Variable thrust liquid rocket engine control system

Abstract

The utility model belongs to the technical field of liquid rocket engine equipment, and particularly relates to a variable thrust liquid rocket engine control system which comprises a thrust chamber and a turbine pump, and an igniter is arranged on the thrust chamber. An oxidizing agent inlet, an oxidizing agent outlet, a fuel inlet and a fuel outlet are formed in the turbine pump, and the oxidizing agent outlet and the fuel outlet are both communicated with the thrust chamber; the turbine pump is connected with a fuel gas generator capable of driving the turbine pump to rotate, the fuel gas generator is provided with a generator oxidant inlet communicated with the oxidant outlet, and the fuel gas generator is further provided with a generator fuel inlet communicated with the fuel outlet; the fuel gas generator is connected with an oxygen electric pump for supplying an oxidizing agent to the fuel gas generator, and is also connected with a fuel electric pump for supplying fuel to the fuel gas generator; according to the method, the problems of complexity in the starting process of an existing engine and high difficulty in depth thrust adjustment of the engine are effectively solved.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engine equipment, and in particular relates to a variable thrust liquid rocket engine control system. Background Art

[0002] A pump-type liquid rocket engine is a rocket engine that relies on a turbopump to pressurize liquid propellant and provide high-pressure propellant for the thrust chamber, generator, igniter and other components. Compared with compression engines, pump-type engines have obvious technical advantages when the thrust exceeds a certain level and the mission time is long. On the one hand, after being pressurized by the pump, the engine can use a higher system pressure, which can effectively reduce the structural size and weight of the engine under consistent performance indicators and better meet the overall installation requirements; on the other hand, since the engine uses a pump to pressurize the propellant, the requirement for the overall tank pressure is only to ensure the inlet pressure when the pump is working normally, and the tank pressure is low, so that the overall propellant tank and its pressurization system can be simplified, reducing the overall structural mass of the entire stage or aircraft.

[0003] In order to adapt to the complex aerospace application environment, especially the booming development of commercial aerospace, the demand for multiple start-up and deep variable thrust capabilities of pump-type liquid rocket engines is becoming more and more urgent.

[0004] At present, the methods for achieving multiple starts of pump-type engines mainly include starting with multiple gunpowder starters, forced starting driven by cold air, starting with a refillable starting box, and starting with an electric pump.

[0005] The gunpowder starter uses the combustion gas of gunpowder as the initial energy source for starting the turbine pump, driving the turbine and driving the pump to start the engine. However, at present, a gunpowder starter can only work once. When the engine needs to be started multiple times, multiple gunpowder starters need to be installed. Due to the limitations of the gunpowder starter's own structural size, weight and engine installation space, this starting method can only be applied to engines with fewer starting requirements, generally not more than 3 times.

[0006] Air-cooled forced start is to start the engine by using high-pressure gas to blow the turbine and drive the pump to rotate when the engine starts. Since the working capacity of high-pressure gas is much smaller than the working capacity of the gas generated by the gas generator, the consumption of high-pressure gas is large during the starting process, thus limiting the number of times the engine can be started. At the same time, a starting turbine is generally required on the engine, which increases the load and weight of the engine during normal operation.

[0007] The starter box starting method is that when the engine is started, the propellant in the starter box is directly squeezed into the gas generator, and the gas generator ignites to drive the turbine and the pump to start the engine. The propellant in the starter box can be replenished before the engine is started or during operation to prepare for the next start. If the starter box solution is adopted, the corresponding starting system needs to be set up on the engine. The system is relatively complex and the structural mass increases significantly.

[0008] The electric pump starting method is to start the pump by the motor when the engine starts, so as to achieve multiple starts of the engine. This system eliminates the turbine gas generator supply system, and the engine system is simple, which is convenient for multiple engine starts and thrust adjustment. However, this system is suitable for the situation where the engine thrust level is small (currently less than 3t thrust in engineering). When the engine thrust is large, the use of this system requires a high-power motor and power supply, which is costly and heavy.

[0009] At present, the coupling degree between the auxiliary system and the main system of the engine of the turbopump system is very high, which increases the complexity of the engine starting process and the difficulty of deep thrust adjustment of the engine.

[0010] When adjusting the thrust of the engine by the traditional method, an additional thrust adjustment system (including pipelines, valves, adjustable cavitation tubes, specially designed injectors, etc.) is required. The thrust adjustment system adjusts the engine operating conditions by changing the fluid flow of the entire system, producing a coupling effect with the turbine pump speed, and ultimately achieving thrust adjustment. Summary of the invention

[0011] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides a variable thrust liquid rocket engine control system, which effectively solves the problems of complexity of the existing engine starting process and high difficulty of deep thrust adjustment of the engine.

[0012] To achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a control system of a variable thrust liquid rocket engine, comprising a thrust chamber and a turbopump, wherein an igniter is provided on the thrust chamber; an oxidant inlet, an oxidant outlet, a fuel inlet and a fuel outlet are provided on the turbopump, and the oxidant outlet and the fuel outlet are both connected to the thrust chamber; the turbopump is connected to a gas generator capable of driving the turbopump to rotate, the gas generator is provided with a generator oxidant inlet connected to the oxidant outlet, and the gas generator is also provided with a generator fuel inlet connected to the fuel outlet; the gas generator is connected to an oxygen electric pump for supplying oxidant to the gas generator, and the gas generator is also connected to a fuel electric pump for supplying fuel to the gas generator; the oxygen electric pump and the fuel electric pump are connected to a driver and controller for starting and adjusting the oxygen electric pump and the fuel electric pump, and the driver and controller are connected to a battery pack.

[0013] Furthermore, the turbopump includes a synchronously rotating gas turbine, an oxidant pump, and a fuel pump. The gas turbine is connected to the gas generator, the oxidant inlet and the oxidant outlet are arranged on the oxidant pump, and the fuel inlet and the fuel outlet are arranged on the fuel pump.

[0014] Furthermore, the oxidant outlet of the oxidant pump is connected to an oxidant outlet pipe communicated with the thrust chamber, and an oxygen main valve is provided on the oxidant outlet pipe; the fuel outlet of the fuel pump is connected to a fuel outlet pipe communicated with the thrust chamber, and a fuel main valve is provided on the fuel outlet pipe.

[0015] Furthermore, the oxygen electric pump is provided with an oxidant pipeline connected to the gas generator, and the fuel electric pump is provided with a fuel pipeline connected to the gas generator; the oxidant outlet pipeline is provided with an oxidant connecting pipeline connected to the oxidant pipeline, and the fuel outlet pipeline is provided with a fuel connecting pipeline connected to the fuel pipeline.

[0016] Furthermore, the oxidant pipeline is provided with an oxygen check valve and a generator oxygen valve, and the oxidant connecting pipeline is provided between the oxygen check valve and the generator oxygen valve; the fuel pipeline is provided with a fuel check valve and a generator fuel valve, and the fuel connecting pipeline is provided between the fuel check valve and the generator fuel valve; the fuel connecting pipeline is provided with a fuel supply valve and a fuel supply check valve, and the oxidant connecting pipeline is provided with an oxygen supply valve and an oxygen supply check valve.

[0017] Furthermore, the igniter is provided with an igniter oxidant inlet and an igniter fuel inlet. The igniter oxidant inlet is connected to the generator oxidant inlet pipeline of the gas generator, and the igniter fuel inlet is connected to the generator fuel inlet pipeline of the gas generator.

[0018] Furthermore, the igniter oxidant inlet is provided with an igniter oxidant pipeline connected to the generator oxidant inlet pipeline of the gas generator, and the igniter oxidant pipeline is provided with an igniter oxygen valve; the igniter fuel inlet is provided with an igniter fuel pipeline connected to the generator fuel inlet pipeline of the gas generator, and the igniter fuel pipeline is provided with an igniter fuel valve.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. When the present invention is in use, the oxygen electric pump and the fuel electric pump are used to start and adjust the gas generator to realize the starting and adjustment of the entire engine system, so that the starting and variable thrust adjustment method is concise and the structure is simple, which is used to solve the shortcomings of the existing engine system that multiple starts and adjustments are realized by configuring a complex starting system and a flow regulating device; at the same time, during the starting and adjustment process of the system, the starting and adjustment system is completely decoupled from the main system, and the system is stable, high in precision, simple and reliable during the starting and adjustment process.

[0021] 2. When the present invention is in use, the starting and adjustment of the oxygen electric pump and the fuel electric pump are achieved by a low-power motor, which is easy to achieve multiple starts and stepless depth adjustment. Therefore, the system is simple, and the engine starting and variable thrust adjustment method is concise, which is used to solve the shortcomings of the existing engine system that multiple starts and adjustments are achieved by configuring a complex starting system and a flow regulating device; at the same time, during the starting and adjustment process of the system, the starting and adjustment system is completely decoupled from the main system, and the system is stable, high-precision, simple and reliable during the starting and adjustment process. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] In the figure: 1. oxidant pump, 2. fuel pump, 3. gas turbine, 4. gas generator, 41. generator fuel valve, 42. generator oxygen valve, 5. battery pack, 51. drive controller, 52. oxygen electric pump, 53. fuel electric pump, 6. thrust chamber, 61. fuel main valve, 62. oxygen main valve, 7. igniter, 71. igniter fuel valve, 72. igniter oxygen valve, 8. fuel check valve, 81. fuel supply valve, 82. fuel supply check valve, 9. oxygen supply valve, 91. oxygen supply check valve, 92. oxygen check valve. DETAILED DESCRIPTION

[0024] A variable thrust liquid rocket engine control system, such as Figure 1 As shown, it includes a thrust chamber 6 and a turbine pump, and an igniter 7 is provided on the thrust chamber 6; the turbine pump is provided with an oxidant inlet, an oxidant outlet, a fuel inlet and a fuel outlet, and the oxidant outlet and the fuel outlet are both connected to the thrust chamber 6; the turbine pump is connected to a gas generator 4 that can drive the turbine pump to rotate, the gas generator 4 is provided with a generator oxidant inlet connected to the oxidant outlet, and the gas generator 4 is also provided with a generator fuel inlet connected to the fuel outlet; the gas generator 4 is connected to an oxygen electric pump 52 for supplying oxidant to the gas generator 4, and the gas generator 4 is also connected to a fuel electric pump 53 for supplying fuel to the gas generator 4; the oxygen electric pump 52 and the fuel electric pump 53 are connected to a driver 51 for starting and adjusting the oxygen electric pump 52 and the fuel electric pump 53, and the driver 51 is connected to a battery pack 5.

[0025] When the present invention is in use, by selecting the oxygen electric pump 52 and the fuel electric pump 53 to cooperate or the turbine pump to supply oxidant and fuel to the gas generator 4, the present application can start and adjust the gas generator 4 through the oxygen electric pump 52 and the fuel electric pump 53 to realize the starting and adjustment of the entire engine system, so that the starting and variable thrust adjustment method is concise and the structure is simple, which is used to solve the shortcomings of the existing engine system that multiple starts and adjustments are realized by configuring a complex starting system and a flow regulating device; the turbine pump is used to supply oxidant and fuel to the gas generator 4, and the gas generator 4 acts on the turbine pump, and the turbine pump supplies propellant to the thrust chamber 6, so that the engine will gradually reach the self-circulating rated working equilibrium state.

[0026] Furthermore, the turbopump includes a synchronously rotating gas turbine 3, an oxidant pump 1, and a fuel pump 2, the gas turbine 3 is connected to the gas generator 4, the oxidant inlet and the oxidant outlet are arranged on the oxidant pump 1, and the fuel inlet and the fuel outlet are arranged on the fuel pump 2.

[0027] The gas generator 4 drives the oxidant pump 1 and the fuel pump 2 to rotate through the gas turbine 3. The oxidant pump 1 and the fuel pump 2 cooperate with each other to supply oxidant and fuel to the gas generator 4 and the thrust chamber 6, so that the engine will gradually reach the self-circulating rated working balance state.

[0028] Furthermore, the oxidant outlet of the oxidant pump 1 is connected to an oxidant outlet pipe connected to the thrust chamber 6, and an oxygen main valve 62 is provided on the oxidant outlet pipe; the fuel outlet of the fuel pump 2 is connected to a fuel outlet pipe connected to the thrust chamber 6, and a fuel main valve 61 is provided on the fuel outlet pipe; the oxidant pump 1 supplies oxidant to the thrust chamber 6 through the oxidant outlet pipe and the oxygen main valve 62 thereon, and the fuel pump 2 supplies fuel to the thrust chamber 6 through the fuel outlet pipe and the fuel main valve 61 thereon, thereby starting the thrust chamber 6.

[0029] Furthermore, the oxygen electric pump 52 is provided with an oxidant pipeline connected to the gas generator 4, and the fuel electric pump 53 is provided with a fuel pipeline connected to the gas generator 4; the oxygen electric pump 52 provides oxidant to the gas generator 4 through the oxidant pipeline, and the fuel electric pump 53 provides fuel to the gas generator 4 through the fuel pipeline, so that the gas generator 4 is started.

[0030] Furthermore, the oxidant outlet pipe is provided with an oxidant connecting pipe connected to the oxidant pipe, and the fuel outlet pipe is provided with a fuel connecting pipe connected to the fuel pipe; the fuel connecting pipe is provided with a fuel supply valve 81 and a fuel supply check valve 82, and the oxidant connecting pipe is provided with an oxygen supply valve 9 and an oxygen supply check valve 91.

[0031] When the engine needs to work at rated conditions, the oxygen electric pump 52 and the fuel electric pump 53 are closed, and the oxygen supply valve 9 and the fuel supply valve 81 are opened to connect the oxidant connecting pipe with the oxidant pipe, so that the oxidant in the oxidant outlet pipe flows to the gas generator 4 through the oxidant connecting pipe and the oxidant pipe; the fuel connecting pipe is connected with the fuel pipe, so that the fuel in the fuel outlet pipe flows to the gas generator 4 through the fuel connecting pipe and the fuel pipe, so that the propellant supply of the gas generator 4 is transferred from the oxygen electric pump 52 and the fuel electric pump 53 to the turbine pump, and the engine will gradually reach the self-circulating rated working equilibrium state; by setting the fuel supply valve 81 and the oxygen supply valve 9, the fuel connecting pipe and the oxidant connecting pipe are opened and closed; by setting the fuel supply check valve 82 and the oxygen supply check valve 91, the fuel and oxidant are supplied in one direction (that is, the turbine pump supplies to the gas generator 4), thereby improving the stability of the operation of the present application.

[0032] Furthermore, the oxidant pipeline is provided with an oxygen check valve 92 and a generator oxygen valve 42, and the oxidant connecting pipeline is provided between the oxygen check valve 92 and the generator oxygen valve 42; by the provision of the oxygen check valve 92 and the generator oxygen valve 42, the oxidant is prevented from flowing back to the oxygen electric pump 52, and the generator oxygen valve 42 is used to open and close the oxidant entering the gas generator 4, so that the oxygen electric pump 52 and the gas generator 4 can operate stably; the fuel pipeline is provided with a fuel check valve 8 and a generator fuel valve 41, and the fuel connecting pipeline is provided between the fuel check valve 8 and the generator fuel valve 41; by the provision of the fuel check valve 8 and the generator fuel valve 41, the fuel is prevented from flowing back to the fuel electric pump 53, and the generator fuel valve 41 is used to open and close the fuel entering the gas generator 4, so that the fuel electric pump 53 and the gas generator 4 can operate stably.

[0033] Furthermore, the igniter 7 is provided with an igniter oxidant inlet and an igniter fuel inlet, the igniter oxidant inlet is connected to the generator oxidant inlet pipeline of the gas generator 4, and the igniter fuel inlet is connected to the generator fuel inlet pipeline of the gas generator 4; the oxidant and fuel in the generator oxidant inlet pipeline and the generator fuel inlet pipeline of the gas generator 4 are supplied to the igniter 7, so that the igniter 7 ignites the thrust chamber 6.

[0034] Furthermore, an igniter oxidant inlet is provided with an igniter oxidant pipeline connected to the generator oxidant inlet pipeline of the gas generator 4, and an igniter oxygen valve 72 is provided on the igniter oxidant pipeline; an igniter fuel inlet is provided with an igniter fuel pipeline connected to the generator fuel inlet pipeline of the gas generator 4, and an igniter fuel valve 71 is provided on the igniter fuel pipeline; specifically, the igniter oxidant pipeline is connected to the oxidant pipeline, and the igniter oxidant pipeline is arranged between the oxygen check valve 92 and the generator oxygen valve 42; the igniter fuel pipeline is connected to the fuel pipeline, and the igniter fuel pipeline is arranged between the fuel check valve 8 and the generator fuel valve 41; by setting the igniter oxygen valve 72 on the igniter oxidant pipeline and the igniter fuel valve 71 on the igniter fuel pipeline, the ignition of the igniter 7 is controlled to improve the control effect of the present application.

[0035] The starting and adjustment process of a variable thrust liquid rocket engine control system is as follows:

[0036] S1. Before starting, fuel is filled before the igniter fuel valve 71, the generator fuel valve 41, the fuel main valve 61, and the fuel supply valve 81, and oxygen is filled before the igniter oxygen valve 72, the generator oxygen valve 42, the oxygen main valve 62, and the oxygen supply valve 9. The igniter fuel valve 71, the igniter oxygen valve 72, the generator fuel valve 41, the generator oxygen valve 42, the fuel main valve 61, the oxygen main valve 62, the fuel supply valve 81, and the oxygen supply valve 9 remain closed.

[0037] At startup, the drive controller 51 receives the startup command from the host computer, and the oxygen electric pump 52 and the fuel electric pump 53 are energized and start to rotate in turn. After the speed of the oxygen electric pump 52 and the fuel electric pump 53 reaches 10%~20% of the rated speed, the generator fuel valve 41 and the generator oxygen valve 42 are opened in turn, and the fuel and the oxidant begin to fill the valve rear cavity of the generator fuel valve 41 and the generator oxygen valve 42 respectively; when the fuel and the oxidant are filled into the gas generator 4, the spark plug of the gas generator 4 is started to ignite, and the combustion produces high-temperature rich fuel gas to drive the gas turbine 3 to rotate, and the gas turbine 3 drives the oxidant pump 1 and the fuel pump 2 to rotate synchronously.

[0038] S2. When the speed of the gas turbine 3 climbs to 20%~50% of the rated speed, the fuel supply valve 81 and the oxygen supply valve 9 are opened in sequence, and the propellant supply of the gas generator 4 is relayed by the fuel electric pump 53 and the oxygen electric pump 52 to the fuel pump 2 and the oxidant pump 1 in the turbine pump; after the fuel electric pump 53 and the oxygen electric pump 52 continue to work for 1~1.5s, the driver 51 receives the stop command of the upper computer to shut down the fuel electric pump 53 and the oxygen electric pump 52; when the speed of the gas turbine 3 reaches 20%~30% of the rated speed, the main fuel valve 61 and the main oxygen valve 62 are opened in sequence, and the fuel and the oxidant begin to fill the valve rear cavities of the main fuel valve 61 and the main oxygen valve 62 of the thrust chamber 6 respectively, so that the oxidant pump 1 and the fuel pump 2 provide the thrust chamber 6 with oxidant and fuel.

[0039] S3. According to the timing arrangement, the igniter fuel valve 71 and the igniter oxygen valve 72 are opened in sequence, and the fuel and oxidant in the fuel pipeline and the oxidant pipeline flow into the igniter fuel pipeline and the igniter oxidant pipeline respectively, and fill the cavity behind the igniter 7 valve; when the fuel and the oxidant are filled into the igniter 7, the spark plug of the igniter 7 is started to ignite, and the igniter 7 produces high-temperature combustion gas; when the fuel and the oxidant are filled into the thrust chamber 6, the high-temperature combustion gas of the igniter 7 ignites the propellant of the thrust chamber 6, and the thrust chamber 6 is ignited successfully; after the igniter 7 works for 1 to 1.5 seconds, the igniter oxygen valve 72 and the igniter fuel valve 71 are closed in sequence.

[0040] S4. The gas generator 4 continues to work in relay under the supply of high-pressure oxidant and fuel from the oxidant pump 1 and the fuel pump 2. The speed of the gas turbine 3 gradually increases, and the head after the pump gradually increases. When the pressure in the thrust chamber 6 gradually increases to the rated operating condition, the engine reaches the rated operating condition equilibrium state. At this point, the engine start-up is completed.

[0041] S5. Before thrust adjustment, start the oxygen electric pump 52 and the fuel electric pump 53, and set the speed to the rated speed; when the speeds of the fuel electric pump 53 and the oxygen electric pump 52 reach the rated speed, close the oxygen supply valve 9 and the fuel supply valve 81 in turn, and the propellant supply to the gas generator 4 is transferred from the oxidizer pump 1 and the fuel pump 2 to the oxygen electric pump 52 and the fuel electric pump 53.

[0042] S6. When adjusting thrust, the speeds of the oxygen electric pump 52 and the fuel electric pump 53 are adjusted and controlled to the set working conditions respectively; the speeds of the oxygen electric pump 52 and the fuel electric pump 53 are used to adjust the amount and the mixing ratio of the propellant supplied to the gas generator 4, adjust the working capacity of the gas of the gas generator 4 on the gas turbine 3, and adjust the output power of the gas turbine 3, that is, adjust the propellant flow and pressure entering the thrust chamber 6 to achieve the thrust requirement of the engine.

Claims

1. A variable thrust liquid rocket engine control system, characterized in that: The invention comprises a thrust chamber (6) and a turbine pump, wherein the thrust chamber (6) is provided with an igniter (7); the turbine pump is provided with an oxidant inlet, an oxidant outlet, a fuel inlet and a fuel outlet, and the oxidant outlet and the fuel outlet are both communicated with the thrust chamber (6); the turbine pump is connected to a gas generator (4) capable of driving the turbine pump to rotate, the gas generator (4) is provided with a generator oxidant inlet communicated with the oxidant outlet, and the gas generator (4) is also provided with a generator fuel inlet communicated with the fuel outlet; the gas generator (4) is connected to an oxygen electric pump (52) for supplying oxidant to the gas generator (4), and the gas generator (4) is also connected to a fuel electric pump (53) for supplying fuel to the gas generator (4); the oxygen electric pump (52) and the fuel electric pump (53) are connected to a driver (51) for starting and regulating the oxygen electric pump (52) and the fuel electric pump (53), and the driver (51) is connected to a battery pack (5).

2. The variable thrust liquid rocket engine control system according to claim 1, characterized in that: The turbo pump comprises a synchronously rotating gas turbine (3), an oxidant pump (1), and a fuel pump (2); the gas turbine (3) is connected to a gas generator (4); an oxidant inlet and an oxidant outlet are arranged on the oxidant pump (1); and a fuel inlet and a fuel outlet are arranged on the fuel pump (2).

3. The variable thrust liquid rocket engine control system according to claim 2, characterized in that: The oxidant outlet of the oxidant pump (1) is connected to an oxidant outlet pipeline communicating with the thrust chamber (6), and an oxygen main valve (62) is provided on the oxidant outlet pipeline; the fuel outlet of the fuel pump (2) is connected to a fuel outlet pipeline communicating with the thrust chamber (6), and a fuel main valve (61) is provided on the fuel outlet pipeline.

4. The variable thrust liquid rocket engine control system according to claim 3, characterized in that: The oxygen electric pump (52) is provided with an oxidant pipeline connected to the gas generator (4), and the fuel electric pump (53) is provided with a fuel pipeline connected to the gas generator (4); the oxidant outlet pipeline is provided with an oxidant communication pipeline connected to the oxidant pipeline, and the fuel outlet pipeline is provided with a fuel communication pipeline connected to the fuel pipeline.

5. The variable thrust liquid rocket engine control system according to claim 4, characterized in that: The oxidant pipeline is provided with an oxygen check valve (92) and a generator oxygen valve (42), and the oxidant communication pipeline is provided between the oxygen check valve (92) and the generator oxygen valve (42); the fuel pipeline is provided with a fuel check valve (8) and a generator fuel valve (41), and the fuel communication pipeline is provided between the fuel check valve (8) and the generator fuel valve (41); the fuel communication pipeline is provided with a fuel supply valve (81) and a fuel supply check valve (82), and the oxidant communication pipeline is provided with an oxygen supply valve (9) and an oxygen supply check valve (91).

6. The variable thrust liquid rocket engine control system according to claim 1, characterized in that: The igniter (7) is provided with an igniter oxidant inlet and an igniter fuel inlet. The igniter oxidant inlet is connected to the generator oxidant inlet pipeline of the gas generator (4), and the igniter fuel inlet is connected to the generator fuel inlet pipeline of the gas generator (4).

7. The variable thrust liquid rocket engine control system according to claim 6, characterized in that: The igniter oxidant inlet is provided with an igniter oxidant pipeline connected to the generator oxidant inlet pipeline of the gas generator (4), and the igniter oxidant pipeline is provided with an igniter oxygen valve (72); the igniter fuel inlet is provided with an igniter (7) fuel pipeline connected to the generator fuel inlet pipeline of the gas generator (4), and the igniter (7) fuel pipeline is provided with an igniter fuel valve (71).

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