Dual-thrust-chamber pump after-swinging liquid rocket engine
By designing a dual-thrust-chamber post-pump gyratory liquid rocket engine, the design difficulty and control problems of a single-thrust-chamber liquid rocket engine under high thrust conditions have been solved. This design achieves symmetrical distribution of the thrust chambers and flexible internal layout of the rocket, enabling pitch, yaw, and roll control capabilities.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AEROSPACE PROPULSION INST
- Filing Date
- 2025-10-29
- Publication Date
- 2026-07-03
Smart Images
Figure CN121382471B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of rocket engine technology, and in particular to a dual-thrust-chamber post-pump oscillating liquid rocket engine. Background Technology
[0002] Currently, all existing pump-fed liquid rocket engines adopt a single turbopump, single thrust chamber configuration. This configuration offers advantages such as a small outer envelope size and ease of parallel assembly. However, this single turbopump, single thrust chamber configuration is unsuitable for high-thrust liquid rocket engines. As thrust increases, the design and manufacturing complexity of the thrust chamber significantly increases, the engine's sway envelope grows, and the design and manufacturing of the sway mechanism becomes considerably more difficult. Furthermore, a single thrust chamber configuration cannot achieve the required roll attitude control of a rocket when used alone, necessitating the addition of a roll control propulsion system, further increasing the complexity of the launch vehicle system. Summary of the Invention
[0003] The purpose of this invention is to provide a dual-thrust-chamber post-pump oscillating liquid rocket engine, which provides a technical solution that can effectively compensate for the shortcomings of the traditional single turbopump, single-thrust-chamber structural layout in high-thrust or heavy liquid rocket engines.
[0004] In a first aspect, the present invention provides a dual-thrust-chamber pump-after-swing liquid rocket engine, the dual-thrust-chamber pump-after-swing liquid rocket engine comprising: a frame, two gas swing devices, two thrust chambers, and a fuel gas assembly; the fuel gas assembly is connected to the corresponding thrust chambers through the two gas swing devices respectively, for supplying fuel to the two thrust chambers respectively.
[0005] The first ends of the two gas swing devices are fixedly installed on both sides of the frame, and the second ends are fixedly connected to 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 installed in the middle area of the frame.
[0006] With the above technical solution adopted, the dual-thrust chamber post-pump gyratory liquid rocket engine provided by the present invention includes a frame, two gas gyratory devices, two thrust chambers, and a fuel-gas assembly. The first ends of the two gas gyratory devices are fixedly disposed on both sides of the frame, and the second ends are fixedly connected to the corresponding thrust chambers. The two gas gyratory devices are symmetrically distributed with respect to the two thrust chambers along the centerline of the frame. The fuel-gas assembly is fixedly disposed in the middle region of the frame. Based on this, the two thrust chambers can be connected to the frame via the gas gyratory devices to transmit the generated thrust to the frame. Furthermore, the symmetrical distribution of the two gas gyratory devices with respect to the two thrust chambers along the centerline of the frame, and the fixed disposal of the fuel-gas assembly in the middle region of the frame, reduces the overall mass eccentricity of the engine.
[0007] It should be understood that for high-thrust or heavy-lift liquid rocket engines, a dual-thrust chamber engine structure layout is more suitable. This layout achieves high thrust while effectively reducing the design and manufacturing difficulty of the thrust chambers and gyratory mechanisms, further reducing gyratory torque, improving the engine's thrust-to-weight ratio, and enabling launch vehicles equipped with a single dual-thrust chamber or multi-thrust chamber engine to perform pitch, yaw, and roll control. Therefore, the dual-thrust chamber and two gas-powered gyratory devices layout in the dual-thrust chamber post-pump gyratory liquid rocket engine provided by this invention can achieve the function of independent gyratory movement of the two thrust chambers. Thus, a single engine can possess the complete vector adjustment and control capabilities to generate pitch, yaw, and roll control for the rocket body.
[0008] Finally, the dual-thrust chamber post-pump gyratory liquid rocket engine provided in this invention involves only two thrust chambers in gyratory operation. Therefore, the thrust level of the thrust chamber can be significantly reduced, and the size of the thrust chamber envelope is also reduced accordingly. Based on this, the gyratory envelope of the entire dual-thrust chamber post-pump gyratory liquid rocket engine will also be significantly reduced. Thus, it has the advantage of flexible internal layout, which is beneficial to improving the surface thrust of the rocket.
[0009] Furthermore, the dual-thrust chamber pump-fed gyratory liquid rocket engine also includes two docking modules, each of which is used to fix a corresponding gas gyratory device to the docking plane of the frame, and the lower end face of each gas gyratory device is fixedly connected to the corresponding thrust chamber through an outlet flange.
[0010] Furthermore, the fuel gas assembly includes a main turbopump and a gas generator, the gas generator being fixed and connected to the main turbopump; the main turbopump is fixed and connected to the gas inlets of the two gas swing devices respectively.
[0011] Furthermore, the fuel gas assembly also includes a gas conduit having one inlet and two outlets. The inlet of the gas conduit is connected to the main turbine pump, and the two outlets of the gas conduit are respectively connected to the two gas swing devices.
[0012] Furthermore, the inlet end face of the gas conduit is parallel to the two outlet end faces of the gas conduit, the two outlet pipes of the gas conduit are symmetrically distributed along the center line of the gas conduit, and the included angle between the two outlet pipes of the gas conduit is an obtuse angle.
[0013] Furthermore, the centerline of the turbopump is parallel to the centerlines of the two thrust chambers, and the line connecting the top view projections of the center of the turbopump and the centers of the two thrust chambers forms an isosceles triangle.
[0014] Furthermore, the gas generator is fixedly connected to the main turbine pump via a flange, and by adjusting the circumferential angle of the flange, the centerline of the gas generator is perpendicular to the first plane containing the centerline of the main turbine pump and the second plane containing the centerlines of the two thrust chambers, and the two thrust chambers and the two gas swing devices are mirror-symmetrical with respect to the first plane.
[0015] Furthermore, the fuel gas assembly also includes a fuel throttle valve and a thrust chamber fuel supply line; the fuel throttle valve is installed at the fuel pump outlet of the main turbine pump, and the thrust chamber fuel supply line is fixed at the outlet of the fuel throttle valve; the thrust chamber fuel supply line has two mirror-symmetrical outlet conduits, and the two outlet conduits are respectively connected to the fuel inlets of the two thrust chambers.
[0016] Furthermore, the fuel gas assembly also includes four fuel swaying devices, with two fuel swaying devices provided in each outlet conduit. The fuel swaying devices are used to provide angle and displacement compensation for the fuel supply pipeline of the thrust chamber during the swaying process of the thrust chamber, and the swaying centers of the four fuel swaying devices are located in the same horizontal plane as the swaying centers of the two gas swaying devices.
[0017] Furthermore, the fuel gas assembly also includes an oxidizer inlet pipe and a fuel inlet pipe, which are connected to the gas generator. The oxidizer inlet pipe and the fuel inlet pipe are located on the same side of the plane containing the center lines of the two thrust chambers, and the angles of the bends of the oxidizer inlet pipe and the fuel inlet pipe are adjustable. Attached Figure Description
[0018] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:
[0019] Figure 1 This is a front view of the overall structure of a dual-thrust chamber post-pump gyratory liquid rocket engine provided in an embodiment of the present invention;
[0020] Figure 2 A top view of the overall structure of a dual-thrust chamber post-pump gyratory liquid rocket engine provided in an embodiment of the present invention;
[0021] Figure 3 The present invention provides an overall structure for a gas swaying device of a dual-thrust chamber post-pump swaying liquid rocket engine.
[0022] In the diagram: 1-frame, 2-gas swing device, 3-thrust chamber fuel supply line, 4-oxidant inlet pipe, 5-fuel throttle valve, 6-thrust chamber, 7-fuel swing device, 8-gas conduit, 9-main turbine pump, 10-fuel inlet pipe, 11-gas generator, 12-upper docking surface of gas swing device, 13-lower docking surface of gas swing device, 14-gas swing device inlet. Detailed Implementation
[0023] Embodiments of the present disclosure will now be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the disclosure. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concepts of the present disclosure.
[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.
[0025] Currently, all existing pump-fed liquid rocket engines adopt a single turbopump, single thrust chamber configuration. This configuration offers advantages such as a small outer envelope size and ease of parallel assembly. However, this single turbopump, single thrust chamber configuration is unsuitable for high-thrust liquid rocket engines. As thrust increases, the design and manufacturing complexity of the thrust chamber significantly increases, the engine's sway envelope grows, and the design and manufacturing of the sway mechanism becomes considerably more difficult. Furthermore, a single thrust chamber configuration cannot achieve the required roll attitude control of a rocket when used alone, necessitating the addition of a roll control propulsion system, further increasing the complexity of the launch vehicle system.
[0026] Based on this, refer to Figures 1 to 3 This invention provides a dual-thrust-chamber, 6-pump-follow-glide liquid rocket engine, comprising: a frame, two gas gyratory devices 2, two thrust chambers 6, and a fuel-gas assembly; the fuel-gas assembly is connected to the corresponding thrust chamber 6 via the two gas gyratory devices 2, respectively, for supplying fuel to the two thrust chambers 6. The thrust chamber 6 burns the fuel to generate thrust, which is transmitted to the frame via the gas gyratory devices 2.
[0027] In actual installation, the first ends of the two gas swing devices 2 are fixedly mounted on both sides of the frame, and the second ends are fixedly connected to the corresponding thrust chambers 6. The two gas swing devices 2 and the two thrust chambers 6 are symmetrically distributed along the centerline of the frame, and the fuel gas assembly is fixedly mounted in the middle area of the frame. Based on this structure, that is, the first end of each gas swing device 2 is fixed to one side of the frame, and the two gas swing devices 2 are fixed on opposite sides of the frame to achieve a balancing effect. Each thrust chamber 6 is fixedly connected to the second end of the corresponding gas swing device 2; specifically, the thrust chamber 6 can be fixedly connected to the second end of the corresponding gas swing device 2 via a flange.
[0028] Based on this, in this embodiment of the invention, the two thrust chambers 6 can be connected to the frame via the gas sway device 2, so that the generated thrust can be transmitted to the frame via the gas sway device 2. In this case, the gas sway device 2 serves as a force transmission mechanism. Furthermore, in this embodiment of the invention, the two gas sway devices 2 and the two thrust chambers 6 are symmetrically distributed along the centerline of the frame, and the fuel gas assembly is fixedly installed in the middle area of the frame. Therefore, this symmetrical distribution structure can reduce the overall mass eccentricity of the engine.
[0029] In practice, for high-thrust or heavy liquid rocket engines, a dual-thrust-chamber (6) engine structure layout is more suitable. This layout achieves high thrust while effectively reducing the design and manufacturing difficulty of the thrust chambers (6) and the gyratory mechanism. It also helps to reduce the gyratory torque, improve the engine's thrust-to-weight ratio, and allows launch vehicles equipped with a single dual-thrust-chamber (6) or multi-thrust-chamber (6) engine to have pitch, yaw, and roll control functions. Based on the above description, and considering that each thrust chamber (6) in the dual-thrust-chamber (6) post-pump gyratory liquid rocket engine provided in this embodiment is connected to a gas-powered gyratory device (2), the layout of the thrust chambers (6) and the gas-powered gyratory device (2) can enable the two thrust chambers (6) to gyrate independently. Therefore, a single engine can possess the complete vector adjustment and control capabilities to generate pitch, yaw, and roll control for the rocket body.
[0030] Finally, in the embodiment of the present invention, the dual-thrust chamber 6 post-pump oscillating liquid rocket engine only has two thrust chambers 6 participating in the oscillation. Therefore, the thrust level of the thrust chamber 6 can be significantly reduced, and the envelope size of the thrust chamber 6 is also reduced accordingly. Based on this, the oscillation envelope of the entire dual-thrust chamber 6 post-pump oscillating liquid rocket engine will also be significantly reduced. Therefore, it has the advantage of flexible layout within the rocket body, which is conducive to improving the surface thrust of the rocket.
[0031] In one example, the dual-thrust chamber 6-pump-follow-swing liquid rocket engine further includes two docking modules, each of which is used to fix a corresponding gas swing device 2 to the docking plane of the frame. The lower end face of each gas swing device 2 is fixedly connected to the corresponding thrust chamber 6 via an outlet flange. The docking module can be any fixing structure capable of fixing the gas swing device 2 to the frame; this embodiment of the invention does not limit this.
[0032] Furthermore, the fuel-gas assembly in this embodiment of the invention is used to supply oxidizer and fuel to the thrust chamber 6. The fuel-gas assembly includes a main turbopump 9 and a gas generator 11, the gas generator 11 being fixed and connected to the main turbopump 9; the main turbopump 9 is fixed and connected to the gas inlets of the two gas swing devices 2 respectively. It is worth noting that, in practice, the gas generator 11 can be fixed to the turbine housing of the main turbopump 9 by welding, and when installing the main turbopump 9, the circumferential angle of the flange can be adjusted to ensure that the plane containing the centerline of the gas generator 11 and the main turbopump 9 is perpendicular to the plane containing the centerlines of the two thrust chambers 6, thereby further reducing the overall mass eccentricity of the dual-thrust chamber 6 pump-driven swing liquid rocket engine.
[0033] The fuel gas assembly also includes a gas conduit 8, which has an inlet and two outlets. The inlet of the gas conduit 8 is connected to the main turbine pump 9, and the two outlets of the gas conduit 8 are respectively connected to the two gas swing devices 2.
[0034] In practice, the two outlets of the gas duct 8 are welded to and connected to the gas inlets of the two gas swing devices 2, respectively. The inlet of the gas duct 8 is connected to the main turbopump 9 via a flange and is also connected to the main turbopump 9. Furthermore, the inlet end face of the gas duct 8 is parallel to the two outlet end faces of the gas duct 8, the two outlet pipes of the gas duct 8 are symmetrically distributed along the centerline of the gas duct 8, and the included angle between the two outlet pipes of the gas duct 8 is an obtuse angle. Because the inlet and outlet end faces of the gas duct 8 are parallel to each other, and the two outlet branch pipes are symmetrically structured and distributed at an obtuse angle, the centerline of the main turbopump 9 is parallel to the centerlines of the two thrust chambers 6, and the line connecting the top view projections of the three centers forms an isosceles triangle. Based on the above description, the gas duct 8, the main turbopump 9, and the two thrust chambers 6 are symmetrically distributed, which can reduce the overall mass eccentricity of the engine to a certain extent.
[0035] The gas generator 11 is fixedly connected to the main turbopump 9 via a flange. By adjusting the circumferential angle of the flange, the centerline of the gas generator 11 is perpendicular to the first plane containing the centerline of the main turbopump 9, and to the second plane containing the centerlines of the two thrust chambers 6. Furthermore, the two thrust chambers 6 and the two gas oscillating devices 2 are mirror-symmetrical with respect to the first plane. Based on this, the two thrust chambers 6 and the two gas oscillating devices 2 are symmetrically distributed on both sides of the gas generator 11 and the main turbopump 9 to improve engine stability and reduce engine mass eccentricity.
[0036] In some embodiments, the fuel gas assembly further includes a fuel throttle valve 5 and a thrust chamber fuel supply line 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 line 3 is fixed at the outlet of the fuel throttle valve 5; the thrust chamber fuel supply line 3 has two mirror-symmetrical outlet conduits, and the two outlet conduits are respectively connected to the fuel inlets of the two thrust chambers 6.
[0037] The aforementioned gas throttle valve is used to adjust the fuel flow rate at the fuel pump outlet of the main turbopump 9. The thrust chamber fuel supply line 3 has two mirror-symmetrical outlet conduits, which are respectively connected to the fuel inlets of the two thrust chambers 6 to supply fuel to the respective thrust chambers 6. Furthermore, because the thrust chamber fuel supply line 3 has two mirror-symmetrical outlet conduits, the engine stability can be further improved.
[0038] Furthermore, the fuel gas assembly also includes four fuel swing devices 7, with two fuel swing devices 7 provided in each outlet conduit. The fuel swing devices 7 are used to provide angle and displacement compensation for the thrust chamber fuel supply pipeline 3 during the swinging process of the thrust chamber 6, and the swing centers of the four fuel swing devices 7 are located in the same horizontal plane as the swing centers of the two gas swing devices 2.
[0039] The two fuel sway devices 7 installed in the outlet conduit are used to ensure that the components upstream of the thrust chamber fuel supply pipeline 3 are in a fixed state. To minimize the displacement generated by the fuel sway devices 7 during swaying deformation, the engine alone can possess a complete set of vector adjustment and control capabilities for pitch, yaw, and roll control of the rocket body. Furthermore, the swaying centers of the four fuel sway devices 7 and the two gas sway devices 2 are located in the same horizontal plane.
[0040] In this embodiment of the invention, the fuel gas assembly further includes an oxidizer inlet pipe 4 and a fuel inlet pipe. The oxidizer inlet pipe 4 and the fuel inlet pipe are connected to the gas generator 11, and are located on the same side of the plane containing the centerlines of the two thrust chambers 6. The angles of the bends in the oxidizer inlet pipe 4 and the fuel inlet pipe are adjustable. Therefore, the angles of the bends in the oxidizer inlet pipe 4 and the fuel inlet pipe can be adjusted to accommodate different rocket body propellant delivery pipeline layouts, particularly providing good adaptability to external propellant delivery pipeline layouts for multi-engine parallel engines.
[0041] In a specific instance, such as Figure 1 , Figure 2 As shown, a dual-thrust chamber pump-fed swaying liquid rocket engine mainly includes: a frame 1, a gas swaying device 2, a thrust chamber fuel supply pipeline 3, an oxidizer inlet pipe 4, a fuel throttle valve 5, a thrust chamber 6, a fuel swaying device 7, a gas conduit 8, a main turbopump 9, a fuel inlet pipe 10, and a gas generator 11.
[0042] like Figure 3 As shown, the gas swing device 2 has an upper docking surface 12 and a lower docking surface 13. The gas swing device inlet 14 is fixed to the gas pipeline by welding, and the lower docking surface 13 is fixed to the thrust chamber 6 by flange connection.
[0043] like Figure 1 , Figure 2As shown, the frame 1 is detachable from the engine. Two docking modules are set on the docking plane between the frame and the engine. Each docking module is connected to the upper docking surface 12 of the gas swing device. Therefore, two gas swing devices 2 can be installed on one frame 1. A thrust chamber 6 is fixed to the outlet flange of the gas swing device 2. 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 process 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.
[0044] like Figure 1 , Figure 2 As shown, the gas duct 8 has one inlet and two outlets. The two outlets are welded to the inlets of the two gas swing devices, respectively. The inlet of the gas duct 8 is connected to the main turbopump 9 via a flange. Since the inlet and outlet end faces of the gas duct 8 are parallel to each other, and the two outlet branch pipes are symmetrical and distributed at obtuse angles, the centerline of the main turbopump 9 is parallel to the centerlines of the two thrust chambers 6, and the top projection of the three centers forms an isosceles triangle. The gas generator 11 is welded and fixed to the turbine housing of the main turbopump 9. When installing the main turbopump 9, the circumferential angle of the flange is adjusted to make the plane containing the centerline of the gas generator 11-main turbopump 9 perpendicular to the plane containing the centerlines of the two thrust chambers 6. The two thrust chambers 6 and the components fixed on the thrust chambers are mirror-symmetrical relative to the plane containing the centerline of the gas generator 11-main turbopump 9. This assembly method places the gas generator 11 and the main turbopump 9 on opposite sides of the thrust chamber centerline plane, achieving a more balanced mass distribution and reducing the mass eccentricity of the engine.
[0045] like Figure 1 , Figure 2 As shown, a fuel throttle valve 5 is installed at the fuel pump outlet of the main turbine pump 9. The outlet of the fuel throttle valve 5 is fixed to the thrust chamber fuel supply line 3. The thrust chamber fuel supply line 3 has two mirror-symmetrical outlet conduits, which are connected to the fuel inlets of the thrust chamber 6 respectively. Each outlet conduit of the thrust chamber fuel supply line 3 is equipped with two fuel swing devices 7. During the swinging process of the thrust chamber 6, the fuel swing devices 7 provide angle and displacement compensation for the thrust chamber fuel supply line 3 to ensure that the upstream components of the thrust chamber fuel supply line 3 are in a fixed state. In order to minimize the displacement generated by the fuel swing devices 7 during the swinging deformation process, the swing centers of the four fuel swing devices 7 are in the same horizontal plane as the swing centers of the two gas swing devices 2.
[0046] like 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. The angle of the bends in the oxidizer inlet pipe 4 and the fuel inlet pipe 10 can be adjusted to adapt to different rocket body propellant delivery pipeline layouts. In particular, it has good adaptability to the external propellant delivery pipeline layout for multi-engine parallel engines.
[0047] Although the invention has been described herein in conjunction with various embodiments, those skilled in the art will understand and implement other variations of the disclosed embodiments by reviewing the accompanying drawings, the disclosure, and the appended claims in carrying out the claimed invention. In the claims, the word "comprising" does not exclude other components or steps, and "a" or "an" does not exclude a plurality. A single processor or other unit can implement several functions listed in the claims. While different dependent claims may recite certain measures, this does not mean that these measures cannot be combined to produce good results.
[0048] Although the invention has been described in conjunction with specific features and embodiments, it is obvious that various modifications and combinations can be made therein without departing from the spirit and scope of the invention. Accordingly, this specification and drawings are merely exemplary descriptions of the invention as defined by the appended claims, and are considered to cover any and all modifications, variations, combinations, or equivalents within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if such modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include such modifications and modifications.
Claims
1. A dual-thrust-chamber post-pump gyratory liquid rocket engine, characterized in that, The dual-thrust chamber pump-fed gyratory liquid rocket engine includes: a frame, two gas gyratory devices, two thrust chambers, and a fuel gas assembly; the fuel gas assembly is connected to the corresponding thrust chamber through the two gas gyratory devices to supply fuel to the two thrust chambers respectively; The first ends of the two gas swing devices are respectively fixedly installed on both sides of the frame, and the second ends are respectively fixedly connected to 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 installed in the middle area of the frame. The dual-thrust chamber pump-fed gyratory liquid rocket engine further includes: two docking modules, each of which is used to fix the corresponding gas gyratory device to the docking plane of the frame, and the lower end face of each gas gyratory device is fixedly connected to the corresponding thrust chamber through an outlet flange; The fuel gas assembly includes a main turbopump and a gas generator, the gas generator being fixed to and connected to the main turbopump; the main turbopump is fixed to and connected to the gas inlets of the two gas swing devices respectively. The fuel gas assembly also includes a gas conduit having one inlet and two outlets. The inlet of the gas conduit is connected to the main turbine pump, and the two outlets of the gas conduit are respectively connected to the two gas swing devices. The fuel gas assembly also includes a thrust chamber fuel supply pipeline; the thrust chamber fuel supply pipeline has two mirror-symmetrical outlet conduits, and the two outlet conduits are respectively connected to the fuel inlets of the two thrust chambers; The fuel gas assembly also includes four fuel swaying devices, with two fuel swaying devices provided in each outlet conduit. The fuel swaying devices are used to provide angle and displacement compensation for the fuel supply pipeline of the thrust chamber during the swaying process of the thrust chamber, and the swaying centers of the four fuel swaying devices are located in the same horizontal plane as the swaying centers of the two gas swaying devices.
2. The dual-thrust chamber post-pump gyratory liquid rocket engine according to claim 1, characterized in that, The inlet end face of the gas conduit is parallel to the two outlet end faces of the gas conduit. The two outlet pipes of the gas conduit are symmetrically distributed along the center line of the gas conduit, and the included angle between the two outlet pipes of the gas conduit is an obtuse angle.
3. The dual-thrust-chamber post-pump gyratory liquid rocket engine according to claim 1, characterized in that, The centerline of the main turbine pump is parallel to the centerlines of the two thrust chambers, and the line connecting the top view projections of the center of the main turbine pump and the centers of the two thrust chambers forms an isosceles triangle.
4. The dual-thrust-chamber post-pump gyratory liquid rocket engine according to claim 1, characterized in that, The gas generator is fixedly connected to the main turbine pump via a flange. By adjusting the circumferential angle of the flange, the centerline of the gas generator is perpendicular to the first plane containing the centerline of the main turbine pump and the second plane containing the centerlines of the two thrust chambers. The two thrust chambers and the two gas swing devices are mirror-symmetrical with respect to the first plane.
5. The dual-thrust chamber post-pump gyratory liquid rocket engine according to any one of claims 1-4, characterized in that, The fuel gas assembly also includes a fuel throttle valve; the fuel throttle valve is installed at the fuel pump outlet of the main turbine pump, and the thrust chamber fuel supply line is fixed to the outlet of the fuel throttle valve.
6. The dual-thrust chamber post-pump gyratory liquid rocket engine according to any one of claims 1-4, characterized in that, The fuel gas assembly also includes an oxidizer inlet pipe and a fuel inlet pipe, which are connected to the gas generator. The oxidizer inlet pipe and the fuel inlet pipe are located on the same side of the plane containing the center lines of the two thrust chambers, and the angles of the bends in the oxidizer inlet pipe and the fuel inlet pipe are adjustable.