Multi-engine propellant isolation control system, control method and carrier rocket

Abstract

The invention provides a multi-engine propellant isolation control system and method and a carrier rocket. The system comprises a first gas storage cylinder and a first gas collecting pipe; wherein the first gas collecting pipe is communicated with the first gas storage bottle, and a plurality of control cavity opening branch gas paths are arranged on the first gas collecting pipe; each control cavity opening branch gas path is communicated with an opening control cavity of an oxygen isolation valve and an opening control cavity of a fuel isolation valve at an inlet of each engine, and a first two-position three-way electromagnetic valve is arranged between each control cavity opening branch gas path and the oxygen isolation valve and the fuel isolation valve at the inlet of the corresponding engine. And the first two-position three-way electromagnetic valve is used for simultaneously controlling the opening control cavities of the oxygen isolation valve and the fuel isolation valve. Opening and closing of the multiple pneumatic isolation valves at inlets of the multiple engines and isolation sealing of propellants can be controlled, multiple paths of control gas are connected with the multiple pneumatic isolation valves, and each path of control gas controls opening and closing of two pneumatic isolation valves at the same time.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket engine propellant isolation control, and in particular to a multi-engine propellant isolation control system, a control method and a launch vehicle. Background Art

[0002] At present, the first stage of medium and large launch vehicles at home and abroad all use multiple engines in parallel to increase the launch thrust. Since multiple engines are connected in parallel in the first stage of the launch vehicle, the propellant pipelines between the propellant tank and the multiple engines also need to be connected in parallel, but the parallel connection of multiple pipelines makes the propellant isolation control more complicated.

[0003] Therefore, in order to meet the requirements of propellant isolation control for complex multi-pipeline parallel connection, it is urgently necessary to provide a nine-engine propellant isolation control technology. Summary of the invention

[0004] In view of this, an object of an embodiment of the present invention is to provide a multi-engine propellant isolation control system, a control method and a launch vehicle to solve the above-mentioned technical problems.

[0005] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a multi-engine propellant isolation control system, the system comprising: a first gas storage bottle and a first gas collecting pipe; wherein the first gas collecting pipe is connected to the first gas storage bottle, and the first gas collecting pipe is provided with a plurality of open control cavity branch gas paths;

[0006] Each of the open control cavity branch gas circuits is respectively connected to the open control cavity of the oxygen isolation valve and the fuel isolation valve at the inlet of each engine, and a two-position three-way solenoid valve is arranged between each of the open control cavity branch gas circuits and the oxygen isolation valve and the fuel isolation valve at the inlet of each engine corresponding thereto, and the open control cavities of the oxygen isolation valve and the fuel isolation valve are simultaneously controlled by the two-position three-way solenoid valve.

[0007] In some possible implementations, the system further includes: a second gas storage cylinder and a second gas collecting pipe, wherein the second gas collecting pipe is provided with a plurality of control chamber branch gas paths;

[0008] Each of the branch gas paths of the closing control chamber is respectively connected to the closing control chamber of the oxygen isolation valve and the fuel isolation valve at the inlet of each engine, and the second gas collecting pipe is provided with a first two-position two-way solenoid valve, and a plurality of the branch gas paths of the closing control chamber are located at the outlet of the first two-position two-way solenoid valve;

[0009] Each of the branch gas paths of the closing control chamber is connected to the oxygen isolation valve and the fuel isolation valve at the inlet of each corresponding engine, and the closing control chambers of the oxygen isolation valve and the fuel isolation valve at the inlet of each engine are simultaneously controlled by the first two-position two-way solenoid valve.

[0010] In some possible embodiments, a one-way valve and a second two-position two-way solenoid valve are also provided on the second gas collecting pipe, the one-way valve is located between the first two-position two-way solenoid valve and the inlet of several branch gas paths of the control chamber, and the second two-position two-way solenoid valve is located at the outlet of several branch gas paths, and the one-way valve cooperates with the second two-position two-way solenoid valve to maintain pressure and seal the gas in the second gas collecting pipe between the one-way valve and the second two-position two-way solenoid valve.

[0011] In some possible implementations, the number of the engines is equal to the number of the open control chamber branch gas paths and the number of the close control chamber branch gas paths.

[0012] In some possible implementations, the number of the engines is nine.

[0013] In some possible implementations, the oxygen isolation valve and the fuel isolation valve are both pneumatic isolation valves.

[0014] In some possible implementations, the pneumatic isolation valve is a pneumatic normally closed butterfly valve.

[0015] In a second aspect, an embodiment of the present invention provides a multi-engine propellant isolation control method, the control method comprising:

[0016] The second two-position two-way solenoid valve is powered on to open, and the control gas in the second gas storage cylinder is sequentially delivered to a plurality of off-control chamber branch gas paths through the second gas collecting pipe, the second two-position two-way solenoid valve and the one-way valve to the off-control chamber and the second two-position two-way solenoid valve of the oxygen isolation valve and the fuel isolation valve corresponding to each engine;

[0017] Cut off the power and close the second two-position two-way solenoid valve, and perform pressure-maintaining and sealing of the gas in the second gas collecting pipe between the one-way valve and the second two-position two-way solenoid valve through the one-way valve and the second two-position two-way solenoid valve;

[0018] Power is turned on to open the two-position three-way solenoid valve on each open control cavity branch gas path, and the gas in the first gas storage cylinder enters the open control cavity of the oxygen isolation valve and the fuel isolation valve corresponding to each engine through the first gas collecting pipe and the plurality of open control cavity branch gas paths, thereby opening the oxygen isolation valve and the fuel isolation valve;

[0019] Open the second two-position two-way solenoid valve, and discharge the control gas in the second air collecting pipe between the one-way valve and the second two-position two-way solenoid valve and the closing control chamber of the oxygen isolation valve and the fuel isolation valve corresponding to each engine through the second two-position two-way solenoid valve.

[0020] In some possible implementations, the method further includes:

[0021] During the flight of the rocket, if one of the multiple engines connected in parallel fails, the fault feedback instruction of the failed engine is used to close the two-position three-way solenoid valve on the open control cavity branch gas path corresponding to the open control cavity of the oxygen isolation valve and the fuel isolation valve at the inlet of the failed engine, so that the control gas in the open control cavity of the oxygen isolation valve and the fuel isolation valve at the inlet of the failed engine is discharged from the second two-position two-way solenoid valve.

[0022] In a third aspect, an embodiment of the present invention further provides a launch vehicle, which adopts a multi-engine propellant isolation control system as described in any one of the first aspects.

[0023] The embodiments of the present invention have the following beneficial effects:

[0024] The embodiment of the present invention can realize the control of the switch actuation of several pneumatic isolation valves at the inlet of multiple engines of the first stage of a rocket and the isolation and sealing of the propellant. It is connected with several pneumatic isolation valves through multi-channel control gas, and each control gas simultaneously controls the switch of two pneumatic isolation valves; one control gas simultaneously controls the closing of multiple pneumatic isolation valves, which greatly simplifies the propellant isolation control pipeline system;

[0025] The embodiments of the present invention can isolate the propellant from entering the engine when the rocket is filled with propellant, and the pneumatic isolation valve can be reliably actuated to open before ignition to allow the propellant to be filled into the engine and pre-cool the engine. In addition, if an engine fails during the flight of the rocket, the two propellant isolation valves at the inlet of the engine can be quickly and reliably closed to reduce the risk of large-scale leakage of propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 It is a structural schematic diagram of a first multi-engine propellant isolation control system according to an embodiment of the present invention;

[0028] Figure 2 It is a structural schematic diagram of a second multi-engine propellant isolation control system according to an embodiment of the present invention;

[0029] Figure 3 It is a structural schematic diagram of a nine-engine propellant isolation control system according to an embodiment of the present invention;

[0030] Figure 4 It is a flow chart of a multi-engine propellant isolation control method according to an embodiment of the present invention.

[0031] Description of Figure Numbers:

[0032] 1. The first oxygen isolation valve; 2. The first fuel isolation valve; 3. The first two-position three-way solenoid valve; 4. The second oxygen isolation valve; 5. The second fuel isolation valve; 6. The second two-position three-way solenoid valve; 7. The third oxygen isolation valve; 8. The third fuel isolation valve; 9. The third two-position three-way solenoid valve; 10. The fourth oxygen isolation valve; 11. The fourth fuel isolation valve; 12. The fourth two-position three-way solenoid valve; 13. The fifth oxygen isolation valve; 14. The fifth fuel isolation valve; 15. The fifth two-position three-way solenoid valve; 16. The sixth oxygen isolation valve; 17. The sixth fuel isolation valve; 18. The sixth two-position three-way solenoid valve; 19. The seventh oxygen isolation valve; 20. The seventh fuel isolation valve; 21. The seventh two-position three-way solenoid valve; 22. The eighth oxygen isolation valve; 23. The eighth fuel isolation valve; 24. The eighth two-position three-way solenoid valve; 25. The ninth oxygen isolation valve; 26. The ninth fuel isolation valve; 27. The ninth two-position three-way solenoid valve;

[0033] 28. The first gas cylinder; 29. ​​The second gas cylinder; 30. The one-way valve; 31. The two-position two-way solenoid valve; 32. The second two-position two-way solenoid valve; 33. The first gas collecting pipe; 34. The first open control chamber branch gas circuit; 35. The second open control chamber branch gas circuit; 36. The third open control chamber branch gas circuit; 37. The fourth open control chamber branch gas circuit; 38. The fifth open control chamber branch gas circuit; 39. The sixth open control chamber branch gas circuit; 40. The seventh open control chamber branch gas circuit; 41. The eighth open control chamber branch gas circuit; 42. The ninth open control chamber branch gas circuit; 43. The second gas collecting pipe. DETAILED DESCRIPTION

[0034] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown in order to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. In addition, the features, structures or characteristics described below may be combined in one or more embodiments in any suitable manner.

[0035] In the prior art, N engines are connected in parallel, and 2N parallel pipelines will branch out from the outlet of the propellant tank to connect to the pneumatic isolation valves at the inlets of the N engines. The pipeline layout is complicated, especially the pipeline system for controlling the switch actuation of the 2N pneumatic isolation valves is more complicated.

[0036] Therefore, in view of the problems existing in the prior art, the present invention provides a multi-engine propellant isolation control technology, which is used to solve the problem of parallel propellant isolation control of multiple engines in the first stage of a large carrier rocket. The present application can effectively control the switch actuation of 2N pneumatic isolation valves at the entrance of N engines and the isolation and sealing of propellants. N control gas lines are connected to 2N pneumatic isolation valves, and each control gas line controls the switch of two pneumatic isolation valves at the same time; one control gas line controls the closing of 2N pneumatic isolation valves at the same time, which greatly simplifies the isolation control pipeline system. It is achieved that the propellant is isolated from entering the engine when the rocket propellant is filled, and the pneumatic isolation valve can be reliably actuated to open before ignition, so that the propellant is filled into the engine and the engine is pre-cooled. If an engine fails during the flight of the rocket, the two propellant isolation valves at the entrance of the engine can be quickly and reliably closed to reduce the loss caused by a large amount of propellant leakage.

[0037] Figure 1 Schematic diagram of the structure of the first multi-engine propellant isolation control system according to an embodiment of the present invention. Figure 1As shown, taking nine engines connected in parallel as an example, the system includes: a first gas storage bottle 28 and a first gas collecting pipe 33; wherein the first gas collecting pipe 33 is connected to the first gas storage bottle 28, and a plurality of open control cavity branch gas paths are arranged on the first gas collecting pipe 33; each of the open control cavity branch gas paths is respectively connected to the open control cavity of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine, and a two-position three-way solenoid valve is arranged between each of the open control cavity branch gas paths and the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine corresponding to it, and the open control cavity of the oxygen isolation valve Y and the fuel isolation valve R is simultaneously controlled by the two-position three-way solenoid valve.

[0038] Specifically, the open control chamber branch gas circuit includes nine control gas branch circuits, each of which is provided with a two-position three-way solenoid valve, and nine engines are provided with a total of eighteen propellant isolation valves, namely, nine oxygen isolation valves Y and nine fuel isolation valves R, that is, each engine inlet is equipped with an oxygen isolation valve Y and a fuel isolation valve R; each two-position three-way solenoid valve controls the simultaneous switching of the two pneumatic isolation valves, the oxygen isolation valve Y and the fuel isolation valve R, at the inlet of one engine;

[0039] Figure 2 : is a schematic diagram of the structure of a second multi-engine propellant isolation control system according to an embodiment of the present invention. Figure 2 As shown, in some embodiments, the system further includes: a second gas storage bottle 29 and a second gas collecting pipe 43, the second gas collecting pipe 43 is provided with a plurality of closing control chamber branch gas circuits; each of the closing control chamber branch gas circuits is respectively connected to the closing control chamber of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine, a first two-position two-way solenoid valve 31 is provided on the second gas collecting pipe 43, and a plurality of the closing control chamber branch gas circuits are located at the outlet of the first two-position two-way solenoid valve 31; each of the closing control chamber branch gas circuits is connected to the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine corresponding to it, and the closing control chambers of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine are simultaneously controlled by the first two-position two-way solenoid valve 31.

[0040] like Figure 2 As shown, in some embodiments, a one-way valve 30 and a second two-position two-way solenoid valve 32 are also provided on the second gas collecting pipe 43, the one-way valve 30 is located between the first two-position two-way solenoid valve 31 and the inlet of several branch gas paths of the control chamber, and the second two-position two-way solenoid valve 32 is located at the outlet of several branch gas paths, and the one-way valve 30 cooperates with the second two-position two-way solenoid valve 32 to maintain pressure and seal the gas in the second gas collecting pipe 43 between the one-way valve 30 and the second two-position two-way solenoid valve 32.

[0041] Specifically, the second gas collecting pipe 43 is provided with nine control gas branch roads and one exhaust branch road. The inlet end of the second gas collecting pipe 43 is connected to the outlet of the second gas storage bottle 29. The second gas collecting pipe 43 is provided with a first two-position two-way solenoid valve 31, a one-way valve 30, and a second two-position two-way solenoid valve 32 in sequence; the nine control gas branch roads are connected to the closing control chambers of eighteen pneumatic isolation valves, and the outlet of one exhaust branch road is connected to the second two-position two-way solenoid valve 32.

[0042] The embodiment of the present invention arranges a first two-position two-way solenoid valve 31, a one-way valve 30, and a second two-position two-way solenoid valve 32 on the path of the second air collecting pipe 43, so that the control gas can reach the closing control chamber of eighteen pneumatic isolation valves and before the valve of the second two-position two-way solenoid valve 32, thereby increasing the sealing force of the eighteen pneumatic isolation valves, so that the isolation valves can meet the reliable sealing requirements; at the same time, the air in the second air collecting pipe 43 can also be pressure-sealed by the one-way valve 30 and the second two-position two-way solenoid valve 32.

[0043] In this embodiment, the number of the engines is nine; the number of the engines is equal to the number of the branch gas paths of the opening control chamber and the number of the branch gas paths of the closing control chamber.

[0044] by Figure 3 As shown in the figure, the nine engines are connected in parallel, including the first gas cylinder 28, the first gas collecting pipe 33, the first open control cavity branch gas path to the ninth open control cavity branch gas path (34-42), the second gas cylinder 29, the second gas collecting pipe 43, eighteen propellant pneumatic isolation valves, nine oxygen isolation valves and nine fuel isolation valves. The inlet end of the first gas collecting pipe 33 is connected to the outlet of the first gas cylinder 28, and the first gas collecting pipe 33 branches out nine open control cavity branch gas paths:

[0045] The first opening control chamber branch gas path 34 is provided with the ninth two-position three-way solenoid valve 27, the opening control chamber of the ninth oxygen isolation valve 25, and the opening control chamber of the ninth fuel isolation valve 26 in sequence;

[0046] The second opening control chamber branch gas path 35 is provided with the eighth two-position three-way solenoid valve 24, the opening control chamber of the eighth oxygen isolation valve 22, and the opening control chamber of the eighth fuel isolation valve 23 in sequence;

[0047] The third opening control chamber branch gas path 36 is provided with the seventh two-position three-way solenoid valve 21, the opening control chamber of the seventh oxygen isolation valve 19, and the opening control chamber of the seventh fuel isolation valve 20 in sequence;

[0048] The fourth opening control chamber branch gas path 37 is provided with a sixth two-position three-way solenoid valve 18, an opening control chamber of a sixth oxygen isolation valve 16, and an opening control chamber of a sixth fuel isolation valve 17 in sequence;

[0049] The fifth opening control chamber branch gas path 38 is provided with a fifth two-position three-way solenoid valve 15, an opening control chamber of the fifth oxygen isolation valve 13, and an opening control chamber of the fifth fuel isolation valve 14 in sequence;

[0050] The sixth opening control chamber branch gas path 39 is provided with a fourth two-position three-way solenoid valve 12, an opening control chamber of the fourth oxygen isolation valve 10, and an opening control chamber of the fourth fuel isolation valve 11 in sequence;

[0051] The seventh opening control chamber branch gas path 40 is provided with a third two-position three-way solenoid valve 9, an opening control chamber of the third oxygen isolation valve 7, and an opening control chamber of the third fuel isolation valve 8 in sequence;

[0052] The eighth opening control chamber branch gas path 41 is provided with the second two-position three-way solenoid valve 6, the opening control chamber of the second oxygen isolation valve 4, and the opening control chamber of the second fuel isolation valve 5 in sequence;

[0053] The ninth opening control chamber branch gas path 42 is provided with the first two-position three-way solenoid valve 3 , the opening control chamber of the first oxygen isolation valve 1 , and the opening control chamber of the first fuel isolation valve 2 in sequence.

[0054] The inlet end of the second gas collecting pipe 43 is connected to the outlet of the second gas storage bottle 29. The second gas collecting pipe 43 is provided with a first two-position two-way solenoid valve 31, a one-way valve 30, and a second two-position two-way solenoid valve 32 in sequence. At the outlet of the one-way valve 30, the second gas collecting pipe 43 is provided with nine closing control chamber branch gas circuits and one exhaust branch circuit. The nine closing control chamber branch gas circuits are connected to the closing control chambers of eighteen isolation valves, and the outlet of the one exhaust branch circuit is connected to the second two-position two-way solenoid valve 32.

[0055] The embodiment of the present invention can realize the control of the switching actuation of eighteen pneumatic isolation valves at the inlets of nine engines of the first stage of a rocket and the isolation and sealing of the propellant. It is connected to the eighteen pneumatic isolation valves through nine control gas lines, and each control gas line controls the switching of two pneumatic isolation valves at the same time; one control gas line controls the closing of the eighteen pneumatic isolation valves at the same time, which greatly simplifies the propellant isolation control pipeline system.

[0056] The embodiments of the present invention can also isolate the propellant from entering the engine when the rocket is filled with propellant, and the pneumatic isolation valve can be reliably actuated to open before ignition to allow the propellant to be filled into the engine and pre-cool the engine. In addition, if an engine fails during the flight of the rocket, the two propellant isolation valves at the inlet of the engine can be quickly and reliably closed to reduce the loss caused by a large amount of propellant leakage.

[0057] In some embodiments, the oxygen isolation valve and the fuel isolation valve are both pneumatic isolation valves; and the pneumatic isolation valve is a pneumatic normally closed butterfly valve.

[0058] Specifically, the pneumatic isolation valve is a pneumatic normally closed butterfly valve, and the opening and closing actuation of the isolation valve is that the cylinder actuator part drives the disc plate assembly of the isolation valve to rotate, thereby realizing the opening and closing function of the valve.

[0059] The cylinder actuator and its working principle are as follows: The cylinder actuator is composed of a cylinder body, a gear shaft, a piston, a spring, a plug cover and other parts. The two pistons are located on both sides of the gear shaft and are symmetrically distributed. The central axes of the two pistons coincide and are perpendicular to the axis of the gear shaft. The gear tooth part of the gear shaft meshes with the rack part of the two pistons. Symmetrical plug covers are arranged on both sides of the cylinder body and are connected to the cylinder body to form a controlled closing chamber. A spring is arranged between the plug cover and the piston. The output end of the gear shaft is connected to the input shaft of the disc plate assembly of the butterfly valve. Working principle of the cylinder mechanism: When the cylinder is not ventilated, the springs on both sides of the cylinder push the pistons on both sides to move toward the middle respectively, and the rack part of the piston pushes the gear shaft to rotate counterclockwise, causing the isolation valve disc to rotate counterclockwise to close the valve. When the closing chambers on both sides of the cylinder are ventilated, the piston is promoted to move toward the middle, increasing the counterclockwise rotation force of the gear shaft, thereby increasing the closing force of the valve; when the middle opening control chamber of the cylinder is ventilated, the piston is pushed to move to both sides, accompanied by compression of the closing control chamber spring and gas, and at the same time, the rack of the piston pulls the gear shaft to rotate clockwise to open the isolation valve; when the opening control chamber is degassing, the gas and spring of the closing control chamber push the piston to move toward the middle, and the rack part of the piston pushes the gear shaft to rotate counterclockwise, and the valve is closed.

[0060] Figure 4 : is a flow chart of a multi-engine propellant isolation control method according to an embodiment of the present invention. Figure 4 As shown, the control method comprises the following steps:

[0061] Step S1, power on to open the first two-position two-way solenoid valve 31, and the control gas in the second gas storage bottle 29 is sequentially delivered to a plurality of off-control chamber branch gas paths through the second gas collecting pipe 43, the first two-position two-way solenoid valve 31 and the one-way valve to the off-control chamber and the second two-position two-way solenoid valve 32 of the oxygen isolation valve Y and the fuel isolation valve R corresponding to each engine;

[0062] Step S2, power off and close the first two-position two-way solenoid valve 31, and pressure-maintain and seal the gas in the second gas collecting pipe 43 between the one-way valve and the second two-position two-way solenoid valve 32 through the one-way valve and the second two-position two-way solenoid valve 32;

[0063] Step S3, power on to open the two-position three-way solenoid valve on each open control cavity branch gas path, and the gas in the first gas storage bottle 28 enters the open control cavity of the oxygen isolation valve Y and the fuel isolation valve R corresponding to each engine through the first gas collecting pipe 33 and a plurality of open control cavity branch gas paths, and opens the oxygen isolation valve Y and the fuel isolation valve R;

[0064] Step S4, open the second two-position two-way solenoid valve 32, and discharge the control gas in the second collecting pipe 43 between the one-way valve and the second two-position two-way solenoid valve 32 and the closing control chamber of the oxygen isolation valve Y and the fuel isolation valve R corresponding to each engine through the second two-position two-way solenoid valve 32.

[0065] Specifically, when the rocket tank is filled with propellant, the eighteen propellant isolation valves connected to the nine engines at the bottom of the tank need to be closed. Although the isolation valves are normally closed valves, they still need to have sufficiently reliable sealing.

[0066] Therefore, the first two-position two-way solenoid valve 31 is powered on to open, and the control gas in the second gas storage bottle 29 is transported through the first two-position two-way solenoid valve 31 and the one-way valve in sequence through the second gas collecting pipe 43 to the closing control chamber of the eighteen pneumatic isolation valves and in front of the second two-position two-way solenoid valve 32, thereby increasing the sealing force of the eighteen pneumatic isolation valves, so that the isolation valves meet reliable sealing performance;

[0067] Then turn off the power and close the first two-position two-way solenoid valve 31. Since a one-way valve and a second two-position two-way solenoid valve 32 are arranged on the second gas collecting pipe 43, the air in the second gas collecting pipe 43 is pressure-sealed to ensure that after closing the first two-position two-way solenoid valve 31, there is still control gas in the control chamber of the eighteen isolation valves and the second gas collecting pipe 43, thereby ensuring the reliable sealing of the eighteen isolation valves.

[0068] Before the rocket engine is ignited, the propellant isolation valve in front of the engine needs to be opened to pre-cool the nine engines and fill the propellant. Therefore, the nine two-position three-way solenoid valves (3, 6, 9, 12, 15, 18, 21, 24, 27) are powered on to open, and the control gas in the first gas cylinder 28 is sent to the open control chamber of the eighteen isolation valves through the first gas collecting pipe 33 and the nine-way open control chamber branch gas path (34-42), prompting the eighteen isolation valves to open. After the eighteen isolation valves are opened, the second two-position two-way solenoid valve 32 is opened to discharge the control gas in the second gas collecting pipe 43 and the closed control chamber of the eighteen isolation valves through the second two-position two-way solenoid valve 32; ensuring the reliable opening and reliable maintenance of the open state of the eighteen pneumatic isolation valves.

[0069] In some embodiments, the method also includes: during the flight of the rocket, if one of the multiple engines connected in parallel fails, the two-position three-way solenoid valve on the open control cavity branch gas path corresponding to the open control cavity of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of the failed engine is closed through the fault feedback instruction of the failed engine, so that the control gas in the open control cavity of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of the failed engine is discharged from the second two-position two-way solenoid valve 32.

[0070] Specifically, when a rocket is flying, if one of the nine parallel engines fails and the two propellant isolation valves at the entrance of the engine need to be closed, the two isolation valves at the entrance of the engine are powered off and closed through the fault feedback instruction of the engine, and the two-position three-way solenoid valve on the gas path of the control cavity is opened. The control gas in the control cavity of the two isolation valves is discharged from the second two-position two-way solenoid valve, and the two pneumatic isolation valves are automatically closed to cut off the propellant. The control cavity is closed for ventilation to ensure the reliability of the closure. Since the pressure of the open control gas is much greater than that of the closed control gas, other valves are not affected by the closed control gas.

[0071] The control method provided by the embodiment of the present invention can not only realize the control of the switching actuation of the eighteen pneumatic isolation valves at the inlets of the nine engines of the first stage of the rocket and the isolation and sealing of the propellant, but also connect the eighteen pneumatic isolation valves through the control gas of the nine-way open control cavity branch gas circuit, and the control gas of each open control cavity branch gas circuit simultaneously controls the switching of two pneumatic isolation valves; at the same time, the control gas of the nine-way closed control cavity branch gas circuit simultaneously controls the closing of the eighteen pneumatic isolation valves, which greatly simplifies the propellant isolation control pipeline system; in addition, the present embodiment can also realize the isolation of the propellant from entering the engine when the rocket propellant is filled, and the pneumatic isolation valve can be reliably actuated to open before ignition, so that the propellant is filled into the engine and the engine is pre-cooled, and if an engine fails during the flight of the rocket, the two propellant isolation valves at the inlet of the engine can be quickly and reliably closed to reduce the loss caused by the large amount of propellant leakage.

[0072] Embodiment 3

[0073] The present invention also provides a launch vehicle, which adopts the multi-engine propellant isolation control system described in Example 1.

[0074] In the description of the embodiments of the present invention, it should be noted that the orientations or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention 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 cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0075] In the embodiments of the present invention, unless otherwise clearly specified and limited, the terms "installed, connected, connected" should be understood in a broad sense, for example: it can be a fixed connection, a detachable connection or an integral connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0076] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A multi-engine propellant isolation control system, characterized in that: It comprises a first gas storage bottle (28) and a first gas collecting pipe (33); wherein the first gas collecting pipe (33) is in communication with the first gas storage bottle (28), and the first gas collecting pipe (33) is provided with a plurality of open control cavity branch gas paths; Each of the open control chamber branch gas circuits is respectively connected to the open control chambers of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each engine, and a two-position three-way solenoid valve is arranged between each of the open control chamber branch gas circuits and the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each engine corresponding thereto, and the open control chambers of the oxygen isolation valve (Y) and the fuel isolation valve (R) are simultaneously controlled by the two-position three-way solenoid valve.

2. A multi-engine propellant isolation control system according to claim 1, characterized in that: The system further comprises: a second gas storage bottle (29) and a second gas collecting pipe (43), wherein the second gas collecting pipe (43) is in communication with the second gas storage bottle (29), and the second gas collecting pipe (43) is provided with a plurality of control chamber branch gas paths; Each of the off-control chamber branch gas paths is respectively connected to the off-control chamber of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each engine; a first two-position two-way solenoid valve (31) is provided on the second gas collecting pipe (43); and a plurality of the off-control chamber branch gas paths are located at the outlet of the first two-position two-way solenoid valve (31); Each of the branch gas paths of the closing control chamber is connected to the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each corresponding engine, and the closing control chambers of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each engine are simultaneously controlled by the first two-position two-way solenoid valve (31).

3. A multi-engine propellant isolation control system according to claim 2, characterized in that: A one-way valve (30) and a second two-position two-way solenoid valve (32) are also provided on the second gas collecting pipe (43); the one-way valve (30) is located between the first two-position two-way solenoid valve (31) and the inlets of the plurality of branch gas paths of the control chamber; the second two-position two-way solenoid valve (32) is located at the outlets of the plurality of branch gas paths.

4. A multi-engine propellant isolation control system according to claim 3, characterized in that: The number of the engines is equal to the number of the open control chamber branch gas paths and the number of the close control chamber branch gas paths.

5. A multi-engine propellant isolation control system according to claim 4, characterized in that: The number of engines is nine.

6. A multi-engine propellant isolation control system according to claim 4, characterized in that: The oxygen isolation valve (Y) and the fuel isolation valve (R) are both pneumatic isolation valves.

7. A multi-engine propellant isolation control system according to claim 6, characterized in that: The pneumatic isolation valve is a pneumatic normally closed butterfly valve.

8. A multi-engine propellant isolation control method, characterized in that: The control method comprises: The first two-position two-way solenoid valve (31) is powered on to open, and the control gas in the second gas storage bottle (29) is sequentially delivered to a plurality of off-control chamber branch gas paths through the second gas collecting pipe (43) and the first two-position two-way solenoid valve (31) and the one-way valve (30) to the off-control chamber of the oxygen isolation valve (Y) and the fuel isolation valve (R) corresponding to each engine and the second two-position two-way solenoid valve (32); The first two-position two-way solenoid valve (31) is powered off and closed, and the gas in the second gas collecting pipe (43) between the one-way valve (30) and the second two-position two-way solenoid valve (32) is pressure-sealed through the one-way valve (30) and the second two-position two-way solenoid valve (32); Power is supplied to open the two-position three-way solenoid valve on each open control cavity branch gas path, and the gas in the first gas storage bottle (28) enters the open control cavity of the oxygen isolation valve (Y) and the fuel isolation valve (R) corresponding to each engine through the first gas collecting pipe (33) and the plurality of open control cavity branch gas paths, thereby opening the oxygen isolation valve (Y) and the fuel isolation valve (R); The second two-position two-way solenoid valve (32) is opened, and the control gas in the second air collecting pipe (43) between the one-way valve (30) and the second two-position two-way solenoid valve (32) and the closing control chamber of the oxygen isolation valve (Y) and the fuel isolation valve (R) corresponding to each engine is discharged through the second two-position two-way solenoid valve (32).

9. A multi-engine propellant isolation control method according to claim 8, characterized in that: The method further comprises: During the flight of a rocket, if any one of the multiple engines connected in parallel fails, the fault feedback instruction of the failed engine is used to close the two-position three-way solenoid valve on the open control cavity branch gas path corresponding to the open control cavity of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of the failed engine, so that the control gas in the open control cavity of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of the failed engine is discharged from the second two-position two-way solenoid valve (32).

10. A launch vehicle, characterized in that: The launch vehicle adopts a multi-engine propellant isolation control system as described in any one of claims 1-7.

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