Modular open liquid rocket engine based on metal hose behind the pump and assembly method

Abstract

The present invention relates to a modular open liquid rocket engine based on a metal hose behind a pump and an assembly method. The existing open circulation pump-back swing liquid rocket engine has a relatively small thrust and relatively low requirements for hoses, and is not suitable for large thrust pump-back swing engines and large launch vehicles. The open liquid rocket engine provided by the present invention uses the cross axis of the gimbal as the swing center, and the axis of the thrust chamber in a vertical state as the swing axis. The servo mechanism telescopes to change the position of the thrust chamber, and at the same time, the metal swing hose behind the engine pump compensates for the deformation of the metal pipeline, so that the thrust chamber can swing 360° around the axis with the cross axis as the swing center. The liquid rocket engine of the present invention utilizes a modular layout, has a compact structure, can greatly shorten the assembly cycle, and saves production costs.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engines, and relates to an open-cycle liquid rocket engine, and specifically refers to a modular open-cycle liquid rocket engine based on a pump-rear metal hose and an assembly method. Background Art

[0002] With the continuous development of space stations, deep space exploration and commercial aerospace, the thrust requirements of engines for launch missions are continuously growing. Currently, the demand is mainly met by increasing the thrust of a single liquid rocket engine while developing multi-engine parallel combination technology.

[0003] At present, the overall layout of open liquid rocket engines at home and abroad is mainly to arrange a swing hose in front of the pump to achieve engine swing. This type of swing hose is a load-relief hose, which achieves engine swing through an external gimbal or an internal gimbal. Since the diameter of this type of hose is large, the pressure bearing capacity is relatively low. At the same time, most of these engines are unidirectional swinging, and the thrust chamber and the turbo pump swing together as a whole, with a small swing angle and limited swing space. At the same time, multiple engines cannot be installed in parallel due to space limitations.

[0004] After searching, the publication number CN112832926A discloses a bidirectional pump back-swing liquid rocket engine, including a frame and two electric drive pump modules; the frame is cross-shaped and extends from the central axis to four directions, forming four quadrants on the projection surface of the top view; the electric drive pump module is fixedly connected to the frame, and the two electric drive pump modules are respectively located in two quadrants with a diagonal relationship. The electric drive pump module of this liquid rocket engine is used to generate a medium driving force to the main system to adjust the engine thrust. Since the engine adopts an electric drive pump, a set of secondary systems centered on the gas generator of the traditional liquid rocket engine is omitted, the engine structure is simplified, the vibration source is reduced, and the vibration is reduced. The electric drive pump components are arranged in the two diagonal quadrants formed by the frame, and the center of gravity of the engine is relatively balanced, which can solve the problem of bidirectional pump back-swing to a certain extent. However, this liquid rocket engine is a 20KN small thrust electric pump propulsion engine, which has low pressure resistance and deformation requirements for the hose, and is not suitable for large thrust pump back-swing engines and large launch vehicles.

[0005] Based on the above reasons, it is necessary to carry out research on large-thrust turbopump driven liquid rocket engines with new structural layouts to provide technical support for the final assembly structural design of new liquid high-thrust rockets. Summary of the invention

[0006] In view of the above problems, the purpose of the present invention is to provide a modular open liquid rocket engine and assembly method based on a metal hose behind the pump. The open-cycle liquid rocket engine of the present invention relies on the turbine pump on the frame and positions it with three-point support, breaking through the traditional open engine that arranges a metal swing hose in front of the turbine pump. The metal swing hose is arranged in the turbine pump outlet duct and a modular layout is performed, so that the open-cycle liquid rocket engine of the present invention has two-way large-angle swing behind the pump and can be assembled quickly and efficiently.

[0007] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0008] A modular open liquid rocket engine based on a rear metal hose of a pump, characterized in that: the engine uses the cross axis of a gimbal as the swing center, and uses the axis of the engine's thrust chamber in a vertical state as the swing axis; when the servo mechanism of the engine is extended or retracted to change the position of the thrust chamber, the engine's oxygen pump rear pipeline and fuel pump rear pipeline compensate for the deformation of the metal pipeline, so that the thrust chamber can swing 360° with the cross axis as the swing center and the axis as the swing axis.

[0009] Furthermore, it also includes a turbo pump, a generator, a gas cylinder module, a solenoid valve module, an ignition agent tank module, a turbo pump connecting bracket, an oxygen inlet conduit and an assembly conduit.

[0010] Furthermore, it also includes a force transmission seat, a gimbal seat and a frame; the frame, the gimbal seat, the force transmission seat and the thrust chamber are connected in sequence by bolts.

[0011] Furthermore, the gimbal is a cross-axis structure with the axis as the swing center, and can rotate 360° in a plane.

[0012] Furthermore, the oxygen pump rear pipeline includes a first metal swing hose and a second metal swing hose behind the oxygen pump; the fuel pump rear pipeline includes a first metal swing hose and a second metal swing hose behind the fuel pump; the pump rear metal swing hose is a multi-layer metal corrugated hose that can withstand high pressure behind the pump, and the outer layer of the multi-layer metal corrugated hose is a metal wire mesh sleeve with a certain angle for axial constraint, and the position of the pump rear metal swing hose is in the same plane as the cross axis of the gimbal, and is arranged parallel to the axis of the gimbal.

[0013] Furthermore, the servo mechanism includes two sets, and the servo mechanism is arranged on the cross axis of the gimbal, one end of the servo mechanism is hinged to the frame, and the other end of the servo mechanism is hinged to the body of the thrust chamber; taking the cross axis of the gimbal as the swing center, and taking the axis of the thrust chamber in a vertical state as the swing axis, when the servo mechanism is extended and retracted to change the position of the thrust chamber, the rear metal swing hose of the pump compensates for the deformation of the metal pipeline composed of the rear pipeline of the oxygen pump and the rear pipeline of the fuel pump, so that the thrust chamber can swing 360° around the axis with the cross axis as the swing center.

[0014] Furthermore, the gas cylinder module includes a gas cylinder mounting plate, a first gas cylinder, a second gas cylinder, a filter, an inflation valve and a gas cylinder solenoid valve, which are installed on the frame by bolt connection; the solenoid valve module includes a solenoid valve mounting plate, a solenoid valve and a solenoid valve seat, which are installed on the frame by bolt connection; the ignition agent tank module includes a tank mounting bracket, an ignition agent tank, a tank fixing bracket, a tank solenoid valve, a double check valve and a check valve, which are installed on the frame by bolt connection.

[0015] Furthermore, the interfaces of the gas cylinder module, the solenoid valve module, the ignition agent tank module, the thrust chamber, the turbo pump, the generator and other components are connected through the assembly conduit to form a complete engine system.

[0016] A method for assembling the above modular open liquid rocket engine based on the rear metal hose of the pump comprises the following steps:

[0017] S1) assembling the gas cylinder module, the solenoid valve module and the ignition agent tank module separately in sequence, and connecting the modules in sequence and installing them on the frame by bolts;

[0018] S2) firstly connecting the gimbal, the force transmission seat and the thrust chamber to the frame in sequence through bolts, and then connecting the turbo pump to the frame through the oxygen inlet conduit and the turbo pump connecting bracket;

[0019] S3) installing the two sets of servo mechanisms between the frame and the thrust chamber via hinge connections;

[0020] S4) connecting the turbo pump to the thrust chamber through the oxygen pump rear pipeline and the fuel pump rear pipeline;

[0021] S5) connecting the modules and the interfaces of the thrust chamber, turbo pump, generator and other components through the final assembly duct to form a complete engine system.

[0022] A method for assembling the above modular open liquid rocket engine based on the rear metal hose of the pump comprises the following steps:

[0023] S1) assembling the gas cylinder module, the solenoid valve module and the ignition agent tank module separately in sequence, and connecting the modules in sequence and installing them on the frame by bolts;

[0024] S2) firstly connecting the turbo pump to the frame through the oxygen inlet conduit and the turbo pump connecting bracket, and then connecting the gimbal, the force transmission seat and the thrust chamber to the frame in sequence through bolts;

[0025] S3) installing the two sets of servo mechanisms between the frame and the thrust chamber via hinge connection;

[0026] S4) connecting the turbo pump to the thrust chamber through the oxygen pump rear pipeline and the fuel pump rear pipeline;

[0027] S5) connecting the modules and the interfaces of the thrust chamber, turbo pump, generator and other components through the final assembly duct to form a complete engine system.

[0028] The present invention adopts the above technical solution, which has the following advantages and effects:

[0029] (1) The present invention provides a modular open liquid rocket engine based on a metal hose behind a pump. A metal swing hose behind the pump is installed on the pipeline behind the turbine pump. The thrust chamber angle is adjusted by telescopic adjustment of a servo mechanism. The metal swing hose behind the pump compensates for the deformation of the metal pipeline, so that the thrust chamber can swing 360° with the cross axis of the gimbal as the swing center and the axis of the thrust chamber in a vertical state as the swing axis.

[0030] (2) The open liquid rocket engine of the present invention utilizes a modular layout to integrate the gas cylinder module, the solenoid valve module and the ignition agent tank module on the frame, which is not only convenient for disassembly and assembly and shortens the assembly cycle, but also can control the assembly quality of the engine.

[0031] (3) The open liquid rocket engine of the present invention adopts a modular layout during assembly, which has a compact structure and effectively saves production costs when the engine is mass-produced. At the same time, the modular layout of the open liquid rocket engine of the present invention can save space in the rocket compartment, which is conducive to the parallel arrangement of multiple engines and improves the rocket's carrying capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of the main structure of the liquid rocket engine of Example 1 of the present invention.

[0033] Figure 2 yes Figure 1 Top view of the .

[0034] Figure 3 It is a schematic diagram of the three-dimensional structure of the liquid rocket engine of Example 1 of the present invention.

[0035] Figure 4 It is a schematic diagram of the assembly structure of the gas cylinder module according to Example 1 of the present invention.

[0036] Figure 5 It is a schematic diagram of the assembly structure of the solenoid valve module of Example 1 of the present invention.

[0037] Figure 6 It is a schematic diagram of the assembly structure of the fire agent tank module according to Example 1 of the present invention.

[0038] Figure 7 It is a schematic diagram of the rack installation module structure of Example 1 of the present invention.

[0039] Figure 8 It is a schematic diagram of the structure of the rear pipeline of the oxygen pump of Example 1 of the present invention.

[0040] Fig. 9 It is a schematic diagram of the fuel pump rear pipeline structure of Example 1 of the present invention.

[0041] Fig.10 This is a schematic diagram of the structure of the pre-assembled thrust chamber and various combined modules of the liquid rocket engine provided in Example 2 of the present invention.

[0042] Fig.11 This is a schematic diagram of the structure of the liquid rocket engine provided by Example 3 of the present invention, which is first assembled with a rack module and a turbo pump

[0043] Among them, 1-thrust chamber, 2-turbo pump, 3-generator, 4-gas cylinder module, 5-solenoid valve module, 6-ignition agent tank module, 7-oxygen pump rear pipeline, 8-fuel pump rear pipeline, 9-force transmission seat, 10-level seat, 11-frame, 12-turbo pump connecting bracket, 13-oxygen inlet duct, 14-assembly duct, 15-servo mechanism, 401-gas cylinder mounting plate, 402-first gas cylinder, 403-second gas cylinder, 404-filter, 405-inflating valve, 406-gas cylinder solenoid valve, 501-solenoid valve mounting plate, 502-solenoid valve, 503-solenoid valve seat, 601-tank mounting bracket, 602-ignition agent tank, 603-tank fixing bracket, 604-tank solenoid valve, 605-double one-way valve, 606-one-way valve, 701-metal swing hose behind the first oxygen pump, 702-metal swing hose behind the second oxygen pump, 801-metal swing hose behind the first fuel pump, 802-metal swing hose behind the second fuel pump. DETAILED DESCRIPTION

[0044] The embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings so that the purpose, features and advantages of the present invention can be more clearly understood. It should be understood that the embodiments shown in the accompanying drawings are not intended to limit the scope of the present invention, but are only intended to illustrate the essential spirit of the technical solution of the present invention.

[0045] like Figure 1 , Figure 2 , Figure 3 The present invention provides a modular open liquid rocket engine based on a rear metal hose, comprising a thrust chamber 1, an oxygen pump rear pipeline 7, a fuel pump rear pipeline 8, a gimbal 10 and a servo mechanism 15. The engine uses the cross axis of the gimbal 10 as the swing center and the axis of the thrust chamber 1 of the engine in a vertical state as the swing axis. When the servo mechanism 15 of the engine is extended and retracted to change the position of the thrust chamber 1, the metal pipelines of the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8 of the engine are deformed and compensated, so that the thrust chamber 1 can swing 360 degrees with the cross axis as the swing center and the axis as the swing axis.

[0046] The four pump rear metal swing hoses included in the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8 compensate for the deformation of the metal pipelines formed by the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8, so that the thrust chamber 1 can swing 360° around the axis with the cross axis as the swing center.

[0047] Furthermore, the liquid rocket engine of the present invention also includes a turbopump 2, a generator 3, a gas cylinder module 4, a solenoid valve module 5, an ignition agent tank module 6, a turbopump connecting bracket 12, an oxygen inlet conduit 13 and an assembly conduit 14.

[0048] Furthermore, the liquid rocket engine of the present invention further comprises a force transmission seat 9, a gimbal 10 and a frame 11, wherein the frame 11, the gimbal 10, the force transmission seat 9 and the thrust chamber 1 are sequentially connected by bolts.

[0049] Specifically, a gimbal 10 is arranged at the lower end of the frame 11, a force transmission seat 9 is arranged at the upper end of the thrust chamber 1, the thrust chamber 1 is connected to the gimbal 10 through the force transmission seat 9, and the thrust chamber 1 is connected to the frame 11 through the servo mechanism 15. The extension and contraction of the servo mechanism 15 can change the swing angle of the thrust chamber 1.

[0050] Furthermore, the gimbal 10 is a cross-axis structure, the axis of the cross-axis is the swing center, and can rotate 360° in a plane.

[0051] Furthermore, the servo mechanism 15 includes two sets, and the two sets of servo mechanisms 15 are arranged on the cross axis of the gimbal 10, one end of the two sets of servo mechanisms 15 is hinged to the frame 11, and the other end of the two sets of servo mechanisms 15 is hinged to the body of the thrust chamber 1. With the cross axis of the gimbal 10 as the swing center, and the axis of the thrust chamber 1 in the vertical state as the swing axis, when the servo mechanism 15 is extended and shortened to change the position of the thrust chamber 1, the rear metal swing hose of the pump compensates for the deformation of the metal pipeline composed of the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8, so that the thrust chamber 1 is swung 360° around the axis with the cross axis as the swing center.

[0052] Specifically, one end of the two sets of servo mechanisms 15 and the hinge point of the thrust chamber 1 are arranged at an angle of 90 degrees on one side of the radial direction of the outer peripheral surface of the thrust chamber 1, and the other end extends outward in an eight-shaped shape along the outer periphery of the thrust chamber 1. When extended outward, the angle between the two ends of the servo mechanism 15 extending toward the side of the thrust chamber 1 is smaller than the angle between the two ends extending toward the side of the frame 11.

[0053] Further, if Figure 4 The gas cylinder module 4 comprises a gas cylinder mounting plate 401, a first gas cylinder 402, a second gas cylinder 403, a filter 404, a charging valve 405 and a gas cylinder solenoid valve 406; and is mounted on the frame 11 by bolt connection.

[0054] Further, if Figure 5 The solenoid valve module 5 comprises a solenoid valve mounting plate 501, a solenoid valve 502, and a solenoid valve seat 503, which are mounted on the frame 11 by bolts.

[0055] Further, if Figure 6 The ignition agent tank module 6 further comprises a tank mounting bracket 601, an ignition agent tank 602, a tank fixing bracket 603, a tank solenoid valve 604, a double check valve 605 and a check valve 606; and is mounted on the frame 11 by bolts.

[0056] like Figure 7 The gas cylinder module 4, the solenoid valve module 5 and the ignition agent tank module 6 are all mounted on the frame 11 by bolts.

[0057] The frame 11 is a trapezoidal table-type frame structure, and the frame 11 is divided into four triangular quadrant spaces along the axial direction, wherein the gas cylinder module 4, the solenoid valve module 5 and the ignition agent tank module 6 are arranged in sequence in the three connected quadrant spaces, and the turbine pump 2 is located below the remaining fourth quadrant space, and the gas cylinder module 4, the solenoid valve module 5 and the ignition agent tank module 6 are respectively installed on the frame 11 of the quadrant space.

[0058] like Figure 8 , Fig. 9 As shown. Further, the oxygen pump rear pipeline 7 includes a first oxygen pump rear metal swing hose 701 and a second oxygen pump rear metal swing hose 702, and the fuel pump rear pipeline 8 includes a first fuel pump rear metal swing hose 801 and a second fuel pump rear metal swing hose 802; the pump rear metal swing hose is a multi-layer metal corrugated hose resistant to high pressure after the pump, and the outer layer of the multi-layer metal corrugated hose is a metal wire mesh sleeve with a certain angle for axial constraint, and the position of the pump rear metal swing hose is in the same plane as the swing center of the gimbal 10, and is arranged parallel to the axis of the gimbal.

[0059] Specifically, the metal swing hose 701 behind the first oxygen pump, the metal swing hose 702 behind the second oxygen pump, the metal swing hose 801 behind the first fuel pump, and the metal swing hose 802 behind the second fuel pump form four metal swing hoses behind the pumps. One end of the metal swing hose 701 behind the first oxygen pump and one end of the metal swing hose 702 behind the second oxygen pump are connected through to form an L-shaped structure; the other end of the metal swing hose 702 behind the second oxygen pump is connected to the turbine pump 2, and the other end of the metal swing hose 701 behind the first oxygen pump is connected to the thrust chamber 1. One end of the metal swing hose 801 behind the first fuel pump is connected through to one end of the metal swing hose 802 behind the second fuel pump, the other end of the metal swing hose 801 behind the first fuel pump is connected to the upper end of the thrust chamber 1, and the other end of the metal swing hose 802 behind the second fuel pump is connected to the lower end of the thrust chamber 1, and the metal swing hose 801 behind the first fuel pump is in an L-shaped structure.

[0060] Since the metal swing hose is a multi-layer metal braided corrugated hose, the hose has a large diameter, a short axial length and can withstand high pressure after the pump. The hose is wrapped with a metal wire mesh sleeve at a certain angle on the outer layer for axial constraint, which can solve the fatigue problem of the hose swinging back and forth. The four metal swing hoses after the pump are arranged in the same plane as the swing center of the gimbal 10 and are parallel to the cross axis of the gimbal 10, so that the four metal swing hoses after the pump compensate for the deformation of the metal pipeline, and realize that the thrust chamber 1 of the engine swings 360° with the cross axis of the gimbal 10 as the swing center and the axis of the thrust chamber 1 of the engine in the vertical state as the swing axis.

[0061] Furthermore, the interfaces of the gas cylinder module 4, the solenoid valve module 5, the ignition agent tank module 6, the thrust chamber 1, the turbo pump 2, the generator 3 and other components are connected through the assembly conduit 14 to form a complete engine system.

[0062] Example 2

[0063] like Fig.10 The present invention provides a method for assembling a modular open liquid rocket engine based on a pump rear metal hose, comprising the following steps:

[0064] Step 1): Separately assemble the gas cylinder module 4, the solenoid valve module 5 and the ignition agent tank module 6 in sequence, and install the gas cylinder module 4, the solenoid valve module 5 and the ignition agent tank module 6 on the frame 11 by bolt connection;

[0065] Step 2): First, the gimbal 10, the force transmission seat 9 and the thrust chamber 1 are connected to the frame 11 by bolts in sequence, and then the turbo pump 2 is connected to the frame 11 through the oxygen inlet conduit 13 and the turbo pump connecting bracket 12;

[0066] Step 3): Two sets of servo mechanisms 15 are installed between the frame 11 and the thrust chamber 1, with the cross axis of the gimbal 10 as the swing center, and the axis of the thrust chamber 1 in the vertical state as the swing axis. The metal swing hose behind the pump can compensate for the deformation of the metal pipeline, so that the thrust chamber 1 can swing 360° around the axis with the cross axis as the swing center;

[0067] Step 4): Connect the turbo pump 2 to the thrust chamber 1 through the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8 equipped with the rear metal swing hose of the pump;

[0068] Step 5): Finally, the interfaces of each module and components such as the thrust chamber 1, the turbo pump 2 and the generator 3 are connected through the final assembly duct 14 to form a complete engine system and complete the modular assembly of the engine.

[0069] Example 3

[0070] like Fig.11 The present invention also provides a method for assembling a modular open liquid rocket engine based on a pump rear metal hose, comprising the following steps:

[0071] Step 1): Sequentially assemble the gas cylinder module 4, the solenoid valve module 5, and the ignition agent tank module 6, and install each module on the frame 11 by bolt connection;

[0072] Step 2): First, the turbo pump 2 is connected to the frame 11 through the oxygen inlet conduit 13 and the turbo pump connecting bracket 12, and then the gimbal 10, the force transmission seat 9 and the thrust chamber 1 are connected to the frame 11 in sequence through bolts;

[0073] Step 3): Two sets of servo mechanisms 15 are installed between the frame 11 and the thrust chamber 1, with the cross axis of the gimbal 10 as the swing center, and the axis of the thrust chamber 1 in the vertical state as the swing axis. The metal swing hose behind the pump can compensate for the deformation of the metal pipeline, so that the thrust chamber 1 can swing 360° around the axis with the cross axis as the swing center;

[0074] Step 4): Connect the turbo pump 2 to the thrust chamber 1 through the oxygen pump rear pipeline 7 and the fuel pump rear pipeline 8 equipped with the rear metal swing hose of the pump;

[0075] Step 5): Finally, the interfaces of each module and components such as the thrust chamber 1, the turbo pump 2 and the generator 3 are connected through the final assembly duct 14 to form a complete engine system and complete the modular assembly of the engine.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A modular open liquid rocket engine based on a metal hose after the pump, characterized in that: The engine uses the cross axis of the gimbal (10) as the swing center and the axis of the engine's thrust chamber (1) in a vertical state as the swing axis. When the engine's servo mechanism (15) is extended or retracted to change the position of the thrust chamber (1), the engine's oxygen pump rear pipeline (7) and fuel pump rear pipeline (8) perform deformation compensation on the metal pipeline, so that the thrust chamber (1) can swing 360 degrees with the cross axis as the swing center and the axis as the swing axis. The oxygen pump rear pipeline (7) includes a first oxygen pump rear metal swing hose (701) and a second oxygen pump rear metal swing hose (702). A metal swing hose (702) is arranged behind the dioxygen pump. The pipeline (8) behind the fuel pump includes a first metal swing hose (801) and a second metal swing hose (802) behind the fuel pump. The metal swing hose behind the pump is a multi-layer metal corrugated hose that can withstand high pressure behind the pump. The outer layer of the multi-layer metal corrugated hose is a metal wire mesh sleeve with a certain angle for axial constraint. The position of the metal swing hose behind the pump is in the same plane as the cross axis of the gimbal (10) and is arranged parallel to the axis of the gimbal (10).

2. The modular open liquid rocket engine based on the rear metal hose of the pump according to claim 1, characterized in that: It also includes a turbo pump (2), a generator (3), a gas cylinder module (4), a solenoid valve module (5), an ignition agent tank module (6), a turbo pump connecting bracket (12), an oxygen inlet conduit (13) and an assembly conduit (14).

3. The modular open liquid rocket engine based on the pump-rear metal hose according to claim 2 is characterized in that: It also includes a force transmission seat (9), a gimbal seat (10) and a frame (11); the frame (11), the gimbal seat (10), the force transmission seat (9) and the thrust chamber (1) are connected in sequence by bolts.

4. The modular open liquid rocket engine based on the rear metal hose of the pump according to claim 3 is characterized in that: The gimbal (10) is a cross-axis structure, the axis is the swing center, and can rotate 360 ​​degrees in a plane.

5. The modular open liquid rocket engine based on the rear metal hose of the pump according to claim 4 is characterized in that: The servo mechanism (15) includes two sets. The servo mechanism (15) is arranged on the cross axis of the gimbal (10). One end of the servo mechanism (15) is hinged to the frame (11), and the other end of the servo mechanism (15) is hinged to the body of the thrust chamber (1). The cross axis of the gimbal (10) is used as the swing center, and the axis of the thrust chamber (1) in a vertical state is used as the swing axis. When the servo mechanism (15) is extended or shortened to change the position of the thrust chamber (1), the metal swing hose behind the pump compensates for the deformation of the metal pipeline formed by the oxygen pump rear pipeline (7) and the fuel pump rear pipeline (8), so that the thrust chamber (1) swings 360° around the axis with the cross axis as the swing center.

6. The modular open liquid rocket engine based on the rear metal hose of the pump according to claim 5, characterized in that: The gas cylinder module (4) comprises a gas cylinder mounting plate (401), a first gas cylinder (402), a second gas cylinder (403), a filter (404), a charging valve (405) and a gas cylinder solenoid valve (406), which are installed on the frame (11) by bolt connection; the solenoid valve module (5) comprises a solenoid valve mounting plate (501), a solenoid valve (502) and a solenoid valve seat (503), which are installed on the frame (11) by bolt connection; the ignition agent tank module (6) comprises a tank mounting bracket (601), an ignition agent tank (602), a tank fixing bracket (603), a tank solenoid valve (604), a double check valve (605) and a check valve (606), which are installed on the frame (11) by bolt connection.

7. The modular open liquid rocket engine based on the rear metal hose of the pump according to claim 5, characterized in that: The interfaces of the gas cylinder module (4), the solenoid valve module (5), the ignition agent tank module (6), the thrust chamber (1), the turbo pump (2), the generator (3) and other components are connected through the assembly conduit (14) to form a complete engine system.

8. A method for assembling a modular open liquid rocket engine based on a post-pump metal hose as claimed in claim 7, comprising the following steps: S1) assembling the gas cylinder module (4), the solenoid valve module (5) and the ignition agent tank module (6) in sequence, and connecting the gas cylinder module (4), the solenoid valve module (5) and the ignition agent tank module (6) in sequence and installing them on the frame (11) by bolts; S2) firstly connecting the gimbal (10), the force transmission seat (9) and the thrust chamber (1) to the frame (11) in sequence through bolts, and then connecting the turbo pump (2) to the frame (11) through the oxygen inlet conduit (13) and the turbo pump connecting bracket (12); S3) installing the two sets of servo mechanisms (15) between the frame (11) and the thrust chamber (1) via hinge connection; S4) connecting the turbo pump (2) to the thrust chamber (1) via the oxygen pump rear pipeline (7) and the fuel pump rear pipeline (8); S5) connecting the interfaces of the modules and the thrust chamber (1), the turbo pump (2), the generator (3) and other components through the final assembly duct (14) to form a complete engine system.

9. A method for assembling a modular open liquid rocket engine based on a post-pump metal hose as claimed in claim 7, comprising the following steps: S1) assembling the gas cylinder module (4), the solenoid valve module (5) and the ignition agent tank module (6) in sequence, and connecting the gas cylinder module (4), the solenoid valve module (5) and the ignition agent tank module (6) in sequence and installing them on the frame (11) by bolts; S2) firstly connect the turbo pump (2) to the frame (11) through the oxygen inlet conduit (13) and the turbo pump connecting bracket (12), and then connect the gimbal (10), the force transmission seat (9) and the thrust chamber (1) to the frame (11) in sequence through bolts; S3) installing the two sets of servo mechanisms (15) between the frame (11) and the thrust chamber (1) via hinge connection; S4) connecting the turbo pump (2) to the thrust chamber (1) via the oxygen pump rear pipeline (7) and the fuel pump rear pipeline (8); S5) connecting the interfaces of the modules and the thrust chamber (1), the turbo pump (2), the generator (3) and other components through the final assembly duct (14) to form a complete engine system.

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