of -45° and the other rotary servo thruster has an azimuth angle of 135°. The output thrust of the two rotary servo thrusters cancels each other out, and the attitude control system has no attitude control force or attitude control torque output. (2) One of the rotary servo thrusters has an azimuth angle of -90° and the other rotary servo thruster has an azimuth angle of 270°. At this time, the attitude control system outputs positive pitch control force. (3) One of the rotary servo thrusters has an azimuth angle of 90° and the other rotary servo thruster has an azimuth angle of 90°. At this time, the attitude control system outputs negative pitch control force. (4) One of the rotary servo thrusters has an azimuth angle of 180° and the other rotary servo thruster has an azimuth angle of -180°. At this time, the attitude control system outputs negative yaw attitude control force. (5) When the azimuth angle of one rotary servo thruster is 0° and the azimuth angle of the other rotary servo thruster is 0°, the attitude control system outputs positive yaw attitude control force. (6) One of the rotary servo thrusters has an azimuth angle of 0° and the other rotary servo thruster has an azimuth angle of 180°. At this time, the attitude control system outputs a positive roll attitude control torque. (7) One of the rotary servo thrusters has an azimuth angle of -90° and the other rotary servo thruster has an azimuth angle of 90°. At this time, the attitude control system outputs a negative roll attitude control torque.

[0043] Specifically, the azimuth angles of the two rotary servo thrusters can be continuously adjusted. By servo control of the azimuth angles of the two rotary servo thrusters, and in combination with the rated output force F0 and roll arm d of the rotary servo thrusters, pitch attitude control force is achieved according to the formula. Yaw attitude control Rolling attitude control torque It can realize servo control of pitch attitude control force, yaw attitude control force and roll attitude control torque, and can output combined pitch attitude control force, yaw attitude control force or roll attitude control torque to realize multi-channel composite control of attitude control system.

[0044] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A rotary servo thruster, characterized in that, include: A first connector, wherein a first receiving ring and a second receiving ring are arranged side by side on the first connector; A steering component is fitted inside the first receiving ring, and a driving component is fitted inside the second receiving ring; The steering assembly is arranged along a first direction, and the steering assembly includes a drive mechanism arranged along the first direction, with a drive gear rotatably connected to the output shaft of the drive mechanism; The drive assembly includes a first housing, one end of which is provided with a fuel inlet along a first direction, and one end of which is provided with a fuel outlet along a second direction. An external gear ring is fitted around the outside of the first housing. The drive gear meshes with the external gear ring, and the first housing can rotate under the drive of the drive gear, so as to change the gas outlet direction of the fuel outlet. The first connector includes a first sleeve, on which a second receiving ring is formed. The first housing is partially fitted inside the first sleeve at the end facing the fuel inlet, and a sealing member is fitted around the outer periphery of the first housing to seal the gap between the first housing and the first sleeve. The first sleeve has a first stepped hole and a second stepped hole along a first direction; the sealing element is provided at the first stepped hole, and the rotating element is provided at the second stepped hole; the rotating element includes a bushing sleeved on the outer wall of the first housing, one end of the bushing abuts against the side wall of the outer gear ring along the first direction, and the other end is provided with a pressure screw; a rotating bearing is sleeved on the outer circumference of the bushing, and the outer ring of the rotating bearing abuts against the inner wall of the second stepped hole; The rotating bearing has one side along the first direction flush with the end face of the first sleeve along the first direction. A bearing cover is coaxially sleeved on the first housing. The bearing cover abuts against the rotating bearing and the end face of the first sleeve, and the bearing cover is threadedly connected to the first sleeve. A limiting ring is also fitted around the outer periphery of the first housing. The outer wall of the limiting ring abuts against the inner wall of the second stepped hole, and one end of the limiting ring along the first direction abuts against the sealing element, while the other end abuts against the side wall of the bearing cover. The sealing element includes a graphite sealing gasket and an isolation gasket that are stacked sequentially along a first direction; the first housing is arranged in a "┌" shape, and a first heat insulation layer is provided inside the first housing, which wraps around the inner wall of the first housing; a nozzle is connected to the end of the first housing facing the fuel outlet, and a second heat insulation layer is provided on the inner wall of the nozzle, with a throat liner provided at the junction of the first heat insulation layer and the second heat insulation layer; a third heat insulation layer is provided at the end of the first housing facing the fuel inlet, and the third heat insulation layer is arranged in a stepped manner at the end facing the first heat insulation layer, with the third heat insulation layer partially extending into the first heat insulation layer along the first direction, and the first heat insulation layer and the third heat insulation layer forming three clearance mating surfaces at their joint end faces, forming air isolation through the clearance mating surfaces.

2. The rotary servo thruster according to claim 1, characterized in that, The first housing and the first sleeve have a gap of 0.02mm to 0.05mm along the second direction, and the first housing and the first sleeve have a gap of 0.05mm to 0.1mm along the first direction.

3. An attitude control system, characterized in that, include: A cover plate, wherein two rotary servo thrusters as described in claim 1 or 2 are arranged radially symmetrically on the cover plate; a gas generator is connected to the fuel inlet of the first housing. The gas generator is fitted with a gas generator bracket, which is connected to the cover plate.

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