Multifunction pump post swing liquid rocket engine single machine rack

Abstract

The present application relates to a kind of multifunctional pump after swing liquid rocket engine single machine rack, two main force beams and two auxiliary force beams, beam is welded into lower transmission frame between the two. Four upper joints are welded into upper transmission frame with four upper connecting beams. Four main force rods are welded with upper and lower transmission frames respectively. Two servo supports are provided, as the upper fulcrum of servo mechanism, can meet the bidirectional swing demand of liquid rocket engine. A pair of turbine pump support seats are symmetrically arranged with one of the servo supports. A pair of turbine pump auxiliary ears are arranged on the same side of the turbine pump support seat. Turbine pump support seat and turbine pump auxiliary ear are jointly responsible for connection with turbine pump, realize the stable fixed support of turbine pump. Main force beam is connected with lower end transmission assembly, upper joint is connected with rocket body or multi-machine rack, realize the thrust transmission function of engine.

Description

Technical Field

[0001] This invention belongs to the field of engine design technology and relates to a multifunctional pump-post-swing liquid rocket engine single-unit frame. Background Technology

[0002] The single-unit layout of a post-pump glide liquid rocket engine is often based on a single-unit frame. As the core component of the post-pump glide engine layout, the single-unit frame not only has the function of transmitting engine thrust load, but also needs to provide 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 a post-pump sway liquid rocket engine, the two propellant delivery mains for the propellant and oxidizer are typically arranged in a ring around the thrust chamber. The inner and outer rings facilitate radial flow of propellant into the thrust chamber head. This layout does not occupy upstream space of the thrust chamber head, allowing for direct connection of the engine sway device to the thrust chamber head. However, its disadvantage is that this layout increases the engine's radial envelope size, which is unfavorable for multiple engine configurations within the rocket's rated diameter. Besides the above layout, another option is to have one oxidizer delivery pipe arranged axially upstream of the thrust chamber head, while the other remains in a ring around the thrust chamber. This layout minimizes the engine's radial envelope size, but when transmitting thrust from the thrust chamber to upstream structures, the design of the force transmission structure must avoid interference with the upstream piping structure of the thrust chamber head, significantly increasing the design difficulty of the frame and other force transmission structures.

[0004] Furthermore, since liquid rockets often require multiple engines to provide thrust, and ground tests typically only involve individual engine firing, the connection structures between the engine and the rocket body, and between the engine and the test stand, differ between in-flight and ground testing states. In in-flight, a multi-engine frame structure is usually used, while in ground testing, a single-engine frame structure is employed. This difference in frame structure leads to variations in the servo support structure for the servo mechanism. For example, in the multi-engine frame structure used in in-flight, the servo support structure providing the upper support point for the servo mechanism is usually integrated into the multi-engine frame design. However, in ground testing, a separate test stand or test fixture is typically designed to provide the upper support point for the servo mechanism. Regardless of whether the upper support point for the servo mechanism is placed on the multi-engine frame or the test stand, it is detrimental to the deformation coordination between the servo support structure and the single-engine frame. This can easily cause significant systemic thrust line misalignment of the engine, thus affecting the rocket's attitude control. Furthermore, the differences between the flight state and the ground test state of the rocket will result in significant differences in the layout and installation of engine components on the frame, 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, meet the axial oxygen intake structure layout of the thrust chamber head of the pump-driven engine, reduce the systematic skew of the thrust line, and minimize the difference in the single-engine structural state between the onboard flight state and the ground test state, it is urgent to design a high-performance pump-driven liquid rocket engine frame. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a multifunctional pump-post-swing liquid rocket engine single-unit frame.

[0007] The solution of the present invention is:

[0008] A multifunctional pump-back-swing liquid rocket engine single-unit frame includes a main load-bearing rod, a main load-bearing beam, a secondary load-bearing beam, an upper joint, a turbopump main support structure, a multifunctional spherical joint, a servo support structure, and an upper connecting beam.

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

[0010] There are two sets of servo support structures, located in quadrants III and IV respectively. Each set 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 set of servo support structures includes a servo mounting bracket, two upper servo support rods, and two lower servo support rods. The outer ends of the two upper servo support rods and the two lower servo support rods are connected to the servo mounting bracket. The inner ends of the two upper servo support rods are connected one-to-one with the two multi-functional ball joints on the corresponding vertical plane. The inner ends of the two lower servo support rods are connected one-to-one with the two upper joints on the corresponding vertical plane.

[0011] There are two sets of main support structures for the turbopump. Each set includes a turbopump support seat and a turbopump support rod. The two sets of main support structures for the turbopump are located in the I quadrant and are symmetrical about the XZ plane. The two sets of main support structures for the turbopump correspond one-to-one with the two main load-bearing rods in the I quadrant. That is, the inner end of the turbopump support seat is connected to the multi-functional ball joint, the body of the turbopump support seat is connected to the lower end of the turbopump support rod, and the upper end of the turbopump support rod is connected to the upper joint that is fixed to the corresponding main load-bearing rod.

[0012] With the center of the lower quadrilateral force transmission frame as the origin, the direction perpendicular to the lower surface of the force transmission frame is defined as the Z-axis, and the direction pointing to the upper connector is defined as +Z; the direction pointing to the turbine pump support is defined as +X; and the direction pointing to the servo mounting base 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 form the thrust transmission structure; wherein, the main load-bearing beam is bolted to the downstream engine swing device, and the upper joint is bolted to the upstream engine test frame or the rocket body docking frame.

[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 thrust chamber head of the pump-driven liquid rocket engine.

[0015] Preferably, the engine thrust is transmitted from the body of the two main load-bearing beams to both ends of the main load-bearing beams and further along the four main load-bearing rods to the four upper joints, thus forming the main force transmission path of the engine thrust and realizing the efficient transmission of engine thrust under the pump rear swing layout.

[0016] Preferably, the fulcrums of the two sets of servo support structures are located in the XZ plane and the YZ plane, respectively.

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

[0018] Preferably, the multi-functional spherical joint has a cylindrical through hole on the basis of a spherical topology to pass through the main load-bearing rod, and a cylindrical through hole or irregular through hole on the side of the multi-functional spherical joint to insert the servo lower support rod or turbine pump support seat for easy welding positioning.

[0019] Preferably, the position of the multi-functional ball joint can be adjusted along the axial direction of the main load-bearing rod during the design phase.

[0020] Preferably, the multi-functional ball joint is designed with a lug structure to assist in the installation of various support plate structures.

[0021] Preferably, the main load-bearing beam has an "I" shaped cross section; the main load-bearing beam has multiple irregularly shaped reinforcing ribs; each main load-bearing beam has two force transmission component connection holes at its lower end; and the main load-bearing beam has a connecting seat at its upper end that connects to the main load-bearing rod.

[0022] Preferably, the main cross-section of the secondary load-bearing beam is I-shaped; multiple weight-reducing holes are provided on the secondary load-bearing beam.

[0023] Preferably, the main cross-section of the upper connecting beam is "T" shaped; the upper connecting beam is provided with multiple weight-reducing holes and auxiliary installation holes.

[0024] The advantages of this invention compared to the prior art are:

[0025] (1) The present invention integrates the thrust transmission structure, servo support structure, turbopump main support structure and turbopump auxiliary support installation structure into a single frame, which enhances the functionality of the structure, improves the utilization rate of the structure, and meets the structural adaptability requirements of the layout scheme of arranging propellant delivery pipes upstream of the thrust chamber head of the pump-back swing liquid rocket engine for the single frame.

[0026] (2) This invention provides a structural basis for the layout design and component assembly of the engine around a single frame. By integrating the design of the turbopump support structure and the servo support structure, most of the components in the engine can be assembled based on a single frame. In particular, the servo support structure provides an mounting fulcrum for the servo mechanism, thereby enabling the engine module itself to have bidirectional swing capability. There is no need to set up additional servo mechanism mounting support structures to consider the differences between the flight state and the ground test state. This is beneficial to maintaining the consistency of the engine single-unit structural state between the flight state and the ground test state, and greatly improves the modularity level of the engine single unit.

[0027] (3) In this invention, the servo support structure and the thrust transmission structure are connected by a multifunctional ball joint, which is conducive to promoting the deformation coordination between the servo support structure and the thrust transmission structure, and thus helps to reduce the systematic thrust line deviation 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 turbopump, the present invention also provides an auxiliary support installation structure. The turbopump is reliably connected to the single engine frame through the main support and the auxiliary support, which helps to suppress the transmission of turbopump vibration to other engine components. Attached Figure Description

[0029] Figure 1 A schematic diagram of the single-unit frame structure of a multi-functional pump-driven liquid rocket engine.

[0030] Figure 2 Top view of the single-unit frame of a multi-functional pump-driven liquid rocket engine;

[0031] Figure 3 A schematic diagram of a thrust transfer structure in the form of a hexahedral frame;

[0032] Figure 4 This is a schematic diagram of a multifunctional ball joint structure. Detailed Implementation

[0033] The invention will now be further described with reference to the accompanying drawings.

[0034] This invention provides a multifunctional frame structure for a pump-driven liquid rocket engine with a thrust chamber head oxygen inlet layout. The frame structure integrates a thrust transmission structure, a servo support structure, a turbopump main support structure, a turbopump auxiliary support installation structure, and a spherical load-bearing structure that also functions as a support rod and support plate for positioning and installation, and as a servo support for stiffness design and adjustment.

[0035] This invention discloses a multifunctional pump-driven liquid rocket engine single-unit frame, comprising 12 types of structural components, including a main load-bearing rod 1, a main load-bearing beam 2, a secondary load-bearing beam 3, an upper connector 4, a turbopump support 5, a turbopump support rod 6, a multifunctional spherical connector 7, a servo mounting bracket 8, a servo upper support rod 9, a servo lower support rod 10, an upper connecting beam 11, and a turbopump auxiliary support mounting lug 12. Figure 1 .

[0036] There are two main load-bearing beams 2, symmetrically distributed about the XZ plane; and two secondary load-bearing beams 3, symmetrically distributed about the YZ plane. The main load-bearing beams 2 and secondary load-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, forming a quadrilateral force transmission frame at the upper end of the frame. There are four main load-bearing rods 1, with their lower ends connected to the ends of the main load-bearing beams 2 and their upper ends connected to the upper joints 4. There are four multi-functional ball joints 7, installed on the body of the main load-bearing rods 1.

[0037] There are two sets of servo support structures, located in quadrants III and IV respectively. Each set 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 set of servo support structures includes a servo mounting bracket 8, two upper servo support rods 9, and two lower servo support rods 10. The outer ends of the two upper servo support rods 9 and the two lower servo support rods 10 are connected to the servo mounting bracket 8. The inner ends of the two upper servo support rods 9 are connected one-to-one with the two multi-functional ball joints 7 in the corresponding vertical plane. The inner ends of the two lower servo support rods 10 are connected one-to-one with the two upper joints in the corresponding vertical plane.

[0038] There are two sets of main support structures for the turbopump. Each set includes a turbopump support seat 5 and a turbopump support rod 6. The two sets of main support structures for the turbopump are located in the I quadrant and are symmetrical about the XZ plane. The two sets of main support structures for the turbopump correspond one-to-one with the two main load-bearing rods in the I quadrant. That is, the inner end of the turbopump support seat 5 is connected to the multi-functional ball joint 7, the body of the turbopump support seat 5 is connected to the lower end of the turbopump support rod 6, and the upper end of the turbopump support rod 6 is connected to the upper joint 4 that is fixed to the corresponding main load-bearing rod.

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

[0040] This invention comprises a thrust transmission structure consisting of a main load-bearing beam 2, a secondary load-bearing beam 3, a main load-bearing rod 1, an upper joint 4, and an upper connecting beam 11, as shown below. Figure 2 The main load-bearing beam can be bolted to the downstream engine swing device, and the upper joint can be bolted to the upstream engine test frame or the rocket body docking frame.

[0041] 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 thrust chamber head of the pump-driven liquid rocket engine.

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

[0043] The hexahedral frame-type thrust transmission structure not only has the ability to bear the axial thrust load of the engine, but also the ability to bear the lateral load generated by the engine when it swings at a large angle.

[0044] The fulcrums of the two servo structures are located in the XZ and YZ planes, respectively.

[0045] This invention can withstand not only the weight of the turbopump itself, but also the lateral and longitudinal overloads caused by the carrier's movement, as well as the turbine exhaust thrust generated by the turbopump's exhaust pipe. Furthermore, the main support structure of the turbopump can limit the deformation caused by the aforementioned loads.

[0046] There are two auxiliary support mounting lugs 12 for the turbopump, located on the same side as the turbopump support structure, both in quadrant I. These lugs provide the mounting position for the auxiliary support structure. By installing the auxiliary support structure on the basis of the main turbopump support structure, the auxiliary support lugs can effectively limit the radial displacement of the turbopump while appropriately releasing its axial displacement, thus helping to suppress vibration transmission.

[0047] The multi-functional spherical joint 7, based on a spherical topology, has a cylindrical through-hole to allow the main load-bearing rod 1 to pass through. Cylindrical through-holes or irregularly shaped through-holes are also provided on the side of the joint to allow insertion of the servo lower support rod 10 or the turbine pump support seat 5 for easy welding and positioning. Figure 4A multi-functional spherical joint connects the servo lower support rod and the turbopump support to the main load-bearing rod. While coupling the servo support structure and the thrust transmission structure, the position of the multi-functional spherical joint 7 can be adjusted along the axial direction of the main load-bearing rod during the design phase, thereby adjusting the servo support stiffness without changing the cross-sectional dimensions of the upper and lower support rods. Since the servo support stiffness and the thrust transmission structure stiffness together determine the systematic skewness of the engine thrust line, adjusting the position of the multi-functional spherical joint and thus the servo support stiffness is beneficial for the deformation coordination between the servo support structure and the thrust transmission structure, thereby optimizing the systematic skewness of the engine thrust line.

[0048] In addition to connecting the servo lower support rod 9 and the turbine pump support, the multi-functional ball joint 7 can also be used to assist in the installation of various support plate structures.

[0049] The main load-bearing beam 2 has an "I"-shaped cross-section; it has multiple irregularly shaped reinforcing ribs; there are two force transmission component connection holes at the lower end of the main load-bearing beam 2; and a connecting seat for connecting to the main load-bearing rod 1 is located at the upper end of the main load-bearing beam 2. The secondary load-bearing beam 3 has an "I"-shaped cross-section; it has multiple weight-reducing holes. The upper connecting beam 10 has a "T"-shaped cross-section; it has multiple weight-reducing holes. All parts are made of 30CrMnSiA material.

[0050] In this invention, two main load-bearing beams and two secondary load-bearing beams are welded together 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, arranged at 90°. The servo supports serve as the upper fulcrum of the servo mechanism, which can meet the bidirectional swing requirements of the liquid rocket engine. A pair of turbopump support seats are arranged symmetrically with one of the servo supports. A pair of turbopump auxiliary lugs are arranged on the same side of the turbopump support. The turbopump support and the turbopump auxiliary lugs are jointly responsible for connecting to the turbopump, realizing the stable fixed support of the turbopump. The main load-bearing beams are connected to the lower force transmission assembly, and the upper joints are connected to the rocket body or multi-engine frame to realize the thrust transmission function of the engine. This invention provides a multifunctional frame structure for a pump-driven liquid rocket engine with a thrust chamber head oxygen inlet layout. The frame structure integrates a thrust transmission structure, a servo support structure, a turbopump main support structure, a turbopump auxiliary support installation structure, and a spherical load-bearing structure that also functions as a support rod and support plate for positioning and installation, and as a servo support for stiffness design and adjustment.

[0051] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A multifunctional pump-driven liquid rocket engine single-unit frame, characterized in that: It includes the main load-bearing rod (1), the main load-bearing beam (2), the secondary load-bearing beam (3), the upper joint (4), the turbine pump main support structure, the multi-functional ball joint (7), the servo support structure, and the upper connecting beam (11); Two main load-bearing beams (2) and two secondary load-bearing beams (3) are connected to form a quadrilateral force transmission frame at the lower end of the frame. The two main load-bearing beams (2) are symmetrically distributed about the XZ plane, and the two secondary load-bearing beams (3) are symmetrically distributed about the YZ plane. Four upper connecting beams (11) are connected by four upper joints (4) to form a quadrilateral force transmission frame at the upper end of the frame. Each main load-bearing beam (2) has a main load-bearing rod (1) installed at both ends. The upper ends of the four main load-bearing rods (1) are connected to the corresponding upper joints (4). Multifunctional ball joints (7) correspond one-to-one with the main load-bearing rods (1). Each multifunctional ball 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 sets of servo support structures, located in quadrants III and IV respectively. Each set of servo support structures corresponds to a vertical plane composed of an upper connecting beam, a main bearing rod, and a main bearing beam. Each set of servo support structures includes a servo mounting bracket (8), two upper servo support rods (9) and two lower servo support rods (10). The outer ends of the two upper servo support rods (9) and the two lower servo support rods (10) are connected to the servo mounting bracket (8). The inner ends of the two upper servo support rods (9) are connected one-to-one with the two multi-functional ball joints (7) of the corresponding vertical plane. The inner ends of the two lower servo support rods (10) are connected one-to-one with the two upper joints of the corresponding vertical plane. There are two sets of main support structures for the turbopump. Each set includes a turbopump support seat (5) and a turbopump support rod (6). The two sets of main support structures for the turbopump are located in the I quadrant and are symmetrical about the XZ plane. The two sets of main support structures for the turbopump correspond one-to-one with the two main load-bearing rods in the I quadrant. That is, the inner end of the turbopump support seat (5) is connected to the multi-functional ball joint (7), the body of the turbopump support seat (5) is connected to the lower end of the turbopump support rod (6), and the upper end of the turbopump support rod (6) is connected to the upper joint (4) that is fixed to the corresponding main load-bearing rod. With the center of the lower quadrilateral force transmission frame as the origin, the direction perpendicular to the lower surface of the force transmission frame is defined as the Z-axis, and the direction pointing to the upper connector is +Z; the direction pointing to the turbine pump support is defined as +X; and the direction pointing to the servo mounting base (8) is defined as +Y.

2. The multifunctional pump-following liquid rocket engine single-unit 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 the thrust transmission structure; among them, the main load-bearing beam is connected to the downstream engine swing device by bolts, and the upper joint is connected to the upstream engine test frame or the rocket body docking frame by bolts.

3. The multifunctional pump-following liquid rocket engine single-unit frame according to claim 2, characterized in that: 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 propellant delivery pipes upstream of the thrust chamber head of the pump-driven liquid rocket engine.

4. The multifunctional pump-following liquid rocket engine single-unit frame according to claim 2, characterized in that: The engine thrust is transmitted through the body of 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), thus forming the main force transmission path of the engine thrust and realizing the efficient transmission of engine thrust under the pump rear swing layout.

5. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The fulcrums of the two sets of servo support structures are located in the XZ plane and the YZ plane, respectively.

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

7. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The multi-functional spherical joint (7) is based on a spherical topology and has a cylindrical through hole to pass through the main load-bearing rod (1). The multi-functional spherical joint has a cylindrical through hole or an irregular through hole on its side to insert the servo lower support rod (10) or the turbine pump support seat (5) for easy welding positioning.

8. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The position of the multi-functional ball joint (7) can be adjusted along the axial direction of the main load-bearing rod during the design phase.

9. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The multi-functional ball joint (7) is designed with a lug structure to assist in the installation of various support plate structures.

10. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The main load-bearing beam (2) has an I-shaped cross section; the main load-bearing beam (2) has multiple irregular reinforcing ribs; each main load-bearing beam (2) has two force transmission component connection holes at its lower end; the main load-bearing beam (2) has a connecting seat at its upper end that connects to the main load-bearing rod (1).

11. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The main cross section of the secondary load-bearing beam (3) is "I" shaped; multiple weight-reducing holes are provided on the secondary load-bearing beam (3).

12. A multifunctional pump-following liquid rocket engine single-unit frame according to claim 1, characterized in that: The main cross section of the upper connecting beam (11) is "T" shaped; multiple weight reduction holes and auxiliary installation holes are provided on the upper connecting beam (11).

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