Multifunctional shut-off solenoid valve for extrusion type liquid rocket engine fuel supply system

Abstract

The invention discloses a multifunctional stop solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, wherein the solenoid valve comprises a valve body, a solenoid valve inlet and a solenoid valve outlet for fuel to pass through are arranged in the valve body, and the valve body also comprises a main control chamber, a pilot control chamber, a connecting branch, a pilot valve core and a main valve core, and the electromagnet switches between two states of power on and power off, and is used to pull the pilot valve core to move back and forth in the pilot control chamber, thereby realizing the conduction or closure of the solenoid valve inlet and the pilot control chamber, and making the secondary shaft move back and forth in the main control chamber, thereby driving the secondary shaft to close or conduct the communication between the solenoid valve inlet and the solenoid valve outlet. The invention solves the problem that the existing fuel supply system of an extrusion type liquid rocket engine controls the on-off function of the fuel by multiple straight-through solenoid valves, which increases the complexity of the system and reduces the reliability of the system.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid fuel control of aerospace engines, and in particular relates to a multifunctional cut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine. Background Art

[0002] Since the main valve core of the pilot solenoid valve is controlled by the pressure difference at both ends of the valve core, and in order to ensure the cut-off effect, the cut-off solenoid valve usually adopts end face sealing, that is, one end of the main valve core of the pilot solenoid valve is always affected by the outlet pressure. Therefore, the conventional pilot cut-off solenoid valve must ensure that a low-pressure path leading to the low-pressure source is added outside the inlet and outlet. When the main valve needs to be opened, the low pressure pressure is compared with the outlet pressure through the pilot valve control. When the main valve needs to be closed, the inlet pressure is compared with the outlet pressure through the pilot valve control. The main valve moves under the action of the liquid pressure. However, the fuel supply system of the extrusion liquid rocket engine can only ensure a relatively stable and small inlet and outlet pressure difference at a large flow rate, so the pilot solenoid valve cannot be used. In the high-flow and high-pressure state, the fuel on-off function can only be controlled by multiple straight-through solenoid valves. This method greatly increases the complexity and weight of the system, and reduces the reliability of the system. While controlling the on-off of the fuel supply of a combustion chamber, it is generally accompanied by the adjustment of structural parameters such as the engine nozzle angle and the aircraft wing shape. At this time, it is necessary to control and backup control through components such as hydraulic cylinders and steering gears. Summary of the invention

[0003] The purpose of the present invention is to provide a multifunctional shut-off solenoid valve for an extrusion type liquid rocket engine fuel supply system, so as to solve the problem that the existing extrusion type liquid rocket engine fuel supply system uses multiple straight-through solenoid valves to jointly control the on-off function of the fuel, which increases the complexity of the system and reduces the reliability of the system.

[0004] The present invention adopts the following technical scheme: a multifunctional stop solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, comprising a valve body, a solenoid valve inlet and a solenoid valve outlet for fuel to pass through are arranged in the valve body, and the valve body also includes:

[0005] a main control chamber, one end of which is connected to the outside of the valve body and the other end of which is connected to the outlet of the solenoid valve;

[0006] a pilot control chamber, one side of which is connected to the inlet of the solenoid valve and the other side of which is connected to the main control chamber;

[0007] A connecting branch, connectingly arranged between the pilot control chamber and the outlet of the solenoid valve;

[0008] A pilot valve core, one end of which passes through the pilot control chamber and is connected to an electromagnet, and the other end of which is located in the pilot control chamber;

[0009] A main valve core is located in the main control chamber, and includes a main shaft and a secondary shaft that are coaxially and integrally arranged. The outer diameter of the secondary shaft is larger than the outer diameter of the main shaft, and a mechanical interface is provided on the end of the main shaft away from the secondary shaft. The main shaft passes through the main control chamber, and the secondary shaft is located in the main control chamber, near the outlet of the solenoid valve;

[0010] The electromagnet switches between the two states of power on and power off, and is used to pull the pilot valve core to move back and forth in the pilot control chamber, thereby realizing the connection or closure of the solenoid valve inlet and the pilot control chamber, and making the secondary shaft reciprocate in the main control chamber, thereby driving the secondary shaft to close or open the connection between the solenoid valve inlet and the solenoid valve outlet.

[0011] Further, the pilot valve core includes a push rod and a shift rod vertically arranged thereon, the push rod is arranged along the moving direction of the pilot valve core, and the shift rod is used to move with the push rod to switch between the following two states:

[0012] State 1: The pilot control chamber is connected to the solenoid valve inlet and the main control chamber respectively, and is disconnected from the connecting branch;

[0013] State 2: The pilot control chamber is disconnected from the solenoid valve inlet and connected to the main control chamber and the connecting branch respectively.

[0014] Furthermore, a dynamic sealing assembly is arranged on the outside of the outlet of the pilot valve core passing through the pilot control chamber.

[0015] Furthermore, a return spring is arranged between the push rod and the dynamic sealing assembly.

[0016] Furthermore, a main valve return spring is sleeved on the outer side of the main shaft.

[0017] Furthermore, a sealing gasket is arranged at one end of the secondary shaft away from the primary shaft, and a sealing protrusion is arranged at a position corresponding to the sealing gasket in the main control chamber.

[0018] Furthermore, the electromagnet includes an iron core connected to the pilot valve core, and a coil is arranged around the iron core.

[0019] Furthermore, one end of the main valve core extending out of the valve body is sleeved with a main valve dynamic sealing assembly and a clamping ring.

[0020] The second technical solution adopted by the present invention is a working method of a multifunctional cut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, comprising the following contents:

[0021] When the coil is energized, the pilot valve core moves under the drive of the iron core, and connects the solenoid valve inlet, the pilot control chamber and the main control chamber. The main valve core moves toward the solenoid valve outlet under the inlet pressure, and finally closes the solenoid valve inlet and the solenoid valve outlet, and the solenoid valve is closed;

[0022] When the coil is powered off, the pilot valve resets and closes the connection between the solenoid valve inlet, the pilot control chamber and the main control chamber. No fuel flows into the pilot control chamber and the end surface of the joint between the main shaft and the secondary shaft. The main valve core resets, thereby connecting the solenoid valve inlet, the main control chamber and the solenoid valve outlet, and the solenoid valve opens.

[0023] The beneficial effects of the present invention are:

[0024] 1. The present invention designs the main valve core as a coaxial integrated main shaft and secondary shaft, and under the control of the pilot valve core, forms a hydraulic pressure to close the valve on the end face of the main shaft and secondary shaft joint surface. At the same time, the pressure at the outlet of the solenoid valve forms a hydraulic pressure to open the valve on the end face of the secondary shaft. The reciprocating movement of the pilot valve core is controlled by the on and off of the electromagnet, so that the magnitude of the hydraulic pressure to close the valve and the hydraulic pressure to open the valve will change. Through a slight change in the pressure difference, the main valve core can be controlled to move to the closed position or the open position. Through this structural design, the pilot valve can be used in scenes with large flow and small pressure difference, such as the fuel supply system of an extrusion liquid rocket engine.

[0025] 2. As the main shaft extends out of the valve body, as the hydraulic oil drives the main valve core, the secondary shaft also moves accordingly. Through the mechanical interface set on the main shaft, the adjustment and control of structural parameters such as the engine nozzle angle and the aircraft wing shape can be achieved at the same time, realizing the multi-function of the multi-function shut-off solenoid valve for the extrusion liquid rocket engine fuel supply system. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the valve body structure of the multifunctional cut-off solenoid valve for the extrusion type liquid rocket engine fuel supply system of the present invention;

[0027] Figure 2 It is a structural schematic diagram of the multifunctional cut-off solenoid valve for the fuel supply system of the extrusion type liquid rocket engine of the present invention when the electromagnet is not energized;

[0028] Figure 3 The present invention is a schematic structural diagram of a multifunctional cut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine when the electromagnet is energized.

[0029] Among them, 1. valve body, 2. coil, 3. iron core, 4. pilot valve core, 5. dynamic sealing assembly, 6. return spring, 7. sealing protrusion, 8. main valve core, 81. main shaft, 82. secondary shaft, 9. sealing gasket, 10. main valve return spring, 11. main valve dynamic sealing assembly, 12. retaining ring; 13. solenoid valve inlet, 14. solenoid valve outlet, 15. connecting branch, 16. pilot control chamber, 17. main control chamber, 18. mechanical interface. DETAILED DESCRIPTION

[0030] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] The present invention provides a multifunctional cut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, such as Figure 1-Figure 3 As shown, it includes a valve body 1, in which a solenoid valve inlet 13 and a solenoid valve outlet 14 for fuel to pass are arranged, and the valve body also includes a main control chamber 17, a pilot control chamber 16, a connecting branch 15, a pilot valve core 4 and a main valve core 8.

[0032] Among them, Figure 1 As shown, the main control chamber 17 is located at the bottom of the valve body 1 , one end of the main control chamber 17 is connected to the outside of the valve body 1 , and the other end is connected to the solenoid valve outlet 14 .

[0033] The pilot control chamber 16 is located in the valve body 1, and is communicated with the solenoid valve inlet 13, and is also communicated with the main control chamber 17. A communication branch 15 is arranged between the pilot control chamber 16 and the solenoid valve outlet 14.

[0034] A pilot valve core 4 is installed in the pilot control chamber 16. The pilot valve core 4 can use various common solenoid valve pilot valve forms such as a cone valve and a ball valve. One end of the pilot valve core 4 passes through the pilot control chamber 16 and is connected to the electromagnet, and the other end of the pilot valve core 4 is located in the pilot control chamber 16. A main valve core 8 is installed in the main control chamber 17. The main valve core 8 includes a coaxial, integrally arranged main shaft 81 and a secondary shaft 82. The outer diameter of the secondary shaft 82 is larger than the outer diameter of the main shaft 81.

[0035] The main shaft 81 passes through the main control chamber 17, and a mechanical interface 18 is provided at one end of the main shaft 81 away from the secondary shaft. The mechanical interface 18 is used to connect various required devices, such as connecting the air intake blades or the tail nozzle, so as to adjust and control the structural parameters such as the engine nozzle angle and the aircraft wing shape. The secondary shaft 82 is located in the main control chamber 17, close to the side of the solenoid valve outlet 14, and the reciprocating movement of the secondary shaft 82 along the main control chamber 17 can realize the closing or opening of the solenoid valve outlet 14.

[0036] The electromagnet switches between the two states of power on and power off, and is used to pull the pilot valve core 4 to move back and forth in the pilot control chamber 16, thereby realizing the connection or closure of the solenoid valve inlet 13 and the pilot control chamber 16, and making the secondary shaft 82 move back and forth in the main control chamber 17, thereby driving the secondary shaft 82 to close or open the connection between the solenoid valve inlet 13 and the solenoid valve outlet 14.

[0037] Specifically, Figure 2As shown, when the electromagnet is powered off, the pilot valve 4 is reset due to the lack of external force, and the connection between the solenoid valve inlet 13, the pilot control chamber 16 and the main control chamber 17 is closed at the same time, and no fuel can enter the pilot control chamber 16 and the end surface of the joint surface between the main shaft 81 and the secondary shaft 82. The main valve core 8 is reset due to the lack of external force, thereby connecting the solenoid valve inlet 13, the main control chamber 17 and the solenoid valve outlet 14. At the same time, the fuel in the pilot control chamber 16 and the end surface of the joint surface between the main shaft 81 and the secondary shaft 82 can maintain a balanced state at the solenoid valve outlet 14 through the connecting branch 15.

[0038] like Figure 3 As shown, when the electromagnet is energized, the electromagnet will pull the pilot valve 4 to move, and at the same time penetrate the solenoid valve inlet 13, the pilot control chamber 16 and the main control chamber 17. The fuel continuously flowing into the valve core drive section 14 will generate pressure, pushing the secondary shaft 82 to move in the direction close to the solenoid valve outlet 14, thereby closing the connection between the solenoid valve inlet 13, the main control chamber 17 and the solenoid valve outlet 14.

[0039] The multifunctional cut-off solenoid valve for the fuel supply system of the extrusion type liquid rocket engine of the present invention can be provided with a plurality of main valve cores 8 and corresponding interfaces, so that one pilot valve core 4 can control the on and off of a plurality of media at the same time.

[0040] In some embodiments, the pilot valve core 4 includes a push rod and a shift rod vertically arranged thereon, and the number of the shift rods can be set as needed. The push rod is arranged along the moving direction of the pilot valve core 4, and the shift rod is used to follow the push rod to switch between the following two states:

[0041] State 1: The pilot control chamber 16 is connected to the solenoid valve inlet 13 and the main control chamber 17 respectively, and is disconnected from the connecting branch 15. At this time, the valve is closed.

[0042] State 2: The pilot control chamber 16 is disconnected from the solenoid valve inlet 13 and is connected to the main control chamber 17 and the connecting branch 15 respectively. At this time, the valve is open.

[0043] In some embodiments, a dynamic sealing assembly 5 is provided on the outer side of the outlet of the pilot valve core 4 passing through the pilot control chamber 16 to ensure that the medium in the valve body does not enter the coil and damage the coil.

[0044] In some embodiments, a return spring 6 is provided between the push rod and the dynamic seal assembly 5 , and the return spring 6 is used as an assisting force for returning the pilot valve 4 .

[0045] In some embodiments, a main valve return spring 10 is mounted on the outer side of the main shaft 81 , and the main valve return spring 10 is used as a booster for returning the main valve core 8 .

[0046] In some embodiments, a sealing pad 9 is provided at one end of the secondary shaft 82 away from the primary shaft 81, and a sealing protrusion 7 is provided at a position corresponding to the sealing pad 9 in the primary control chamber 17. The sealing pad 9 and the sealing protrusion 7 are deformed by abutting against each other to seal the oil path between the inlet and outlet of the valve. The sealing pad 9 can be made of polytetrafluoroethylene, copper, rubber, etc. according to the temperature and flow rate of the medium. When the sealing requirement is high, multiple sealing protrusions 7 can be provided, and the cross-section of the sealing protrusion 7 can be set to a circular, rectangular, conical, etc. shape.

[0047] In some embodiments, the electromagnet includes an iron core 3 connected to the pilot valve core 4 , and a coil 2 is arranged around the iron core 3 .

[0048] In some embodiments, the main valve core 8 extends out of one end of the valve body 1 and is sleeved with a main valve dynamic sealing assembly 11 and a clamping ring 12 .

[0049] The present invention also provides a working process of a multifunctional cut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, which includes the following contents:

[0050] 1. If Figure 2 As shown, when the electromagnet is powered off, the pilot valve 4 is reset due to the lack of external traction, and at the same time, the connection between the solenoid valve inlet 13, the pilot control chamber 16 and the main control chamber 17 is closed, and no fuel can flow into the pilot control chamber 16 and the end surface of the joint between the main shaft 81 and the secondary shaft 82. The main valve core 8 is reset due to the lack of external force, thereby connecting the solenoid valve inlet 13, the main control chamber 17 and the solenoid valve outlet 14, that is, the multifunctional shut-off solenoid valve for the extrusion liquid rocket engine fuel supply system is opened.

[0051] 2. If Figure 3 As shown, when the electromagnet is energized, the electromagnet will pull the pilot valve 4 to move, and at the same time penetrate the solenoid valve inlet 13, the pilot control chamber 16 and the main control chamber 17. The fuel continuously entering the valve core drive section 14 will generate pressure, pushing the secondary shaft 82 to move toward the solenoid valve outlet 14, thereby closing the connection between the solenoid valve inlet 13, the main control chamber 17 and the solenoid valve outlet 14, that is, the multi-functional shut-off solenoid valve is used to close the fuel supply system of the extrusion type liquid rocket engine.

[0052] The multifunctional stop solenoid valve for the fuel supply system of the extrusion type liquid rocket engine of the present invention is formed by dividing the main valve core 8 into a main shaft 81 and a secondary shaft 82 which are coaxially and integrally arranged. The main shaft 81 extends out of the solenoid valve body, and a spring is mounted on the main shaft 81, so that the main valve core 8 is subjected to elastic force in the direction of the outlet 14 of the solenoid valve. Due to the control of the pilot valve core 4, a hydraulic pressure in the direction of the outlet 14 of the solenoid valve and closing the valve is formed on the end surface of the joint surface of the main shaft 81 and the secondary shaft 82. At the same time, the pressure of the outlet 14 of the solenoid valve acts on the end surface of the secondary shaft 82 to form a reverse hydraulic pressure to open the valve. When the coil is energized, the pilot valve core 4, driven by the iron core 3, acts the inlet pressure of the solenoid valve on the secondary shaft 82, forming a hydraulic pressure of the main valve core 8 in the direction of the outlet of the solenoid valve. At this time, the structural size ensures that the hydraulic pressure for closing the valve is greater than the hydraulic pressure for opening the valve, and the main valve core 8 moves to the closed position. When the coil is de-energized, the pilot valve core 4, driven by the iron core 3, applies the outlet pressure of the solenoid valve to the end face of the secondary shaft 82 to form a liquid pressure to open the valve. If the liquid pressure and elastic force acting on the main valve core 8 to close the valve are less than the liquid pressure to open the valve, the main valve core 8 moves to the open position.

[0053] Conventional pilot solenoid valves control the pressure at both ends of the main valve core through the pilot valve, and drive the main valve core to move through the pressure difference and the spring. Therefore, the existing pilot valve needs to be used in scenarios with large pressure differences. However, the extrusion type liquid rocket engine fuel supply system belongs to the use scenario of large flow and small pressure difference. The present invention adopts a pilot valve in the valve structure, cooperates with the main shaft and the secondary shaft arranged in a coaxial and integrated manner, and controls the reciprocating movement of the pilot valve core through the on-off of the electromagnet, so that the size of the liquid pressure of the valve core driving section and the valve core opening and closing section will change slightly, so that the main valve core can be controlled to move to the closed position or the open position. The present invention adopts area difference, pressure difference and spring to drive together, which is equivalent to amplifying the pressure difference value through area difference. Therefore, the present invention can also be controlled under small pressure difference, which solves the problem that the existing extrusion type liquid rocket engine fuel supply system cannot use the pilot solenoid valve to control the on-off function of the fuel when the flow rate is large and the pressure difference is small.

[0054] Since the main shaft extends out of the valve body, as the hydraulic oil drives the main valve core, the secondary shaft also moves accordingly. Through the mechanical interface arranged on the main shaft, the adjustment and control of structural parameters such as the engine nozzle angle and the aircraft wing shape can be achieved simultaneously, thereby realizing the multi-function of the multi-function shut-off solenoid valve for the extrusion liquid rocket engine fuel supply system.

Claims

1. A multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine, characterized in that: The invention comprises a valve body (1), wherein the valve body (1) is provided with a solenoid valve inlet (13) and a solenoid valve outlet (14) for fuel to pass through, and the valve body (1) further comprises: a main control chamber (17), one end of which is connected to the outside of the valve body (1) and the other end of which is connected to the solenoid valve outlet (14); a pilot control chamber (16), one side of which is in communication with the solenoid valve inlet (13) and the other side of which is in communication with the main control chamber (17); a connecting branch (15) connected between the pilot control chamber (16) and the solenoid valve outlet (14); a pilot valve core (4), one end of which passes through the pilot control chamber (16) and is connected to an electromagnet, and the other end of which is located in the pilot control chamber (16); A main valve core (8) is located in the main control chamber (17), and comprises a main shaft (81) and a secondary shaft (82) which are coaxially and integrally arranged, wherein the outer diameter of the secondary shaft (82) is larger than the outer diameter of the main shaft (81), and a mechanical interface (18) is provided on one end of the main shaft (81) away from the secondary shaft, wherein the mechanical interface (18) is used for connecting to an external device to achieve adjustment and control of the structural parameters of the external device; the main shaft (81) passes through the main control chamber (17), and the secondary shaft (82) is located in the main control chamber (17), on a side close to the outlet (14) of the solenoid valve; The electromagnet switches between two states, namely, an energized state and an unenergized state, and is used to pull the pilot valve core (4) to move back and forth in the pilot control chamber (16), thereby realizing the connection or closure of the solenoid valve inlet (13) and the pilot control chamber (16), and enables the secondary shaft (82) to move back and forth in the main control chamber (17), thereby driving the secondary shaft (82) to close or open the connection between the solenoid valve inlet (13) and the solenoid valve outlet (14).

2. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1, characterized in that: The pilot valve core (4) comprises a push rod and a shift rod vertically arranged thereon, wherein the push rod is arranged along the moving direction of the pilot valve core (4), and the shift rod is used to move along with the push rod to switch between the following two states: State 1: the pilot control chamber (16) is connected to the solenoid valve inlet (13) and the main control chamber (17) respectively, and is disconnected from the connecting branch (15); State 2: The pilot control chamber (16) is disconnected from the solenoid valve inlet (13), and is connected to the main control chamber (17) and the connecting branch (15) respectively.

3. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1 or 2, characterized in that: A dynamic sealing assembly (5) is arranged on the outside of the outlet of the pilot valve core (4) passing through the pilot control chamber (16).

4. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 2, characterized in that: A return spring (6) is arranged between the push rod and the dynamic sealing assembly (5).

5. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1 or 2, characterized in that: A main valve return spring (10) is sleeved on the outside of the main shaft (81).

6. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1 or 2, characterized in that: A sealing gasket (9) is arranged at one end of the secondary shaft (82) away from the primary shaft (81), and a sealing protrusion (7) is arranged at a position corresponding to the sealing gasket (9) in the primary control chamber (17).

7. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1 or 2, characterized in that: The electromagnet comprises an iron core (3) connected to the pilot valve core (4), and a coil (2) is arranged around the iron core (3).

8. The multifunctional shut-off solenoid valve for a fuel supply system of an extrusion type liquid rocket engine according to claim 1 or 2, characterized in that: One end of the main valve core (8) extending out of the valve body (1) is sleeved with a main valve dynamic sealing component (11) and a clamping ring (12).

9. The working method of the multifunctional cut-off solenoid valve for the fuel supply system of the extrusion type liquid rocket engine is characterized in that: Based on the multifunctional shut-off solenoid valve for the extrusion type liquid rocket engine fuel supply system as described in any one of claims 1 to 8, Includes the following: When the coil is energized, the pilot valve core (4) moves under the drive of the iron core (3), and connects the solenoid valve inlet (13), the pilot control chamber (16) and the main control chamber (17), and the main valve core (8) moves toward the solenoid valve outlet (14) under the inlet pressure, and finally closes the solenoid valve inlet (13) and the solenoid valve outlet (14), and the solenoid valve is closed; When the coil is powered off, the pilot valve core (4) is reset and closes the connection between the solenoid valve inlet (13), the pilot control chamber (16) and the main control chamber (17), and no fuel flows into the pilot control chamber (16) and the end surface of the joint between the main shaft (81) and the secondary shaft (82). The main valve core (8) is reset, thereby connecting the solenoid valve inlet (13), the main control chamber (17) and the solenoid valve outlet (14), and the solenoid valve is opened.

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