Multi-engine propellant isolation control system, control method and launch vehicle

Abstract

This invention provides a multi-engine propellant isolation control system, control method, and launch vehicle. The system includes a first gas storage cylinder and a first gas collecting pipe. The first gas collecting pipe is connected to the first gas storage cylinder and has several branch gas paths for opening control chambers. Each branch gas path is connected to the opening control chamber of an oxygen isolation valve and a fuel isolation valve at the inlet of each engine. A first two-position three-way solenoid valve is provided between each branch gas path and its corresponding oxygen isolation valve and fuel isolation valve at the engine inlet. The first two-position three-way solenoid valve simultaneously controls the opening control chambers of the oxygen isolation valve and the fuel isolation valve. This invention can control the opening and closing of multiple pneumatic isolation valves at the inlets of multiple engines and the isolation and sealing of the propellant. Multiple control gas paths are connected to multiple pneumatic isolation valves, and each control gas path simultaneously controls the opening and closing of two pneumatic isolation valves.

Description

Technical Field

[0001] This invention relates to the field of rocket engine propellant isolation control technology, specifically to a multi-engine propellant isolation control system, control method, and launch vehicle. Background Technology

[0002] Currently, both domestic and international medium and large launch vehicles employ multiple engines connected in parallel at the first stage to increase payload thrust. Because multiple engines in the first stage of a launch vehicle are connected in parallel, the propellant pipeline connections between the propellant tanks and these engines also need to be paralleled. However, the parallel connection of multiple pipelines makes propellant isolation and control quite complex.

[0003] Therefore, in order to meet the propellant isolation control requirements of complex multi-pipeline parallel operation, there is an urgent need to provide a propellant isolation control technology for a nine-engine system. Summary of the Invention

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

[0005] To achieve the above objectives, in a first aspect, embodiments of the present invention provide a multi-engine propellant isolation control system, the system comprising: a first gas storage cylinder and a first gas collecting pipe; wherein, the first gas collecting pipe is connected to the first gas storage cylinder, and the first gas collecting pipe is provided with a plurality of open control chamber branch gas paths;

[0006] Each of the opening control chamber branch gas paths is connected to the opening control chamber of the oxygen isolation valve and the fuel isolation valve at the inlet of each engine. A two-position three-way solenoid valve is provided between each of the opening control chamber branch gas paths and the corresponding oxygen isolation valve and fuel isolation valve at the inlet of each engine. The opening control chamber of the oxygen isolation valve and the fuel isolation valve are controlled simultaneously 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 closed control chamber branch gas paths is connected to the closed control chamber of the oxygen isolation valve and the fuel isolation valve at the inlet of each engine. A first two-position two-way solenoid valve is provided on the second gas collection pipe, and several of the closed control chamber branch gas paths are located at the outlet of the first two-position two-way solenoid valve.

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

[0010] In some possible implementations, a one-way valve and a second two-position two-way solenoid valve are also provided on the second gas collection pipe. The one-way valve is located between the first two-position two-way solenoid valve and the inlet of the several control chamber branch gas paths, and the second two-position two-way solenoid valve is located at the outlet of the several branch gas paths. The gas in the second gas collection pipe between the one-way valve and the second two-position two-way solenoid valve is pressure-maintained and sealed by the cooperation of the one-way valve and the second two-position two-way solenoid valve.

[0011] In some possible implementations, the number of engines is equal to the number of open control chamber branch air passages and the number of closed control chamber branch air passages.

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

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

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

[0015] Secondly, embodiments of the present invention provide a propellant isolation control method for multi-engine systems, the control method comprising:

[0016] When the second two-position two-way solenoid valve is opened by power, the control gas in the second gas cylinder is delivered through the second gas collection pipe, the second two-position two-way solenoid valve and the check valve to several control chamber branch gas lines to the control chamber of the oxygen isolation valve and fuel isolation valve corresponding to each engine and the second two-position two-way solenoid valve.

[0017] When the power is cut off, the second two-position two-way solenoid valve is closed, and the gas in the second gas collection pipe between the one-way valve and the second two-position two-way solenoid valve is pressure-maintained and sealed through the one-way valve and the second two-position two-way solenoid valve.

[0018] When energized, the two-position three-way solenoid valves on each branch gas path of the control chamber are opened. The gas in the first gas storage cylinder enters the control chamber of the oxygen isolation valve and the fuel isolation valve corresponding to each engine through the first gas collection pipe and several branch gas paths of the control chamber, thus 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 gas collection pipe between the one-way valve and the second two-position two-way solenoid valve, as well as the control chamber of the oxygen isolation valve and 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 rocket flight, if one of the multiple parallel engines malfunctions, the fault feedback command from the malfunctioning engine closes the two-position three-way solenoid valve on the branch gas path corresponding to the opening control chamber of the oxygen isolation valve and fuel isolation valve at the inlet of the malfunctioning engine. This allows the control gas in the opening control chamber of the oxygen isolation valve and fuel isolation valve at the inlet of the malfunctioning engine to be discharged through the second two-position two-way solenoid valve.

[0022] Thirdly, embodiments of the present invention also provide a launch vehicle, wherein the launch vehicle employs 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 embodiments of the present invention can realize the opening and closing of several pneumatic isolation valves at the inlet of multiple engines in the first stage of a rocket and the isolation and sealing of propellant. By connecting multiple control gas to several pneumatic isolation valves, each control gas simultaneously controls the opening and closing 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 propellant from entering the engine during rocket propellant loading, ensure that the pneumatic isolation valve can be reliably opened before ignition to allow propellant to fill the engine and pre-cool the engine, and quickly and reliably close the two propellant isolation valves at the engine inlet if an engine malfunctions during rocket flight, thereby reducing the risk of large-scale propellant leakage. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

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

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

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

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

[0031] Explanation of icon numbers:

[0032] 1. First oxygen isolation valve; 2. First fuel isolation valve; 3. First two-position three-way solenoid valve; 4. Second oxygen isolation valve; 5. Second fuel isolation valve; 6. Second two-position three-way solenoid valve; 7. Third oxygen isolation valve; 8. Third fuel isolation valve; 9. Third two-position three-way solenoid valve; 10. Fourth oxygen isolation valve; 11. Fourth fuel isolation valve; 12. Fourth two-position three-way solenoid valve; 13. Fifth oxygen isolation valve; 14. Fifth fuel isolation valve; 15. Fifth two-position three-way solenoid valve; 16. Sixth oxygen isolation valve; 17. Sixth fuel isolation valve; 18. Sixth two-position three-way solenoid valve; 19. Seventh oxygen isolation valve; 20. Seventh fuel isolation valve; 21. Seventh two-position three-way solenoid valve; 22. Eighth oxygen isolation valve; 23. Eighth fuel isolation valve; 24. Eighth two-position three-way solenoid valve; 25. Ninth oxygen isolation valve; 26. Ninth fuel isolation valve; 27. Ninth two-position three-way solenoid valve;

[0033] 28. First gas cylinder; 29. ​​Second gas cylinder; 30. One-way valve; 31. Two-position two-way solenoid valve; 32. Second two-position two-way solenoid valve; 33. First gas collecting pipe; 34. First open control chamber branch gas path; 35. Second open control chamber branch gas path; 36. Third open control chamber branch gas path; 37. Fourth open control chamber branch gas path; 38. Fifth open control chamber branch gas path; 39. Sixth open control chamber branch gas path; 40. Seventh open control chamber branch gas path; 41. Eighth open control chamber branch gas path; 42. Ninth open control chamber branch gas path; 43. Second gas collecting pipe. Detailed Implementation

[0034] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. In the accompanying drawings and the following description, at least some well-known structures and techniques have not been shown in order to avoid unnecessarily obscuring the invention; and, for clarity, the dimensions of some structures may be exaggerated. Furthermore, the features, structures, or characteristics described below may be combined in any suitable manner in one or more embodiments.

[0035] In the existing technology, when N engines are connected in parallel, 2N parallel pipelines will branch off from the propellant tank outlet and connect to the pneumatic isolation valves at the inlets of the N engines. The pipeline layout is complex, especially the pipeline system that controls the opening and closing of the 2N pneumatic isolation valves.

[0036] Therefore, addressing the problems existing in the prior art, this invention provides a multi-engine propellant isolation control technology to solve the problem of propellant isolation control for multiple engines in the first stage of a large launch vehicle. This application can effectively control the opening and closing of 2N pneumatic isolation valves at the inlet of N engines and the isolation and sealing of the propellant. By connecting N control gas lines to the 2N pneumatic isolation valves, each control gas line simultaneously controls the opening and closing of two pneumatic isolation valves; one control gas line simultaneously controls the closing of 2N pneumatic isolation valves, greatly simplifying the isolation control pipeline system. This achieves the isolation of propellant entering the engine during rocket propellant loading, reliable opening of the pneumatic isolation valves before ignition to allow propellant to fill the engine and pre-cool the engine, and rapid and reliable closure of the two propellant isolation valves at the inlet of the engine in case of a malfunction during rocket flight, thereby reducing losses caused by large-scale propellant leakage.

[0037] Figure 1 This is a schematic diagram of the structure of the first multi-engine propellant isolation control system according to an embodiment of the present invention, as shown below. Figure 1As shown, taking nine engines connected in parallel as an example, the system includes: a first gas storage cylinder 28 and a first gas collection pipe 33; wherein, the first gas collection pipe 33 is connected to the first gas storage cylinder 28, and the first gas collection pipe 33 is provided with several opening control chamber branch gas paths; each of the opening control chamber branch gas paths is connected to the opening control chamber 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 provided between each of the opening control chamber branch gas paths and the corresponding oxygen isolation valve Y and fuel isolation valve R at the inlet of each engine, and the opening control chamber of the oxygen isolation valve Y and the fuel isolation valve R are simultaneously controlled by the two-position three-way solenoid valve.

[0038] Specifically, the control chamber branch gas path includes nine control gas branches, each equipped with a two-position three-way solenoid valve. The nine engines are equipped 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 one oxygen isolation valve Y and one fuel isolation valve R. Each two-position three-way solenoid valve controls the simultaneous opening and closing of the two pneumatic isolation valves, oxygen isolation valve Y and fuel isolation valve R, at the inlet of one engine.

[0039] Figure 2 This is a schematic diagram of the structure of the second type of multi-engine propellant isolation control system according to an embodiment of the present invention, as shown below. Figure 2 As shown, in some embodiments, the system further includes: a second gas storage cylinder 29 and a second gas collection pipe 43, the second gas collection pipe 43 being provided with a plurality of control chamber branch gas paths; each of the control chamber branch gas paths is connected to the control chamber of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each engine, the second gas collection pipe 43 being provided with a first two-position two-way solenoid valve 31, the plurality of control chamber branch gas paths being located at the outlet of the first two-position two-way solenoid valve 31; each of the control chamber branch gas paths is connected to the oxygen isolation valve Y and the fuel isolation valve R at the inlet of each corresponding engine, and the 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 collection pipe 43. The one-way valve 30 is located between the first two-position two-way solenoid valve 31 and the inlet of the several control chamber branch gas paths, and the second two-position two-way solenoid valve 32 is located at the outlet of the several branch gas paths. Through the cooperation of the one-way valve 30 and the second two-position two-way solenoid valve 32, the gas in the second gas collection pipe 43 between the one-way valve 30 and the second two-position two-way solenoid valve 32 is pressure-sealed.

[0041] Specifically, the second gas collection pipe 43 is equipped with nine control gas branches and one exhaust branch. The inlet of the second gas collection pipe 43 is connected to the outlet of the second gas storage cylinder 29. The second gas collection pipe 43 is equipped 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 branches are connected to the closing control chambers of eighteen pneumatic isolation valves, and the outlet of the exhaust branch is connected to the second two-position two-way solenoid valve 32.

[0042] In this embodiment of the invention, by setting a first two-position two-way solenoid valve 31, a one-way valve 30, and a second two-position two-way solenoid valve 32 along the path of the second gas collection pipe 43, the control air can be directed to the closing control chamber of the 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 and enabling the isolation valves to meet reliable sealing requirements. At the same time, the one-way valve 30 and the second two-position two-way solenoid valve 32 can also be used to maintain pressure and seal the air in the second gas collection pipe 43.

[0043] In this embodiment, the number of engines is nine; the number of engines is equal to the number of the open control chamber branch air passages and the number of the close control chamber branch air passages.

[0044] by Figure 3 Taking the nine engines in parallel as an example, the system includes a first gas cylinder 28, a first gas collecting pipe 33, a first open control chamber branch gas path to a ninth open control chamber branch gas path (34-42), a second gas cylinder 29, a second gas collecting pipe 43, eighteen propellant pneumatic isolation valves, nine oxygen isolation valves, and nine fuel isolation valves. The inlet of the first gas collecting pipe 33 is connected to the outlet of the first gas cylinder 28, and nine open control chamber branch gas paths branch off from the first gas collecting pipe 33.

[0045] The first control chamber branch gas passage 34 is sequentially provided with the control chambers for the opening of the ninth two-position three-way solenoid valve 27, the ninth oxygen isolation valve 25, and the ninth fuel isolation valve 26.

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

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

[0048] The fourth control chamber branch gas passage 37 is sequentially provided with the opening control chambers of the sixth two-position three-way solenoid valve 18, the sixth oxygen isolation valve 16, and the sixth fuel isolation valve 17.

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

[0050] The sixth control chamber branch gas passage 39 is sequentially provided with the control chambers for the fourth two-position three-way solenoid valve 12, the fourth oxygen isolation valve 10, and the fourth fuel isolation valve 11.

[0051] The seventh open control chamber branch gas passage 40 is sequentially equipped with the opening control chambers of the third two-position three-way solenoid valve 9, the third oxygen isolation valve 7, and the third fuel isolation valve 8.

[0052] The second two-position three-way solenoid valve 6, the second oxygen isolation valve 4, and the second fuel isolation valve 5 are sequentially installed on the eighth open control chamber branch gas line 41.

[0053] The ninth control chamber branch gas path 42 is sequentially 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.

[0054] The inlet of the second gas collecting pipe 43 is connected to the outlet of the second gas storage cylinder 29. The second gas collecting pipe 43 is sequentially equipped 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. At the outlet of the one-way valve 30, the second gas collecting pipe 43 is provided with nine closing control chamber branch gas paths and one exhaust branch gas path. The nine closing control chamber branch gas paths are connected to the closing control chambers of eighteen isolation valves, and the outlet of the exhaust branch gas path is connected to the second two-position two-way solenoid valve 32.

[0055] The embodiments of the present invention can control the opening and closing of eighteen pneumatic isolation valves at the inlet of nine engines in the first stage of a rocket and the isolation and sealing of propellant. Nine control gas lines are connected to the eighteen pneumatic isolation valves. Each control gas line controls the opening and closing of two pneumatic isolation valves at the same time, and one control gas line controls the closing of all 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 propellant from entering the engine during rocket propellant loading, ensure that the pneumatic isolation valve can be reliably opened before ignition to allow propellant to fill the engine and pre-cool the engine, and quickly and reliably close the two propellant isolation valves at the engine inlet if an engine malfunctions during rocket flight, so as to reduce the losses caused by a large amount of propellant leakage.

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

[0058] Specifically, the pneumatic isolation valve is a normally closed pneumatic butterfly valve. The valve is opened and closed by the rotation of the disc assembly driven by the cylinder actuator.

[0059] The cylinder actuator and its working principle are as follows: The cylinder actuator consists of a cylinder body, gear shaft, piston, spring, plug, and other parts. Two pistons are located on both sides of the gear shaft, symmetrically distributed. The central axes of the two pistons coincide and are perpendicular to the axis of the gear shaft. The gear teeth of the gear shaft mesh with the rack parts of the two pistons. Symmetrical plugs are provided on both sides of the cylinder body and connected to the cylinder body to form a control closing chamber. A spring is provided between the plug and the piston. The output end of the gear shaft is connected to the input shaft of the butterfly valve's disc assembly. The working principle of the cylinder mechanism: When the cylinder is not vented, the springs on both sides of the cylinder push the pistons on both sides to move towards the middle. The rack part of the piston pushes the gear shaft to rotate counterclockwise, causing the isolation valve disc to rotate counterclockwise and close the valve. When the closing chambers on both sides of the cylinder are vented, it promotes the piston to move towards the middle, increasing the counterclockwise rotation force of the gear shaft, thereby increasing the closing force of the valve. When the opening control chamber in the middle of the cylinder is vented, it pushes the piston to move to both sides, compressing the spring and gas in the closing control chamber. At the same time, the rack of the piston pulls the gear shaft to rotate clockwise, opening the isolation valve. When the opening control chamber is devented, the gas and spring in the closing control chamber push the piston to move towards the middle. The rack part of the piston pushes the gear shaft to rotate counterclockwise, closing the valve.

[0060] Figure 4 This is a flowchart of a multi-engine propellant isolation control method according to an embodiment of the present invention, such as... Figure 4 As shown, the control method includes the following steps:

[0061] Step S1: Power on and open the first two-position two-way solenoid valve 31. The control gas in the second gas storage cylinder 29 is delivered through the second gas collection pipe 43, through the first two-position two-way solenoid valve 31 and the one-way valve to several control chamber branch gas paths to the control chambers of the oxygen isolation valve Y and fuel isolation valve R corresponding to each engine and the second two-position two-way solenoid valve 32.

[0062] Step S2: Power off and close the first two-position two-way solenoid valve 31, and use the one-way valve and the second two-position two-way solenoid valve 32 to maintain pressure and seal the gas in the second gas collection pipe 43 between the one-way valve and the second two-position two-way solenoid valve 32.

[0063] Step S3: Power on the two-position three-way solenoid valves on each branch gas path of the control chamber. The gas in the first gas storage cylinder 28 enters the control chamber of the oxygen isolation valve Y and fuel isolation valve R corresponding to each engine through the first gas collection pipe 33 and several branch gas paths of the control chamber. The oxygen isolation valve Y and fuel isolation valve R are opened.

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

[0065] Specifically, when the rocket propellant 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, they still need to have sufficient reliable sealing.

[0066] Therefore, the first two-position two-way solenoid valve 31 is opened by first powering on. The control gas in the second gas storage cylinder 29 is then transported through the second gas collection pipe 43, passing through the first two-position two-way solenoid valve 31 and the check valve, to the closing control chamber of the eighteen pneumatic isolation valves and the valve in front of the second two-position two-way solenoid valve 32, thereby increasing the sealing force of the eighteen pneumatic isolation valves and ensuring that the isolation valves meet the requirements of reliable sealing.

[0067] Then, the first two-position two-way solenoid valve 31 is closed by power-off. Because the second gas collection pipe 43 is equipped with a one-way valve and the second two-position two-way solenoid valve 32, the air in the second gas collection pipe 43 is pressure-maintained and sealed. This ensures that after the first two-position two-way solenoid valve 31 is closed, there is still control gas in the control chamber of the eighteen isolation valves and the second gas collection pipe 43, thus ensuring the reliable sealing of the eighteen isolation valves.

[0068] Before rocket engine ignition, the propellant isolation valves in front of the engines need to be opened for pre-cooling of the nine engines and propellant filling. Therefore, energizing the nine two-position three-way solenoid valves (3, 6, 9, 12, 15, 18, 21, 24, 27) allows control gas from the first gas cylinder 28 to flow through the first gas collecting pipe 33 and the nine branch gas lines (34-42) to the opening control chambers of the eighteen isolation valves, causing them to open. After the eighteen isolation valves have opened, the second two-position two-way solenoid valve 32 is opened, releasing the control gas from the second gas collecting pipe 43 and the closing control chambers of the eighteen isolation valves; ensuring the reliable opening and maintenance of the open state of the eighteen pneumatic isolation valves.

[0069] In some embodiments, the method further includes: during rocket flight, if one of the multiple parallel engines malfunctions, by means of a fault feedback command from the malfunctioning engine, closing the two-position three-way solenoid valve on the branch gas path of the opening control chamber corresponding to the opening control chamber of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of the malfunctioning engine, so that the control gas in the opening control chamber of the oxygen isolation valve Y and the fuel isolation valve R at the inlet of the malfunctioning engine is discharged from the second two-position two-way solenoid valve 32.

[0070] Specifically, during rocket flight, if one of the nine parallel engines malfunctions and requires the closure of the two propellant isolation valves at its inlet, a fault feedback command from that engine de-energizes and closes the two isolation valves at the engine inlet. The two-position three-way solenoid valves in the control chamber gas path then release the control gas from the two isolation valves through the second two-position two-way solenoid valve. The two pneumatic isolation valves automatically remain closed, cutting off the propellant supply. Ventilation is then maintained in the control chamber to ensure reliable closure. Since the control gas pressure during opening is much higher than that during closing, the other valves are unaffected by the control gas pressure during closing.

[0071] The control method provided in this invention not only controls the opening and closing of eighteen pneumatic isolation valves at the inlets of the nine engines in the first stage of a rocket and the isolation and sealing of the propellant, but also connects the control gas of the nine open control chamber branch gas paths to the eighteen pneumatic isolation valves. Each open control chamber branch gas path simultaneously controls the opening and closing of two pneumatic isolation valves. Simultaneously, the control gas of the nine closed control chamber branch gas paths simultaneously controls the closing of the eighteen pneumatic isolation valves, greatly simplifying the propellant isolation control pipeline system. Furthermore, this embodiment also enables the isolation of propellant entering the engine during rocket propellant loading, ensures the reliable opening of the pneumatic isolation valves before ignition to allow propellant to fill the engine and pre-cool it, and quickly and reliably closes the two propellant isolation valves at the engine inlet if an engine malfunctions during rocket flight, thereby reducing losses caused by large-scale propellant leakage.

[0072] Example 3

[0073] The present invention also provides a launch vehicle that employs a multi-engine propellant isolation control system as described in Embodiment 1.

[0074] In the description of the embodiments of the present invention, it should be noted that the terms "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention. In addition, the terms "first," "second," or "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0075] Unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" in this invention embodiment should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; similarly, they can refer to mechanical connections, electrical connections, or direct connections, or indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0076] Although the invention has been described with reference to preferred embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the invention. In particular, the technical features mentioned in the various embodiments can be combined in any manner as long as there is no structural conflict. The 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 propellant isolation control system for multi-engine engines, characterized in that, It includes a first gas storage cylinder (28) and a first gas collecting pipe (33); wherein, the first gas collecting pipe (33) is connected to the first gas storage cylinder (28), and the first gas collecting pipe (33) is provided with several open control chamber branch gas paths; Each of the opening control chamber branch gas paths is connected to the opening control chamber of the oxygen isolation valve (Y) and the fuel isolation valve (R) at the inlet of each engine. A two-position three-way solenoid valve is provided between each of the opening control chamber branch gas paths and the corresponding oxygen isolation valve (Y) and fuel isolation valve (R) at the inlet of each engine. The opening control chambers of the oxygen isolation valve (Y) and the fuel isolation valve (R) are controlled simultaneously by the two-position three-way solenoid valve. The system further includes: a second gas storage cylinder (29) and a second gas collecting pipe (43), the second gas collecting pipe (43) being connected to the second gas storage cylinder (29), and the second gas collecting pipe (43) being provided with several control chamber branch gas paths; Each of the closed control chamber branch gas paths is connected to the closed control chamber of the oxygen isolation valve (Y) and 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 collection pipe (43). Several of the closed control chamber branch gas paths are located at the outlet of the first two-position two-way solenoid valve (31). Each of the closed control chamber branch gas paths is connected to the oxygen isolation valve (Y) and fuel isolation valve (R) at the inlet of each corresponding engine, and the closed control chamber of the oxygen isolation valve (Y) and fuel isolation valve (R) at the inlet of each engine is simultaneously controlled by the first two-position two-way solenoid valve (31).

2. The multi-engine propellant isolation control system according to claim 1, 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 collection pipe (43). The one-way valve (30) is located between the first two-position two-way solenoid valve (31) and the inlet of the several control chamber branch gas paths, and the second two-position two-way solenoid valve (32) is located at the outlet of the several branch gas paths.

3. The multi-engine propellant isolation control system according to claim 2, characterized in that, The number of engines is equal to the number of the open control chamber branch air passages and the number of the closed control chamber branch air passages.

4. A multi-engine propellant isolation control system according to claim 3, characterized in that, The number of engines is nine.

5. A multi-engine propellant isolation control system according to claim 3, characterized in that, Both the oxygen isolation valve (Y) and the fuel isolation valve (R) are pneumatic isolation valves.

6. A multi-engine propellant isolation control system according to claim 5, characterized in that, The pneumatic isolation valve is a normally closed pneumatic butterfly valve.

7. A method for propellant isolation control in multi-engine systems, characterized in that, The control method includes: When the first two-position two-way solenoid valve (31) is opened by power, the control gas in the second gas cylinder (29) is delivered sequentially through the second gas collection pipe (43) to the first two-position two-way solenoid valve (31) and the one-way valve (30) to several control chamber branch gas lines to the control chamber of the oxygen isolation valve (Y) and fuel isolation valve (R) corresponding to each engine and the second two-position two-way solenoid valve (32). Power off and close the first two-position two-way solenoid valve (31), and use the one-way valve (30) and the second two-position two-way solenoid valve (32) to maintain pressure and seal the gas in the second gas collection pipe (43) between the one-way valve (30) and the second two-position two-way solenoid valve (32); When the power is turned on, the two-position three-way solenoid valves on each branch gas line of the control chamber are opened. The gas in the first gas storage cylinder (28) enters the control chamber of the oxygen isolation valve (Y) and the fuel isolation valve (R) corresponding to each engine through the first gas collection pipe (33) and several branch gas lines of the control chamber, and opens the oxygen isolation valve (Y) and the fuel isolation valve (R). Open the second two-position two-way solenoid valve (32) to discharge the control gas in the second gas collection pipe (43) between the one-way valve (30) and the second two-position two-way solenoid valve (32) and the control chamber of the oxygen isolation valve (Y) and fuel isolation valve (R) corresponding to each engine through the second two-position two-way solenoid valve (32).

8. The multi-engine propellant isolation control method according to claim 7, characterized in that, The method further includes: During rocket flight, if any one of the parallel engines malfunctions, the two-position three-way solenoid valves on the branch gas path of the opening control chamber corresponding to the opening control chamber of the oxygen isolation valve (Y) and fuel isolation valve (R) at the inlet of the malfunctioning engine are closed by the fault feedback command of the malfunctioning engine. This allows the control gas in the opening control chamber of the oxygen isolation valve (Y) and fuel isolation valve (R) at the inlet of the malfunctioning engine to be discharged from the second two-position two-way solenoid valve (32).

9. A launch vehicle, characterized in that, The launch vehicle employs a multi-engine propellant isolation control system as described in any one of claims 1-6.

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