Liquid attitude control power system quickly sleeved with rocket engine

Abstract

The invention provides a liquid attitude control power system rapidly sleeved with a rocket engine. The liquid attitude control power system comprises a pressurizing gas cylinder, a propellant storage box, a pressure reducing valve, an electric explosion valve, a charging and discharging valve, a rack, an attitude control engine and a cabin, and the cabin is arranged at the tail of the rocket engine in a sleeving mode; the pressurizing gas cylinder, the propellant storage box, the pressure reducing valve, the electric explosion valve, the charging and discharging valve, the rack and the attitude control engine are all fixedly mounted on the inner side wall of the cabin body, and the radial protruding distance does not exceed the envelope of a tail nozzle of a rocket engine; the two propellant storage boxes are arranged at an angle of 150 degrees, the two racks are symmetrically arranged, and attitude control engines are symmetrically arranged on the two sides of any rack. The overall attitude control power system is formed on the cabin body, then the cabin body is directly arranged at the tail of the rocket engine in a sleeving mode, the size of the cabin body can be adaptively adjusted according to the diameter of the rocket engine, the attitude control power system and the rocket engine are simple in installation step, rapid sleeving is achieved, and the rocket final assembly production efficiency is improved; and the assembling and testing cost is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid attitude and orbit control power systems, and in particular, to a liquid attitude control power system that can be quickly assembled with a rocket engine. Background Art

[0002] As an important part of the power systems of various satellites, manned spacecraft, missiles, rockets, and aircraft, the liquid attitude control power system is mainly used to achieve attitude control such as pitch, yaw, and roll during flight, and has the advantages of high control accuracy and multiple start-stop capabilities.

[0003] The existing Chinese patent with the publication number CN117108413B discloses a terminal correction attitude control power system, which includes a power module, a propellant storage module, and a propellant supply module; the power module includes several terminal correction engines; several terminal correction engines are fixedly connected to the rocket body; the terminal correction engines have the ability of multiple starts, and the terminal correction engines have two working modes: steady-state continuous and pulse; the propellant storage module includes a fuel tank and an oxidizer tank; the propellant storage module is fixedly arranged inside the rocket body; the propellant supply module is configured to supply the propellant stored in the propellant storage module to the terminal correction engines as required.

[0004] Currently, most mainstream liquid attitude control power systems adopt the extrusion-type propellant supply scheme. The principle is to fill the extrusion gas into a pressurized gas cylinder. When attitude control is required, the extrusion gas is used to extrude the propellant stored in the storage tank to the front of the attitude control engine, and the output of the attitude control force is controlled by the switch of the engine to achieve the effect of adjusting the attitude.

[0005] The difficulty in the above scheme in terms of structure is the layout of the pressurized gas cylinder and the storage tank. The gas cylinder and the storage tank are pressure vessels, and their outer shapes are usually spherical, cylindrical, annular, etc., which are shapes that are easy to bear pressure. They occupy a large space in the structural layout, have low structural efficiency, and strong specificity. As a result, the structures of most attitude control power systems need to be designed separately for a certain type of rocket. At the same time, special gas cylinders and storage tanks need to be developed, and the development cycle is long and the development cost is high. In addition, usually, relatively complex process methods are required to assemble the attitude control power system onto the rocket, resulting in a long overall assembly cycle of the rocket, a complex process, and high requirements for the assembly environment, test environment, etc.

[0006] Therefore, there is a need to provide a liquid attitude control power system that can be quickly assembled with a rocket engine, which can solve the problems of complex installation steps and cumbersome processes between the attitude control power system and the rocket engine, can improve the overall assembly production efficiency of the rocket, reduce the assembly and test costs, and has higher versatility and universality. Summary of the Invention

[0007] Aiming at the defects in the prior art, the object of the present invention is to provide a liquid attitude control power system that can be quickly assembled with a rocket engine.

[0008] A liquid attitude control power system that can be quickly assembled with a rocket engine according to the present invention includes: a pressurized gas cylinder, a propellant tank, a pressure reducing valve, an electric explosion valve, a filling and discharging valve, a frame, an attitude control engine, and a cabin. The cabin is cylindrical and is sleeved on the tail of the rocket engine.

[0009] The pressurized gas cylinder is long cylindrical, and the propellant tank is dish-shaped. The pressurized gas cylinder, the propellant tank, the pressure reducing valve, the electric explosion valve, the filling and discharging valve, the frame, and the attitude control engine are all fixedly installed on the inner side wall of the cabin, and the radial protruding distance does not exceed the envelope of the rocket engine tail nozzle.

[0010] The two propellant tanks are arranged at 150°, and the two frames are symmetrically arranged. Attitude control engines are symmetrically arranged on both sides of any one of the frames.

[0011] The pressurized gas cylinder, the electric explosion valve, and the pressure reducing valve are connected in sequence and are arranged between a group of adjacent frames and propellant tanks. The output end of the pressure reducing valve is respectively connected to the input ends of the two propellant tanks, and the output end of any one of the propellant tanks is respectively connected to the two frames.

[0012] A filling and discharging valve is arranged downstream of the pressurized gas cylinder, and a filling and discharging valve is arranged downstream of any one of the propellant tanks.

[0013] Preferably, the pressurized gas cylinder, the propellant tank, the pressure reducing valve, the electric explosion valve, the filling and discharging valve, and the frame are all connected by pipelines, and the pipelines are arranged close to the cabin.

[0014] Preferably, the central axis of the pressurized gas cylinder is parallel to the central axis of the cabin. The pressurized gas cylinder is fastened to the cabin by a hoop band, and the pressurized gas cylinder is used to store and supply the gas required for extruding the propellant.

[0015] Preferably, the front of the propellant tank is circular, and the section is elliptical. The propellant tank is fixedly installed on the cabin through an installation flange, and the propellant tank is used to store and supply the propellant.

[0016] Preferably, the pressure reducing valve is a flat cylindrical shape, and the inlet and outlet of the pressure reducing valve are arranged on the left and right sides of the valve body. The pressure reducing valve is used to reduce the high-pressure gas in the pressurized gas cylinder to the working pressure of the propellant tank.

[0017] Preferably, the electric explosion valve is a flat cylindrical shape, and the inlet and outlet of the electric explosion valve are arranged on the left and right sides of the valve body. The electric explosion valve is used to isolate the high-pressure gas in the pressurized gas cylinder from the downstream pipeline during storage.

[0018] Preferably, the filling and discharging valve is cylindrical, and the inlet and outlet of the filling and discharging valve are arranged on the left and right sides of the valve body. The filling and discharging valve is used to fill the pressurized gas cylinder with gas or fill the propellant tank with propellant.

[0019] Preferably, the frame is a cuboid, and the propellant delivery flow channel is integrated inside the frame to provide propellant for the attitude control engine to work.

[0020] Preferably, the attitude control engine is cylindrical and is used to provide the thrust required by the rocket. The thrust generated by the attitude control engine is transmitted to the rocket through the frame.

[0021] Preferably, the diameter of the cabin body matches the diameter of the rocket engine.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. In the present invention, by installing the pressurized gas cylinder, propellant tank, pressure reducing valve, electric blasting valve, filling and discharging valve, frame, and attitude control engine on the cabin body to form an integrated attitude control power system, and then directly sleeving the cabin body on the tail of the rocket engine, the size of the cabin body can be adaptively adjusted according to the diameter of the rocket engine, solving the problems of complex installation steps and cumbersome process between the attitude control power system and the rocket engine. Through the structural design, the whole set of attitude control power system is directly installed on the tail of the rocket engine, realizing rapid sleeving, improving the overall assembly production efficiency of the rocket, and reducing the assembly and test cost.

[0024] 2. In the present invention, by docking and installing with the rocket engine after filling the propellant, the preparation process before rocket launch is shortened, meeting the current market demand for rapid response launch of rockets; if the rocket fails and needs to be disassembled, the system can be directly removed as a whole without discharging the filled propellant, greatly improving the maintainability.

[0025] 3. In the present invention, by being able to adapt to multiple rocket engines with the same diameter at the same time, by changing the diameter and length of the cabin body, it can adapt to more types of rocket engines, and can also change the volume of the pressurized gas cylinder, propellant tank and the type of attitude control engine to meet different attitude control requirements, having higher versatility and universality. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] By reading the detailed description of the non-restrictive embodiments with reference to the following drawings, other features, purposes and advantages of the present invention will become more obvious:

[0027] Figure 1 It is a schematic structural diagram of the liquid attitude control power system mainly reflecting the rapid sleeving with the rocket engine of the present invention;

[0028] Figure 2This is a schematic diagram of the pipeline connection of the liquid attitude control power system that is mainly embodied in the quick assembly with a rocket engine;

[0029] Figure 3 This is a schematic diagram after the liquid attitude control power system that is mainly embodied in the quick assembly with a rocket engine is docked with the rocket engine.

[0030] As shown in the figure:

[0031] Pressurized gas cylinder 1, propellant storage tank 2, pressure reducing valve 3

[0032] Electric blasting valve 4, filling and draining valve 5, frame 6

[0033] Attitude control engine 7, cabin 8 Specific implementation manner

[0034] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0035] As Figures 1-3 shown, a liquid attitude control power system that is quickly assembled with a rocket engine according to the present invention includes: a pressurized gas cylinder 1, a propellant storage tank 2, a pressure reducing valve 3, an electric blasting valve 4, a filling and draining valve 5, a frame 6, an attitude control engine 7, and a cabin 8. The cabin 8 is cylindrical and is sleeved on the tail of the rocket engine; the pressurized gas cylinder 1 is long and cylindrical, the propellant storage tank 2 is dish-shaped, and the pressurized gas cylinder 1, the propellant storage tank 2, the pressure reducing valve 3, the electric blasting valve 4, the filling and draining valve 5, the frame 6, and the attitude control engine 7 are all firmly installed on the inner side wall of the cabin 8, and the radial protrusion distance does not exceed the envelope of the rocket engine tail nozzle; the two propellant storage tanks 2 are arranged at 150°, the two frames 6 are symmetrically arranged, and attitude control engines 7 are symmetrically arranged on both sides of any one of the frames 6; the pressurized gas cylinder 1, the electric blasting valve 4, and the pressure reducing valve 3 are connected in sequence and are arranged between a group of adjacent frames 6 and propellant storage tanks 2. The output end of the pressure reducing valve 3 is respectively connected to the input ends of the two propellant storage tanks 2, and the output end of any one of the propellant storage tanks 2 is respectively connected to the two frames 6; a filling and draining valve 5 is arranged downstream of the pressurized gas cylinder 1, and a filling and draining valve 5 is arranged downstream of any one of the propellant storage tanks 2.

[0036] Through the structural design of the main components such as the pressurized gas cylinder 1, the propellant tank 2, and the frame 6, this application minimizes the radial protrusion distance on the cabin 8 as much as possible, controls the structural envelope range, and realizes that after the attitude control power system is assembled on the cylindrical cabin 8, it can be directly sleeved on the tail of the rocket engine, greatly improving the overall rocket assembly production efficiency. At the same time, this attitude control power system can be applied to a variety of different rocket engines through simple design improvements.

[0037] The pressurized gas cylinder 1, the propellant tank 2, the pressure reducing valve 3, the electric explosion valve 4, the filling and discharging valve 5, and the frame 6 are all connected by pipelines, and the pipelines are arranged closely against the cabin 8, forming a complete set of attitude control power systems.

[0038] The central axis of the pressurized gas cylinder 1 is arranged parallel to the central axis of the cabin 8. The pressurized gas cylinder 1 is tightened on the cabin 8 by a hoop band. The pressurized gas cylinder 1 is used to store and supply the gas required for extruding the propellant. The pressurized gas cylinder 1 is designed to be a long cylindrical shape. By optimizing the diameter and height of the pressurized gas cylinder 1 (the diameter and height jointly determine the size and volume of the pressurized gas cylinder 1), the volume of the pressurized gas cylinder 1 meets the gas volume requirements for extruding the propellant, and the radial protrusion distance of the pressurized gas cylinder 1 after installation does not exceed the envelope of the rocket engine tail nozzle. The pressurized gas cylinder 1 is tightened on the cabin 8 by a hoop band to store and supply the gas required for extruding the propellant.

[0039] The front of the propellant tank 2 is circular, and the cross-section is elliptical. The propellant tank 2 is fixedly installed on the cabin 8 through an installation flange. The propellant tank 2 is used to store and supply the propellant. The propellant tank 2 is designed as a dish-shaped structure, with a circular front and an elliptical cross-section. This shape can not only ensure that the volume of the propellant tank 2 meets the rocket requirements but also control the radial protrusion distance of the propellant tank 2 installed on the cabin section 8.

[0040] The pressure reducing valve 3 is a flat cylindrical shape and is installed closely against the cabin 8 by screws. The inlet and outlet of the pressure reducing valve 3 are arranged on the left and right sides of the valve body. The pressure reducing valve 3 is used to reduce the high-pressure gas in the pressurized gas cylinder 1 to the working pressure of the propellant tank 2.

[0041] The electric explosion valve 4 is a flat cylindrical shape. The inlet and outlet of the electric explosion valve 4 are arranged on the left and right sides of the valve body. It is fastened to the cabin 8 by screws. The electric explosion valve 4 is used to isolate the high-pressure gas in the pressurized gas cylinder 1 from the downstream pipeline during storage.

[0042] The filling and discharging valve 5 is cylindrical. The inlet and outlet of the filling and discharging valve 5 are arranged on the left and right sides of the valve body. It is fastened to the cabin 8 by screws. The filling and discharging valve 5 is used to inflate the pressurized gas cylinder 1 or fill the propellant tank 2 with propellant.

[0043] The frame 6 is a cuboid. Symmetrically arranged tangential attitude control engines 7 are installed on each frame 6. The internal integrated propellant delivery flow channels in the frame 6 provide propellants for the operation of the attitude control engines 7, and at the same time transfer the thrust generated by the attitude control engines 7 to the rocket to achieve attitude control.

[0044] The attitude control engine 7 is cylindrical and is installed on the frame 6 to provide the thrust required by the rocket. The thrust generated by the attitude control engine 7 is transferred to the rocket through the frame 6.

[0045] The diameter of the cabin 8 matches the diameter of the rocket engine. The pressurized gas cylinder 1, the propellant tank 2, the pressure reducing valve 3, the electric explosion valve 4, the filling and draining valve 5, the frame 6, and the attitude control engine 7 are installed on the cabin 8 to form an integral body, and then the cabin 8 is directly sleeved on the tail of the rocket engine. The size of the cabin 8 can be adaptively adjusted according to the diameter of the rocket engine. There is a certain gap between the diameter of the rocket engine tail nozzle and the cabin 8, which can ensure the normal installation of the pressurized gas cylinder 1 and the propellant tank 2. When this gap is too small, the following methods can be adopted: 1. Increase the diameter of the propellant tank 2 and reduce the height, that is, design the propellant tank 2 to be flatter; 2. Increase the number of propellant tanks 2, from 2 to 4; 3. Reduce the diameter of the pressurized gas cylinder 1 and increase the axial length, that is, make the pressurized gas cylinder 1 slender.

[0046] More specifically, the pressurized gas cylinder 1, the propellant tank 2, the pressure reducing valve 3, the electric explosion valve 4, the filling and draining valve 5, the frame 6, and the attitude control engine 7 are connected by pipelines; the electric explosion valve 4 and one filling and draining valve 5 are connected after the pressurized gas cylinder 1, the pressure reducing valve 3 is connected after the electric explosion valve 4, the two propellant tanks 2 are connected after the pressure reducing valve 3, one filling and draining valve 5 is connected after each of the two propellant tanks 2, and then the frame 6 is connected. The attitude control engine 7 is directly installed on the frame 6.

[0047] The cabin 8 is designed to be cylindrical, and the diameter of the cabin 8 is designed to be the same as the diameter of the rocket engine. When the diameter of the rocket engine changes, the diameter of the cabin 8 also changes accordingly, so that it can be docked with the tail of the rocket engine. Corresponding mounting brackets are provided on the cabin 8 to mount the above components and connecting pipelines. The propellant tank 2, which has the largest mass among all components, is arranged on both sides of the cabin 8 at an angle of 150°. The remaining components are arranged at the remaining positions of the cabin 8 according to their respective masses and connection sequences, so that the center of mass of the attitude control power system is located on the axis of the cabin 8 to reduce the interference caused by the offset of the center of mass during the rocket flight.

[0048] According to the diameter of the rocket engine tail nozzle to be adapted, the radial protrusion distance of the above components in the radial direction of the cabin 8 is restricted to ensure that the components and pipelines of the attitude control power system do not exceed the envelope of the rocket engine tail nozzle, and a safety distance of more than 10 mm is reserved, so that when the rocket engine is sleeved with the cabin 8, the rocket engine tail nozzle can directly pass through the cabin 8 to achieve sleeving.

[0049] After the attitude control power system is completely installed on the cabin 8, a system test is carried out on it. After the test is qualified, the gas cylinder is inflated and the propellant is filled into the storage tank, and then it is delivered to the rocket final assembly factory. At the rocket final assembly factory, as Figure 3 shown, only the pressurized gas cylinder and the propellant storage tank are drawn, and the other components with smaller volumes are ignored. The attitude control power system can be directly sleeved on the tail of the rocket engine, and then the control system is connected for joint testing. After the test is qualified, all the final assembly and testing work of the attitude control power system is completed, and it can be launched with the rocket.

[0050] When attitude control is required during the rocket flight, the electric explosion valve 4 is energized to open to form a passage. The gas in the pressurized gas cylinder 1 enters the propellant storage tank 2 after being decompressed by the pressure reducing valve 3, and the propellant is squeezed into the inner flow channel of the frame 6. The propellant enters the attitude control engine 7 through the inner flow channel, burns to generate thrust, and realizes rocket attitude control.

[0051] This application solves the problems of complex installation steps and cumbersome processes between the attitude control power system and the rocket engine. Through structural design, the whole set of attitude control power system is directly installed on the tail of the rocket engine to achieve rapid sleeving, improve the rocket final assembly production efficiency, and reduce the assembly and testing costs.

[0052] Compared with the traditional attitude control power system, this application can be docked and installed with the rocket engine after filling the propellant, shortening the preparation process before rocket launch and meeting the current market demand for rapid response rocket launch. In addition, if the rocket fails and needs to be disassembled, this system can be directly removed without discharging the filled propellant, and the maintainability is greatly improved compared with the traditional structure.

[0053] Compared with the traditional attitude control power system structure, this application has higher versatility and universality. This system can adapt to multiple rocket engines with the same diameter at the same time. By changing the diameter and length of the cabin 8, it can adapt to more types of rocket engines. It can also change the volumes of the pressurized gas cylinder 1 and the propellant storage tank 2 and the types of attitude control engines 7 to meet different attitude control requirements.

[0054] In the description of this application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing this application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to this application.

[0055] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A liquid attitude control power system that can be quickly mounted on a rocket engine, characterized in that: include: A pressurized gas cylinder (1), a propellant tank (2), a pressure reducing valve (3), an electric explosion valve (4), a charging and discharging valve (5), a frame (6), an attitude control engine (7) and a cabin (8), wherein the cabin (8) is cylindrical and is mounted on the tail of a rocket engine; The pressurized gas cylinder (1) is in the shape of an elongated cylinder, the propellant tank (2) is in the shape of a disc, the pressurized gas cylinder (1), the propellant tank (2), the pressure reducing valve (3), the electric explosion valve (4), the adding and discharging valve (5), the frame (6), and the attitude control engine (7) are all fixedly mounted on the inner wall of the cabin (8), and the radial protrusion distance does not exceed the envelope of the rocket engine tail nozzle; The two propellant tanks (2) are arranged at an angle of 150 degrees, the two frames (6) are arranged symmetrically, and attitude control engines (7) are symmetrically arranged on both sides of any frame (6); The pressurized gas cylinder (1), the electric explosion valve (4), and the pressure reducing valve (3) are sequentially connected and arranged between a group of adjacent frames (6) and the propellant tank (2); the output end of the pressure reducing valve (3) is respectively connected to the input ends of the two propellant tanks (2); and the output end of any of the propellant tanks (2) is respectively connected to the two frames (6); A charging and discharging valve (5) is provided downstream of the pressurized gas cylinder (1), and a charging and discharging valve (5) is provided downstream of any of the propellant storage tanks (2).

2. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The pressurized gas cylinder (1), the propellant tank (2), the pressure reducing valve (3), the electric explosion valve (4), the charging and discharging valve (5), and the frame (6) are all connected via pipelines, and the pipelines are arranged in close proximity to the cabin (8).

3. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The central axis of the pressurized gas cylinder (1) is arranged parallel to the central axis of the cabin (8), and the pressurized gas cylinder (1) is clamped on the cabin (8) by a clamp. The pressurized gas cylinder (1) is used to store and supply the gas required for extruding the propellant.

4. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The front of the propellant tank (2) is circular and the cross section is elliptical. The propellant tank (2) is fastened to the cabin (8) via a mounting flange. The propellant tank (2) is used to store and supply propellant.

5. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The pressure reducing valve (3) is in the shape of a flat cylinder. The inlet and outlet of the pressure reducing valve (3) are arranged on the left and right sides of the valve body. The pressure reducing valve (3) is used to reduce the pressure of the high-pressure gas in the pressurized gas cylinder (1) to the working pressure of the propellant tank (2).

6. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The electric explosion valve (4) is in the shape of a flat cylinder. The inlet and outlet of the electric explosion valve (4) are arranged on the left and right sides of the valve body. The electric explosion valve (4) is used to isolate the high-pressure gas in the pressurized gas cylinder (1) from the downstream pipeline during storage.

7. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The adding and discharging valve (5) is cylindrical, and the inlet and outlet of the adding and discharging valve (5) are arranged on the left and right sides of the valve body. The adding and discharging valve (5) is used to inflate the pressurized gas cylinder (1) or to add propellant to the propellant tank (2).

8. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The frame (6) is a rectangular parallelepiped, and a propellant delivery channel is integrated inside the frame (6) to provide propellant for the attitude control engine (7) to operate.

9. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The attitude control engine (7) is cylindrical and is used to provide the thrust required by the rocket. The thrust generated by the attitude control engine (7) is transmitted to the rocket through the frame (6).

10. The liquid attitude control power system for rapid assembly with a rocket engine as claimed in claim 1, characterized in that: The diameter of the cabin (8) matches the diameter of the rocket engine.

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