Multi-medium blow-off switching and fault monitoring system for liquid rocket engine

Abstract

The invention discloses a multi-medium blow-off switching and fault monitoring system for a liquid rocket engine. Comprising a high-pressure helium tank, a first electromagnetic valve, a blow-off switching valve, a pressure signal monitor, a first one-way valve, a generator nitrogen blow-off throttling element, a second one-way valve, a generator helium blow-off throttling element, a first filter, a second filter, a second electromagnetic valve, a third one-way valve, a fourth one-way valve, a fifth one-way valve and a sixth one-way valve. The system comprises a first electromagnetic valve, a thrust chamber cooling ring belt blowing throttling element, a thrust chamber injector blowing throttling element, a third electromagnetic valve, a pipeline A, a pipeline B, a pipeline C, a pipeline D, a pipeline E, a pipeline F, a pipeline G, a pipeline H, a pipeline I, a pipeline J, a pipeline K, a pipeline L, a pipeline M, a pipeline N and a pipeline O. According to the system, the control problem that the blowing-off states of the engine are different due to the fact that the varieties of gas sources are varied at the ignition moment at present is solved, and the consistency of the ignition quality of the engine under different task scenes is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engine design, and in particular relates to a liquid rocket engine multi-media purge switching and fault monitoring system. Background Art

[0002] During the pre-start preparation stages of cryogenic liquid rocket engines, such as cryogenic propellant filling and liquid oxygen system precooling, in order to prevent the temperature from being too low during the precooling process, causing water vapor in the air to freeze and cause the generator / thrust chamber injector nozzles to become blocked by ice, it is necessary to use inert gases such as nitrogen or helium to blow out the injector cavity to achieve air replacement.

[0003] During the starting phase, blowing out the injector cavity of the generator (thrust chamber) also has the following effects: 1) Preventing the oxidant (oxygen-rich gas / fuel-rich gas) that has entered the generator (thrust chamber) earlier from entering the injector cavity; 2) The emulsification effect on the propellant can increase the injection pressure drop at the starting time and improve the atomization effect; 3) Shorten the time difference of the propellant entering the generator (thrust chamber).

[0004] At present, the purge gas at the ignition moment of the starting process of cryogenic liquid rocket engines mostly uses a single medium such as nitrogen. It has the advantages of a variety of gas sources, easy preparation, and low cost. However, from the perspective of engine working reliability and environmental adaptability, a variety of gas sources means that the engine purge state is changeable and has the disadvantage of being difficult to control. For example, nitrogen can be supplied by the ground test bench, by its own nitrogen bottle, or by the rocket as a whole. The different supply methods in different mission scenarios will greatly affect the ignition quality when the engine is started.

[0005] In terms of control gas, most cryogenic liquid rocket engines are equipped with helium cylinders to achieve a stable and reliable supply of control gas. Taking advantage of the stable and reliable supply of control gas, switching the nitrogen purge of the generator / thrust chamber to helium purge during the startup phase can achieve consistency in the engine's ignition quality in different mission scenarios. At present, there is no relevant technology for nitrogen / helium multi-media purge switching, and due to the importance of helium purge before startup to ignition, it is crucial to monitor the switching process for faults. At present, there is no relevant technology for purge switching fault monitoring. Summary of the invention

[0006] The technology of the present invention solves the problem: Overcoming the shortcomings of the prior art, providing a liquid rocket engine multi-media purge switching and fault monitoring system, solving the current control problem of different engine purge states caused by the changing types of gas sources at the ignition moment, and achieving consistency in the engine's ignition quality under different mission scenarios.

[0007] In order to solve the above technical problems, the present invention discloses a liquid rocket engine multi-media purge switching and fault monitoring system, comprising: a high-pressure helium cylinder, a first solenoid valve, a purge switching valve, a pressure signal monitor, a first non-return valve, a generator nitrogen purge throttling element, a second non-return valve, a generator helium purge throttling element, a first filter, a second filter, a second solenoid valve, a third non-return valve, a fourth non-return valve, a fifth non-return valve, a sixth non-return valve, a thrust chamber cooling ring belt purge throttling element, a thrust chamber injector purge throttling element, a third solenoid valve, a pipeline A, a pipeline B, a pipeline C, a pipeline D, a pipeline E, a pipeline F, a pipeline G, a pipeline H, a pipeline I, a pipeline J, a pipeline K, a pipeline L, a pipeline M, a pipeline N and a pipeline O; the purge switching valve comprises 5 ports: a helium inlet f, a nitrogen inlet d, a control gas port h, a helium outlet k and a nitrogen outlet e;

[0008] One end of the pipeline A is connected to a high-pressure helium bottle, and the other end is used as a second blow-off outlet g; wherein a third solenoid valve is provided on the pipeline A;

[0009] One end of pipeline B is connected to a high-pressure helium cylinder, and the other end is connected to pipeline F; one end of pipeline F is connected to a pressure signal monitor, and the other end is connected to a control port h of a blow-off switching valve; wherein a first solenoid valve is provided on pipeline B;

[0010] One end of the pipeline C is connected to a high-pressure helium cylinder, and the other end is connected to the helium inlet f of the blow-off switching valve;

[0011] One end of the pipeline D is used as the first nitrogen blowing inlet i, and the other end is connected to the pipeline G; wherein the first filter, the second solenoid valve and the third one-way valve are sequentially arranged on the pipeline D;

[0012] One end of the pipeline E is used as the second nitrogen blow-off inlet j, and the other end is connected to one end of the pipeline G; the other end of the pipeline G is connected to the nitrogen inlet d of the blow-off switching valve; wherein, the pipeline E is provided with a second filter, and the pipeline G is provided with a fourth one-way valve;

[0013] One end of the pipeline H is connected to the helium outlet k of the blow-off switching valve, and the other end is connected to the pipeline K; one end of the pipeline K is connected to the pipeline L, and the other end is connected to the pipeline M; wherein the second one-way valve, the generator helium blow-off throttling element and the sixth one-way valve are sequentially arranged on the pipeline K, the second one-way valve and the generator helium blow-off throttling element are located on one side of the pipeline H, and the sixth one-way valve is located on the other side of the pipeline H;

[0014] One end of pipeline I is connected to the nitrogen outlet e of the blow-off switching valve, and the other end is connected to pipeline J; one end of pipeline J is connected to one end of pipeline L, and the other end is connected to one end of pipeline M; the other end of pipeline L serves as the first blow-off outlet a; the other end of pipeline M is respectively connected to one end of pipeline N and one end of pipeline O; the other end of pipeline N serves as the third blow-off outlet b; the other end of pipeline O serves as the fourth blow-off outlet c; wherein, the first one-way valve, the generator nitrogen blow-off throttling element and the fifth one-way valve are sequentially arranged on pipeline J, the first one-way valve and the generator nitrogen blow-off throttling element are located on one side of pipeline I, and the fifth one-way valve is located on the other side of pipeline I; the thrust chamber injector blow-off throttling element is arranged on pipeline N; the thrust chamber cooling annulus blow-off throttling element is arranged on pipeline O.

[0015] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the first nitrogen purge inlet i is connected to high-pressure nitrogen; the second nitrogen purge inlet j is connected to low-pressure nitrogen; the first purge outlet a and the second purge outlet g are respectively connected to the generator; the third purge outlet b is connected to the thrust chamber injector; and the fourth purge outlet c is connected to the thrust chamber cooling ring.

[0016] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the purge switching between nitrogen and helium is achieved by the on-off control of the first solenoid valve:

[0017] When the first solenoid valve is in the de-energized state, the second solenoid valve is in the energized or de-energized state, and the third solenoid valve is in the de-energized state, the nitrogen inlet d and the nitrogen outlet e of the purge switching valve are in the connected state, and the helium inlet f and the helium outlet k are in the disconnected state, that is, the nitrogen passage of the purge switching valve is in the open state, and the helium passage is in the closed state; nitrogen flows in through the first purge inlet i or the second nitrogen purge inlet j, so as to realize nitrogen purge of the generator downstream of the first purge outlet a, the thrust chamber injector downstream of the third purge outlet b, and the thrust chamber cooling annulus downstream of the fourth purge outlet c;

[0018] When the first solenoid valve is in the power-on state, the second solenoid valve is in the power-off state, and the third solenoid valve is in the power-off state, the high-pressure helium in the high-pressure helium bottle enters the control chamber of the purge switching valve through the control gas port h of the purge switching valve, the helium inlet f and the helium outlet k of the purge switching valve are in a connected state, and the nitrogen inlet d and the nitrogen outlet e are in a disconnected state, that is, the nitrogen passage of the purge switching valve is in a closed state, and the helium passage is in an open state; the high-pressure helium in the high-pressure helium bottle flows in through the helium inlet f of the purge switching valve, so as to realize the helium purge of the generator downstream of the first purge outlet a, the thrust chamber injector downstream of the third purge outlet b, and the thrust chamber cooling annulus downstream of the fourth purge outlet c.

[0019] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the purge switching process between nitrogen and helium is judged by opening and closing the pressure signal monitor:

[0020] When the first solenoid valve is in the de-energized state, the second solenoid valve is in the energized or de-energized state, and the third solenoid valve is in the de-energized state, the air cavity pressure of the pressure signal monitor is normal pressure, and the pressure signal monitor is in the disconnected state, indicating that the nitrogen passage of the purge switching valve is in the open state and the helium passage is in the closed state;

[0021] When the first solenoid valve is energized, the second solenoid valve is de-energized, and the third solenoid valve is de-energized, the high-pressure helium in the high-pressure helium bottle simultaneously enters the air cavity of the pressure signal monitor and the control cavity of the blow-off switching valve, pushing the pressure sensitive diaphragm to contact the positive and negative electrodes, and the pressure signal monitor turns to a closed state, indicating that the nitrogen passage of the blow-off switching valve is closed and the helium passage is open.

[0022] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the nitrogen purge gas source is supplied by ground equipment in the ground state, and the nitrogen purge gas source is supplied by the rocket body during multiple starts in the flight state.

[0023] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the switching between high-pressure nitrogen purge and low-pressure nitrogen purge is achieved by turning on and off the second solenoid valve:

[0024] When the second solenoid valve is in the power-off state, the low-pressure nitrogen is divided into two paths after passing through the nitrogen blowing second inlet j, the second filter, the fourth one-way valve, and the nitrogen passage of the blowing switching valve. One path passes through the generator nitrogen blowing throttling element and the first one-way valve to blow the generator with a small flow of nitrogen, and the other path passes through the fifth one-way valve, the thrust chamber cooling annulus blowing throttling element and the thrust chamber injector blowing throttling element to blow the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen.

[0025] When the second solenoid valve is energized, the high-pressure nitrogen is divided into two paths after passing through the nitrogen blowing first inlet i, the first filter, the second solenoid valve, the third one-way valve, and the nitrogen passage of the blowing switching valve. One path passes through the generator nitrogen blowing throttling element and the first one-way valve to blow a large amount of nitrogen to the generator, and the other path passes through the fifth one-way valve, the thrust chamber cooling annulus blowing throttling element and the thrust chamber injector blowing throttling element to blow a large amount of nitrogen to the thrust chamber cooling annulus and the thrust chamber injector; wherein, the high-pressure nitrogen builds up a pressure higher than the nitrogen pressure at the nitrogen blowing second inlet j after the third one-way valve, and the low-pressure nitrogen blowing stops automatically.

[0026] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the first one-way valve, the second one-way valve, the third one-way valve, the fourth one-way valve, the fifth one-way valve and the sixth one-way valve are used to prevent mutual interference between the operations of different purge gases.

[0027] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the generator nitrogen purge throttling element is used for the nitrogen purge flow of the generator; the generator helium purge throttling element is used to control the helium purge flow of the generator; the thrust chamber cooling annulus purge throttling element is used to control the nitrogen or helium purge flow of the thrust chamber cooling annulus; the thrust chamber injector purge throttling element is used to control the nitrogen or helium purge flow of the thrust chamber injector.

[0028] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the first filter is used to filter the high-pressure nitrogen flowing in through the first nitrogen purge inlet i to prevent impurities in the high-pressure nitrogen from entering the downstream second solenoid valve; the second filter is used to filter the low-pressure nitrogen flowing in through the second nitrogen purge inlet j to prevent impurities in the low-pressure nitrogen from entering the downstream pipeline E.

[0029] In the above-mentioned cryogenic liquid rocket engine multi-media purge switching and fault monitoring system, the system works as follows:

[0030] Perform a pre-work status check to confirm that all solenoid valves and pressure signal monitors are in the power-off state, and confirm that there is high-pressure helium in the high-pressure helium cylinder; the first nitrogen blow-off inlet i is connected to high-pressure nitrogen, and the second nitrogen blow-off inlet j is connected to low-pressure nitrogen; in this state, the low-pressure nitrogen is divided into two paths after passing through the second filter, the fourth one-way valve, and the nitrogen passage of the blow-off switching valve, one of which passes through the generator nitrogen blow-off throttling element and the first one-way valve to blow off the generator with a small flow of nitrogen, and the other passes through the fifth one-way valve, the thrust chamber cooling annulus blow-off throttling element and the thrust chamber injector blow-off throttling element to blow off the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen;

[0031] Before the engine is started, the second solenoid valve is controlled to be energized and opened, and the high-pressure nitrogen is divided into two paths after passing through the first filter, the second solenoid valve, the third one-way valve, and the nitrogen passage of the blow-off switching valve. One path passes through the generator nitrogen blow-off throttling element and the first one-way valve to blow off the generator with a large flow of nitrogen, and the other path passes through the fifth one-way valve, the thrust chamber cooling annulus blow-off throttling element and the thrust chamber injector blow-off throttling element to blow off the thrust chamber cooling annulus and the thrust chamber injector with a large flow of nitrogen;

[0032] At the time of engine starting, the first solenoid valve is controlled to be energized and opened, the nitrogen passage of the purge switching valve is closed, the helium passage is opened, the pressure signal monitor is closed, and the high-pressure helium in the high-pressure helium cylinder is divided into two paths after passing through the helium passage of the purge switching valve, one of which passes through the generator helium purge throttling element and the second one-way valve to purge the generator with helium, and the other passes through the sixth one-way valve, the thrust chamber cooling annulus purge throttling element and the thrust chamber injector purge throttling element to purge the thrust chamber cooling annulus and the thrust chamber injector with helium;

[0033] After the engine is started, when the combustion pressure of the generator and thrust chamber exceeds the pressure of the high-pressure helium cylinder, the helium purge stops automatically, the first solenoid valve is powered off and closed, and the purge switching valve is switched to the nitrogen passage open state;

[0034] When the engine is shut down, the third solenoid valve is energized and opened;

[0035] During the shutdown process of the engine, when the pressure of the generator is reduced to less than the pressure of the high-pressure helium cylinder, the high-pressure helium in the high-pressure helium cylinder passes through the third solenoid valve and the second blow-off outlet g, and the helium blow-off of the generator downstream of the second blow-off outlet g is performed; when the pressure of the generator and the thrust chamber is lower than the pressure of the high-pressure nitrogen at the first nitrogen blow-off inlet i, it is switched to high-flow nitrogen blow-off, that is, high-pressure nitrogen flows in through the first nitrogen blow-off inlet i, and the generator and the thrust chamber are blown with high-flow nitrogen;

[0036] After the engine is shut down for a period of time, the second solenoid valve and the third solenoid valve are powered off and closed, and switched to low-flow nitrogen purge, that is, low-pressure nitrogen flows in through the first nitrogen purge inlet j, and the generator and thrust chamber are purged with low-flow nitrogen;

[0037] After the engine temperature returns to normal temperature, cut off the air supply to the first nitrogen purge inlet j by the ground equipment or the rocket body.

[0038] The present invention has the following advantages:

[0039] The present invention discloses a liquid rocket engine multi-media purge switching and fault monitoring system. By utilizing the advantage of the stable and reliable supply of control gas from the engine's own gas cylinder, the purge gas source at the engine ignition moment is set to be supplied by the engine's own gas cylinder, thereby achieving consistency in the purge gas supply mode in different mission scenarios and ensuring the ignition quality when the engine is started. At the same time, the proposed purge gas switching process fault monitoring method can effectively ensure the reliable supply and identification of purge gas when the engine is started and ignited. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a structural schematic diagram of a liquid rocket engine multi-media purge switching and fault monitoring system according to an embodiment of the present invention;

[0041] Figure 2 1 is a schematic diagram of a state in which a nitrogen passage of a purge switching valve is opened and a helium passage is closed in an embodiment of the present invention;

[0042] Figure 3 It is a schematic diagram of a state in which a nitrogen passage of a purge switching valve is closed and a helium passage is opened in an embodiment of the present invention. DETAILED DESCRIPTION

[0043] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0044] The core idea of ​​the present invention is: a liquid rocket engine multi-media purge switching and fault monitoring system is disclosed, which mainly includes a helium purge path, a nitrogen purge path, a purge switching valve control and fault monitoring path. Among them, the helium purge path is mainly composed of a high-pressure helium cylinder, a purge switching valve, a second one-way valve, a generator helium purge throttling element, a sixth one-way valve, a thrust chamber cooling annulus purge throttling element, a thrust chamber injector purge throttling element, a third solenoid valve and related connecting pipelines. The nitrogen purge path is mainly composed of a first filter, a second filter, a second solenoid valve, a first one-way valve, a third one-way valve, a fourth one-way valve, a fifth one-way valve, a purge switching valve, a generator nitrogen purge throttling element, a thrust chamber cooling annulus purge throttling element, a thrust chamber injector purge throttling element and related connecting pipelines. The purge switching valve control and fault monitoring path is mainly composed of a high-pressure helium cylinder, a first solenoid valve, a pressure signal detector, a purge switching valve and related connecting pipelines.

[0045] In this embodiment, if Figure 1As shown, the liquid rocket engine multi-media purge switching and fault monitoring system includes: a high-pressure helium cylinder 1, a first solenoid valve 2, a purge switching valve 3, a pressure signal monitor 4, a first one-way valve 5, a generator nitrogen purge throttling element 6, a second one-way valve 7, a generator helium purge throttling element 8, a first filter 9, a second filter 10, a second solenoid valve 11, a third one-way valve 12, a fourth one-way valve 13, a fifth one-way valve 14, a sixth one-way valve 15, a thrust chamber cooling annulus purge The throttling element 16, the thrust chamber injector blow-off throttling element 17, the third solenoid valve 18, the pipeline A19, the pipeline B20, the pipeline C21, the pipeline D22, the pipeline E23, the pipeline F24, the pipeline G25, the pipeline H26, the pipeline I27, the pipeline J28, the pipeline K29, the pipeline L30, the pipeline M31, the pipeline N32 and the pipeline O33; the blow-off switching valve 3 includes 5 ports: the helium inlet f, the nitrogen inlet d, the control gas port h, the helium outlet k and the nitrogen outlet e. Among them, one end of the pipeline A19 is connected to the high-pressure helium cylinder 1, and the other end is used as the second blow-off outlet g; the third solenoid valve 18 is arranged on the pipeline A19. One end of pipeline B20 is connected to high-pressure helium cylinder 1, and the other end is connected to pipeline F24; one end of pipeline F24 is connected to pressure signal monitor 4, and the other end is connected to control gas port h of purge switching valve 3; pipeline B20 is provided with first solenoid valve 2. One end of pipeline C21 is connected to high-pressure helium cylinder 1, and the other end is connected to helium inlet f of purge switching valve 3. One end of pipeline D22 is used as first nitrogen purge inlet i, and the other end is connected to pipeline G25; pipeline D22 is provided with first filter 9, second solenoid valve 11 and third check valve 12 in sequence. One end of pipeline E23 is used as second nitrogen purge inlet j, and the other end is connected to one end of pipeline G25; the other end of pipeline G25 is connected to nitrogen inlet d of purge switching valve 3; pipeline E23 is provided with second filter 10, and pipeline G25 is provided with fourth check valve 13. One end of pipeline H26 is connected to the helium outlet k of the blow-off switching valve 3, and the other end is connected to pipeline K29; one end of pipeline K29 is connected to pipeline L30, and the other end is connected to pipeline M31; the second one-way valve 7, the generator helium blow-off throttling element 8 and the sixth one-way valve 15 are sequentially arranged on pipeline K29, the second one-way valve 7 and the generator helium blow-off throttling element 8 are located on one side of pipeline H26, and the sixth one-way valve 15 is located on the other side of pipeline H26.One end of pipeline I27 is connected to the nitrogen outlet e of the blow-off switching valve 3, and the other end is connected to pipeline J28; one end of pipeline J28 is connected to one end of pipeline L30, and the other end is connected to one end of pipeline M31; the other end of pipeline L30 serves as the first blow-off outlet a; the other end of pipeline M31 is respectively connected to one end of pipeline N32 and one end of pipeline O33; the other end of pipeline N32 serves as the third blow-off outlet b; the other end of pipeline O33 serves as the fourth blow-off outlet c; the first one-way valve 5, the generator nitrogen blow-off throttling element 6 and the fifth one-way valve 14 are sequentially arranged on pipeline J28, the first one-way valve 5 and the generator nitrogen blow-off throttling element 6 are located on one side of pipeline I27, and the fifth one-way valve 14 is located on the other side of pipeline I27; the thrust chamber injector blow-off throttling element 17 is arranged on pipeline N32; the thrust chamber cooling annulus blow-off throttling element 16 is arranged on pipeline O33.

[0046] In this embodiment, the first nitrogen blow-off inlet i is connected to high-pressure nitrogen; the second nitrogen blow-off inlet j is connected to low-pressure nitrogen; the first blow-off outlet a and the second blow-off outlet g are respectively connected to the generator; the third blow-off outlet b is connected to the thrust chamber injector; and the fourth blow-off outlet c is connected to the thrust chamber cooling annulus.

[0047] In this embodiment, the purge switching between nitrogen and helium is achieved by the on-off control of the first solenoid valve 2: when the first solenoid valve 2 is in the off state, the second solenoid valve 11 is in the on or off state, and the third solenoid valve 18 is in the off state, the nitrogen inlet d and the nitrogen outlet e of the purge switching valve 3 are in the connected state, and the helium inlet f and the helium outlet k are in the disconnected state, that is, the nitrogen passage of the purge switching valve 3 is in the open state, and the helium passage is in the closed state. Figure 2 As shown; nitrogen flows in through the first blow-off inlet i or the second blow-off inlet j, to achieve nitrogen blow-off of the generator downstream of the first blow-off outlet a, the thrust chamber injector downstream of the third blow-off outlet b, and the thrust chamber cooling annulus downstream of the fourth blow-off outlet c. When the first solenoid valve 2 is powered on, the second solenoid valve 11 is powered off, and the third solenoid valve 18 is powered off, the high-pressure helium in the high-pressure helium cylinder 1 enters the control chamber of the blow-off switching valve 3 through the control gas port h of the blow-off switching valve 3, the helium inlet f and the helium outlet k of the blow-off switching valve 3 are in a connected state, and the nitrogen inlet d and the nitrogen outlet e are in a disconnected state, that is, the nitrogen passage of the blow-off switching valve 3 is in a closed state, and the helium passage is in an open state, as shown in FIG. Figure 3 As shown; the high-pressure helium in the high-pressure helium cylinder 1 flows in through the helium inlet f of the blow-off switching valve 3, so as to blow off the helium of the generator downstream of the first blow-off outlet a, the thrust chamber injector downstream of the third blow-off outlet b, and the thrust chamber cooling annulus downstream of the fourth blow-off outlet c.

[0048] In this embodiment, the judgment of the blowing switching process between nitrogen and helium is realized by opening and closing the pressure signal monitor 4: when the first solenoid valve 2 is in the power-off state, the second solenoid valve 11 is in the power-on or power-off state, and the third solenoid valve 18 is in the power-off state, the air cavity pressure of the pressure signal monitor 4 is normal pressure, and the pressure signal monitor 4 is in the power-off state, indicating that the nitrogen passage of the blowing switching valve 3 is in the open state and the helium passage is in the closed state. When the first solenoid valve 2 is in the power-on state, the second solenoid valve 11 is in the power-off state, and the third solenoid valve 18 is in the power-off state, the high-pressure helium in the high-pressure helium cylinder 1 simultaneously enters the air cavity of the pressure signal monitor 4 and the control cavity of the blowing switching valve 3, pushing the pressure sensitive diaphragm to contact the positive and negative electrodes, and the pressure signal monitor 4 turns to the closed state, indicating that the nitrogen passage of the blowing switching valve 3 is in the closed state and the helium passage is in the open state.

[0049] In this embodiment, the switching between high-pressure nitrogen purge and low-pressure nitrogen purge is achieved by turning the second solenoid valve 11 on and off: when the second solenoid valve 11 is in the off state, the low-pressure nitrogen is divided into two paths after passing through the nitrogen purge second inlet j, the second filter 10, the fourth one-way valve 13, and the nitrogen passage of the purge switching valve 3. One path passes through the generator nitrogen purge throttling element 6 and the first one-way valve 5 to purge the generator with a small flow of nitrogen, and the other path passes through the fifth one-way valve 14, the thrust chamber cooling annulus purge throttling element 16 and the thrust chamber injector purge throttling element 17 to purge the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen. When the second solenoid valve 11 is energized, the high-pressure nitrogen is divided into two paths after passing through the nitrogen blowing first inlet i, the first filter 9, the second solenoid valve 11, the third one-way valve 12, and the nitrogen passage of the blowing switching valve 3. One path is used to blow the generator with a large flow of nitrogen after passing through the generator nitrogen blowing throttling element 6 and the first one-way valve 5, and the other path is used to blow the thrust chamber cooling annulus and the thrust chamber injector with a large flow of nitrogen after passing through the fifth one-way valve 14, the thrust chamber cooling annulus blowing throttling element 16 and the thrust chamber injector blowing throttling element 17; wherein, the high-pressure nitrogen builds up a pressure higher than the nitrogen pressure at the nitrogen blowing second inlet j after the third one-way valve 12, and the low-pressure nitrogen blowing stops automatically.

[0050] In this embodiment, the nitrogen purge gas source is supplied by ground equipment in the ground state, and the nitrogen purge gas source is supplied by the rocket body during multiple starts in the flight state.

[0051] In this embodiment, the first one-way valve 5, the second one-way valve 7, the third one-way valve 12, the fourth one-way valve 13, the fifth one-way valve 14 and the sixth one-way valve 15 are used to prevent the mutual interference between the operations of different purge gases. The generator nitrogen purge throttling element 6 is used for the nitrogen purge flow of the generator; the generator helium purge throttling element 8 is used to control the helium purge flow of the generator; the thrust chamber cooling annulus purge throttling element 16 is used to control the nitrogen or helium purge flow of the thrust chamber cooling annulus; the thrust chamber injector purge throttling element 17 is used to control the nitrogen or helium purge flow of the thrust chamber injector. The first filter 9 is used to filter the high-pressure nitrogen flowing in through the first nitrogen purge inlet i to prevent impurities in the high-pressure nitrogen from entering the downstream second solenoid valve 11; the second filter 10 is used to filter the low-pressure nitrogen flowing in through the second nitrogen purge inlet j to prevent impurities in the low-pressure nitrogen from entering the downstream pipeline E23.

[0052] In this embodiment, the working process of the cryogenic liquid rocket engine multi-media purge switching and fault monitoring system is as follows:

[0053] Perform a status check before work to confirm that all solenoid valves and pressure signal monitor 4 are in the power-off state, and confirm that there is high-pressure helium in the high-pressure helium cylinder 1; the first nitrogen blow-off inlet i is connected to high-pressure nitrogen, and the second nitrogen blow-off inlet j is connected to low-pressure nitrogen; in this state, the low-pressure nitrogen is divided into two paths after passing through the second filter 10, the fourth one-way valve 13, and the nitrogen passage of the blow-off switching valve 3, one of which passes through the generator nitrogen blow-off throttling element 6 and the first one-way valve 5 to blow off the generator with a small flow of nitrogen, and the other passes through the fifth one-way valve 14, the thrust chamber cooling annulus blow-off throttling element 16 and the thrust chamber injector blow-off throttling element 17 to blow off the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen.

[0054] Before the engine is started, the second solenoid valve 11 is controlled to be energized and opened, and the high-pressure nitrogen is divided into two paths after passing through the first filter 9, the second solenoid valve 11, the third one-way valve 12, and the nitrogen passage of the blow-off switching valve 3. One path passes through the generator nitrogen blow-off throttling element 6 and the first one-way valve 5 to blow off the generator with a large flow of nitrogen, and the other path passes through the fifth one-way valve 14, the thrust chamber cooling annulus blow-off throttling element 16 and the thrust chamber injector blow-off throttling element 17 to blow off the thrust chamber cooling annulus and the thrust chamber injector with a large flow of nitrogen.

[0055] At the time of engine starting, the first solenoid valve 2 is controlled to be energized and opened, the nitrogen passage of the purge switching valve 3 is closed, the helium passage is opened, the pressure signal monitor 4 is closed, and the high-pressure helium in the high-pressure helium cylinder 1 is divided into two paths after passing through the helium passage of the purge switching valve 3. One path passes through the generator helium purge throttling element 8 and the second one-way valve 7 to purge the generator with helium, and the other path passes through the sixth one-way valve 15, the thrust chamber cooling annulus purge throttling element 16 and the thrust chamber injector purge throttling element 17 to purge the thrust chamber cooling annulus and the thrust chamber injector with helium.

[0056] After the engine is started, when the combustion pressure of the generator and thrust chamber exceeds the pressure of the high-pressure helium tank 1, the helium purge stops automatically, the first solenoid valve 2 is powered off and closed, and the purge switching valve 3 is switched to the nitrogen passage open state.

[0057] When the engine is shut down, the third solenoid valve 18 is energized and opened.

[0058] During the engine shutdown process, when the generator pressure drops to less than the pressure of the high-pressure helium cylinder 1, the high-pressure helium in the high-pressure helium cylinder 1 passes through the third solenoid valve 18 and the second blow-off outlet g, and the generator downstream of the second blow-off outlet g is purged with helium; when the pressure of the generator and the thrust chamber is lower than the pressure of the high-pressure nitrogen at the first nitrogen blow-off inlet i, it is switched to high-flow nitrogen blow-off, that is, high-pressure nitrogen flows in through the first nitrogen blow-off inlet i, and the generator and the thrust chamber are purged with high-flow nitrogen.

[0059] Some time after the engine is shut down, the second solenoid valve 11 and the third solenoid valve 18 are powered off and closed, and switched to low-flow nitrogen purge, that is, low-pressure nitrogen flows in through the first nitrogen purge inlet j to purge the generator and thrust chamber with low-flow nitrogen.

[0060] After the engine temperature returns to normal temperature, cut off the air supply to the first nitrogen purge inlet j by the ground equipment or the rocket body.

[0061] It should be noted that high-pressure nitrogen generally refers to nitrogen with a pressure in the range of 1.0 to 30 MPa, low-pressure nitrogen generally refers to nitrogen with a pressure in the range of 0.1 to 1.0 MPa, and high-pressure helium generally refers to helium with a pressure in the range of 15 to 30 MPa.

[0062] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0063] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A liquid rocket engine multi-media purge switching and fault monitoring system, characterized in that: include: High-pressure helium cylinder (1), a first solenoid valve (2), a blow-off switching valve (3), a pressure signal monitor (4), a first non-return valve (5), a generator nitrogen blow-off throttling element (6), a second non-return valve (7), a generator helium blow-off throttling element (8), a first filter (9), a second filter (10), a second solenoid valve (11), a third non-return valve (12), a fourth non-return valve (13), a fifth non-return valve (14), a sixth non-return valve (15), a thrust chamber cooling ring blow-off throttling element (16), a thrust chamber injector blow-off throttling element (17), a thrust chamber cooling ring belt blow-off throttling element (18), a thrust chamber injector blow-off throttling element (19), a thrust chamber cooling ring belt blow-off throttling element (20), a thrust chamber cooling ring belt blow-off throttling element (21), a thrust chamber cooling ring belt blow-off throttling element (22), a thrust chamber cooling ring belt blow-off throttling element (23), a thrust chamber cooling ring belt blow-off throttling element (24), a thrust chamber cooling ring belt blow-off throttling element (25), a thrust chamber cooling ring belt blow-off throttling element (26), a thrust chamber cooling ring belt blow-off throttling element (27), a thrust chamber cooling ring belt blow-off throttling element (28), a thrust chamber cooling ring belt blow-off throttling element (29), a thrust chamber cooling ring belt blow-off throttling element (30), a thrust chamber cooling ring belt blow-off throttling element (31), a thrust chamber cooling ring belt blow-off throttling element (32), a thrust chamber cooling ring belt blow-off throttling element (33), a thrust chamber cooling ring belt blow-off throttling element (34 flow element (17), a third solenoid valve (18), a pipeline A (19), a pipeline B (20), a pipeline C (21), a pipeline D (22), a pipeline E (23), a pipeline F (24), a pipeline G (25), a pipeline H (26), a pipeline I (27), a pipeline J (28), a pipeline K (29), a pipeline L (30), a pipeline M (31), a pipeline N (32) and a pipeline O (33); the purge switching valve (3) comprises five ports: a helium inlet f, a nitrogen inlet d, a control gas port h, a helium outlet k and a nitrogen outlet e; One end of the pipeline A (19) is connected to the high-pressure helium bottle (1), and the other end serves as a second blow-off outlet g; wherein a third solenoid valve (18) is provided on the pipeline A (19); One end of the pipeline B (20) is connected to the high-pressure helium bottle (1), and the other end is connected to the pipeline F (24); one end of the pipeline F (24) is connected to the pressure signal monitor (4), and the other end is connected to the control gas port h of the blow-off switching valve (3); wherein a first solenoid valve (2) is provided on the pipeline B (20); One end of the pipeline C (21) is connected to the high-pressure helium bottle (1), and the other end is connected to the helium inlet f of the blow-off switching valve (3); One end of the pipeline D (22) is used as a first nitrogen blowing inlet i, and the other end is connected to the pipeline G (25); wherein the pipeline D (22) is provided with a first filter (9), a second solenoid valve (11) and a third one-way valve (12) in sequence; One end of the pipeline E (23) serves as a second nitrogen purge inlet j, and the other end is connected to one end of the pipeline G (25); the other end of the pipeline G (25) is connected to a nitrogen inlet d of a purge switching valve (3); wherein a second filter (10) is provided on the pipeline E (23), and a fourth non-return valve (13) is provided on the pipeline G (25); One end of the pipeline H (26) is connected to the helium outlet k of the blow-off switching valve (3), and the other end is connected to the pipeline K (29); one end of the pipeline K (29) is connected to the pipeline L (30), and the other end is connected to the pipeline M (31); wherein the pipeline K (29) is provided with a second one-way valve (7), a generator helium blow-off throttling element (8) and a sixth one-way valve (15) in sequence, the second one-way valve (7) and the generator helium blow-off throttling element (8) are located on one side of the pipeline H (26), and the sixth one-way valve (15) is located on the other side of the pipeline H (26); One end of the pipeline I (27) is connected to the nitrogen outlet e of the blow-off switching valve (3), and the other end is connected to the pipeline J (28); one end of the pipeline J (28) is connected to one end of the pipeline L (30), and the other end is connected to one end of the pipeline M (31); the other end of the pipeline L (30) serves as the first blow-off outlet a; the other end of the pipeline M (31) is connected to one end of the pipeline N (32) and one end of the pipeline O (33); the other end of the pipeline N (32) serves as the third blow-off outlet b; the other end of the pipeline O (33) serves as the third blow-off outlet Four outlets c; wherein the pipeline J (28) is provided with a first non-return valve (5), a generator nitrogen blow-off throttling element (6) and a fifth non-return valve (14) in sequence, the first non-return valve (5) and the generator nitrogen blow-off throttling element (6) are located on one side of the pipeline I (27), and the fifth non-return valve (14) is located on the other side of the pipeline I (27); the pipeline N (32) is provided with a thrust chamber injector blow-off throttling element (17); and the pipeline O (33) is provided with a thrust chamber cooling annulus blow-off throttling element (16).

2. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 1, characterized in that: The first nitrogen blow-off inlet i is connected to high-pressure nitrogen; the second nitrogen blow-off inlet j is connected to low-pressure nitrogen; the first blow-off outlet a and the second blow-off outlet g are respectively connected to the generator; the third blow-off outlet b is connected to the thrust chamber injector; and the fourth blow-off outlet c is connected to the thrust chamber cooling ring.

3. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 2, characterized in that: The blowing switch between nitrogen and helium is realized by the on-off control of the first solenoid valve (2): When the first solenoid valve (2) is in the de-energized state, the second solenoid valve (11) is in the energized or de-energized state, and the third solenoid valve (18) is in the de-energized state, the nitrogen inlet d and the nitrogen outlet e of the purge switching valve (3) are in the connected state, and the helium inlet f and the helium outlet k are in the disconnected state, that is, the nitrogen passage of the purge switching valve (3) is in the open state, and the helium passage is in the closed state; nitrogen flows in through the first purge inlet i or the second nitrogen purge inlet j, so as to achieve nitrogen purge of the generator downstream of the first purge outlet a, the thrust chamber injector downstream of the third purge outlet b, and the thrust chamber cooling annulus downstream of the fourth purge outlet c; When the first solenoid valve (2) is in an energized state, the second solenoid valve (11) is in an energized state, and the third solenoid valve (18) is in an energized state, the high-pressure helium in the high-pressure helium cylinder (1) enters the control chamber of the purge switching valve (3) through the control gas port h of the purge switching valve (3), the helium inlet f and the helium outlet k of the purge switching valve (3) are in a connected state, and the nitrogen inlet d and the nitrogen outlet e are in a disconnected state, that is, the nitrogen passage of the purge switching valve (3) is in a closed state, and the helium passage is in an open state; the high-pressure helium in the high-pressure helium cylinder (1) flows in through the helium inlet f of the purge switching valve (3), so as to realize the helium purge of the generator downstream of the first purge outlet a, the thrust chamber injector downstream of the third purge outlet b, and the thrust chamber cooling annulus downstream of the fourth purge outlet c.

4. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: The switching process between nitrogen and helium is judged by opening and closing the pressure signal monitor (4): When the first solenoid valve (2) is in a power-off state, the second solenoid valve (11) is in a power-on or power-off state, and the third solenoid valve (18) is in a power-off state, the air cavity pressure of the pressure signal monitor (4) is normal pressure, and the pressure signal monitor (4) is in a disconnected state, indicating that the nitrogen passage of the purge switching valve (3) is in an open state and the helium passage is in a closed state; When the first solenoid valve (2) is in an energized state, the second solenoid valve (11) is in an energized state, and the third solenoid valve (18) is in an energized state, the high-pressure helium in the high-pressure helium cylinder (1) simultaneously enters the air cavity of the pressure signal monitor (4) and the control cavity of the blow-off switching valve (3), pushing the pressure sensitive diaphragm to contact the positive and negative electrodes, and the pressure signal monitor (4) turns to a closed state, indicating that the nitrogen passage of the blow-off switching valve (3) is in a closed state and the helium passage is in an open state.

5. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: When in ground state, the nitrogen purge gas source is supplied by ground equipment. When in flight state and multiple starts, the nitrogen purge gas source is supplied by the rocket body.

6. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 5, characterized in that: The switching between high-pressure nitrogen purge and low-pressure nitrogen purge is achieved by turning on and off the second solenoid valve (11): When the second solenoid valve (11) is in the power-off state, the low-pressure nitrogen is divided into two paths after passing through the nitrogen blowing second inlet j, the second filter (10), the fourth one-way valve (13), and the nitrogen passage of the blowing switching valve (3). One path passes through the generator nitrogen blowing throttling element (6) and the first one-way valve (5) to blow the generator with a small flow of nitrogen, and the other path passes through the fifth one-way valve (14), the thrust chamber cooling annulus blowing throttling element (16) and the thrust chamber injector blowing throttling element (17) to blow the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen; When the second solenoid valve (11) is in the energized state, the high-pressure nitrogen is divided into two paths after passing through the nitrogen blowing first inlet i, the first filter (9), the second solenoid valve (11), the third non-return valve (12), and the nitrogen passage of the blowing switching valve (3). One path is used to blow the generator with a large flow of nitrogen after passing through the generator nitrogen blowing throttling element (6) and the first non-return valve (5), and the other path is used to blow the thrust chamber cooling annulus and the thrust chamber injector with a large flow of nitrogen after passing through the fifth non-return valve (14), the thrust chamber cooling annulus blowing throttling element (16) and the thrust chamber injector blowing throttling element (17); wherein, the high-pressure nitrogen builds up a pressure higher than the nitrogen pressure at the nitrogen blowing second inlet j after the third non-return valve (12), and the low-pressure nitrogen blowing stops automatically.

7. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: The first one-way valve (5), the second one-way valve (7), the third one-way valve (12), the fourth one-way valve (13), the fifth one-way valve (14) and the sixth one-way valve (15) are used to prevent the operations of different purge gases from interfering with each other.

8. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: The generator nitrogen purge throttling element (6) is used for the nitrogen purge flow rate of the generator; the generator helium purge throttling element (8) is used for controlling the helium purge flow rate of the generator; the thrust chamber cooling annulus purge throttling element (16) is used for controlling the nitrogen or helium purge flow rate of the thrust chamber cooling annulus; the thrust chamber injector purge throttling element (17) is used for controlling the nitrogen or helium purge flow rate of the thrust chamber injector.

9. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: The first filter (9) is used to filter the high-pressure nitrogen flowing in through the first nitrogen blowing inlet i, so as to prevent impurities in the high-pressure nitrogen from entering the second solenoid valve (11) downstream; the second filter (10) is used to filter the low-pressure nitrogen flowing in through the second nitrogen blowing inlet j, so as to prevent impurities in the low-pressure nitrogen from entering the downstream pipeline E (23).

10. The cryogenic liquid rocket engine multi-media purge switching and fault monitoring system according to claim 3, characterized in that: The system works as follows: A pre-operation status check is performed to confirm that all electromagnetic valves and pressure signal monitors (4) are in a power-off state, and that the high-pressure helium cylinder (1) contains high-pressure helium; the first nitrogen blow-off inlet i is connected to high-pressure nitrogen, and the second nitrogen blow-off inlet j is connected to low-pressure nitrogen; in this state, the low-pressure nitrogen is divided into two paths after passing through the second filter (10), the fourth one-way valve (13), and the nitrogen passage of the blow-off switching valve (3), one of which passes through the generator nitrogen blow-off throttling element (6) and the first one-way valve (5) to blow off the generator with a small flow of nitrogen, and the other passes through the fifth one-way valve (14), the thrust chamber cooling annulus blow-off throttling element (16) and the thrust chamber injector blow-off throttling element (17) to blow off the thrust chamber cooling annulus and the thrust chamber injector with a small flow of nitrogen; Before the engine is started, the second solenoid valve (11) is controlled to be powered on and opened, and the high-pressure nitrogen is divided into two paths after passing through the first filter (9), the second solenoid valve (11), the third non-return valve (12), and the nitrogen passage of the blow-off switching valve (3). One path passes through the generator nitrogen blow-off throttling element (6) and the first non-return valve (5) to blow off the generator with a large flow of nitrogen, and the other path passes through the fifth non-return valve (14), the thrust chamber cooling annulus blow-off throttling element (16) and the thrust chamber injector blow-off throttling element (17) to blow off the thrust chamber cooling annulus and the thrust chamber injector with a large flow of nitrogen; At the time of engine starting, the first solenoid valve (2) is controlled to be powered on and opened, the nitrogen passage of the purge switching valve (3) is closed, the helium passage is opened, the pressure signal monitor (4) is closed, and the high-pressure helium in the high-pressure helium cylinder (1) is divided into two paths after passing through the helium passage of the purge switching valve (3), one of which passes through the generator helium purge throttling element (8) and the second one-way valve (7) to purge the generator with helium, and the other passes through the sixth one-way valve (15), the thrust chamber cooling annulus purge throttling element (16) and the thrust chamber injector purge throttling element (17) to purge the thrust chamber cooling annulus and the thrust chamber injector with helium; After the engine is started, when the combustion pressure of the generator and the thrust chamber exceeds the pressure of the high-pressure helium bottle (1), the helium purge stops automatically, the first solenoid valve (2) is powered off and closed, and the purge switching valve (3) is switched to a nitrogen passage open state; When the engine is shut down, the third solenoid valve (18) is controlled to be energized and opened; During the shutdown process of the engine, when the pressure of the generator is reduced to less than the pressure of the high-pressure helium bottle (1), the high-pressure helium in the high-pressure helium bottle (1) passes through the third solenoid valve (18) and the second blow-off outlet g, and the helium blow-off of the generator downstream of the second blow-off outlet g is performed; when the pressure of the generator and the thrust chamber is lower than the pressure of the high-pressure nitrogen at the first nitrogen blow-off inlet i, the high-flow nitrogen blow-off is switched to high-flow nitrogen blow-off, that is, the high-pressure nitrogen flows in through the first nitrogen blow-off inlet i, and the high-flow nitrogen blow-off of the generator and the thrust chamber is performed; After the engine is shut down for a period of time, the second solenoid valve (11) and the third solenoid valve (18) are powered off and closed, and switched to low-flow nitrogen purge, that is, low-pressure nitrogen flows in through the first nitrogen purge inlet j, and the generator and the thrust chamber are purged with low-flow nitrogen; After the engine temperature returns to normal temperature, cut off the air supply to the first nitrogen purge inlet j by the ground equipment or the rocket body.

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