阅读说明：本技术 基于液压双调系统的变推力常温液体推进剂火箭发动机 (Variable-thrust normal-temperature liquid propellant rocket engine based on hydraulic double-regulation system ) 是由 朱韶华 孟彤 刘红军 胡一凡 徐震 黄铎铎 黄希文 张静瑀 郭美含 安山 张峻铭 于 2020-09-16 设计创作，主要内容包括：本发明公开了基于液压双调系统的变推力常温液体推进剂火箭发动机,包括：底座,为一腔体结构,其后端用于与烧室轴向连接。针栓孔,轴向开设于底座的中轴线。针栓孔内设置有一第一滑动密封分割件,针栓孔的位于第一滑动密封分割件的后部为第一导流部。文氏管,轴向开设于底座上,为一前端开口,后端封闭的孔,其内设置有一第二滑动密封分割件。在文氏管内套设有文氏杆,与第二滑动密封分割件固定连接,文氏杆的前端连接有一动力机构,后端连接有一针头,该针头设置于第二导流部内。该基于液压双调系统的变推力常温液体推进剂火箭发动机采用一个电机实现了推力在大范围内可调,调节范围可达到1：10,且减轻了发动机的重量。(The invention discloses a variable thrust normal temperature liquid propellant rocket engine based on a hydraulic double-regulation system, which comprises: the base is of a cavity structure, and the rear end of the base is axially connected with the burning chamber. The pintle hole is axially arranged on the central axis of the base. The pintle hole is internally provided with a first sliding seal partition part, and the rear part of the pintle hole, which is positioned on the first sliding seal partition part, is a first flow guide part. The venturi is axially arranged on the base and is a hole with an opening at the front end and a closed rear end, and a second sliding sealing partition piece is arranged in the venturi. The venturi tube is internally sleeved with a venturi rod which is fixedly connected with the second sliding sealing partition piece, the front end of the venturi rod is connected with a power mechanism, the rear end of the venturi rod is connected with a needle head, and the needle head is arranged in the second flow guide part. This become thrust normal atmospheric temperature liquid propellant rocket engine based on hydraulic pressure bitonic system adopts a motor to realize that thrust is adjustable in a large scale, and the control range can reach 1: 10 and the weight of the engine is reduced.)

1. Variable thrust normal temperature liquid propellant rocket engine based on hydraulic pressure bitonic system, its characterized in that includes:

the base (1) is of a cavity structure, and the rear end of the base is axially connected with the combustion chamber (13);

the needle bolt hole (8) is axially arranged on the central axis of the base (1), and the rear end of the needle bolt hole is open and is a fuel outlet; a first sliding seal partition part (14) is arranged in the pintle hole (8), a first flow guide part (8-2) is arranged at the rear part of the pintle hole (8) positioned on the first sliding seal partition part (14), and the first flow guide part (8-2) is used for containing flow guide fuel;

the venturi (9) is axially arranged on the base (1) and is a hole with an open front end and a closed rear end, a second sliding sealing partition piece (15) is arranged in the venturi (9), a second flow guide part (9-2) is arranged at the rear part of the venturi (9) positioned on the second sliding sealing partition piece (15), and the second flow guide part (9-2) is connected with a fuel supply pipeline; the second flow guide part (9-2) is communicated with the first flow guide part (8-2), and fuel is guided into the first flow guide part (8-2) and is sprayed into the combustion chamber (13) from a fuel outlet;

a Venturi rod (4) is sleeved in the Venturi tube (9) and fixedly connected with the second sliding sealing dividing piece (15), the front end of the Venturi rod (4) is connected with a power mechanism, the rear end of the Venturi rod is connected with a needle head (4-1), and the needle head (4-1) is arranged in the second flow guide part (9-2);

the power mechanism is used for driving the Venturi rod (4) to move back and forth so as to change the size of a gap between the needle head (4-1) and the second flow guide part (9-2) and further adjust the flow of fuel passing through the gap.

2. The variable thrust normal temperature liquid propellant rocket engine based on hydraulic pressure bitonic system of claim 1, characterized in that a pintle shaft (6) is arranged in the pintle hole (8), a first fixed sealing element (16) is arranged between the pintle shaft (6) and the pintle hole (8), and the first sliding sealing element (14) is installed on the pintle shaft (6);

a cavity in the front of the first sliding seal partition (14) on the pin hole (8) is a first pressure regulating part (8-1), a pin head (5) with a spiral jet port is arranged at the rear end of the pin rod (6), and the pin head (5) and the end part of the first flow guide part (8-2) form a fuel injection port;

a cavity of the venturi (4) positioned at the front part of the second sliding seal dividing piece (15) is a second pressure regulating part (9-1), and a second fixed sealing piece (17) is annularly arranged between the front section of the venturi (4) and the second pressure regulating part (9-1);

a third sliding sealing piece (11) is installed in the first pressure regulating part (8-1), and the front and the back of an inner cavity of the first pressure regulating part (8-1) are respectively provided with a first hydraulic cavity (8-1-1) and a second hydraulic cavity (8-1-2) by the third sliding sealing piece (11);

a fourth sliding sealing piece (18) is arranged on the Venturi rod (4) and positioned in the second pressure regulating part (9-1), and the fourth sliding sealing piece (18) divides the second pressure regulating part (9-1) into a first injection cavity (9-1-1) and a second injection cavity (9-1-2) in front and at the back;

the first injection cavity (9-1-1) and the second injection cavity (9-1-2) are respectively and independently connected with an external hydraulic oil pipeline, and hydraulic oil is correspondingly led into or out of the first hydraulic cavity (8-1-1) and the second hydraulic cavity (8-1-2) through two pipeline channels which are arranged in parallel.

3. The variable thrust normal temperature liquid propellant rocket engine based on hydraulic pressure bitonic system of claim 2, characterized in that the second diversion part (9-2) of the venturi tube (9) is shaped as: the needle comprises a convergent section, a cylindrical section and an expansion section which are connected from front to back, wherein the needle head (4-1) penetrates through the convergent section, the cylindrical section and the expansion section.

4. The variable thrust normal temperature liquid propellant rocket engine based on hydraulic pressure double-adjusting system of claim 2 or 3, characterized in that the diameter of the first pressure adjusting part (8-1) is larger than the diameter of the first flow guiding part (8-2).

5. The variable thrust normal temperature liquid propellant rocket engine based on the hydraulic pressure bitonic system is characterized in that the back end of the base (1) is provided with an oxygen chamber (12) in a circumferential direction, and a plurality of oxygen injection ports are arranged on the bottom plate of the oxygen chamber (12) in a circumferential direction for injecting oxygen into the combustion chamber (13) to be mixed with fuel.

6. The working method of the variable thrust normal temperature liquid propellant rocket engine based on the hydraulic pressure double-regulation system is characterized by comprising the following steps:

the power mechanism drives the Venturi rod (4) to move forwards to drive the needle head (4-1) to move forwards, a gap between the needle head (4-1) and the end part of the convergence section is enlarged, the flow of fuel passing through the gap is further adjusted, and the flow of the fuel flowing into the first flow guide part (8-2) is increased; meanwhile, the volume in the first injection cavity (9-1-1) is reduced, hydraulic oil in the first injection cavity is introduced into the first hydraulic cavity (8-1-1), the pressure in the first hydraulic cavity (8-1-1) is increased, the third sliding sealing element (11) is pushed and pressed, the pintle rod (6) and the pintle head (5) are driven to move backwards, the fuel injection port is enlarged, and fuel with large flow is injected into a combustion chamber and mixed with oxygen injected into the combustion chamber (13);

the power mechanism drives the Venturi rod (4) to move backwards to drive the needle head (4-1) to move backwards, a gap between the needle head (4-1) and the end part of the convergence section is reduced, the flow of fuel passing through the gap is further adjusted, and the flow of the fuel flowing into the first flow guide part (8-2) is reduced; meanwhile, the volume of the second injection cavity (9-1-2) is reduced, hydraulic oil in the second injection cavity is introduced into the second hydraulic cavity (8-1-2), the third sliding sealing element (11) is pushed and pressed, the pintle rod (6) and the pintle head (5) are driven to move forwards, the fuel injection port is reduced, and fuel with small flow is injected into the combustion chamber (13) and mixed with oxygen injected into the combustion chamber (13).

[ technical field ] A method for producing a semiconductor device

The invention belongs to the technical field of variable thrust rocket engines, and particularly relates to a variable thrust normal temperature liquid propellant rocket engine based on a hydraulic double-regulation system.

[ background of the invention ]

The variable thrust rocket engine refers to a rocket engine with adjustable thrust. The engine can adjust the thrust of the rocket engine in a large range according to the flight mission or the design requirement of the rocket, such as vertical take-off or landing on the earth and take-off or landing on the moon or other stars, and the like, so as to reduce the overload requirement of the rocket in flight. The power device of the space transportation system adopts a variable thrust engine, and the optimal thrust control can be realized, so that the carrying capacity is maximized; the variable thrust engine is used for propelling during the active flight of manned space flight, so that the overload of an astronaut can be strictly controlled, and the flight safety of the astronaut is ensured; for rendezvous docking and orbital maneuvers of spacecraft, variable thrust engines may improve the flexibility of maneuvering control.

To achieve the variable thrust objective of rocket engines, flow regulation systems are required. The existing regulating system has a complex structure and low integration level.

[ summary of the invention ]

The invention aims to provide a variable-thrust normal-temperature liquid propellant rocket engine based on a hydraulic double-regulation system, wherein the thrust is adjustable in a large range by adopting a motor, and the adjusting range can reach 1: 10 and the weight of the engine is reduced.

The invention adopts the following technical scheme: a variable thrust normal temperature liquid propellant rocket engine based on a hydraulic double-regulation system, comprising:

the base is of a cavity structure, and the rear end of the base is axially connected with the combustion chamber.

The needle bolt hole is axially arranged on the central axis of the base, and the rear end of the needle bolt hole is provided with an opening and is a fuel outlet;

the pintle hole is internally provided with a first sliding seal partition part, the rear part of the pintle hole, which is positioned on the first sliding seal partition part, is provided with a first flow guide part, and the first flow guide part is used for containing flow guide fuel.

The venturi is axially arranged on the base and is a hole with an opening at the front end and a closed rear end, a second sliding sealing partition piece is arranged in the venturi, a second flow guide part is arranged at the rear part of the venturi, which is positioned on the second sliding sealing partition piece, and the second flow guide part is connected with a fuel supply pipeline; the second diversion part is communicated with the first diversion part, and introduces the fuel into the first diversion part and sprays the fuel into the combustion chamber from the fuel outlet.

The venturi tube is internally sleeved with a venturi rod which is fixedly connected with the second sliding sealing partition piece, the front end of the venturi rod is connected with a power mechanism, the rear end of the venturi rod is connected with a needle head, and the needle head is arranged in the second flow guide part.

The power mechanism is used for driving the Venturi rod to move back and forth so as to change the size of the gap between the needle head and the second flow guide part and further adjust the flow of the fuel passing through the gap.

Furthermore, a pintle rod is arranged in the pintle hole, a first fixed sealing element is arranged between the pintle rod and the pintle hole, and a first sliding sealing element is arranged on the pintle rod. The cavity of the pintle hole positioned in the front part of the first sliding seal partition piece is a first pressure regulating part, the rear end of the pintle rod is provided with a pintle head with a spiral jet orifice, and the pintle head and the end part of the first flow guide part form a fuel injection port.

The cavity of the venturi tube positioned at the front part of the second sliding seal partition piece is a second pressure regulating part, and a second fixed sealing piece is annularly arranged between the front section of the venturi tube and the second pressure regulating part.

And a third sliding sealing piece is arranged in the first pressure regulating part, and the front part and the rear part of the inner cavity of the first pressure regulating part are respectively a first hydraulic cavity and a second hydraulic cavity by the third sliding sealing piece. And a fourth sliding sealing piece is arranged on the Venturi rod and in the second pressure regulating part, and the fourth sliding sealing piece divides the second pressure regulating part into a first pressure injection cavity and a second pressure injection cavity in front and at the back.

The first injection cavity and the second injection cavity are respectively and independently connected with an external hydraulic oil pipeline, and hydraulic oil is correspondingly led into or out of the first hydraulic cavity and the second hydraulic cavity through two pipeline channels which are arranged in parallel.

Further, the shape of the second flow guiding part of the venturi tube is as follows: the needle head sequentially comprises a convergent section, a cylindrical section and an expansion section which are connected from front to back, wherein the needle head penetrates through the convergent section, the cylindrical section and the expansion section.

Further, the diameter of the first pressure regulating part is larger than that of the first flow guide part.

Furthermore, the rear end of the base is circumferentially provided with an oxygen chamber, and a plurality of oxygen injection ports are circumferentially arranged on a bottom plate of the oxygen chamber and used for injecting oxygen into the combustion chamber to be mixed with fuel.

The invention also discloses a working method of the variable thrust normal temperature liquid propellant rocket engine based on the hydraulic double-regulation system, which comprises the following steps:

the power mechanism drives the Venturi rod to move forwards to drive the needle head to move forwards, the gap between the needle head and the end part of the convergence section is enlarged, the flow of the fuel passing through the gap is further adjusted, and the flow of the fuel flowing into the first flow guide part is increased; meanwhile, the volume in the first injection pressure cavity is reduced, hydraulic oil in the first injection pressure cavity is introduced into the first hydraulic cavity, the pressure in the first hydraulic cavity is increased, the third sliding sealing piece is pushed and pressed to drive the pintle rod and the pintle head to move backwards, and the fuel injection port is enlarged, so that fuel with large flow is injected into the combustion chamber and mixed with oxygen injected into the combustion chamber;

the power mechanism drives the Venturi rod to move backwards to drive the needle head to move backwards, the gap between the needle head and the end part of the convergence section is reduced, the flow of the fuel passing through the gap is further adjusted, and the flow of the fuel flowing into the first flow guide part is reduced; meanwhile, the volume of the second injection cavity is reduced, hydraulic oil in the second injection cavity is led into the second hydraulic cavity, the third sliding sealing element is pushed and pressed, the pintle rod and the pintle head are driven to move forwards, and the fuel injection port is reduced, so that small-flow fuel is injected into the combustion chamber and is mixed with oxygen injected into the combustion chamber.

The invention has the beneficial effects that: 1. a set of power device is used for simultaneously driving two devices of flow regulation and injection regulation, so that the space required by the system work and the weight of an engine are reduced. 2. Through the through flow of filling liquid, realize the regulation to the pintle pole to adjust the spouting atomizing effect of fuel, can accurate control flow.

[ description of the drawings ]

FIG. 1 is a schematic structural view of a base;

FIG. 2 is a schematic structural diagram of a variable thrust normal temperature liquid propellant rocket engine based on a hydraulic double-regulation system;

wherein: 1. a base; 2. a plug; 3. blocking the cover; 4. a venturi rod; 4-1. a needle head; 5. a pintle head; 6. a pintle rod 8, a pintle hole; 8-1, a first pressure regulating part; 8-1-1. a first hydraulic chamber; 8-1-2. a second hydraulic chamber; 8-2, a first flow guide part; 9. a venturi; 9-1, a second pressure regulating part; 9-2. a second diversion part; 9-1-1. a first injection cavity; 9-1-2. a second injection cavity; 10. a fuel injection port; 11. a third sliding seal; 12. an oxygen chamber; 13. a combustion chamber; 14. a first sliding seal partition; 15. a second sliding seal partition; 16. a first stationary seal; 17. a second stationary seal; 18. a fourth sliding seal.

[ detailed description ] embodiments

The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

The invention discloses a variable thrust normal temperature liquid propellant rocket engine based on a hydraulic double-regulation system, wherein kerosene is selected as fuel.

One embodiment is as follows: as shown in fig. 1 and 2, the combustion chamber comprises a base 1 which is a cavity structure, and the rear end of the base is used for being axially connected with a combustion chamber 13; the pintle hole 8 is axially arranged on the central axis of the base 1, and the rear end of the pintle hole is open and is a fuel outlet. A first sliding seal partition part 14 is arranged in the needle bolt hole 8, a first flow guide part 8-2 is arranged at the rear part of the needle bolt hole 8, which is positioned on the first sliding seal partition part 14, and the first flow guide part 8-2 is used for containing flow guide fuel.

The venturi 9 is axially arranged on the base 1, is a hole with an opening at the front end and a closed rear end, is internally provided with a second sliding sealing partition member 15, the rear part of the venturi 9, which is positioned on the second sliding sealing partition member 15, is provided with a second flow guide part 9-2, and the second flow guide part 9-2 is connected with an external fuel pipeline.

The venturi tube 9 is internally sleeved with a venturi rod 4 which is fixedly connected with the second sliding seal partition 15, the front end of the venturi rod 4 is connected with a power mechanism, the rear end of the venturi rod 4 is connected with a needle 4-1, and the needle 4-1 is arranged in the second flow guide part 9-2. The power mechanism is used for driving the Venturi rod 4 to move back and forth so as to change the size of the gap between the needle head 4-1 and the second flow guide part 9-2 and further adjust the flow of the fuel passing through the gap. The second flow guiding part 9-2 is connected with a fuel supply pipeline, a fuel injection port 10 is radially arranged on the side wall of the second flow guiding part 9-2 and is connected with an external fuel supply device pipeline through the fuel injection port 10, the second flow guiding part 9-2 is communicated with the first flow guiding part 8-2, fuel is guided into the first flow guiding part 8-2 and is sprayed into the combustion chamber 13 through a fuel outlet.

The venturi tube 9 is internally sleeved with a venturi rod 4 which is fixedly connected with the second sliding seal partition 15, the front end of the venturi rod 4 is connected with a power mechanism, the rear end of the venturi rod 4 is connected with a needle 4-1, and the needle 4-1 is arranged in the second flow guide part 9-2. The power mechanism is used for driving the Venturi rod 4 to move back and forth so as to change the size of the gap between the needle head 4-1 and the second flow guide part 9-2 and further adjust the flow of the fuel passing through the gap.

In this embodiment, the power mechanism is used to drive the venturi rod 4 to move back and forth to drive the needle 4-1 to move back and forth, and the venturi rod is matched with the power mechanism to control the fuel flow. The venturi 9 is a multi-step hole structure, the diameters of the venturi 9 are sequentially reduced from front to back, and the venturi rod 4 is sleeved in the venturi 9, so that the shape of the venturi rod 4 is required to be consistent with the shape of the venturi 9. The second flow guide 9-2 of the venturi 9 has the shape: the needle head 4-1 penetrates through the convergence section, the cylindrical section and the expansion section. And the needle 4-1 is a cone with a big front end and a big back end. When the needle 4-1 moves back and forth, the size of the gap between the needle and the rear end of the convergent section changes, so that the flow of the fuel passing through the gap is adjusted, the flow of the fuel flowing into the first guide part 8-2 is changed, and the flow of the fuel injected into the combustion chamber 13 is also changed. The power mechanism adopts a motor and is connected with the front end of the Venturi rod 4 through threads. When the venturi tube does not work, the motor is detached from the venturi rod 4, and the plug cover 3 covers the opening at the front end of the venturi tube 9.

When fuel is injected into the combustion chamber 13, oxygen is also injected into the combustion chamber 13 to be mixed with the fuel for combustion, and the oxygen is injected from the oxygen cavity 12 in the following specific arrangement mode: an oxygen cavity 12 is formed in the back end of the base 1 in a circumferential mode, a plurality of oxygen injection ports are formed in the bottom plate of the oxygen cavity 12 in a circumferential mode and used for injecting oxygen into the combustion chamber 13, mixing with fuel and combusting in the combustion chamber 13, and due to the fact that the injection amount of the fuel is adjusted and the injection amount of the oxygen can also be adjusted, the thrust generated after the fuel is combusted is different.

When the fuel injection device works, fuel is injected into the second flow guide part 9-2 through the fuel injection port 10, flows from front to back through a gap between the needle 4-1 and the convergent section of the second flow guide part 9-2, and flows into the first flow guide part 8-2. When the power mechanism drives the venturi rod 4 to move forward, namely the venturi rod 4 moves from back to front in the venturi 4, and the needle 4-1 moves backward, the gap between the needle 4-1 and the convergent section of the second flow guide part is enlarged, and simultaneously the fuel supply amount of the fuel supply device is increased, passes through the large gap and is guided into the first flow guide part 8-2. When the power mechanism drives the venturi rod 4 to move backwards, the gap is reduced, and the small-flow fuel passes through the gap and is guided into the first flow guide part 8-2, which is opposite to the process.

Another embodiment is as follows, and in the structure of the previous embodiment, the following is further provided: a pintle rod 6 is arranged in the pintle hole 8, a first fixed sealing element 16 is arranged between the pintle rod 6 and the pintle hole 8, and a first sliding sealing element 14 is arranged on the pintle rod 6; the first fixed sealing element 16 is sleeved at the front end of the pintle rod 6 to realize the sealing of the front end of the first pressure regulating part 8-1.

The cavity of the pintle hole 8 positioned at the front part of the first sliding sealing partition 14 is a first pressure regulating part 8-1, the rear end of the pintle rod 6 is provided with a pintle head 5 with a spiral jet port, and the pintle head 5 and the end part of the first flow guide part 8-2 form a fuel injection port;

the cavity of the venturi 4 positioned at the front part of the second sliding seal partition 15 is a second pressure regulating part 9-1, and a second fixed sealing part 17 is annularly arranged between the front section of the venturi rod 4 and the second pressure regulating part 9-1;

a third sliding sealing piece 11 is arranged in the first pressure regulating part 8-1, and the front and the back of the inner cavity of the first pressure regulating part 8-1 are respectively a first hydraulic cavity 8-1-1 and a second hydraulic cavity 8-1-2 by the third sliding sealing piece 11;

a fourth sliding sealing element 18 is arranged on the Venturi rod 4 and in the second pressure regulating part 9-1, and the fourth sliding sealing element 18 divides the second pressure regulating part 9-1 into a first injection cavity 9-1-1 and a second injection cavity 9-1-2 in front and back;

the first injection cavity 9-1-1 and the second injection cavity 9-1-2 are respectively and independently connected with an external hydraulic oil pipeline, and hydraulic oil is correspondingly led into or out of the first hydraulic cavity 8-1-1 and the second hydraulic cavity 8-1-2 through two pipeline channels which are arranged in parallel.

The upper fourth sliding seal 18 may be a sealing ring which is in close contact with the inner wall of the venturi 9 to provide a seal. Other components that perform the sealing function may also be used.

The side walls of the first injection cavity 9-1-1 and the second injection cavity 9-1-2 are respectively provided with a hydraulic oil injection port, before use, hydraulic oil is injected into the first injection cavity 9-1-1 and the second injection cavity 9-1-2, and then is guided into the first hydraulic cavity 8-1-1 and the second hydraulic cavity 8-1-2 by the first injection cavity 9-1-1 and the second injection cavity 9-1-2 respectively. Then, each hydraulic oil injection opening is blocked by a plug 2.

When the power mechanism drives the Venturi rod 4 to move forwards and drives the needle 4-1 to move forwards, the gap between the needle 4-1 and the end part of the convergence section is enlarged, so that the flow of the fuel passing through the gap is adjusted, and the flow of the fuel flowing into the first flow guide part 8-2 is increased; meanwhile, the volume of the first injection cavity 9-1-1 is reduced, hydraulic oil in the first injection cavity is introduced into the first hydraulic cavity 8-1-1, the pressure in the first hydraulic cavity 8-1-1 is increased, the third sliding sealing piece 11 is pushed and pressed, the needle bolt rod 6 and the needle bolt head 5 are driven to move backwards, a fuel injection port is enlarged, and fuel with large flow is injected into the combustion chamber and mixed with oxygen injected into the combustion chamber 13.

When the power mechanism drives the Venturi rod 4 to move backwards and drives the needle head 4-1 to move backwards, the gap between the needle head 4-1 and the end part of the convergence section is reduced, so that the flow of the fuel passing through the gap is adjusted, and the flow of the fuel flowing into the first flow guide part 8-2 is reduced; meanwhile, the volume of the second injection cavity 9-1-2 is reduced, hydraulic oil in the second injection cavity is introduced into the second hydraulic cavity 8-1-2, the third sliding sealing piece 11 is pushed and pressed, the pintle rod 6 and the pintle head 5 are driven to move forwards, a fuel injection port is reduced, and small-flow fuel is injected into the combustion chamber 13 and is mixed with oxygen injected into the combustion chamber 13.

To verify the effect of the use of the combustion chamber in the present invention, the following simulation was performed. Aiming at the scheme of a variable thrust liquid propellant rocket engine thrust chamber with the total propellant flow within the variation range of 0.15 kg/s-1.5 kg/s, ground state simulation experiments are carried out under two working conditions of minimum flow, maximum flow and the like so as to verify the wide-range working capacity of the engine, and the numerical simulation result is as follows:

when the kerosene flow rate is as follows: 50g/s, oxygen flow: at 100g/s, the simulation test obtains: combustion chamber pressure: 0.67 MPa; ground thrust of the transmitter: 271N; combustion efficiency: 98 percent;

when the kerosene flow rate is as follows: 500g/s, oxygen flow: 1000g/s, the simulation test obtains:

combustion chamber pressure: 6.17 MPa; ground thrust of the transmitter: 2464N, combustion efficiency: 99 percent.

According to the simulation data, the pressure of the ground rocket thrust chamber under the low-flow condition is 0.67MPa, and the ground thrust is 271N; the pressure of the ground rocket thrust chamber under the condition of large flow is 6.17MPa, and the ground thrust is 2464N. Therefore, the engine can realize high-efficiency stable combustion under the condition of ten times of flow rate transformation ratio, and the thrust change can reach 9.1 times.