Double-thrust-chamber pump rear swing liquid rocket engine

Abstract

The invention discloses a double-thrust-chamber pump rear-swinging liquid rocket engine, relates to the technical field of rocket engines, and provides a technical scheme capable of effectively making up for the defects of a traditional single-turbine pump and single-thrust-chamber structural layout in a high-thrust or heavy-duty liquid rocket engine. The invention discloses a double-thrust-chamber pump rear swing liquid rocket engine which comprises a rack, two fuel gas swing devices, two thrust chambers and a fuel gas assembly. The fuel gas assembly communicates with the corresponding thrust chambers through the two gas swing devices and is used for providing fuel for the two thrust chambers correspondingly. The first ends of the two fuel gas swing devices are fixedly arranged on the two sides of the rack correspondingly, the second ends of the two fuel gas swing devices are fixedly connected with the corresponding thrust chambers correspondingly, and the two fuel gas swing devices and the two thrust chambers are symmetrically distributed along the center line of the rack. The fuel gas assembly is fixedly arranged in the middle area of the rack.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket engine, and particularly relates to a double-thrust-chamber pump-afterburning liquid rocket engine. BACKGROUND

[0002] At present, the existing pump pressure type liquid rocket engine adopts a single turbine pump and a single thrust chamber structure layout mode. The liquid rocket engine with the structure has the advantages of small outer envelope size and convenient parallel combination use. However, the single turbine pump and single thrust chamber structure mode of the liquid rocket engine is not suitable for a large-thrust liquid rocket engine. With the increase of the thrust, the design and production difficulty of the thrust chamber will be significantly increased, the engine swing envelope is increased, the design and production difficulty of the swing mechanism is greatly increased, and the liquid rocket engine with the single thrust chamber layout cannot realize the roll attitude control requirement of the rocket when used alone, and a roll control power device needs to be added, which increases the system complexity of the carrier rocket. SUMMARY

[0003] The present application aims to provide a double-thrust-chamber pump-afterburning liquid rocket engine, so as to provide a technical solution which can effectively make up for the deficiency of the traditional single turbine pump and single thrust chamber structure layout in a large-thrust or heavy liquid rocket engine.

[0004] In a first aspect, the present application provides a double-thrust-chamber pump-afterburning liquid rocket engine, which comprises a rack, two gas swing devices, two thrust chambers and a fuel gas assembly. The fuel gas assembly is communicated with the corresponding thrust chamber through the two gas swing devices, and is used for providing fuel to the two thrust chambers respectively.

[0005] The first end of the two gas swing devices is fixedly arranged on the two sides of the rack respectively, and the second end is fixedly connected with the corresponding thrust chamber. The two gas swing devices and the two thrust chambers are symmetrically distributed along the center line of the rack, and the fuel gas assembly is fixedly arranged in the middle region of the rack.

[0006] In the technical scheme, the double-thrust chamber pump post-swing liquid rocket engine comprises a frame, two gas swing devices, two thrust chambers and a fuel gas assembly, wherein the first ends of the two gas swing devices are fixedly arranged on the two sides of the frame, the second ends are fixedly connected with the corresponding thrust chambers, the two gas swing devices and the two thrust chambers are symmetrically distributed along the center line of the frame, and the fuel gas assembly is fixedly arranged in the middle region of the frame. Based on this, the two thrust chambers can be docked with the frame through the gas swing devices to transmit the generated thrust to the frame through the gas swing devices, the two gas swing devices are symmetrically distributed along the center line of the frame, and the fuel gas assembly is fixedly arranged in the middle region of the frame, so that the overall mass eccentricity of the engine can be reduced.

[0007] It should be understood that for a large-thrust or heavy liquid rocket engine, a double-thrust chamber engine structure layout scheme is more suitable, which can effectively reduce the design and production difficulty of the thrust chamber and the swing mechanism, is more conducive to reducing the swing torque, improving the thrust-to-weight ratio of the engine, and the launch vehicle with a single double-thrust chamber or multi-thrust chamber engine has the functions of pitch, yaw and roll control. Therefore, the layout of the double-thrust chamber and the two gas swing devices in the double-thrust chamber pump post-swing liquid rocket engine can realize the function of independent swing of the two thrust chambers, so that the engine can have a complete set of vector adjustment and control capability to generate pitch, yaw and roll control of the rocket body.

[0008] Finally, in the double-thrust chamber pump post-swing liquid rocket engine, only two thrust chambers participate in swing, so that the thrust level of the thrust chamber can be greatly reduced, and the thrust chamber envelope size is also reduced, based on which the swing envelope of the entire double-thrust chamber pump post-swing liquid rocket engine will be greatly reduced, so it has the advantage of flexible internal layout of the rocket body, which is conducive to improving the surface thrust of the rocket.

[0009] Further, the double-thrust chamber pump post-swing liquid rocket engine further comprises two docking modules, each of which is used for fixing the corresponding gas swing device to the docking plane of the frame, and the lower end surface of each gas swing device is fixedly connected with the corresponding thrust chamber through an outlet flange.

[0010] Further, the fuel gas assembly comprises a main turbine pump and a gas generator, the gas generator is fixedly connected with the main turbine pump and in communication with the main turbine pump, and the main turbine pump is fixedly connected with the gas inlets of the two gas swing devices and in communication with the gas inlets of the two gas swing devices.

[0011] Further, the fuel gas assembly further comprises a gas duct, the gas duct has one inlet and two outlets, the inlet of the gas duct is communicated with the main turbine pump, and the two outlets of the gas duct are communicated with the two gas swing devices respectively.

[0012] Further, the end face of the inlet of the gas duct is parallel to the end faces of the two outlets of the gas duct, the two outlet pipes of the gas duct are symmetrically distributed along the center line of the gas duct, and the included angle between the two outlet pipes of the gas duct is obtuse.

[0013] Further, the center line of the turbine pump is parallel to the center lines of the two thrust chambers, and the line of sight of the top view projection of the center of the turbine pump and the centers of the two thrust chambers forms an isosceles triangle.

[0014] Further, the gas generator is fixedly connected with the main turbine pump through a flange, and by adjusting the circumferential angle of the flange, the center line of the gas generator is perpendicular to the first plane in which the center line of the main turbine pump is located and the second plane in which the center lines of the two thrust chambers are located, and the two thrust chambers and the two gas swing devices are mirror symmetric with respect to the first plane.

[0015] Further, the fuel gas assembly further comprises a fuel throttle valve and a thrust chamber fuel supply pipeline, the fuel throttle valve is installed at the fuel pump outlet of the main turbine pump, and the thrust chamber fuel supply pipeline is fixed at the outlet of the fuel throttle valve; the thrust chamber fuel supply pipeline has two mirror-symmetric outlet conduits, and the two outlet conduits are respectively connected with the fuel inlets of the two thrust chambers.

[0016] Further, the fuel gas assembly further comprises four fuel swing devices, two fuel swing devices are arranged on each of the outlet conduits, the fuel swing devices are used to provide angle and displacement compensation for the thrust chamber fuel supply pipeline during the swinging of the thrust chambers, and the swinging centers of the four fuel swing devices are located in the same horizontal plane as the swinging centers of the two gas swing devices.

[0017] Further, the fuel gas assembly further comprises an oxidant inlet pipe and a fuel inlet pipe, the oxidant inlet pipe and the fuel inlet pipe are communicated with the gas generator, the oxidant inlet pipe and the fuel inlet pipe are located on the same side of the plane in which the center lines of the two thrust chambers are located, and the angles of the bent pipe sections of the oxidant inlet pipe and the fuel inlet pipe are adjustable. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings: Figure 1 A front view of the overall structure of a double-thrust-chamber pump after-swing liquid rocket engine according to an embodiment of the present application is provided; Figure 2 A front view of the overall structure of a double-thrust-chamber pump after-swing liquid rocket engine according to an embodiment of the present application is provided; Figure 3 A front view of the overall structure of a double-thrust-chamber pump after-swing liquid rocket engine according to an embodiment of the present application is provided;

[0019] In the figure: 1 - frame, 2 - gas swing device, 3 - thrust chamber fuel supply pipeline, 4 - oxidizer inlet pipe, 5 - fuel throttle valve, 6 - thrust chamber, 7 - fuel swing device, 8 - gas guide pipe, 9 - main turbine pump, 10 - fuel inlet pipe, 11 - gas generator, 12 - upper end of the gas swing device, 13 - lower end of the gas swing device, 14 - gas swing device inlet. DETAILED DESCRIPTION

[0020] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It is to be understood, however, that the description is merely exemplary of the present disclosure, but not intended to limit the scope of the present disclosure. Also, in the following description, description of well-known functions and constructions will be omitted so as not to obscure the concept of the present disclosure with unnecessary detail.

[0021] Further, the terms "first" and "second" are used only for the purpose of description and are not to be construed as indicating or implying relative importance or an indicated number of features. Thus, features defined with "first" and "second" can include one or more of the features explicitly or implicitly. In the description of the present application, the meaning of "plurality" is two or more, unless specifically limited otherwise. The meaning of "several" is one or more, unless specifically limited otherwise.

[0022] At present, the existing pump pressure type liquid rocket engine adopts a single turbine pump and single thrust chamber structure layout mode. The liquid rocket engine of this structure has the advantages of small external envelope size and convenient parallel combination use. However, the single turbine pump and single thrust chamber structure of the liquid rocket engine is not suitable for large-thrust liquid rocket engines. As the thrust increases, the design and production difficulty of the thrust chamber will significantly increase, the swing envelope of the engine will increase, the design and production difficulty of the swing mechanism will greatly increase, and the liquid rocket engine with single thrust chamber layout cannot realize the roll attitude control requirement of the rocket when used alone, and a roll control power device needs to be added, which increases the system complexity of the launch vehicle.

[0023] Based on this, referring to Figures 1 to 3 The embodiment of the present application provides a double-thrust-chamber 6 pump after swing liquid rocket engine, which comprises a rack, two gas swing devices 2, two thrust chambers 6 and a fuel gas assembly; the fuel gas assembly is communicated with the corresponding thrust chamber 6 through the two gas swing devices 2 respectively, and is used for providing fuel to the two thrust chambers 6 respectively. The thrust chamber 6 burns the fuel to generate thrust, and the thrust is transmitted to the rack through the gas swing device 2.

[0024] In actual installation, the first ends of the two gas swing devices 2 are fixedly arranged on the two sides of the rack respectively, the second ends are fixedly connected with the corresponding thrust chambers 6 respectively, and the two gas swing devices 2 and the two thrust chambers 6 are symmetrically distributed along the center line of the rack, and the fuel gas assembly is fixedly arranged in the middle region of the rack. Based on the above structure, that is, the first end of each gas swing device 2 is fixed with one side of the rack, and the two gas swing devices 2 are fixed on the opposite sides of the rack to play a balancing role. Each thrust chamber 6 is fixedly connected at the second end of the corresponding gas swing device 2, and specifically, the thrust chamber 6 can be fixedly connected with the second end of the corresponding gas swing device 2 through a flange.

[0025] Based on this, the two thrust chambers 6 in the embodiment of the present application can be respectively connected with the rack through the gas swing device 2 to transmit the generated thrust to the rack through the gas swing device 2, at this time, the gas swing device 2 is used as a force transmission mechanism. And the two gas swing devices 2 and the two thrust chambers 6 in the embodiment of the present application are symmetrically distributed along the center line of the rack, and the fuel gas assembly is fixedly arranged in the middle region of the rack, so that the symmetrical distribution structure can reduce the overall mass eccentricity of the engine.

[0026] In actual use, for a large-thrust or heavy liquid rocket engine, a double-thrust-chamber 6 engine structure layout scheme is more suitable, which can not only realize large thrust but also effectively reduce the design and production difficulty of the thrust chamber 6 and the swing mechanism, is more conducive to reducing the swing torque, improving the thrust-to-weight ratio of the engine, and the launch vehicle assembled with a single double-thrust-chamber 6 or multi-thrust-chamber 6 engine has the functions of pitch, yaw and roll control. Based on the above description, and each thrust chamber 6 in the double-thrust-chamber 6 pump after swing liquid rocket engine provided by the embodiment of the present application is connected with a gas swing device 2, so that the layout mode of the thrust chamber 6 and the gas swing device 2 can realize the function of independent swing of the two thrust chambers 6, and therefore the single engine can have a complete set of vector adjustment and control capability to make the rocket body produce pitch, yaw and roll control.

[0027] Finally, the two-pulse chamber 6 pump post-swing liquid rocket engine provided by the embodiment of the present application only involves two pulse chambers 6 in swinging, thus the thrust level of the pulse chamber 6 can be greatly reduced, and the envelope size of the pulse chamber 6 is also reduced, and on this basis, the swing envelope of the entire two-pulse chamber 6 pump post-swing liquid rocket engine will be greatly reduced, so it has the advantage of flexible internal layout of the rocket body, which is beneficial to improve the surface thrust of the rocket.

[0028] In an example, the two-pulse chamber 6 pump post-swing liquid rocket engine further comprises two docking modules, each of which is used to fix the corresponding gas swing device 2 on the docking plane of the rack, and the lower end surface of each gas swing device 2 is fixedly connected with the corresponding pulse chamber 6 through an outlet flange. Wherein, the docking module can be any fixing structure that can fix the gas swing device 2 to the rack, and the embodiment of the present application does not limit this.

[0029] Further, the fuel gas assembly in the embodiment of the present application is used to provide oxidant and fuel to the pulse chamber 6. The fuel gas assembly comprises a main turbine pump 9 and a gas generator 11, the gas generator 11 is fixed and communicated with the main turbine pump 9; the main turbine pump 9 is fixed and communicated with the gas inlet of the two gas swing devices 2 respectively. It is worth noting that in practice, the gas generator 11 can be fixed on the turbine shell of the main turbine pump 9 by welding, and when the main turbine pump 9 is installed, the plane where the center line of the gas generator 11-main turbine pump 9 is located and the plane where the center line of the two pulse chambers 6 are located can be perpendicular to each other by adjusting the flange circumferential angle, so as to further eccentric the overall mass of the two-pulse chamber 6 pump post-swing liquid rocket engine.

[0030] The fuel gas assembly further comprises a gas conduit 8, the gas conduit 8 has one inlet and two outlets, the inlet of the gas conduit 8 is communicated with the main turbine pump 9, and the two outlets of the gas conduit 8 are communicated with the two gas swing devices 2 respectively.

[0031] In practice, the two outlets of the gas conduit 8 are respectively welded and communicated with the gas inlets of the two gas swing devices 2, the inlet of the gas conduit 8 is connected with the main turbine pump 9 through a flange, and is communicated with the main turbine pump 9. Further, the end surface of the inlet of the gas conduit 8 is parallel to the end surfaces of the two outlets of the gas conduit 8, the two outlet pipes of the gas conduit 8 are symmetrically distributed along the center line of the gas conduit 8, and the included angle between the two outlet pipes of the gas conduit 8 is obtuse. Since the end surfaces of the inlet and outlet of the gas conduit 8 are parallel to each other, and the two outlet branch pipe structures are symmetrically distributed and obtuse, the center lines of the main turbine pump 9 and the two thrust chambers 6 are parallel to each other, and the overhead projection of the three centers is an isosceles triangle. Based on the above description, the gas conduit 8, the main turbine pump 9 and the two thrust chambers 6 are symmetrically distributed as a whole, which can reduce the overall mass eccentricity of the engine to a certain extent.

[0032] The gas generator 11 is fixedly connected with the main turbine pump 9 through a flange, and the center line of the gas generator 11 is perpendicular to the first plane in which the center lines of the main turbine pump 9 and the two thrust chambers 6 are located, and the second plane in which the center lines of the two thrust chambers 6 are located, and the two thrust chambers 6 and the two gas swing devices 2 are mirror-symmetrically arranged with respect to the first plane. Based on this, the two thrust chambers 6 and the two gas swing devices 2 are symmetrically distributed on both sides of the gas generator 11 and the main turbine pump 9, so as to improve the stability of the engine and reduce the mass eccentricity of the engine.

[0033] In some embodiments, the fuel gas assembly further comprises a fuel throttle valve 5 and a thrust chamber fuel supply pipeline 3; the fuel throttle valve 5 is installed at the fuel pump outlet of the main turbine pump 9, and the thrust chamber fuel supply pipeline 3 is fixed at the outlet of the fuel throttle valve 5; the thrust chamber fuel supply pipeline 3 has two mirror-symmetric outlet conduits, and the two outlet conduits are respectively connected with the fuel inlets of the two thrust chambers 6.

[0034] The above-mentioned gas throttle valve is used to adjust the flow of fuel at the fuel pump outlet of the main turbine pump 9, the thrust chamber fuel supply pipeline 3 has two mirror-symmetric outlet conduits, and the two outlet conduits are respectively connected with the fuel inlets of the two thrust chambers 6, so as to respectively supply fuel to the corresponding thrust chambers 6. Since the thrust chamber fuel supply pipeline 3 has two mirror-symmetric outlet conduits, the stability of the engine can be further improved.

[0035] Further, the fuel-gas assembly further comprises four fuel rocking devices 7, two of which are arranged on each of the outlet conduits, and the four fuel rocking devices 7 are used to provide angle and displacement compensation for the thrust chamber fuel supply pipeline 3 during rocking of the thrust chamber 6, and the rocking centers of the four fuel rocking devices 7 are located in the same horizontal plane as the rocking centers of the two gas rocking devices 2.

[0036] The two fuel rocking devices 7 arranged on the outlet conduits are used to ensure that the components upstream of the thrust chamber fuel supply pipeline 3 are fixed, so as to minimize the displacement of the fuel rocking devices 7 during rocking deformation, so that the engine alone has the complete vector adjustment and control capability for generating pitch, yaw and roll control of the rocket body. And the rocking centers of the four fuel rocking devices 7 are located in the same horizontal plane as the rocking centers of the two gas rocking devices 2.

[0037] In the embodiment of the present application, the fuel-gas assembly further comprises an oxidant inlet pipe 4 and a fuel inlet pipe, which are in communication with the gas generator 11, and the oxidant inlet pipe 4 and the fuel inlet pipe are located on the same side of the plane in which the center lines of the two thrust chambers 6 are located, and the angles of the elbow sections of the oxidant inlet pipe 4 and the fuel inlet pipe are adjustable. Based on this, the angles of the elbow sections of the oxidant inlet pipe 4 and the fuel inlet pipe can be adjusted to adapt to different rocket body propellant delivery pipe layouts, especially for the external propellant delivery pipe layout of multiple engine parallel engines.

[0038] In a specific example, as shown in Figure 1 、 Figure 2 , a double-thrust chamber pump-afterburning liquid rocket engine mainly comprises a frame 1, a gas rocking device 2, a thrust chamber fuel supply pipeline 3, an oxidant inlet pipe 4, a fuel throttle valve 5, a thrust chamber 6, a fuel rocking device 7, a gas conduit 8, a main turbine pump 9, a fuel inlet pipe 10 and a gas generator 11.

[0039] As shown in Figure 3 , the gas rocking device 2 has a gas rocking device upper end abutting surface 12 and a gas rocking device lower end abutting surface 13, a gas rocking device inlet 14 is fixed by welding with a gas pipeline, and the gas rocking device lower end abutting surface 13 is fixed with the thrust chamber 6 through flange connection.

[0040] As shown in Figure 1 、 Figure 2As shown, the whole frame 1 is detachable with the engine, the frame and the engine are connected by two docking modules, each docking module is connected with the upper end docking surface 12 of the gas swing device, so that one frame 1 can install two gas swing devices 2, the outlet flange of the gas swing device 2 is fixed with a thrust chamber 6, the thrust generated by the thrust chamber 6 is transmitted to the frame 1 through the force transmission structure of the gas swing device 2, and then the frame transmits the thrust to the rocket body. Another function of the gas swing device 2 is to provide angle and displacement compensation for the gas supply pipeline during the swinging of the thrust chamber 6, so as to ensure that the components upstream of the gas swing device inlet 14 are in a fixed state.

[0041] As shown in Figure 1 , Figure 2 , the gas guide pipe 8 has one inlet and two outlets, the two outlets are welded with the two gas swing device inlets respectively, the inlet of the gas guide pipe 8 is connected with the main turbine pump 9 through a flange, since the end faces of the inlet and outlet of the gas guide pipe 8 are parallel to each other, and the two outlet branch pipe structures are symmetrical and distributed at an obtuse angle, therefore, the center lines of the main turbine pump 9 and the two thrust chambers 6 are parallel to each other, and the projection of the three centers on the top surface is an isosceles triangle. The gas generator 11 is welded and fixed on the turbine housing of the main turbine pump 9, when the main turbine pump 9 is installed, the center line of the gas generator 11-main turbine pump 9 is adjusted to be perpendicular to the center line of the two thrust chambers 6 by adjusting the circumferential angle of the flange, and the two thrust chambers 6 and the components fixed on the thrust chamber are in a mirror image symmetry with respect to the center line of the gas generator 11-main turbine pump 9. Such assembly mode makes the gas generator 11 and the main turbine pump 9 be arranged on both sides of the center line plane of the thrust chamber, so as to realize more balanced mass distribution and reduce the mass eccentricity of the engine.

[0042] As shown in Figure 1 , Figure 2 , the fuel pump outlet of the main turbine pump 9 is provided with a fuel throttle valve 5, the outlet of the fuel throttle valve 5 is fixed with a thrust chamber fuel supply pipeline 3, the thrust chamber fuel supply pipeline 3 has two outlet conduits which are mirror image symmetrical, the conduits are connected with the fuel inlets of the thrust chambers 6 respectively, and each outlet conduit of the thrust chamber fuel supply pipeline 3 is provided with two fuel swing devices 7. The fuel swing devices 7 provide angle and displacement compensation for the thrust chamber fuel supply pipeline 3 during the swinging of the thrust chamber 6, so as to ensure that the components upstream of the thrust chamber fuel supply pipeline 3 are in a fixed state. In order to minimize the displacement amount generated by the fuel swing devices 7 during the swinging deformation, the swinging centers of the four fuel swing devices 7 are in the same horizontal plane with the swinging centers of the two gas swing devices 2.

[0043] As shown in Figure 1 , Figure 2 Figure 1 Figure 2As shown, the oxidizer inlet pipe 4 and the fuel inlet pipe 10 are located on the same side of the thrust chamber centerline plane, and the angle of the elbow sections of the oxidizer inlet pipe 4 and the fuel inlet pipe 10 can be adjusted to adapt to different rocket body propellant delivery pipe routing layouts, and in particular, have good adaptability to the external propellant delivery pipe routing layout of multiple parallel engines.

[0044] Although the present application has been described in connection with various embodiments thereof, those skilled in the art will understand that various modifications in form and detail can be made therein without departing from the spirit and scope of the application. In the claims, the word "comprising" does not exclude other elements or steps, and the indefinite articles "a" or "an" do not exclude a plurality. A single processor or other unit can fulfil the functions of several items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to an advantage. The reference signs in the claims should not be construed as limiting the scope of the application.

[0045] Although the present application has been described in connection with specific features thereof, it will be evident for a person skilled in the art that various modifications and combinations can be made without departing from the spirit and scope of the application. Accordingly, the description and drawings are to be regarded as illustrative in nature and not as restrictive. It is intended that all potential modifications and alterations are included within the scope of the present application as defined by the appended claims and their equivalents. Obviously, many modifications and variations of the present application are possible in light of the above teachings. It is, therefore, to be understood that within the scope of the appended claims and their equivalents, the application can be practiced otherwise than as specifically described.

Claims

1. A dual-thrust-chamber pump-post- swing liquid rocket engine characterized by, The double-thrust chamber pump post-swing liquid rocket engine comprises a frame, two gas swing devices, two thrust chambers and a fuel gas assembly; the fuel gas assembly is communicated with the corresponding thrust chamber through the two gas swing devices respectively, and is used for providing fuel to the two thrust chambers respectively; The first end of the two gas swing devices is fixedly arranged on the two sides of the frame respectively, and the second end is fixedly connected with the corresponding thrust chamber; the two gas swing devices and the two thrust chambers are symmetrically distributed along the center line of the frame, and the fuel gas assembly is fixedly arranged in the middle region of the frame.

2. The dual-thrust-chamber pump-post-rockedydrogen-oxygen rocket engine of claim 1, wherein, The double-thrust chamber pump post-swing liquid rocket engine further comprises two docking modules, each of which is used for fixing the corresponding gas swing device on the docking plane of the frame; the lower end surface of each gas swing device is fixedly connected with the corresponding thrust chamber through an outlet flange.

3. The dual-thrust-chamber pump-post-rockedydrogen-oxygen rocket engine of claim 1, wherein, The fuel gas assembly comprises a main turbine pump and a gas generator, the gas generator is fixedly and communicated with the main turbine pump; the main turbine pump is fixedly and communicated with the gas inlet of the two gas swing devices respectively.

4. The dual-thrust-chamber pump-post-rockiet engine of claim 3, wherein, The fuel gas assembly further comprises a gas guide pipe, the gas guide pipe has one inlet and two outlets, the inlet of the gas guide pipe is communicated with the main turbine pump, and the two outlets of the gas guide pipe are communicated with the two gas swing devices respectively.

5. The dual-thrust-chamber pump-post-rockiet engine of claim 4, wherein, The inlet end surface of the gas guide pipe is parallel to the two outlet end surfaces of the gas guide pipe, the two outlet pipelines of the gas guide pipe are symmetrically distributed along the center line of the gas guide pipe, and the included angle between the two outlet pipelines of the gas guide pipe is obtuse.

6. The dual-thrust-chamber pump-post-rockedydrogen-oxygen rocket engine of claim 3, wherein, The center line of the turbine pump is parallel to the center line of the two thrust chambers, and the center line of the turbine pump and the center line of the two thrust chambers form an isosceles triangle in the top view.

7. The dual-thrust-chamber pump-post-rockedydrogen-oxygen rocket engine of claim 3, wherein, The gas generator is fixedly connected with the main turbine pump through a flange, and the circumferential angle of the flange is adjusted to make the center line of the gas generator and the first plane in which the center line of the main turbine pump is located perpendicular to the second plane in which the center line of the two thrust chambers is located, and the two thrust chambers and the two gas swing devices are mirror-symmetrically relative to the first plane.

8. The dual-thrust-chamber pump aft-swinging liquid rocket engine of any of claims 3-7, wherein, The fuel gas assembly further comprises a fuel throttle valve and a thrust chamber fuel supply pipeline; the fuel throttle valve is installed at the fuel pump outlet of the main turbine pump, and the thrust chamber fuel supply pipeline is fixed at the outlet of the fuel throttle valve; the thrust chamber fuel supply pipeline has two mirror-symmetric outlet conduits, and the two outlet conduits are connected with the fuel inlets of the two thrust chambers respectively.

9. The dual-thrust-chamber pump-post-rockiet liquid rocket engine of claim 8, wherein, The fuel gas assembly further comprises four fuel swing devices, two fuel swing devices are arranged in each outlet conduit, the fuel swing devices are used for providing angle and displacement compensation for the thrust chamber fuel supply pipeline in the swinging process of the thrust chamber, and the swinging centers of the four fuel swing devices and the swinging centers of the two gas swing devices are located in the same horizontal plane.

10. The dual-thrust-chamber pump aft-swinging liquid rocket engine of any of claims 3-7, wherein, The fuel gas assembly further comprises an oxidizer inlet pipe and a fuel inlet pipe, which are in communication with the gas generator, and the oxidizer inlet pipe and the fuel inlet pipe are located on the same side of the plane where the center lines of the two thrust chambers are located, and the angles of the elbow sections of the oxidizer inlet pipe and the fuel inlet pipe are adjustable.

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