Pilot-operated type integrated electromagnetic valve, carrier rocket engine and carrier rocket attitude adjustment and control method

Abstract

The invention discloses a pilot-operated type integrated electromagnetic valve, a carrier rocket engine and a carrier rocket attitude adjustment and control method. The pilot-operated type integrated electromagnetic valve is used for attitude adjustment and control of the carrier rocket engine. The pilot-operated type integrated electromagnetic valve is integrated by adopting one shell, one pilot-operated type integrated electromagnetic valve can be provided with four engine thrust chambers, and four engines are combined. The pilot-operated type integrated electromagnetic valve is ingenious and compact in internal structural design, has the characteristics of reasonable layout and light weight, and can reduce the use of carrier rocket pipelines and reduce the occupied space of an engine.

Description

Technical Field

[0001] The invention discloses an integrated electromagnetic valve for a carrier rocket engine, belongs to the technical field of aerospace, and can also be applied to other valve control fields. Background Art

[0002] Solenoid valves are indispensable components in liquid attitude control power systems, and their main function is to control the on / off of liquids and gases. In liquid rocket engines, solenoid valves play a key role, determining the on / off of rockets.

[0003] At present, rocket engines are controlled by a single solenoid valve, that is, a solenoid valve is connected to a thrust chamber to form a single engine, and each engine is installed on the four ring surfaces of a rectangular mounting bracket, thus forming four engines. This structure requires four oxidizer (a type of rocket propellant) pipelines, four fuel (another type of propellant) pipelines, four pilot valve pipelines, and a rectangular mounting bracket; at the same time, the rectangular mounting bracket needs to occupy the overall installation space of the engine, which greatly increases the size and weight of the engine. The use of this type of solenoid valve results in the engine occupying a large space and complex pipeline connections, which leads to the disadvantages of low system reliability and heavy overall weight. Summary of the invention

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

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

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

[0007] A housing, wherein the housing comprises four pilot valve mounting positions and four main valve mounting positions, wherein the four pilot valve mounting positions are respectively located on four side edges of a first regular quadrangular prism, and the four main valve mounting positions are respectively located on four side edges of a second regular quadrangular prism, the side edges of the first regular quadrangular prism are parallel to the side edges of the second regular quadrangular prism, and the side angle between the side of the first regular quadrangular prism and the side of the second regular quadrangular prism is 45°;

[0008] An oxidant inlet channel and a fuel inlet channel, wherein the oxidant inlet channel and the fuel inlet channel are coaxially arranged in the shell, and the axes of the oxidant inlet channel and the fuel inlet channel pass through the centers of the bottom surfaces of the first regular quadrangular prism and the second regular quadrangular prism;

[0009] A pilot valve, wherein the four pilot valves are respectively installed on four pilot valve installation positions and the axis of the pilot valve coincides with the side edge of the first regular quadrangular prism, the pilot valve comprises 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 seat arranged in sequence along the axis direction of the pilot valve, wherein the end of the push rod away from the right end valve core passes through the suction seat and is connected to the armature, an electromagnet for driving the armature to move is arranged on the outside of the armature, an exhaust port is arranged between the right end valve core and the suction seat, a main valve air inlet is opened on the valve seat, and the left end valve core and the right end valve core are connected to form a synchronous linkage structure;

[0010] A main valve, four of the main valves are respectively installed on four main valve installation positions and the axis of the main valve coincides with the side edge of the second regular quadrangular prism, the main valve comprises a main valve air cavity, the main valve air cavity is connected to the main valve air inlet, an oxidant end valve seat and a fuel end valve seat are symmetrically arranged on both sides of the main valve air cavity, an oxygen end outlet is arranged on the oxidant end valve seat, an oxidant end main valve piston is slidably connected to the oxidant end valve seat, an oxidant end valve core is arranged at one end of the oxidant end main valve piston away from the main valve air cavity, the other end of the oxidant end valve core is closely attached to the first main spring, an oxygen end inlet is provided 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, the fuel end valve seat is slidably connected to the fuel end main valve piston, an end of the fuel end main valve piston away from the main valve air cavity is provided with a fuel end valve core, the other end of the fuel end valve core is closely attached to the second main spring, a fuel inlet is provided in the area where the second main spring is located, and the fuel inlet is connected to the fuel inlet channel.

[0011] As a solution, in the pilot valve, the left end spring, the left end valve core, the valve seat and the right end valve core are located inside the shell, the electromagnet, the armature and the suction base are located outside the shell, and the surfaces of the left end valve core and the right end valve core are provided with air flow channels.

[0012] As a scheme, in the main valve, the main valve air cavity, the oxidant end main valve piston, the fuel end main valve piston, the oxidant end valve core, the oxidant end valve seat, the fuel end valve core, the fuel end valve seat, the first main spring and the second main spring are all located in the shell, and the surface of the oxidant end valve core is provided with an oxidant flow channel, and the surface of the fuel end valve core is provided with a fuel flow channel.

[0013] A launch vehicle engine, comprising:

[0014] The above-mentioned pilot-operated integrated solenoid valve;

[0015] The engine thrust chamber, the four engine thrust chambers are respectively mounted on the four sides of the circumscribed regular quadrangular prism of the second regular quadrangular prism in the pilot integrated solenoid valve, and the engine thrust chambers are connected to the oxygen end outlet and the fuel outlet of the main valve on the four main valve mounting positions, and different engine thrust chambers are used for attitude adjustment and control in different directions of the launch vehicle.

[0016] The method for adjusting and controlling the attitude of a launch vehicle adopts the above-mentioned launch vehicle engine and comprises:

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

[0018] Step 2: Start or shut down the engine thrust chamber, wherein:

[0019] The starting engine thrust chamber comprises: energizing the electromagnet in the pilot valve corresponding to the engine thrust chamber, so that the left-end valve core and the right-end valve core move relative to the valve seat, the air inlet is connected with the main valve air inlet, and the exhaust port is disconnected with the main valve air inlet, and the gas enters the main valve air cavity of the main valve through the pilot valve air inlet, the valve seat and the main valve air inlet in sequence, thereby pushing the oxidant end main valve piston to move relative to the oxidant end valve seat, and the fuel end main valve piston to move relative to the fuel end valve seat, the oxidant enters the engine thrust chamber through the oxidant inlet channel, the oxygen end inlet, the oxidant end valve seat and the oxygen end outlet, and at the same time, the fuel enters the engine thrust chamber through the fuel inlet channel, the fuel inlet, the fuel end valve seat and the fuel outlet to mix and burn with the oxidant, thereby completing the starting of the engine thrust chamber;

[0020] The closing of the engine thrust chamber comprises: de-energizing the electromagnet in the pilot valve corresponding to the engine thrust chamber, so that the left-end valve core and the right-end valve core move relative to the valve seat, the air inlet is disconnected from the main valve air inlet, the exhaust port is connected to the main valve air inlet, and the gas enters the exhaust port through the main valve air cavity, the main valve air inlet and the valve seat in sequence, thereby pushing the oxidant end main valve piston to move relative to the oxidant end valve seat, and the fuel end main valve piston to move relative to the fuel end valve seat, the oxidant inlet channel is disconnected, and at the same time, the fuel is disconnected through the fuel inlet channel, thereby completing the closing of the engine thrust chamber.

[0021] Compared with the prior art, the present invention discloses an integrated solenoid valve for a launch vehicle engine. The solenoid valve uses a hexagonal shell to rationally integrate four pilot solenoid valves and four main valves. The interfaces of the oxidizer (rocket propellant) end and the fuel (another propellant) end are integrated. The four pilot solenoid valves and the four main valves are rationally arranged to make the structure simple, compact, reasonable and reliable. Multiple independent oxidizer pipelines, fuel pipelines, pilot valve pipelines and mounting brackets in the traditional design are omitted, which reduces the weight and volume while reducing the complexity of the structural design and improving reliability.

[0022] In the scheme of the present invention, four pilot 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, and then four engines are formed, which are respectively used for attitude adjustment and control in four directions of the launch vehicle.

[0023] The internal features of the solenoid valve are: the four pilot valve air inlets are connected to the air source respectively, and the pilot valve spool is subjected to the combined force of the spring force and the gas force, so that the solenoid valve is in a closed state. When the engine needs to work in any of the four directions, the electromagnet corresponding to that direction is energized, and the armature will push the push rod to move under the action of the magnetic field force, and the push rod will push the valve core and valve seat in the closed state to separate; at the same time, the valve core and valve seat in the open state at the other end are closed by the push rod. At this time, the gas enters the main valve air cavity, and the main valve piston will simultaneously push the valve core and valve seat at the oxidizer end and the fuel end to separate under the action of the gas pressure, and the oxidizer will flow out from the oxidizer outlet, and the fuel will flow out from the fuel outlet. The two propellants enter the thrust chamber, and the engine ignites.

[0024] When the engine needs to be shut down, the power is cut off to the corresponding electromagnet, the electromagnetic force on the armature disappears, and the valve core and valve seat of the pilot valve in the open state will be re-fitted due to the action of spring force and gas force; at the same time, the valve core and valve seat of the pilot valve in the closed state will be pushed to separate, and the gas in the main valve air cavity will flow out from the exhaust port of the pilot valve, the gas pressure in the main valve air cavity will disappear, and the valve cores at the oxidizer end and the fuel end of the main valve will be respectively acted upon by spring force, and will recover from the separated state to the fitted state, the piston will recover to the shutdown position, and the engine will be shut down. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 and Figure 2 It is the appearance diagram of the solenoid valve in different angles of the present invention;

[0026] Figure 3 This is the appearance diagram of the engine after the electromagnetic valve and the thrust chamber in the present invention form a complete engine;

[0027] Figure 4 It is the structural diagram of the pilot valve in the present invention;

[0028] Figure 5 It is the main valve structure diagram of the present invention;

[0029] Figure 6 is a gas flow path diagram in the present invention;

[0030] Figure 7 It is a diagram of the oxidant flow channel and the fuel flow channel in the present invention;

[0031] In the figure: 1-hexagonal housing; 2-electromagnet; 3-armature; 4-suction base; 5-push rod; 6-left end valve core; 7-left end valve seat; 8-right end valve seat; 9-right end 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 DESCRIPTION

[0032] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0033] Figure 1 and Figure 2 The appearance features of the integrated pilot solenoid valve designed by the present invention are shown, wherein the four outermost sides correspond to the four main valves and their oxygen end outlets and fuel outlets, the central axis position corresponds to the oxidant inlet channel and the fuel inlet channel, and each main valve is flanked by a pilot valve. Figure 1 The upper end of the middle pilot valve is an electromagnet. Figure 2 The upper end of the middle pilot valve is the air inlet. Figure 3 The pilot integrated solenoid valve designed by the present invention and four thrust chambers form an engine. The pilot valve structure is as follows Figure 4 , the main valve structure is as follows Figure 5 , the pilot airflow path is as follows Figure 6 , Figure 6 correspond Figure 3 A cross section through the center of two pilot valves and one main valve shows the oxidant flow path and the fuel flow path. Figure 7 , Figure 7 correspond Figure 3 A cross section passing through the centers of the two main valves, the oxidant inlet channel, and the fuel inlet channel.

[0034] like Figure 4 As shown, the pilot-operated integrated solenoid valve has an air inlet, an exhaust port, a main valve air inlet, an electromagnet 2, an armature 3, a suction seat 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. Among them, the valve seat is composed of two parts, the left-end valve seat 7 and the right-end valve seat 8, and a sealing pair is formed at the left and right ends of the valve seat, that is, the left-end valve seat 7 and the left-end valve core 6 form a sealing pair, and the right-end valve seat 8 and the right-end valve core 9 form a sealing pair. The left-end valve core 6 and the right-end valve core 9 are connected by a barbell-like structure, so that they move synchronously and realize the closing or opening of the left-end valve seat 7 and the right-end valve seat 8. Figure 4 The leftmost end of the hexagonal shell 1 is sealed by a plugging cover, and a hole is opened on the plugging cover to form an air inlet. Figure 4 An exhaust port is provided at the suction seat 4. The two ends of the left end spring 16 are respectively close to the plug cover and the left end valve core 6. The surfaces of the left end valve core 6 and the right end valve core 9 are notched to form an air flow channel. The inside and surface of the valve seat are connected with an air flow channel, and one end of the air flow channel serves as the main valve air inlet.

[0035] like Figure 5As shown, the main valve includes an oxygen end inlet, an oxygen end outlet, a fuel inlet, a fuel outlet, a main valve air cavity, 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 air cavity, 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 and the main spring 17 are all designed inside the hexagonal shell 1. The oxygen end inlet, the oxygen end outlet, the fuel inlet and the fuel outlet are opened on the surface of the hexagonal shell 1, and the left and right ends of the hexagonal shell 1 are blocked by plugging covers. There are two main springs 17, which are respectively installed between the plugging cover and the oxidant end valve core 12 and the fuel end valve core 14.

[0036] Specifically, if Figure 1 to Figure 5 The pilot-operated integrated solenoid valve integrates four pilot-operated solenoid valves and four main valves into one body by using a hexagonal housing 1. 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 also Figure 6 and Figure 7 When the engine needs to work in any of the four directions, the electromagnet 2 corresponding to the direction is energized. After the electromagnet 2 is energized, the coil generates a magnetic field, and the armature 3 is magnetized by the magnetic field to generate magnetic force, and then moves toward the end face of the suction seat 4. Then, the push rod 5 is acted by the armature force to push the left end valve core 6 and the left end valve seat 7 to separate, and the right end valve seat 8 and the right end valve core 9 are sealed. At this time, the gas at the air inlet of the pilot solenoid valve flows into the main valve air cavity from the main valve air inlet; the main valve piston 10 at the oxidant end and the main valve piston 11 at the fuel end are affected by the gas pressure and will move in two directions respectively, thereby pushing the oxidant end valve core 12 and valve seat 13, and the fuel end valve core 14 and valve seat 15 to separate. At this time, the oxidant and fuel flow out from their respective flow channels, enter the thrust chamber flow channel, and then burn in the thrust chamber combustion chamber to generate thrust. When the engine needs to be shut down in this direction, the current of the electromagnet 2 in this direction is cut off. After the electromagnet 2 is powered off, the magnetic field of the coil disappears, and the magnetic force on the armature 3 disappears. The left end valve core 6 is acted upon by the force of the left end spring 16, so that the left end valve core 6 and the valve seat 7 are re-fitted; the right end valve seat 8 and the right end valve core 9 are separated again. At this time, the gas entering the main valve air cavity will flow out from the exhaust port, and the fuel end main valve piston 11 and the oxidant end main valve piston 10 are acted upon by their respective main springs 17, so that the oxidant end valve core 12 and the oxidant end valve seat 13, the fuel end valve core 14 and the fuel end valve seat 15 are re-fitted, the oxidant and fuel flow paths are cut off, and the engine is shut down.

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

Claims

1. A pilot-operated integrated solenoid valve, characterized in that: include: A housing, wherein the housing comprises four pilot valve mounting positions and four main valve mounting positions, wherein the four pilot valve mounting positions are respectively located on four side edges of a first regular quadrangular prism, and the four main valve mounting positions are respectively located on four side edges of a second regular quadrangular prism, the side edges of the first regular quadrangular prism are parallel to the side edges of the second regular quadrangular prism, and the side angle between the side of the first regular quadrangular prism and the side of the second regular quadrangular prism is 45°; An oxidant inlet channel and a fuel inlet channel, wherein the oxidant inlet channel and the fuel inlet channel are coaxially arranged in the shell, and the axes of the oxidant inlet channel and the fuel inlet channel pass through the centers of the bottom surfaces of the first regular quadrangular prism and the second regular quadrangular prism; A pilot valve, wherein the four pilot valves are respectively mounted on four pilot valve mounting positions and the axis of the pilot valve coincides with the side edge of the first regular quadrangular prism, the pilot valve comprising 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 seat (4) arranged in sequence along the axis of the pilot valve, wherein the end of the push rod (5) away from the right end valve core (9) passes through the suction seat (4) and is connected to the armature (3), an electromagnet (2) for driving the armature (3) to move is arranged on the outer side of the armature (3), an exhaust port is arranged between the right end valve core (9) and the suction seat (4), a main valve air inlet is opened on the valve seat, and the left end valve core (6) and the right end valve core (9) are connected to form a synchronous linkage structure; The main valve is provided with four main valve installation positions, and the axis of the main valve coincides with the side edge of the second regular quadrangular prism. The main valve comprises a main valve air cavity, which is connected with the main valve air inlet. An oxidant end valve seat (13) and a fuel end valve seat (15) are symmetrically arranged on both sides of the main valve air cavity. An oxygen end outlet is provided on the oxidant end valve seat (13). An oxidant end main valve piston (10) is slidably connected to the oxidant end valve seat (13). An oxidant end valve core (12) is provided at one end of the oxidant end main valve piston (10) away from the main valve air cavity. The other end of the end valve core (12) is in close contact with the first main spring, an oxygen end inlet is provided in the area where the first main spring is located, and the oxygen end inlet is communicated with the oxidant inlet channel, a fuel outlet is provided on the fuel end valve seat (15), and the fuel end valve seat (15) is slidably connected to the fuel end main valve piston (11), a fuel end valve core (14) is provided at one end of the fuel end main valve piston (11) away from the main valve air cavity, the other end of the fuel end valve core (14) is in close contact with the second main spring, a fuel inlet is provided in the area where the second main spring is located, and the fuel inlet is communicated with the fuel inlet channel.

2. A pilot-operated integrated solenoid valve according to claim 1, characterized in that: In the pilot valve, a left end spring (16), a left end valve core (6), a valve seat and a right end valve core (9) are located inside a housing, an electromagnet (2), an armature (3) and a suction seat (4) are located outside the housing, and air flow channels are provided on the surfaces of the left end valve core (6) and the right end valve core (9).

3. The pilot-operated integrated solenoid valve according to claim 1, characterized in that: In the main valve, the main valve air cavity, 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 in the shell, and the surface of the oxidant end valve core (12) is provided with an oxidant flow channel, and the surface of the fuel end valve core (14) is provided with a fuel flow channel.

4. A launch vehicle engine, characterized in that: include: The pilot-operated integrated solenoid valve according to claim 1; The engine thrust chamber, the four engine thrust chambers are respectively mounted on the four sides of the circumscribed regular quadrangular prism of the second regular quadrangular prism in the pilot integrated solenoid valve, and the engine thrust chambers are connected to the oxygen end outlet and the fuel outlet of the main valve on the four main valve mounting positions, and different engine thrust chambers are used for attitude adjustment and control in different directions of the launch vehicle.

5. A method for adjusting and controlling the attitude of a launch vehicle, characterized in that: The launch vehicle engine according to claim 4 is used, and comprises: Step 1: Select one or more of the four engine thrust chambers according to attitude adjustment and control requirements; Step 2: Start or shut down the engine thrust chamber, wherein: The starting engine thrust chamber comprises: energizing the electromagnet (2) in the pilot valve corresponding to the engine thrust chamber, so that the left end valve core (6) and the right end valve core (9) move relative to the valve seat, the air inlet is connected with the main valve air inlet, and the exhaust port is disconnected with the main valve air inlet, and the gas enters the main valve air cavity of the main valve through the pilot valve air inlet, the valve seat and the main valve air inlet in sequence, 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), and 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, and 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, thereby completing the starting of the engine thrust chamber; The closing of the engine thrust chamber comprises: disconnecting the electromagnet (2) in the pilot valve corresponding to the engine thrust chamber, so that the left end valve core (6) and the right end valve core (9) move relative to the valve seat, the air inlet is disconnected from the main valve air inlet, the exhaust port is connected to the main valve air inlet, and the gas enters the exhaust port through the main valve air cavity, the main valve air inlet and the valve seat in sequence, 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 is disconnected, and at the same time, the fuel is disconnected through the fuel inlet channel, thereby completing the closing of the engine thrust chamber.

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