Single rack of multifunctional pump rear-swing liquid rocket engine

Abstract

The invention relates to a multifunctional pump rear swing liquid rocket engine single-machine rack which is characterized in that two main force bearing beams and two auxiliary force bearing beams are welded to form a lower force transmission frame; the four upper connectors and the four upper connecting beams are welded to form an upper force transmission frame. The four main force bearing rods are welded to the upper force transmission frame and the lower force transmission frame respectively. The two servo supports are arranged to serve as upper fulcrums of the servo mechanism, and the bidirectional swing requirement of the liquid rocket engine can be met. And a pair of turbine pump supporting seats are symmetrically arranged with one of the servo supports. And a pair of turbine pump auxiliary support lugs is arranged on the same side of the turbine pump support. The turbine pump support and the turbine pump auxiliary supporting lug are jointly responsible for being connected with the turbine pump, and stable fixed supporting of the turbine pump is achieved. The main force bearing beam is connected with the lower end force transmission assembly, the upper connector is connected with a rocket body or a multi-machine rack, and the thrust transmission function of the engine is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of engine design and relates to a single-machine frame of a multifunctional pump-swinging liquid rocket engine. Background Art

[0002] The single-unit layout of a pump-swing liquid rocket engine is often based on a single-unit frame. As the core component of the pump-swing engine layout, the single-unit frame not only has the function of transmitting the engine thrust load, but also provides a reliable support structure for the turbopump. In addition, it also needs to take into account the layout and installation of other engine components.

[0003] In the overall layout of the pump-back swing liquid rocket engine structure, the two main propellant delivery pipes of the fuel and oxidizer are usually arranged around the thrust chamber in a circumferential manner. The inner and outer layers of the circumferential pipes facilitate the propellant to flow radially into the thrust chamber head. This pipe layout does not occupy the upstream space of the thrust chamber head, which facilitates the engine swing device to be directly connected to the thrust chamber head. However, its disadvantage is that this pipe layout will increase the radial envelope size of the engine, which is not conducive to the layout of multiple engines within the rated diameter range of the rocket body. In addition to the above layout, the layout method can also be adopted in which one of the oxidizer delivery pipe and the fuel delivery pipe is arranged axially upstream of the thrust chamber head, and the other is still arranged around the thrust chamber in a circumferential manner. The advantage of this layout method is that the radial envelope size of the engine can be reduced as much as possible, but when the thrust chamber transmits thrust to the upstream structure, the design of the force transmission structure needs to consider avoiding interference with the upstream pipe structure of the thrust chamber head, which greatly increases the design difficulty of the force transmission structure such as the frame.

[0004] In addition, since liquid rockets often require multiple engines to provide thrust, and during ground tests, only a single engine test is usually carried out, this results in inconsistent connection structures between the engine and the rocket body, and between the engine and the test bench in the rocket flight state and the ground test state. That is, a multi-machine frame structure is usually used for connection in the rocket flight state, while a single-machine frame structure is used in the ground test state. The difference in frame structure form leads to differences in the servo support structure for installing the servo mechanism. For example, for the multi-machine frame structure used in the rocket flight state, the servo support structure providing the upper fulcrum of the servo mechanism is usually integrated with the multi-machine frame, while in the ground test state, a test frame or test fixture is usually designed separately to provide the upper fulcrum of the servo mechanism. However, whether the upper fulcrum of the servo mechanism is set on the multi-machine frame or the test frame, it is not conducive to the deformation coordination of the servo support structure and the single-machine frame, which can easily cause a large deviation of the engine's systematic thrust line and affect the rocket body attitude control. In addition, due to the difference between the flight state on the arrow and the ground test state, the layout and installation forms of the engine components on the frame will also vary greatly, which is not conducive to the convenience and standardization of engine assembly and maintenance.

[0005] In summary, in order to minimize the radial envelope size of the engine as much as possible, meet the axial oxygen inlet structure layout of the thrust chamber head of the pump-swing engine, reduce the systematic deviation of the thrust line, and narrow the difference in the single-unit structural state of the engine between the flight state on the arrow and the ground test state, it is urgent to design a high-performance pump-swing liquid rocket engine frame. Summary of the invention

[0006] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and provide a single-machine frame of a multifunctional pump-back-swinging liquid rocket engine.

[0007] The solution of the present invention is:

[0008] A multifunctional pump-backward swing liquid rocket engine stand-alone frame, comprising a main load-bearing rod, a main load-bearing beam, a secondary load-bearing beam, an upper joint, a main support structure of a turbine pump, a multifunctional spherical joint, a servo support structure, and an upper connecting beam;

[0009] Two main bearing beams and two auxiliary bearing beams are connected to form a quadrilateral force transmission frame at the lower end of the frame, and the two main bearing beams are symmetrically distributed about the XZ plane, and the two auxiliary bearing beams are symmetrically distributed about the YZ plane; four upper connecting beams are connected through four upper joints to form a quadrilateral force transmission frame at the upper end of the frame; a main bearing rod is installed at both ends of each main bearing beam, and the upper ends of the four main bearing rods are connected to the corresponding upper joints; the multifunctional spherical joints correspond to the main bearing rods one by one, and each multifunctional spherical joint passes through the corresponding main bearing rod body and is fixedly connected to the corresponding main bearing rod;

[0010] There are two groups of servo support structures, which are respectively located in quadrants III and IV, that is, each group of servo support structures corresponds to a vertical surface composed of an upper connecting beam, a main load-bearing rod and a main load-bearing beam; each group of servo support structures includes a servo mounting support, two servo upper support rods and two servo lower support rods, the outer ends of the two servo upper support rods and the outer ends of the two servo lower support rods are connected to the servo mounting support, the inner ends of the two servo upper support rods are connected to two multifunctional spherical joints of the corresponding vertical surface in a one-to-one correspondence, and the inner ends of the two servo lower support rods are connected to two upper joints of the corresponding vertical surface in a one-to-one correspondence;

[0011] There are two groups of main support structures of the turbine pump, each group includes a turbine pump support seat and a turbine pump support rod, the two groups of main support structures of the turbine pump are located in quadrant I and are symmetrical about the XZ plane, and the two groups of main support structures of the turbine pump correspond one to one with the two main load-bearing rods in quadrant I, that is, the inner end of the turbine pump support seat is connected to the multifunctional spherical joint, the body of the turbine pump support seat is connected to the lower end of the turbine pump support rod, and the upper end of the turbine pump support rod is connected to the upper joint fixedly connected to the corresponding main load-bearing rod;

[0012] The center of the lower quadrilateral force transmission frame is taken as the origin, and the direction perpendicular to the lower surface of the force transmission frame is defined as the coordinate axis Z axis, and the direction pointing to the upper joint is +Z; the opposite direction pointing to the turbine pump support is defined as +X; and the direction pointing to the servo mounting seat is defined as +Y.

[0013] Preferably, the main load-bearing beam, the secondary load-bearing beam, the main load-bearing rod, the upper joint and the upper connecting beam together constitute a thrust transmission structure; wherein the main load-bearing beam is connected to the downstream engine rocking device by bolts, and the upper joint is connected to the upstream engine test frame or the rocket body docking frame by bolts.

[0014] Preferably, the basic structural form of the thrust transfer structure is a hexahedral frame structure, which meets the adaptability requirements of the layout scheme of arranging the propellant delivery pipe upstream of the head of the thrust chamber of the pump-backward swing liquid rocket engine.

[0015] Preferably, the engine thrust is transmitted through the bodies of the two main load-bearing beams to the two ends of the main load-bearing beams and further along the four main load-bearing rods to the four upper joints, thereby forming a main force transmission path for the engine thrust and realizing efficient transmission of the engine thrust under the pump-back swing layout.

[0016] Preferably, the supporting points on the two groups of servo support structures are respectively located in the XZ plane and the YZ plane.

[0017] Preferably, it also includes two turbine pump auxiliary support mounting ears, each of which is arranged on the same side as the corresponding turbine pump main support structure, both are located in quadrant I, and are connected to the lower end surface of the main load-bearing beam; the turbine pump auxiliary support mounting ears are used to install the turbine pump auxiliary support structure.

[0018] Preferably, the multifunctional spherical joint has a cylindrical through hole on the basis of the spherical topology to pass the main load-bearing rod, and a cylindrical through hole or a special-shaped through hole is opened on the side of the multifunctional spherical joint to insert the servo lower support rod or the turbine pump support seat to facilitate welding positioning.

[0019] Preferably, the position of the multifunctional spherical joint can be adjusted along the axial direction of the main bearing rod during the design stage.

[0020] Preferably, a lug structure is designed on the multifunctional spherical joint to assist in the installation of various types of supporting plate structures.

[0021] Preferably, the main cross-section of the main load-bearing beam is an "I" shape; there are multiple special-shaped reinforcement ribs on the main load-bearing beam; there are two force transmission component connection holes at the lower end of each main load-bearing beam; and there is a connecting seat connected to the main load-bearing rod at the upper end of the main load-bearing beam.

[0022] Preferably, the main body cross-section of the auxiliary load-bearing beam is an "I" shape; and a plurality of weight-reducing holes are provided on the auxiliary load-bearing beam.

[0023] Preferably, the main body cross-section of the upper connecting beam is "T"-shaped; a plurality of weight-reducing holes and auxiliary installation holes are arranged on the upper connecting beam.

[0024] The beneficial effects of the present invention compared with the prior art are:

[0025] (1) The present invention integrates the thrust transmission structure, the servo support structure, the main support structure of the turbopump, and the auxiliary support installation structure of the turbopump into a single-machine frame, thereby enhancing the functionality of the structure and improving the utilization rate of the structure, thereby meeting the structural adaptability requirements of the layout scheme of arranging the propellant delivery pipe upstream of the head of the thrust chamber of a pump-post-swing liquid rocket engine for a single-machine frame.

[0026] (2) The present invention provides a structural basis for the layout design and assembly of components of the engine around a single-machine frame. By integrating the design of a turbine pump support structure and a servo support structure, most of the components in the engine can be assembled based on a single-machine frame. In particular, the servo support structure provides a mounting fulcrum for the servo mechanism, so that the engine single-machine module itself has a two-way swing capability. There is no need to set up other servo mechanism mounting support structures to consider the difference between the flight state on the arrow and the ground test state. This is conducive to maintaining the consistency of the engine single-machine structural state in the flight state on the arrow and the ground test state, and greatly improves the modularization level of the engine single-machine.

[0027] (3) In the present invention, the servo support structure and the thrust transmission structure are connected by a multifunctional spherical joint, which is beneficial to promoting the deformation coordination between the servo support structure and the thrust transmission structure, and further beneficial to reducing the systematic thrust line deflection determined by the stiffness of the thrust transmission structure and the stiffness of the servo support structure.

[0028] (4) In addition to providing a main support structure for the turbine pump, the present invention also provides an auxiliary support mounting structure, which reliably connects the turbine pump to a single-machine frame through the main support and the auxiliary support, thereby helping to suppress the transmission of turbine pump vibration to other engine components. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the single-unit frame structure of a multifunctional pump-swinging liquid rocket engine;

[0030] Figure 2 It is a top view of a single-unit frame of a multi-functional pump-swinging liquid rocket engine;

[0031] Figure 3 It is a schematic diagram of a thrust transmission structure in the form of a hexahedral frame;

[0032] Figure 4 It is a schematic diagram of the multifunctional spherical joint structure. DETAILED DESCRIPTION

[0033] The present invention will be further described below in conjunction with the accompanying drawings.

[0034] The present invention provides a multifunctional frame structure suitable for a pump-backward swing liquid rocket engine with an oxygen inlet layout at the head of a thrust chamber, which integrates a thrust transmission structure, a servo support structure, a main support structure of a turbopump, an auxiliary support installation structure of a turbopump, and a spherical bearing structure with the functions of positioning and installing support rods and support plates and designing and adjusting the stiffness of a servo support.

[0035] The present invention discloses a multifunctional pump-backward swing liquid rocket engine stand-alone frame, comprising a main bearing rod 1, a main bearing beam 2, a secondary bearing beam 3, an upper joint 4, a turbine pump support seat 5, a turbine pump support rod 6, a multifunctional spherical joint 7, a servo mounting support 8, a servo upper support rod 9, a servo lower support rod 10, an upper connecting beam 11, a turbine pump auxiliary support mounting lug 12, and a total of 12 types of structural components, such as Figure 1 .

[0036] There are two main bearing beams 2, which are symmetrically distributed about the XZ plane; there are two auxiliary bearing beams 3, which are symmetrically distributed about the YZ plane; the main bearing beams 2 and the auxiliary bearing beams 3 are connected to form a quadrilateral force transmission frame at the lower end of the frame. Four upper connecting beams 11 are connected to four upper joints 4 to form a quadrilateral force transmission frame at the upper end of the frame. There are four main bearing rods 1, the lower end is connected to the end of the main bearing beam 2, and the upper end is connected to the upper joint 4. There are four multifunctional spherical joints 7, which are installed on the body of the main bearing rod 1.

[0037] There are two groups of servo support structures, which are located in quadrants III and IV respectively, that is, each group of servo support structures corresponds to a vertical plane composed of an upper connecting beam, a main load-bearing rod and a main load-bearing beam; each group of servo support structures includes a servo mounting support 8, two servo upper support rods 9 and two servo lower support rods 10, the outer ends of the two servo upper support rods 9 and the outer ends of the two servo lower support rods 10 are connected to the servo mounting support 8, the inner ends of the two servo upper support rods 9 are connected one-to-one with the two multifunctional spherical joints 7 in the corresponding vertical plane, and the inner ends of the two servo lower support rods 10 are connected one-to-one with the two upper joints in the corresponding vertical plane.

[0038] There are two groups of main supporting structures of the turbine pump, each group includes a turbine pump supporting seat 5 and a turbine pump supporting rod 6. The two groups of main supporting structures of the turbine pump are located in quadrant I and are symmetrical about the XZ plane. The two groups of main supporting structures of the turbine pump correspond one-to-one to the two main load-bearing rods in quadrant I, that is, the inner end of the turbine pump supporting seat 5 is connected to the multifunctional spherical joint 7, the body of the turbine pump supporting seat 5 is connected to the lower end of the turbine pump supporting rod 6, and the upper end of the turbine pump supporting rod 6 is connected to the upper joint 4 fixedly connected to the corresponding main load-bearing rod.

[0039] The center of the lower quadrilateral force transmission frame is defined as the origin, the direction perpendicular to the lower surface of the force transmission frame is defined as the coordinate axis Z axis, the direction pointing to the upper joint is defined as +Z; the opposite direction pointing to the turbine pump support is defined as +X; and the direction pointing to the servo mounting seat (8) is defined as +Y.

[0040] The present invention comprises a main bearing beam 2, a secondary bearing beam 3, a main bearing rod 1, an upper joint 4 and an upper connecting beam 11 to form a thrust transmission structure. Figure 2 Among them, the main load-bearing beam can be connected to the downstream engine swing device by bolts, and the upper joint can be connected to the upstream engine test frame or the rocket body docking frame by bolts.

[0041] The basic structural form of the thrust transmission structure is a hexahedral frame structure, which meets the adaptability requirements of the layout scheme of arranging the propellant delivery pipe upstream of the head of the thrust chamber of the pump-backward swing liquid rocket engine.

[0042] The engine thrust is mainly transmitted through the two main load-bearing beams 2 to the two ends of the main load-bearing beams 2 and further along the four main load-bearing rods 1 to the four upper joints 4, thereby forming the main force transmission path of the engine thrust and realizing the efficient transmission of the engine thrust under the pump-back swing layout.

[0043] The hexahedral frame-type thrust transfer structure not only has the bearing capacity of the engine thrust load along the axial direction, but also has the bearing capacity of the lateral load generated when the engine swings at a large angle.

[0044] The supporting points on the two sets of servo structures are located in the XZ plane and the YZ plane respectively.

[0045] The present invention can not only bear the deadweight of the turbo pump, but also bear the lateral and longitudinal overloads of the turbo pump caused by the maneuvering of the carrier, and the turbine exhaust thrust generated by the turbo pump exhaust pipe. In addition, the main support structure of the turbo pump can limit the deformation caused by the above loads.

[0046] There are two auxiliary support mounting ears 12 of the turbine pump, which are arranged on the same side as the turbine pump support structure and are both located in quadrant I. This provides an installation position for the auxiliary support structure of the turbine pump. On the basis of the main support structure of the turbine pump, the auxiliary support structure of the turbine pump is installed by the auxiliary support mounting ears of the turbine pump, which can limit the radial displacement of the turbine pump while appropriately releasing the axial displacement of the turbine pump, and help to suppress the vibration transmission of the turbine pump.

[0047] The multifunctional spherical joint 7 is based on the spherical topology, and a cylindrical through hole is opened to pass through the main bearing rod 1. A cylindrical through hole or a special-shaped through hole is opened on the side of the joint to insert the servo lower support rod 10 or the turbine pump support seat 5 for easy welding positioning. Figure 4. The servo lower support rod and the turbine pump support seat are connected to the main load-bearing rod through a multifunctional spherical joint. While the functional spherical joint 7 couples the servo support structure and the thrust transfer structure, its position can be adjusted along the axial direction of the main load-bearing rod during the design stage, thereby adjusting the servo support stiffness without changing the cross-sectional dimensions of the servo support upper support rod and the lower support rod. Since the servo support stiffness and the thrust transfer structure stiffness jointly determine the systematic deflection of the engine thrust line, adjusting the servo support stiffness by adjusting the position of the multifunctional spherical joint is beneficial to the deformation coordination of the servo support structure and the thrust transfer structure, thereby optimizing the deflection of the engine thrust line system.

[0048] The multifunctional spherical joint 7 can be used not only to connect the servo lower support rod 9 and the turbine pump support seat, but also the ear structure on the multifunctional spherical joint can be used to assist in the installation of various support plate structures.

[0049] The main cross section of the main bearing beam 2 is an "I" shape; there are multiple special-shaped reinforcement ribs on the main bearing beam 2; there are two force transmission component connection holes at the lower end of the main bearing beam 2; the upper end of the main bearing beam 2 has a connection seat connected to the main bearing rod 1. The main cross section of the auxiliary bearing beam 3 is an "I" shape; multiple weight reduction holes are set on the auxiliary bearing beam 3. The main cross section of the upper connecting beam 10 is a "T" shape; multiple weight reduction holes are set on the upper connecting beam 10. All parts are made of 30CrMnSiA material.

[0050] In the present invention, two main load-bearing beams and two secondary load-bearing beams are welded between the beams to form a lower force transmission frame. Four upper joints are welded to four upper connecting beams to form an upper force transmission frame. Four main load-bearing rods are welded to the upper and lower force transmission frames respectively. Two servo supports are provided, and the two servo supports are arranged at 90 degrees. The servo supports serve as the upper fulcrums of the servo mechanism and can meet the two-way swing requirements of the liquid rocket engine. A pair of turbine pump support seats are arranged symmetrically with one of the servo supports. A pair of turbine pump auxiliary lugs are arranged on the same side of the turbine pump support. The turbine pump support and the turbine pump auxiliary lug are jointly responsible for connecting with the turbine pump to achieve stable fixed support of the turbine pump. The main load-bearing beam is connected to the lower end force transmission assembly, and the upper joint is connected to the rocket body or the multi-machine frame to realize the thrust transmission function of the engine. The present invention provides a multifunctional frame structure suitable for a pump-backward swing liquid rocket engine with an oxygen inlet layout at the head of a thrust chamber, which integrates a thrust transmission structure, a servo support structure, a main support structure of a turbopump, an auxiliary support installation structure of a turbopump, and a spherical bearing structure with the functions of positioning and installing support rods and support plates and designing and adjusting the stiffness of a servo support.

[0051] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A multifunctional pump-backward liquid rocket engine stand-alone frame, characterized in that: It comprises a main bearing rod (1), a main bearing beam (2), a secondary bearing beam (3), an upper joint (4), a main bearing structure of a turbine pump, a multifunctional spherical joint (7), a servo bearing structure, and an upper connecting beam (11); Two main load-bearing beams (2) and two auxiliary load-bearing beams (3) are connected to form a quadrilateral force transmission frame at the lower end of the frame, and the two main load-bearing beams (2) are symmetrically distributed about the XZ plane, and the two auxiliary load-bearing beams (3) are symmetrically distributed about the YZ plane; four upper connecting beams (11) are connected through four upper joints (4) to form a quadrilateral force transmission frame at the upper end of the frame; a main load-bearing rod (1) is installed at both ends of each main load-bearing beam (2), and the upper ends of the four main load-bearing rods (1) are connected to the corresponding upper joints (4); the multifunctional spherical joints (7) correspond to the main load-bearing rods (1) one by one, and each multifunctional spherical joint (7) passes through the body of the corresponding main load-bearing rod (1) and is fixedly connected to the corresponding main load-bearing rod (1); There are two groups of servo support structures, which are respectively located in quadrants III and IV, that is, each group of servo support structures corresponds to a vertical surface composed of an upper connecting beam, a main load-bearing rod and a main load-bearing beam; each group of servo support structures includes a servo mounting support (8), two servo upper support rods (9) and two servo lower support rods (10); the outer ends of the two servo upper support rods (9) and the outer ends of the two servo lower support rods (10) are connected to the servo mounting support (8); the inner ends of the two servo upper support rods (9) are connected to two multifunctional spherical joints (7) of the corresponding vertical surface in a one-to-one correspondence; and the inner ends of the two servo lower support rods (10) are connected to two upper joints of the corresponding vertical surface in a one-to-one correspondence; There are two groups of turbine pump main support structures, each group includes a turbine pump support seat (5) and a turbine pump support rod (6), the two groups of turbine pump main support structures are located in quadrant I and are symmetrical about the XZ plane, and the two groups of turbine pump main support structures correspond to the two main load-bearing rods in quadrant I one by one, that is, the inner end of the turbine pump support seat (5) is connected to the multifunctional spherical joint (7), the body of the turbine pump support seat (5) is connected to the lower end of the turbine pump support rod (6), and the upper end of the turbine pump support rod (6) is connected to the upper joint (4) fixedly connected to the corresponding main load-bearing rod; The center of the lower quadrilateral force transmission frame is defined as the origin, the direction perpendicular to the lower surface of the force transmission frame is defined as the coordinate axis Z axis, the direction pointing to the upper joint is defined as +Z; the opposite direction pointing to the turbine pump support is defined as +X; and the direction pointing to the servo mounting seat (8) is defined as +Y.

2. A multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The main load-bearing beam (2), the secondary load-bearing beam (3), the main load-bearing rod (1), the upper joint (4) and the upper connecting beam (11) together form a thrust transmission structure; wherein the main load-bearing beam is connected to the downstream engine swing device through bolts, and the upper joint is connected to the upstream engine test frame or the rocket body docking frame through bolts.

3. A multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 2, characterized in that: The basic structural form of the thrust transmission structure is a hexahedral frame structure, which meets the adaptability requirements of the layout scheme of arranging the propellant delivery pipe upstream of the head of the thrust chamber of a pump-backward liquid rocket engine.

4. A multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 2, characterized in that: The engine thrust is transmitted through the two main load-bearing beams (2) to the two ends of the main load-bearing beams (2) and further along the four main load-bearing rods (1) to the four upper joints (4), thereby forming a main force transmission path for the engine thrust, and realizing efficient transmission of the engine thrust in the pump-back swing layout.

5. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The upper supporting points of the two groups of servo support structures are respectively located in the XZ plane and the YZ plane.

6. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: It also includes two turbine pump auxiliary support mounting ears (12), each of which is arranged on the same side as the corresponding turbine pump main support structure, both are located in quadrant I, and are connected to the lower end surface of the main load-bearing beam (2); the turbine pump auxiliary support mounting ears are used to install the turbine pump auxiliary support structure.

7. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The multifunctional spherical joint (7) is based on the spherical topology, and a cylindrical through hole is opened to pass through the main load-bearing rod (1). A cylindrical through hole or a special-shaped through hole is opened on the side of the multifunctional spherical joint to insert the servo lower support rod (10) or the turbine pump support seat (5) to facilitate welding positioning.

8. The multifunctional pump-backward-swinging liquid rocket engine stand-alone frame according to claim 1, characterized in that: The position of the multifunctional spherical joint (7) can be adjusted along the axial direction of the main bearing rod during the design stage.

9. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The multifunctional spherical joint (7) is designed with a lug structure for assisting the installation of various supporting plate structures.

10. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The main cross section of the main load-bearing beam (2) is an "I" shape; the main load-bearing beam (2) is provided with a plurality of special-shaped reinforcing ribs; the lower end of each main load-bearing beam (2) is provided with two force transmission component connection holes; the upper end of the main load-bearing beam (2) is provided with a connection seat connected to the main load-bearing rod (1).

11. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The main body cross section of the auxiliary load-bearing beam (3) is an "I" shape; a plurality of weight-reducing holes are arranged on the auxiliary load-bearing beam (3).

12. The multifunctional pump-back-swing liquid rocket engine stand-alone frame according to claim 1, characterized in that: The main cross section of the upper connecting beam (10) is in a "T" shape; a plurality of weight-reducing holes and auxiliary installation holes are arranged on the upper connecting beam (10).

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