A pilot-operated integrated solenoid valve, a launch vehicle engine, and a launch vehicle attitude adjustment and control method.

Abstract

This invention discloses a pilot-operated integrated solenoid valve, a launch vehicle engine, and a method for attitude adjustment and control of the launch vehicle, used for attitude adjustment and control of the launch vehicle engine. The pilot-operated integrated solenoid valve is integrated into a single housing; one pilot-operated integrated solenoid valve can be installed in the thrust chambers of four engines, forming a four-engine configuration. The pilot-operated integrated solenoid valve designed in this invention has a clever and compact internal structure, featuring a reasonable layout and light weight, which can reduce the use of launch vehicle piping and reduce the space occupied by the engine.

Description

Technical Field

[0001] This invention discloses an integrated solenoid valve for a launch vehicle engine, which belongs to the field of aerospace technology and can also be applied to other valve control fields. Background Technology

[0002] Solenoid valves are indispensable components in liquid attitude control propulsion systems, primarily used to control the on / off state of liquids and gases. In liquid rocket engines, solenoid valves play a crucial role, determining the rocket's start-up and shutdown.

[0003] Currently, rocket engines are controlled by a single solenoid valve. One solenoid valve connects to one thrust chamber to form a single engine, and each engine is mounted on one of the four annular surfaces of a cuboid mounting bracket, resulting in four engines. This structure requires four oxidizer (one type of rocket propellant) lines, four fuel (another type of propellant) lines, four pilot valve lines, and one cuboid mounting bracket. Furthermore, the cuboid mounting bracket occupies significant space, substantially increasing the engine's size and weight. The use of this type of solenoid valve leads to a large engine footprint and complex piping connections, resulting in low system reliability and a heavy overall weight. Summary of the Invention

[0004] The present invention aims to provide a pilot-operated integrated solenoid valve, a launch vehicle engine, and a launch vehicle attitude adjustment and control method. The valve has a clever and compact internal structure design, with reasonable layout and light weight, which can reduce the use of launch vehicle pipelines and reduce the space occupied by the engine.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A pilot-operated integrated solenoid valve, comprising:

[0007] The housing contains four pilot valve mounting positions and four main valve mounting positions. The four pilot valve mounting positions are located on the four side edges of a first regular square prism, and the four main valve mounting positions are located on the four side edges of a second regular square prism. The side edges of the first regular square prism are parallel to the side edges of the second regular square prism, and the angle between the side surfaces of the first regular square prism and the side surfaces of the second regular square prism is 45°.

[0008] An oxidant inlet channel and a fuel inlet channel are coaxially arranged inside the housing, and the axes of the oxidant inlet channel and the fuel inlet channel pass through the center of the bottom surface of the first regular square prism and the second regular square prism.

[0009] The pilot valves are respectively installed in four pilot valve mounting positions and the axis of the pilot valves coincides with the side edge of the first square prism. The pilot valves include an air inlet, a left-end spring, a left-end valve core, a valve seat, a right-end valve core, a push rod, and a suction platform arranged sequentially along the axis of the pilot valve. The end of the push rod away from the right-end valve core passes through the suction platform and is connected to the armature. An electromagnet for driving the armature to move is provided on the outside of the armature. An exhaust port is provided between the right-end valve core and the suction platform. The valve seat has a main valve air inlet. The left-end valve core and the right-end valve core are connected to form a synchronous linkage structure.

[0010] The four main valves are respectively installed in four main valve mounting positions, and the axis of the main valve coincides with the side edge of the second regular square prism. The main valve includes a main valve chamber, which is connected to the main valve inlet. Oxidant end valve seats and fuel end valve seats are symmetrically arranged on both sides of the main valve chamber. The oxidant end valve seat is provided with an oxygen end outlet. An oxidant end main valve piston is slidably connected to the oxidant end valve seat. An oxidant end valve core is provided at the end of the oxidant end main valve piston away from the main valve chamber. The other end of the oxidant end valve core is in close contact with the first main spring. An oxygen end inlet is opened in the area where the first main spring is located. The oxygen end inlet is connected to the oxidant inlet channel. A fuel outlet is provided on the fuel end valve seat. A fuel end main valve piston is slidably connected to the fuel end valve seat. A fuel end valve core is provided at the end of the fuel end main valve piston away from the main valve chamber. The other end of the fuel end valve core is in close contact with the second main spring. A fuel inlet is opened in the area where the second main spring is located. The fuel inlet is connected to the fuel inlet channel.

[0011] In one embodiment, the pilot valve has a left-end spring, a left-end valve core, a valve seat, and a right-end valve core located inside the housing, while the electromagnet, armature, and attraction platform are located outside the housing. Airflow channels are opened on the surfaces of the left-end valve core and the right-end valve core.

[0012] In one embodiment, the main valve includes a main valve gas chamber, an oxidant-end main valve piston, a fuel-end main valve piston, an oxidant-end valve core, an oxidant-end valve seat, a fuel-end valve core, a fuel-end valve seat, a first main spring, and a second main spring, all located within the housing. An oxidant flow channel is formed on the surface of the oxidant-end valve core, and a fuel flow channel is formed on the surface of the fuel-end valve core.

[0013] A launch vehicle engine, comprising:

[0014] The aforementioned pilot-operated integrated solenoid valve;

[0015] The four engine thrust chambers are respectively installed on the four sides of the outer square prism of the second square prism in the pilot-operated integrated solenoid valve, and the engine thrust chambers are connected to the oxygen outlet and fuel outlet of the main valves on the four main valve mounting positions. Different engine thrust chambers are used for attitude adjustment and control of the launch vehicle in different directions.

[0016] The attitude adjustment and control method for the launch vehicle employs the aforementioned launch vehicle engine and includes:

[0017] Step 1: Select one or more from the four engine thrust chambers according to attitude adjustment and control requirements;

[0018] Step two, start or shut down the engine thrust chamber, wherein:

[0019] The starting of the engine thrust chamber includes: energizing the electromagnet in the pilot valve corresponding to the engine thrust chamber, causing the left and right valve cores to move relative to the valve seat, connecting the air inlet to the main valve inlet, and disconnecting the exhaust port from the main valve inlet. Gas sequentially enters the main valve chamber of the main valve through the pilot valve inlet, valve seat, and main valve inlet, thereby pushing the oxidant-side main valve piston to move relative to the oxidant-side valve seat, and the fuel-side main valve piston to move relative to the fuel-side valve seat. Oxidant enters the engine thrust chamber through the oxidant inlet channel, oxygen inlet, oxidant-side valve seat, and oxygen outlet. Simultaneously, fuel enters the engine thrust chamber through the fuel inlet channel, fuel inlet, fuel-side valve seat, and fuel outlet to mix and burn with the oxidant, thus completing the starting of the engine thrust chamber.

[0020] The process of shutting down the engine thrust chamber includes: de-energizing the electromagnet in the pilot valve corresponding to the engine thrust chamber, causing the left and right valve cores to move relative to the valve seat, discontinuing the connection between the intake port and the main valve intake port, and connecting the exhaust port and the main valve intake port. Gas then sequentially enters the exhaust port through the main valve chamber, the main valve intake port, and the valve seat, thereby pushing the oxidizer-side main valve piston to move relative to the oxidizer-side valve seat, and the fuel-side main valve piston to move relative to the fuel-side valve seat. The oxidizer inlet channel is de-energized, and simultaneously, the fuel inlet channel is de-energized, thus completing the shutdown of the engine thrust chamber.

[0021] Compared with existing technologies, this invention discloses an integrated solenoid valve for a launch vehicle engine. The solenoid valve rationally integrates four pilot-operated solenoid valves and four main valves into a hexagonal housing. The interfaces for the oxidizer (rocket propellant) and fuel (another propellant) ends are integrated. The four pilot-operated solenoid valves and four main valves are rationally arranged, resulting in a simple, compact, rational, and reliable structure. It eliminates the need for multiple independent oxidizer lines, fuel lines, pilot valve lines, and mounting brackets found in traditional designs, reducing weight and volume while simplifying the structural design and improving reliability.

[0022] In the present invention, four pilot-operated solenoid valves are located on one end face of the hexagonal shell, four air inlets are located on the other end face of the hexagonal shell, and four engine thrust chambers are installed on the four annular surfaces of the solenoid valves, thus forming four engines, which are respectively used for attitude adjustment and control of the launch vehicle in four directions.

[0023] The solenoid valve's internal features are as follows: four pilot valve inlets are connected to the air source, and the pilot valve core is closed by the combined force of the spring force and the gas force. When any of the four engines needs to operate, the corresponding electromagnet is energized. The armature, under the action of the magnetic field, pushes the push rod, which in turn pushes the closed valve core and valve seat apart. Simultaneously, the valve core and valve seat at the other end, which were in the open state, are closed by the push rod. At this time, gas enters the main valve chamber, and the main valve piston, under the action of gas pressure, simultaneously pushes the valve core and valve seat at both the oxidizer and fuel ends apart. The oxidizer flows out from the oxidizer outlet, and the fuel flows out from the fuel outlet. Both propellants enter the thrust chamber, and the engine ignites.

[0024] When the engine needs to be shut down, the corresponding electromagnet is de-energized, the electromagnetic force on the armature disappears, and the pilot valve core and seat, which are in the open state, will re-close under the action of spring force and gas force. At the same time, the pilot valve core and seat, which are in the closed state, will be pushed to separate, and the gas in the main valve chamber will flow out from the pilot valve exhaust port. The gas pressure in the main valve chamber will disappear, and the valve cores at the oxidizer end and fuel end of the main valve will be restored from the separated state to the closed state under the action of spring force. The piston will return to the position when the engine is shut down, and the engine will shut down. Attached Figure Description

[0025] Figure 1 and Figure 2 These are outline views of the solenoid valve in this invention from different angles;

[0026] Figure 3 This is an external view of the engine formed by the solenoid valve and the thrust chamber in this invention;

[0027] Figure 4 This is a structural diagram of the pilot valve in this invention;

[0028] Figure 5 This is a structural diagram of the main valve in this invention;

[0029] Figure 6 This is a gas flow path diagram in this invention;

[0030] Figure 7 This is a diagram of the oxidant flow path and fuel flow path in this invention;

[0031] In the diagram: 1-Hexagonal housing; 2-Electromagnet; 3-Armature; 4-Attracting platform; 5-Push rod; 6-Left valve core; 7-Left valve seat; 8-Right valve seat; 9-Right valve core; 10-Oxidizer end main valve piston; 11-Fuel end main valve piston; 12-Oxidizer end valve core; 13-Oxidizer end valve seat; 14-Fuel end valve core; 15-Fuel end valve seat; 16-Left end spring force; 17-Main spring. Detailed Implementation

[0032] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0033] Figure 1 and Figure 2 The external features of the integrated pilot-operated solenoid valve designed in this invention are shown. The four outermost sides correspond to four main valves and their oxygen and fuel outlets. The central axis corresponds to the oxidizer and fuel inlet channels. Each main valve has pilot valves on both sides. Figure 1 The upper end of the pilot valve is an electromagnet. Figure 2 The upper end of the pilot valve is the air inlet. Figure 3 This invention demonstrates the state of an engine composed of a pilot-operated integrated solenoid valve and four thrust chambers. The pilot valve structure is as follows: Figure 4 The main valve structure is as follows Figure 5 pilot airflow channel, such as Figure 6 , Figure 6 correspond Figure 3 A cross-section through the center of two pilot valves and one main valve shows the oxidizer flow path and the fuel flow path as follows: Figure 7 , Figure 7 correspond Figure 3 The cross-section of the center of the two main valves, the center of the oxidizer inlet channel, and the center of the fuel inlet channel.

[0034] like Figure 4 As shown, the pilot-operated integrated solenoid valve includes an air inlet, an exhaust port, a main valve air inlet, an electromagnet 2, an armature 3, a suction platform 4, a push rod 5, a left-end valve core 6, a valve seat, a right-end valve core 9, and a left-end spring 16. The valve seat consists of two parts: a left-end valve seat 7 and a right-end valve seat 8. A sealing pair is formed at each end of the valve seat; specifically, the left-end valve seat 7 and the left-end valve core 6 form one sealing pair, and the right-end valve seat 8 and the right-end valve core 9 form another. The left-end valve core 6 and the right-end valve core 9 are connected by a barbell-like structure, allowing them to move synchronously and achieve the closing or opening of the left-end valve seat 7 and the right-end valve seat 8. Figure 4 The leftmost part is sealed by a plug to block the hexagonal housing 1, and an air inlet is formed by opening a hole in the plug. Figure 4 An exhaust port is provided at the suction platform 4. The two ends of the left spring 16 are tightly attached to the plug and the left valve core 6, respectively. The surfaces of the left valve core 6 and the right valve core 9 are grooved to form an airflow channel. The valve seat has a connected airflow channel inside and on its surface, and one end of the airflow channel serves as the main valve inlet.

[0035] like Figure 5As shown, the main valve includes an oxygen inlet, an oxygen outlet, a fuel inlet, a fuel outlet, a main valve chamber, an oxidant-end main valve piston 10, a fuel-end main valve piston 11, an oxidant-end valve core 12, an oxidant-end valve seat 13, a fuel-end valve core 14, a fuel-end valve seat 15, and a main spring 17. The main valve chamber, oxidant-end main valve piston 10, fuel-end main valve piston 11, oxidant-end valve core 12, oxidant-end valve seat 13, fuel-end valve core 14, fuel-end valve seat 15, and main spring 17 are all designed inside the hexagonal housing 1. The oxygen inlet, oxygen outlet, fuel inlet, and fuel outlet are located on the surface of the hexagonal housing 1, and the left and right ends of the hexagonal housing 1 are sealed with plugs. There are two main springs 17, which are respectively installed between the plugs and the oxidant-end valve core 12 and the fuel-end valve core 14.

[0036] Specifically, such as Figures 1-5 The pilot-operated integrated solenoid valve uses a hexagonal housing 1 to integrate four pilot-operated solenoid valves and four main valves into one unit. The air inlets of the four pilot valves are connected to the air source, the oxidant end is connected to the oxidant pipeline, and the fuel end is connected to the fuel pipeline.

[0037] See Figure 6 and Figure 7 When any of the four engines needs to operate, the corresponding electromagnet 2 is energized. When electromagnet 2 is energized, the coil generates a magnetic field, which magnetizes the armature 3, causing it to move towards the end face of the engagement platform 4. The push rod 5, under the force of the armature, pushes the left valve core 6 and left valve seat 7 to separate, while the right valve seat 8 and right valve core 9 seal together. At this time, gas from the pilot-operated solenoid valve inlet flows into the main valve chamber from the main valve inlet. The oxidizer-side main valve piston 10 and the fuel-side main valve piston 11, under the pressure of the gas, move in two directions respectively, thus pushing the oxidizer-side valve core 12 and valve seat 13, and the fuel-side valve core 14 and valve seat 15 to separate. The oxidizer and fuel then flow out from their respective channels into the thrust chamber channel, where they burn and generate thrust. When the engine needs to be shut off in that direction, the current to the electromagnet 2 in that direction is cut off. After the electromagnet 2 is de-energized, the magnetic field of the coil disappears, and the magnetic force on the armature 3 disappears. The left valve core 6 is subjected to the force of the left spring 16, causing the left valve core 6 to re-fit with the valve seat 7; then the right valve seat 8 and the right valve core 9 separate again. At this time, the gas entering the main valve chamber will flow out from the exhaust port, and the fuel end main valve piston 11 and the oxidizer end main valve piston 10 are subjected to the action of their respective main springs 17, causing the oxidizer end valve core 12 and the oxidizer end valve seat 13, and the fuel end valve core 14 and the fuel end valve seat 15 to re-fit. The oxidizer and fuel flow channels are cut off, and the engine shuts off.

[0038] The above are the main concepts of the invention. All pilot-type integrated solenoid valves, launch vehicle engines, and launch vehicle attitude adjustment and control methods designed based on the concepts of this invention fall within the protection scope of this invention.

Claims

1. A pilot-operated integrated solenoid valve, characterized in that, include: The housing contains four pilot valve mounting positions and four main valve mounting positions. The four pilot valve mounting positions are located on the four side edges of a first regular square prism, and the four main valve mounting positions are located on the four side edges of a second regular square prism. The side edges of the first regular square prism are parallel to the side edges of the second regular square prism, and the angle between the side surfaces of the first regular square prism and the side surfaces of the second regular square prism is 45°. An oxidant inlet channel and a fuel inlet channel are coaxially arranged inside the housing, and the axes of the oxidant inlet channel and the fuel inlet channel pass through the center of the bottom surface of the first regular square prism and the second regular square prism. Pilot valves, four of which are respectively installed in four pilot valve mounting positions and the axis of the pilot valve coincides with the side edge of the first square prism. The pilot valve includes an air inlet, a left end spring (16), a left end valve core (6), a valve seat, a right end valve core (9), a push rod (5), and a suction platform (4) arranged sequentially along the axis of the pilot valve. The end of the push rod (5) away from the right end valve core (9) passes through the suction platform (4) and is connected to the armature (3). An electromagnet (2) for driving the armature (3) to move is provided on the outside of the armature (3). An exhaust port is provided between the right end valve core (9) and the suction platform (4). A main valve air inlet is opened on the valve seat. The left end valve core (6) and the right end valve core (9) are connected to form a synchronous linkage structure. The four main valves are respectively installed in four main valve mounting positions, and the axis of the main valve coincides with the side edge of the second square prism. The main valve includes a main valve gas chamber, which is connected to the main valve inlet. Oxidizer end valve seat (13) and fuel end valve seat (15) are symmetrically arranged on both sides of the main valve gas chamber. The oxidizer end valve seat (13) is provided with an oxygen end outlet. The oxidizer end valve seat (13) is slidably connected to the oxidizer end main valve piston (10). The end of the oxidizer end main valve piston (10) away from the main valve gas chamber is provided with an oxidizer end valve core (12). The other end of the end valve core (12) is close to the first main spring. An oxygen end inlet is opened in the area where the first main spring is located. The oxygen end inlet is connected to the oxidant inlet channel. A fuel outlet is provided on the fuel end valve seat (15). A fuel end main valve piston (11) is slidably connected on the fuel end valve seat (15). A fuel end valve core (14) is provided at the end of the fuel end main valve piston (11) away from the main valve gas chamber. The other end of the fuel end valve core (14) is close to the second main spring. A fuel inlet is opened in the area where the second main spring is located. The fuel inlet is connected to the fuel inlet channel. In the pilot valve, the left end spring (16), the left end valve core (6), the valve seat and the right end valve core (9) are located inside the housing, the electromagnet (2), the armature (3) and the suction platform (4) are located outside the housing, and the surfaces of the left end valve core (6) and the right end valve core (9) have airflow channels. In the main valve, the main valve gas chamber, the oxidant end main valve piston (10), the fuel end main valve piston (11), the oxidant end valve core (12), the oxidant end valve seat (13), the fuel end valve core (14), the fuel end valve seat (15), the first main spring and the second main spring are all located inside the housing. The oxidant end valve core (12) has an oxidant flow channel on its surface, and the fuel end valve core (14) has a fuel flow channel on its surface.

2. A launch vehicle engine, characterized in that, include: The pilot-operated integrated solenoid valve as described in claim 1; The four engine thrust chambers are respectively installed on the four sides of the outer square prism of the second square prism in the pilot-operated integrated solenoid valve, and the engine thrust chambers are connected to the oxygen outlet and fuel outlet of the main valves on the four main valve mounting positions. Different engine thrust chambers are used for attitude adjustment and control of the launch vehicle in different directions.

3. A method for attitude adjustment and control of a launch vehicle, characterized in that: The launch vehicle engine of claim 2 is employed, and includes: Step 1: Select one or more from the four engine thrust chambers according to attitude adjustment and control requirements; Step two, start or shut down the engine thrust chamber, wherein: The starting of the engine thrust chamber includes: energizing the electromagnet (2) in the pilot valve corresponding to the engine thrust chamber, causing the left valve core (6) and the right valve core (9) to move relative to the valve seat, the air inlet to be connected to the main valve air inlet, and the exhaust port to be disconnected from the main valve air inlet. The gas enters the main valve gas chamber of the main valve in sequence through the pilot valve air inlet, the valve seat and the main valve air inlet, thereby pushing the oxidant end main valve piston (10) to move relative to the oxidant end valve seat (13) and the fuel end main valve piston (11) to move relative to the fuel end valve seat (15). The oxidant enters the engine thrust chamber through the oxidant inlet channel, the oxygen end inlet, the oxidant end valve seat (13) and the oxygen end outlet. At the same time, the fuel enters the engine thrust chamber through the fuel inlet channel, the fuel inlet, the fuel end valve seat (15) and the fuel outlet to mix and burn with the oxidant, thus completing the starting of the engine thrust chamber. The process of shutting down the engine thrust chamber includes: de-energizing the electromagnet (2) in the pilot valve corresponding to the engine thrust chamber, causing the left valve core (6) and the right valve core (9) to move relative to the valve seat, the air inlet and the main valve air inlet to be disconnected, the exhaust port and the main valve air inlet to be connected, the gas sequentially enters the exhaust port through the main valve air chamber, the main valve air inlet and the valve seat, thereby pushing the oxidant end main valve piston (10) to move relative to the oxidant end valve seat (13), and the fuel end main valve piston (11) to move relative to the fuel end valve seat (15), the oxidant inlet channel to be disconnected, and at the same time, the fuel inlet channel to be disconnected, thus completing the shutdown of the engine thrust chamber.

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