Novel spaceflight attitude control mechanical device

Abstract

The utility model provides a novel spaceflight attitude control mechanical device, which relates to the technical field of spaceflight equipment and comprises a positioning base and a main thruster, the main thruster is arranged on the top surface of the positioning base, a positioning ring seat is bolted on the surface of the main thruster, a linear guide rail is arranged on the circumference of the surface of the positioning ring seat, and a T-shaped guide groove is arranged outside the linear guide rail. The bottom face of the T-shaped guide groove is vertically bolted with a pushing hydraulic cylinder, the top end of the pushing hydraulic cylinder is connected with a T-shaped guide block, the exterior of the T-shaped guide block is connected with a power nozzle, the surface of the main propeller is connected with a plurality of linear guide rails through a positioning ring base for driving control, and the pushing hydraulic cylinder drives the power nozzle to move up and down to adjust the position. The main thruster can adjust different torques at the circumferential position of the surface of the main thruster by controlling the position of the power nozzle in the flying process, so that the flying attitude and the inclination angle of the main thruster are adjusted, attitude control and adjustment of the main thruster are achieved, and the adaptability of the flying attitude of the main thruster is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace equipment, in particular to a novel aerospace attitude control mechanical device. Background Art

[0002] Spacecraft attitude control is a key technology to ensure that spacecraft can fly stably in space according to the predetermined orbit, attitude and direction. With the development of aerospace technology, the requirements for the accuracy and stability of spacecraft attitude control are getting higher and higher. Traditional spacecraft attitude control methods mainly rely on passive stabilization such as spin stabilization and active control technology such as reaction wheel control. However, these methods have certain limitations when dealing with complex flight missions and diversified attitude adjustment requirements.

[0003] The existing technology has the problem that spacecraft need to rely on limited energy supply during flight. The traditional use of reaction wheels for mechanical control cannot adjust the power energy while adjusting the attitude, resulting in insufficient energy utilization of the spacecraft and insufficient attitude adjustment accuracy. Utility Model Content

[0004] The utility model aims to solve the shortcomings of insufficient spacecraft attitude adjustment accuracy and insufficient energy utilization in the prior art, and proposes a new type of spacecraft attitude control mechanical device.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a new type of aerospace attitude control mechanical device, including a positioning base and a main thruster, the main thruster is provided on the top surface of the positioning base, a positioning ring seat is bolted on the surface of the main thruster, a linear guide rail is provided on the circumference of the surface of the positioning ring seat, a T-shaped guide groove is provided on the outside of the linear guide rail, a pushing hydraulic cylinder is vertically bolted on the bottom surface of the T-shaped guide groove, a T-shaped guide block is connected to the top end of the pushing hydraulic cylinder, and a power nozzle is connected to the outside of the T-shaped guide block.

[0006] Preferably, auxiliary thrusters are distributed circumferentially on the surface of the main thruster close to the positioning base, and a positioning clamp is provided on the surface of the auxiliary thruster, and the positioning clamp is bolted to the surface of the main thruster.

[0007] Preferably, the adjacent pushing hydraulic cylinders are controlled independently of each other, and the adjacent linear guide rails are of the same length and size.

[0008] Preferably, the T-shaped guide groove is clearance-matched with the inner part of the linear guide rail, and the T-shaped guide block is slidably connected with the linear guide groove.

[0009] Preferably, the power nozzle is bolted to the surface of the T-shaped slider, and adjacent power nozzles are independently controlled from each other.

[0010] Preferably, at least two groups of positioning hoops are provided on the surface of the auxiliary propeller, and the inner walls of the positioning hoops abut against the surface of the auxiliary propeller.

[0011] Preferably, the inner wall of the linear guide rail abuts against the surface of the main thruster, and the abutment position of the inner wall of the linear guide rail is the same as the contour of the surface of the main thruster.

[0012] Beneficial Effects

[0013] In the utility model, the main thruster surface is connected to multiple linear guides through a positioning ring seat for drive control, and the power nozzle is driven to move up and down to adjust the position by pushing the hydraulic cylinder, so that during the flight of the main thruster, the position of the power nozzle can be controlled to adjust the different torques of the circumferential position of the main thruster surface, thereby adjusting the flight attitude and inclination angle of the main thruster, realizing attitude control and adjustment of the main thruster, increasing the adaptability of the flight attitude of the main thruster, controlling the attitude adjustment through power energy, improving energy utilization, and improving attitude adjustment accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a three-dimensional structural diagram of the utility model;

[0015] Figure 2 It is a bottom axonometric view of the utility model;

[0016] Figure 3 This is a flight attitude structure diagram of the utility model;

[0017] Figure 4 This is a connection structure diagram of the positioning ring seat of the utility model;

[0018] Figure 5 This is the axonometric view of the locating ring seat connection of the utility model;

[0019] Figure 6 This is a structural diagram of the internal system of the main thruster of the present utility model.

[0020] Legend:

[0021] 1. Positioning base; 2. Main thruster; 3. Auxiliary thruster; 4. Positioning clamp; 5. Positioning ring seat; 6. Linear guide rail; 7. T-type guide groove; 8. T-type guide block; 9. Push hydraulic cylinder; 10. Power nozzle. DETAILED DESCRIPTION

[0022] In order to make the technical means, creative features, objectives and effects of the present invention easy to understand, the present invention is further described below in conjunction with specific embodiments and drawings, but the following embodiments are only preferred embodiments of the present invention, not all. Based on the embodiments in the implementation mode, other embodiments obtained by those skilled in the art without creative work are all within the protection scope of the present invention.

[0023] The specific embodiments of the present utility model are described below in conjunction with the accompanying drawings. Specific embodiment one:

[0025] Reference Figure 1-6 A novel aerospace attitude control mechanical device comprises a positioning base 1 and a main thruster 2. The main thruster 2 is arranged on the top surface of the positioning base 1. A positioning ring seat 5 is bolted on the surface of the main thruster 2. A linear guide rail 6 is arranged on the circumference of the surface of the positioning ring seat 5. A T-shaped guide groove 7 is provided on the outside of the linear guide rail 6. A pushing hydraulic cylinder 9 is vertically bolted on the bottom surface of the T-shaped guide groove 7. A T-shaped guide block 8 is connected to the top of the pushing hydraulic cylinder 9. A power nozzle 10 is connected to the outside of the T-shaped guide block 8. When the whole device is actually used, the flight operation of the whole device is mainly carried out by the main thruster 2. By installing the positioning ring seat 5, a plurality of power nozzles 10 are arranged on the surface of the main thruster 2 to adjust the flight power. When the power nozzle 10 is adjusted, the movable end of the pushing hydraulic cylinder 9 is extended and retracted to drive the moving end of the hydraulic cylinder 9 to move. The T-shaped guide block 8 moves. Since the power nozzle 10 is bolted to the surface of the T-shaped slider, adjacent power nozzles 10 are independently controlled. Therefore, the power nozzle 10 can be driven to move up and down by pushing the movable end of the hydraulic cylinder 9 to extend and retract. After the power nozzle 10 moves, the power positions released by the power nozzles 10 at the circumferential positions on the surface of the main thruster 2 are different, resulting in a change in the torque between the power nozzle 10 and the main thruster 2. As a result, when the position of the power nozzle 10 moves, the power position on the side of the main thruster 2 changes, thereby driving the main thruster 2 to tilt. Therefore, in actual use, the power nozzles 10 at different angles of the circumferential position are controlled to adjust their positions according to the flight requirements of the main thruster 2, so as to realize the control and adjustment of the flight attitude and tilt angle of the main thruster 2.

[0026] In order to increase the power of the entire main propeller 2, auxiliary propellers 3 are arranged on the circumference of the surface of the main propeller close to the positioning base 1, and a positioning clamp 4 is provided on the surface of the auxiliary propeller 3. The positioning clamp 4 is bolted to the surface of the main propeller 2. The flight is carried out by cooperating with the auxiliary propeller 3 through the main propeller 2, and secondary propulsion is carried out through the auxiliary propeller 3, which is convenient for the entire main propulsion machine to be used in flight.

[0027] Other limiting structures of the entire device are as follows: adjacent pushing hydraulic cylinders 9 are independently controlled, and adjacent linear guide rails 6 are of the same length and size, which is convenient for controlling the extension and retraction of the pushing hydraulic cylinder 9 as needed to achieve adjustment of the power nozzle 10 at different angles. The T-shaped guide groove 7 is matched with the internal clearance of the linear guide rail 6, and the T-shaped guide block 8 is slidably connected with the linear slide groove. At least two sets of positioning clamps 4 are provided on the surface of the auxiliary thruster 3, and the inner wall of the positioning clamp 4 is against the surface of the auxiliary thruster 3, the inner wall of the linear guide rail 6 is against the surface of the main thruster 2, and the abutment position of the inner wall of the linear guide rail 6 is the same as the surface contour of the main thruster 2, thereby increasing the tightness of the connection. Specific embodiment 2:

[0029] Reference Figure 1-6 According to the content of the specific embodiment 1, the following contents are further disclosed:

[0030] In actual use, the main controller is provided with a controller structure for the hydraulic cylinder 9, the power nozzle 10 and the auxiliary thruster 3. The main thruster 2 is the main power source of the device. The main thruster 2 is responsible for the overall flight operation of the spacecraft. Its design takes high efficiency and stability into consideration and can generate sufficient thrust to meet the basic flight requirements of the spacecraft. The auxiliary thruster 3 provides a more sophisticated attitude adjustment capability based on the main thruster 2. They are usually located at different positions of the spacecraft and work together to achieve precise control of the spacecraft in three-dimensional space. The main thruster 2 and the auxiliary thruster 3 are connected and coordinated through an advanced control system. The control system calculates and outputs control instructions according to the preset flight trajectory and attitude requirements, drives the main thruster 2 and the auxiliary thruster 3 to work together, and achieves stable flight and attitude adjustment of the spacecraft.

[0031] In order to ensure the posture monitoring and adjustment of the main thruster 2, in actual use, the main thruster 2 has at least the following structures inside:

[0032] Attitude measurement system: mainly includes inertial sensors, star sensors and geomagnetic sensors, etc., which are used to measure the attitude information of the spacecraft in real time.

[0033] Control system: Responsible for receiving data provided by the attitude measurement system and generating attitude control instructions, using advanced control algorithms and logical judgments to ensure the stable flight and precise attitude adjustment of the spacecraft.

[0034] Execution system: including the main thruster 2, auxiliary thruster 3 and power nozzle 10 and other actuators, which are responsible for executing the attitude control instructions issued by the control system. The main thruster 2 provides basic flight power, and the auxiliary thruster 3 and power nozzle 10 are used to achieve precise attitude adjustment.

[0035] Communication system: responsible for communication and data transmission between the control system and external terminals, so that operators can obtain spacecraft status information in real time and perform remote control;

[0036] Energy system: provides energy support for the entire attitude control system to ensure that the system can work continuously and stably;

[0037] Safety monitoring system: monitors the various parameters of the spacecraft and the status of the attitude control system in real time, and immediately issues an alarm and takes corresponding measures if any abnormal situation is detected.

[0038] When adjusting the posture, use the following method:

[0039] Attitude measurement and data processing: Using attitude measurement systems such as inertial sensors, star sensors, geomagnetic sensors, etc. to obtain spacecraft attitude information in real time;

[0040] The control system analyzes and processes the measured attitude data to determine the difference between the actual attitude of the spacecraft and the desired attitude.

[0041] Attitude control instruction generation: Based on the results of attitude data processing, the control system uses appropriate control algorithms such as PID control, fuzzy control, adaptive control, etc. to generate attitude control instructions. The instruction content includes the thrust size and direction of the main thruster 2 and the auxiliary thruster 3, as well as the adjustment position and thrust size of the power nozzle 10.

[0042] Adjustment of the power nozzle 10: The control system drives the movable end of the hydraulic cylinder 9 to extend and retract according to the posture control instruction, driving the T-shaped guide block 8 to move in the T-shaped guide groove 7, thereby adjusting the position of the power nozzle 10 and further changing the direction and size of the thrust released.

[0043] The main thruster 2 and the auxiliary thruster 3 work together. The main thruster 2 is responsible for the basic flight power of the spacecraft, while the auxiliary thruster 3 is used to provide fine attitude adjustment capability. The control system achieves stable flight and attitude adjustment of the spacecraft by collaboratively controlling the thrust size and direction of the main thruster 2 and the auxiliary thruster 3.

[0044] Through the design of the above control method and system architecture, the new aerospace attitude control mechanical device can achieve high-precision attitude control of the spacecraft during flight and ensure the smooth completion of the space mission.

[0045] In summary:

[0046] The surface of the main thruster 2 is connected to multiple linear guides 6 through a positioning ring seat 5 for drive control, and the power nozzle 10 is driven to move up and down to adjust the position by pushing the hydraulic cylinder 9. During the flight of the main thruster 2, the position of the power nozzle 10 can be controlled to adjust the torque of the circumferential position on the surface of the main thruster 2, thereby adjusting the flight attitude and tilt angle of the main thruster 2, realizing attitude control and adjustment of the main thruster 2, and increasing the adaptability of the flight attitude of the main thruster 2.

[0047] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0048] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the utility model and are not used to limit the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection claimed by the utility model is defined by the attached claims and their equivalents.

Claims

1. A novel aerospace attitude control mechanical device, comprising a positioning base (1) and a main thruster (2), characterized in that: The top surface of the positioning base (1) is provided with a main thruster (2), the surface of the main thruster (2) is bolted with a positioning ring seat (5), the surface of the positioning ring seat (5) is provided with a linear guide rail (6) on its circumference, the outside of the linear guide rail (6) is provided with a T-shaped guide groove (7), the bottom surface of the T-shaped guide groove (7) is vertically bolted with a pushing hydraulic cylinder (9), the top end of the pushing hydraulic cylinder (9) is connected with a T-shaped guide block (8), and the outside of the T-shaped guide block (8) is connected with a power nozzle (10).

2. A novel aerospace attitude control mechanical device according to claim 1, characterized in that: Auxiliary thrusters (3) are distributed circumferentially on the surface of the main thruster close to the positioning base (1); a positioning clamp (4) is provided on the surface of the auxiliary thruster (3); and the positioning clamp (4) is bolted to the surface of the main thruster (2).

3. A novel aerospace attitude control mechanical device according to claim 1, characterized in that: The adjacent pushing hydraulic cylinders (9) are controlled independently of each other, and the adjacent linear guide rails (6) are of the same length and size.

4. A novel aerospace attitude control mechanical device according to claim 1, characterized in that: The T-shaped guide groove (7) is clearance-matched with the inner part of the linear guide rail (6), and the T-shaped guide block (8) is slidably connected with the linear guide groove.

5. A novel aerospace attitude control mechanical device according to claim 1, characterized in that: The power nozzles (10) are bolted to the surface of the T-shaped slider, and adjacent power nozzles (10) are independently controlled from each other.

6. A novel aerospace attitude control mechanical device according to claim 2, characterized in that: At least two groups of positioning hoops (4) are provided on the surface of the auxiliary propeller (3), and the inner walls of the positioning hoops (4) are in contact with the surface of the auxiliary propeller (3).

7. The novel aerospace attitude control mechanical device according to claim 1 is characterized in that: The inner wall of the linear guide rail (6) abuts against the surface of the main thruster (2), and the abutment position of the inner wall of the linear guide rail (6) is the same as the surface profile of the main thruster (2).

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