Open cycle variable thrust rocket engine, rocket and control method

Abstract

The present application relates to aerospace propulsion technology field, specifically to a kind of open variable thrust rocket engine, rocket and control method, open variable thrust rocket engine includes: pressurizing device;Thrust chamber, with first fuel inlet, first oxidant inlet, first fuel inlet is communicated with fuel outlet fuel main road, fuel main road is equipped with fuel main valve, first oxidant inlet is communicated with oxidant outlet through oxygen main road;Gas generator, with second fuel inlet, second oxidant inlet, gas outlet, second fuel inlet is connected with fuel main road through fuel auxiliary road, second oxidant inlet is connected with oxygen main road through oxygen auxiliary road;Gas outlet is connected with the driving inlet of pressurizing device through gas main road, pressurizing device is also communicated with gas main road by gas shunt road in interior, gas shunt road is equipped with gas regulating valve, gas generated by gas generator is suitable for entering pressurizing device by gas shunt road and discharging.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, specifically to an open-type variable thrust rocket engine, rocket, and control method. Background Technology

[0002] A typical rocket engine has only one thrust operating mode, and both the engine and the rocket can only be used once. To achieve the recovery and reuse of rockets and other spacecraft and reduce launch costs, rocket engines must have thrust adjustment capabilities. Summary of the Invention

[0003] Therefore, the purpose of this invention is to provide an open variable thrust rocket engine, rocket, and control method with thrust adjustment capability.

[0004] To solve the above-mentioned technical problems, the present invention provides an open variable thrust rocket engine, comprising:

[0005] The booster unit has an oxidizer outlet and a fuel outlet;

[0006] The thrust chamber has a first fuel inlet and a first oxidant inlet. The first fuel inlet and the fuel outlet are connected through a fuel main line, and a fuel main valve is provided on the fuel main line. The first oxidant inlet and the oxidant outlet are connected through an oxygen main line, and an oxygen main valve is provided on the oxygen main line.

[0007] A gas generator has a second fuel inlet, a second oxidant inlet, and a gas outlet. The second fuel inlet is connected to the main fuel line through a secondary fuel line, and a secondary fuel valve is provided on the secondary fuel line. The second oxidant inlet is connected to the main oxygen line through a secondary oxygen line, and an secondary oxygen valve is provided on the secondary oxygen line.

[0008] The gas outlet is connected to the drive inlet of the booster device via a main gas line to drive the booster device to rotate. The booster device is also connected to the main gas line via a gas diversion line. A gas regulating valve is provided on the gas diversion line. The gas generated by the gas generator is suitable for entering the booster device through the gas diversion line and then being discharged.

[0009] Optionally, the thrust chamber is equipped with a pressure detection device for detecting the pressure in the thrust chamber.

[0010] Optionally, the pressure detection device includes a first pressure sensor and a second pressure sensor.

[0011] Optionally, the booster includes a turbine, an oxygen pump, and a fuel pump arranged coaxially. The main oxygen line is connected to the oxygen pump, the main fuel line is connected to the fuel pump, the main gas line is connected to the drive inlet of the turbine, and the gas branch line is connected to the inside of the turbine.

[0012] Optionally, the open-type variable thrust rocket engine further includes:

[0013] A fuel inlet pipe, one end of which is adapted to be connected to a fuel source, and the other end of which is connected to the fuel pump, wherein the fuel inlet pipe is equipped with a first flow meter;

[0014] An oxidant inlet pipe is provided with a second flow meter on one end, which is adapted to be connected to an oxidant source and the other end to the oxygen pump.

[0015] Optionally, an oxygen main regulating valve is provided on the oxygen main line downstream of the oxygen main valve.

[0016] Optionally, a temperature detection device is provided on the main gas pipeline, and an oxygen auxiliary regulating valve is provided on the oxygen auxiliary pipeline downstream of the oxygen auxiliary valve.

[0017] Optionally, the temperature detection device includes a first temperature sensor and a second temperature sensor.

[0018] Optionally, the thrust chamber includes a main body and a cooling jacket disposed outside the main body, the main fuel line is connected to the inlet of the cooling jacket, and the outlet of the cooling jacket is connected to the first fuel inlet.

[0019] The present invention also provides a rocket, including the aforementioned open variable thrust rocket engine.

[0020] The present invention also provides a control method for an open variable thrust rocket engine, applied to the aforementioned open variable thrust rocket engine, comprising:

[0021] Obtain thrust command;

[0022] Converting thrust into the pressure required for the thrust chamber;

[0023] Adjust the opening of the gas regulating valve according to the required pressure.

[0024] Optionally, adjusting the opening degree of the gas regulating valve according to the required pressure includes:

[0025] Obtain the current pressure in the thrust chamber;

[0026] Calculate the first deviation between the required pressure and the current pressure;

[0027] Calculate the first opening change of the gas regulating valve based on the first deviation;

[0028] The opening of the gas regulating valve is adjusted according to the first change in opening degree.

[0029] Optionally, obtaining the current pressure of the thrust chamber includes:

[0030] The first pressure value detected by the first pressure sensor and the second pressure value detected by the second pressure sensor are obtained, and the current pressure is calculated based on the first pressure value and the second pressure value.

[0031] Optionally, the control method further includes:

[0032] Obtain the engine air-fuel ratio command;

[0033] Adjust the opening of the main oxygen regulating valve according to the engine mixture ratio command.

[0034] Optionally, adjusting the opening of the main oxygen regulating valve according to the engine mixture ratio command includes:

[0035] Obtain the fuel flow rate measured by the first flow meter and the oxygen flow rate measured by the second flow meter;

[0036] Calculate the ratio of the oxygen flow rate to the fuel flow rate, where the ratio is the current engine air-fuel mixture ratio;

[0037] Calculate the second deviation between the engine mixture ratio command and the current engine mixture ratio;

[0038] Calculate the second opening change of the oxygen main control valve based on the second deviation;

[0039] Adjust the opening of the main oxygen control valve according to the second opening change.

[0040] Optionally, the control method further includes:

[0041] Obtain the current temperature value detected by the temperature detection device;

[0042] Calculate the third deviation between the current temperature value and the preset temperature value;

[0043] The third opening change of the oxygen auxiliary regulating valve is calculated based on the third deviation.

[0044] The opening of the oxygen auxiliary regulating valve is adjusted according to the third opening change.

[0045] Optionally, the current temperature value detected by the temperature detection device includes:

[0046] The system acquires a first temperature value detected by a first temperature sensor and a second temperature value detected by a second temperature sensor, and calculates the current temperature value based on the first temperature value and the second temperature value.

[0047] The technical solution of this invention has the following advantages:

[0048] 1. The open-type variable thrust rocket engine provided by this invention, by setting a gas regulating valve in the gas splitting path, allows for increased gas flow rate when the engine thrust requirement decreases. This increases the gas flow rate discharged from the engine through the pressurization device, thereby reducing the gas flow rate driving the pressurization device and thus reducing the engine thrust. Conversely, when the engine thrust requirement increases, the gas regulating valve opening can be decreased. By setting the gas regulating valve, variable thrust adjustment of the engine can be achieved, with a thrust adjustment depth of 20%–100%. Attached Figure Description

[0049] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0050] Figure 1 This is a schematic diagram of the open variable thrust rocket engine provided in Embodiment 1 of the present invention.

[0051] Explanation of reference numerals in the attached figures:

[0052] 1. Thrust chamber; 2. Turbine; 3. Gas generator; 4. Fuel main valve; 5. Fuel auxiliary valve; 6. Oxygen main valve; 7. Oxygen auxiliary valve; 8. Oxygen pump; 9. Fuel pump; A1. First temperature sensor; A2. Second temperature sensor; B1. First pressure sensor; B2. Second pressure sensor; C1. Gas regulating valve; C2. Oxygen auxiliary regulating valve; C3. Oxygen main regulating valve; E1. First flow meter; E2. Second flow meter. Detailed Implementation

[0053] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0054] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for 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 limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0055] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0056] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0057] Example 1

[0058] This embodiment provides an open-type variable-thrust rocket engine that can achieve deep thrust adjustment. In one implementation, such as... Figure 1 As shown, the open variable thrust rocket engine includes: a pressurization device, a thrust chamber 1, and a gas generator 3.

[0059] The booster has an oxidizer outlet and a fuel outlet; the thrust chamber 1 has a first fuel inlet and a first oxidizer inlet, the first fuel inlet and the fuel outlet are connected through a main fuel line, and a main fuel valve 4 is provided on the main fuel line; the first oxidizer inlet and the oxidizer outlet are connected through an oxygen main line, and an oxygen main valve 6 is provided on the oxygen main line; the gas generator 3 has a second fuel inlet, a second oxidizer inlet, and a gas outlet, the second fuel inlet is connected to the main fuel line through a secondary fuel line, and a secondary fuel valve 5 is provided on the secondary fuel line; the second oxidizer inlet is connected to the main oxygen line through a secondary oxygen line, and a secondary oxygen valve 7 is provided on the secondary oxygen line; the gas outlet is connected to the drive inlet of the booster through the main gas line, and is used to drive the booster to rotate; the booster is also connected to the main gas line through a gas diversion line, and a gas regulating valve C1 is provided on the gas diversion line; the gas generated by the gas generator 3 is suitable for entering the booster through the gas diversion line and then being discharged.

[0060] The working principle of the engine provided in this embodiment is as follows: After the fuel exits from the fuel outlet of the turbocharger, most of the fuel flow enters the main fuel line, passes through the main fuel valve 4, and enters the thrust chamber 1; a small portion of the flow enters the auxiliary fuel line, passes through the auxiliary fuel valve 5, and enters the gas generator 3. After the oxidizer exits from the oxidizer outlet of the turbocharger, most of the oxidizer flow enters the main oxygen line, passes through the main oxygen valve 6, and enters the thrust chamber 1; a small portion of the oxidizer flow enters the auxiliary oxygen line, passes through the auxiliary oxygen valve 7, and enters the gas generator 3. The fuel and oxidizer in the gas generator 3 burn to produce low-temperature gas. After the gas exits from the gas outlet, it is divided into two paths: one part flows into the main gas line to drive the turbocharger, and the other part flows into the gas diversion line, passes through the gas regulating valve C1, enters the turbocharger, and is finally discharged from the engine. The fuel and oxidizer in the thrust chamber 1 burn to produce high-temperature gas, which accelerates within the thrust chamber 1, is discharged from the engine, and generates thrust. This embodiment uses a gas regulating valve C1 installed in the gas splitter path. When the engine thrust requirement decreases, the opening of the gas regulating valve C1 can be increased, thereby increasing the gas flow rate discharged from the engine through the turbocharger and reducing the gas flow rate driving the turbocharger, thus reducing the engine thrust. When the engine thrust requirement increases, the opening of the gas regulating valve C1 can be decreased. By installing the gas regulating valve C1, variable thrust adjustment of the engine can be achieved, and a thrust adjustment depth of 20%-100% can be realized.

[0061] Based on the above embodiments, in a preferred embodiment, the thrust chamber 1 is equipped with a pressure detection device for detecting the pressure in the thrust chamber 1. By setting up a pressure detection device to detect the pressure in the thrust chamber 1, the current pressure value of the thrust chamber 1 can be obtained in real time. When it is necessary to adjust the thrust, the required thrust can be converted into the required pressure, and the opening adjustment amount of the gas regulating valve C1 can be determined based on the current pressure value, making the adjustment more precise.

[0062] Based on the above embodiments, in a preferred embodiment, the pressure detection device includes a first pressure sensor B1 and a second pressure sensor B2. By setting two pressure sensors in the thrust chamber 1 to detect the pressure value of the thrust chamber 1, the accuracy of the detection can be ensured, and if one pressure sensor fails, the other pressure sensor can still accurately detect the pressure of the thrust chamber 1.

[0063] Based on the above embodiments, in a preferred embodiment, the booster device is a turbopump, including a turbine 2, an oxygen pump 8, and a fuel pump 9 coaxially arranged. The main oxygen line is connected to the oxygen pump 8, the main fuel line is connected to the fuel pump 9, the main gas line is connected to the drive inlet of the turbine 2, and the gas splitter line is connected to the inside of the turbine 2. Specifically, as follows... Figure 1As shown, fuel pump 9 includes a primary fuel pump and a secondary fuel pump, with the main fuel line connected to the secondary fuel pump. In an alternative embodiment, the booster device can be a piston pump.

[0064] Based on the above embodiments, in a preferred embodiment, the open-type variable-thrust rocket engine further includes a fuel inlet pipe and an oxidizer inlet pipe. One end of the fuel inlet pipe is adapted to be connected to a fuel source, and the other end is connected to a fuel pump 9. The fuel inlet pipe is equipped with a first flow meter E1. The oxidizer inlet pipe is adapted to be connected to an oxidizer source at one end and to an oxygen pump 8 at the other end. The oxidizer inlet pipe is equipped with a second flow meter E2. In this embodiment, by installing the first flow meter E1 on the fuel inlet pipe, the fuel flow rate can be detected in real time. By installing the second flow meter E2 on the oxidizer inlet pipe, the oxidizer flow rate can be detected in real time, thereby obtaining the real-time engine mixture ratio, which refers to the ratio of oxidizer flow rate to fuel flow rate.

[0065] Based on the above embodiments, in a preferred embodiment, an oxygen main regulating valve C3 is provided downstream of the oxygen main valve 6 on the oxygen main line. In this embodiment, by adjusting the opening of the oxygen main regulating valve C3, the oxidant flow rate entering the thrust chamber 1 can be adjusted, thereby enabling engine mixture ratio regulation.

[0066] Based on the above embodiments, in a preferred embodiment, a temperature detection device is provided on the main gas pipeline, and an oxygen auxiliary regulating valve C2 is provided downstream of the oxygen auxiliary valve 7 on the auxiliary oxygen pipeline. In this embodiment, by providing a temperature detection device on the main gas pipeline, the temperature of the gas produced by combustion can be detected. When the detected temperature value is too high, the opening of the oxygen auxiliary regulating valve C2 is reduced by adjusting it; when the detected temperature value is too low, the opening of the oxygen auxiliary regulating valve C2 is increased by adjusting it, thereby maintaining the gas temperature within the required range (800K-860K).

[0067] In a preferred embodiment, the temperature detection device includes a first temperature sensor A1 and a second temperature sensor A2. By installing two temperature sensors on the gas main pipeline to detect the gas temperature, accuracy of the detection can be ensured, and if one temperature sensor fails, the other temperature sensor can still accurately detect the gas temperature. Preferably, the temperature sensors are fast-changing gas temperature sensors.

[0068] Based on the above embodiments, in a preferred embodiment, the thrust chamber 1 includes a main body and a cooling jacket disposed outside the main body. The main fuel line is connected to the inlet of the cooling jacket, and the outlet of the cooling jacket is connected to the first fuel inlet. In this embodiment, fuel enters the cooling jacket through the main fuel line, which can first cool the main body of the thrust chamber 1 before entering the thrust chamber 1.

[0069] The working principle of the open variable thrust rocket engine provided in this embodiment is as follows:

[0070] Fuel enters fuel pump 9 through the first flow meter E1 in the fuel inlet pipe. After exiting fuel pump 9, it is divided into two paths. Most of the flow enters the main fuel path, passes through the main fuel valve 4, enters the cooling jacket of the thrust chamber 1, and finally enters the thrust chamber 1. A small portion of the flow enters the auxiliary fuel path, passes through the auxiliary fuel valve 5, and enters the gas generator 3.

[0071] The oxidant enters the oxygen pump 8 through the second flow meter E2 in the oxidant inlet pipe. After exiting the oxygen pump 8, it is divided into two paths. Most of the flow enters the main oxygen path, passes through the main oxygen valve 6 and the main oxygen regulating valve C3, and then enters the thrust chamber 1. The main oxygen regulating valve C3 can be adjusted to control the flow rate of the main oxygen path. A small portion of the flow enters the secondary oxygen path, passes through the secondary oxygen valve 7 and the secondary oxygen regulating valve C2, and then enters the gas generator 3. The secondary oxygen regulating valve C2 can be adjusted to control the flow rate of the secondary oxygen path.

[0072] The fuel and oxidizer entering the gas generator 3 combust to produce low-temperature gas. Two fast-changing gas temperature sensors are redundantly installed at the gas outlet to measure the gas temperature. The gas is then divided into two paths: one part flows into the main gas path to drive turbine 2 and perform work, while the other part flows into the gas split path, passes through the gas regulating valve C1, and then enters turbine 2 without performing work on turbine 2. The two gas paths are mixed and then discharged from the engine. The opening of the gas regulating valve C1 can be adjusted to control the gas flow in the split path.

[0073] The fuel and oxidizer entering the thrust chamber 1 are burned to produce high-temperature gas, which accelerates and flows within the thrust chamber 1 before being discharged from the engine, generating thrust. The thrust chamber 1 is redundantly equipped with two pressure sensors to measure the pressure in the thrust chamber 1.

[0074] Example 2

[0075] This embodiment provides a rocket, including the open variable thrust rocket engine provided in the above embodiment.

[0076] Example 3

[0077] This embodiment provides a control method for an open-type variable-thrust rocket engine, applied to the open-type variable-thrust rocket engine provided in Embodiment 1. In one implementation, the control method includes the following steps:

[0078] S1: Obtain thrust command;

[0079] S2: The pressure required to convert thrust into thrust chamber 1;

[0080] S3: Adjust the opening of the gas regulating valve C1 according to the required pressure.

[0081] In this embodiment, there is a relationship between the thrust and the pressure in thrust chamber 1. Specifically, this relationship can be obtained from multiple sets of thrust and pressure values ​​statistically analyzed during the test, or by directly recording corresponding thrust and pressure values ​​during the test. When a thrust command is received and the thrust magnitude needs to be adjusted, the required pressure is first calculated based on the relationship between the thrust and the pressure in thrust chamber 1. Then, the opening of the gas regulating valve C1 is adjusted according to the required pressure. When the engine thrust requirement decreases, the opening of the gas regulating valve C1 can be increased, thereby increasing the flow rate of gas discharged from the engine through turbine 2, which reduces the flow rate of gas driving turbine 2, thus reducing the engine thrust. When the engine thrust requirement increases, the opening of the gas regulating valve C1 can be decreased. By adjusting the opening of the gas regulating valve C1, variable thrust adjustment of the engine can be achieved, and a thrust adjustment depth of 20%-100% can be realized.

[0082] Based on the above embodiments, in a preferred embodiment, step S3 includes:

[0083] S31: Obtain the current pressure of thrust chamber 1;

[0084] S32: Calculate the first deviation between the required pressure and the current pressure;

[0085] S33: Calculate the first opening change of gas regulating valve C1 based on the first deviation;

[0086] S34: Adjust the opening of the gas regulating valve C1 according to the change in the first opening degree.

[0087] In this embodiment, by obtaining the current pressure of the thrust chamber 1 and calculating the first opening change of the gas regulating valve C1 based on the first deviation between the required pressure and the current pressure, the opening of the gas regulating valve C1 can be adjusted according to the first opening change, thereby achieving precise adjustment of the gas regulating valve C1 and thus precise adjustment of the thrust.

[0088] In one specific implementation, step S31 includes:

[0089] S31: Obtain the first pressure value detected by the first pressure sensor B1 and the second pressure value detected by the second pressure sensor B2, and calculate the current pressure based on the first and second pressure values. By setting two pressure sensors in the thrust chamber 1 to detect the pressure value of the thrust chamber 1, the accuracy of the detection can be ensured, and if one pressure sensor fails, the other pressure sensor can still accurately detect the pressure of the thrust chamber 1. Specifically, when both pressure sensors are working normally, the current pressure can be the average of the first and second pressure values. When one pressure sensor fails, the current pressure is the pressure value detected by the undamaged pressure sensor.

[0090] Based on the above embodiments, in a preferred embodiment, the control method further includes the following steps:

[0091] S4: Obtain engine air-fuel ratio command;

[0092] S5: Adjust the opening of the main oxygen regulating valve C3 according to the engine mixture ratio command.

[0093] In this embodiment, the oxidizer flow rate entering the thrust chamber 1 can be adjusted by regulating the opening of the oxygen main regulating valve C3, thereby adjusting the engine mixture ratio to meet the overall mixture ratio adjustment requirements of the rocket.

[0094] In a preferred embodiment, step S5 includes:

[0095] S51: Obtain the fuel flow rate measured by the first flow meter E1 and the oxygen flow rate measured by the second flow meter E2;

[0096] S52: Calculates the ratio of oxygen flow rate to fuel flow rate, which is the current engine mixture ratio;

[0097] S53: Calculate the second deviation between the engine mixture ratio command and the current engine mixture ratio;

[0098] S54: Calculate the second opening change of the oxygen main control valve C3 based on the second deviation;

[0099] S55: Adjust the opening of the main oxygen control valve C3 according to the change in the second opening degree.

[0100] In this embodiment, the second opening change of the oxygen main regulating valve C3 is accurately calculated based on the second deviation between the engine mixture ratio command and the current engine mixture ratio, and the opening of the oxygen main regulating valve C3 is adjusted according to the second opening change, thereby achieving precise adjustment of the engine mixture ratio.

[0101] Based on the above embodiments, in a preferred embodiment, the control method further includes the following steps:

[0102] S6: Obtain the current temperature value detected by the temperature detection device;

[0103] S7: Calculate the third deviation between the current temperature value and the preset temperature value;

[0104] S8: Calculate the third opening change of oxygen auxiliary regulating valve C2 based on the third deviation;

[0105] S9: Adjust the opening of oxygen auxiliary regulating valve C2 according to the change in the third opening.

[0106] In this embodiment, when the detected current temperature value is too high, the opening of the oxygen auxiliary regulating valve C2 is reduced by adjusting the valve. When the detected current temperature value is too low, the opening of the oxygen auxiliary regulating valve C2 is increased by adjusting the valve. The gas temperature can be kept within the required range (800K-860K) by precisely adjusting the opening of the oxygen auxiliary regulating valve C2.

[0107] In a preferred embodiment, step S6 includes:

[0108] S61: Obtain the first temperature value detected by the first temperature sensor A1 and the second temperature value detected by the second temperature sensor A2, and calculate the current temperature value based on the first and second temperature values. By setting two temperature sensors on the gas main pipeline to detect the gas temperature, the accuracy of the detection can be ensured, and if one temperature sensor fails, the other temperature sensor can still accurately detect the gas temperature. Specifically, when both temperature sensors are working normally, the current temperature can be the average of the first and second temperature values. When one temperature sensor fails, the current temperature is the temperature value detected by the undamaged temperature sensor.

[0109] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. An open-type variable thrust rocket engine, characterized in that, include: The booster unit has an oxidizer outlet and a fuel outlet; The thrust chamber (1) has a first fuel inlet and a first oxidant inlet. The first fuel inlet and the fuel outlet are connected through a fuel main line. A fuel main valve (4) is provided on the fuel main line. The first oxidant inlet and the oxidant outlet are connected through an oxygen main line. An oxygen main valve (6) is provided on the oxygen main line. The gas generator (3) has a second fuel inlet, a second oxidant inlet and a gas outlet. The second fuel inlet is connected to the main fuel line through a fuel secondary line. A fuel secondary valve (5) is provided on the fuel secondary line. The second oxidant inlet is connected to the main oxygen line through an oxygen secondary line. An oxygen secondary valve (7) is provided on the oxygen secondary line. The gas outlet is connected to the drive inlet of the booster device through the main gas line, which is used to drive the booster device to rotate. The booster device is also connected to the main gas line through a gas diversion line. A gas regulating valve (C1) is provided on the gas diversion line. The gas generated by the gas generator (3) is suitable to enter the booster device through the gas diversion line and then be discharged. The booster device includes a turbine (2), an oxygen pump (8), and a fuel pump (9) arranged coaxially. The main oxygen line is connected to the oxygen pump (8), the main fuel line is connected to the fuel pump (9), the main gas line is connected to the drive inlet of the turbine (2), and the gas branch line is connected to the inside of the turbine (2). The thrust chamber (1) includes a main body and a cooling jacket disposed outside the main body. The main fuel line is connected to the inlet of the cooling jacket, and the outlet of the cooling jacket is connected to the first fuel inlet. An oxygen main regulating valve (C3) is provided downstream of the oxygen main valve (6) on the oxygen main line. Adjusting the opening of the oxygen main regulating valve (C3) can adjust the engine mixture ratio. A temperature detection device is installed on the main gas pipeline.

2. The open-type variable thrust rocket engine according to claim 1, characterized in that, The thrust chamber (1) is equipped with a pressure detection device, which is used to detect the pressure of the thrust chamber (1).

3. The open-type variable thrust rocket engine according to claim 2, characterized in that, The pressure detection device includes a first pressure sensor (B1) and a second pressure sensor (B2).

4. The open-type variable thrust rocket engine according to claim 1, characterized in that, The open-ended variable-thrust rocket engine also includes: A fuel inlet pipe is provided with a first flow meter (E1) at one end, which is adapted to be connected to a fuel source and the other end is connected to the fuel pump (9). The oxidant inlet pipe is adapted to be connected to an oxidant source at one end and to the oxygen pump (8) at the other end. A second flow meter (E2) is provided on the oxidant inlet pipe.

5. The open-type variable thrust rocket engine according to claim 1, characterized in that, An oxygen regulating valve (C2) is provided on the oxygen auxiliary line downstream of the oxygen auxiliary valve (7).

6. The open-type variable thrust rocket engine according to claim 5, characterized in that, The temperature detection device includes a first temperature sensor (A1) and a second temperature sensor (A2).

7. A rocket, characterized in that, The open variable thrust rocket engine includes any one of claims 1-6.

8. A control method for an open-type variable thrust rocket engine, characterized in that, The open variable thrust rocket engine applied to any one of claims 1-7 comprises: Obtain thrust command; The thrust is converted into the required pressure in the thrust chamber (1); Adjust the opening of the gas regulating valve (C1) according to the required pressure.

9. The control method according to claim 8, characterized in that, The adjustment of the opening degree of the gas regulating valve (C1) according to the required pressure includes: Obtain the current pressure of the thrust chamber (1); Calculate the first deviation between the required pressure and the current pressure; The first opening change of the gas regulating valve (C1) is calculated based on the first deviation. Adjust the opening of the gas regulating valve (C1) according to the first opening change.

10. The control method according to claim 9, characterized in that, The process of obtaining the current pressure of the thrust chamber (1) includes: The first pressure value detected by the first pressure sensor (B1) and the second pressure value detected by the second pressure sensor (B2) are obtained, and the current pressure is calculated based on the first pressure value and the second pressure value.

11. The control method according to claim 10, characterized in that, The control method further includes: Obtain the engine air-fuel ratio command; Adjust the opening of the main oxygen regulating valve (C3) according to the engine mixture ratio command.

12. The control method according to claim 11, characterized in that, The adjustment of the opening degree of the main oxygen regulating valve (C3) according to the engine mixture ratio command includes: Obtain the fuel flow rate measured by the first flow meter (E1) and the oxygen flow rate measured by the second flow meter (E2); Calculate the ratio of the oxygen flow rate to the fuel flow rate, where the ratio is the current engine air-fuel mixture ratio; Calculate the second deviation between the engine mixture ratio command and the current engine mixture ratio; The second opening change of the oxygen main control valve (C3) is calculated based on the second deviation. Adjust the opening of the main oxygen control valve (C3) according to the second opening change.

13. The control method according to claim 9, characterized in that, The control method further includes: Obtain the current temperature value detected by the temperature detection device; Calculate the third deviation between the current temperature value and the preset temperature value; The third opening change of the oxygen auxiliary regulating valve (C2) is calculated based on the third deviation. Adjust the opening of the oxygen auxiliary regulating valve (C2) according to the third opening change.

14. The control method according to claim 13, characterized in that, The current temperature value detected by the temperature detection device includes: The first temperature value detected by the first temperature sensor (A1) and the second temperature value detected by the second temperature sensor (A2) are obtained, and the current temperature value is calculated based on the first temperature value and the second temperature value.

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