A lightweight three-engine parallel engine frame

Abstract

The present invention relates to a lightweight three-machine parallel engine frame, which belongs to the technical field of rocket engines; the axial top ends of the main auxiliary rod and the auxiliary auxiliary rod are connected to a corner point of a hexagonal frame, and the axial bottom ends of the main auxiliary rod and the auxiliary auxiliary rod are connected to a ring plate; three main auxiliary rods and three auxiliary auxiliary rods are distributed at intervals; two ear seats are symmetrically installed on the auxiliary auxiliary rods corresponding to the top of the corner points of the hexagonal frame; two main rods are symmetrically installed on both sides of each main auxiliary rod; two auxiliary rods are symmetrically installed on both sides of each auxiliary auxiliary rod; an upper joint is installed at the lower end of adjacent main rods and auxiliary rods, and is fixedly connected to the top of an external rocket box through the upper joint; the frame of the present invention is used for connecting a rocket engine to a rocket body, and has the characteristics of advanced structure, uniform force, strong bearing capacity, light weight, etc.

Description

Technical Field

[0001] The invention belongs to the technical field of rocket engines and relates to a lightweight three-engine parallel engine frame. Background Art

[0002] The rocket engine frame, as the connecting structure between the engine and the rocket body, plays a crucial role in transmitting engine thrust. Currently, rocket engine frames primarily include rod-type, beam-type, shell-type, and a combination of rods and beams—the truss-type. The frame design should meet the design specifications of the overall mission statement, including compact dimensions, low mass, uniform stress distribution, and sufficient strength, rigidity, and stability.

[0003] Existing multi-engine racks, both domestically and internationally, primarily consist of dual-engine parallel racks and four-stage parallel racks, primarily constructed from structural steel. A new hydrogen-oxygen engine utilizes three parallel engines, requiring minimal weight. These three engines are assembled on a triple-engine rack and delivered as a single engine to the rocket body for docking. Therefore, a lightweight engine rack suitable for parallel operation with three engines is required. Summary of the Invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the existing technology and propose a lightweight three-engine parallel engine frame, which is used to connect the rocket engine and the rocket body, and has the characteristics of advanced structure, uniform force, strong load-bearing capacity and light weight.

[0005] The solution of the present invention is:

[0006] A lightweight three-engine parallel engine frame, comprising a hexagonal frame, a main rod, a secondary rod, three main auxiliary rods, three secondary auxiliary rods, an upper joint, a ring plate, and six ear seats;

[0007] Among them, the ring plate is placed horizontally on the top of the external rocket box; the hexagonal frame is concentrically arranged above the ring plate; the axial top of the main auxiliary rod is connected to a corner point of the hexagonal frame, and the axial bottom end of the main auxiliary rod is connected to the ring plate; the axial top of the auxiliary auxiliary rod is connected to a corner point of the hexagonal frame, and the axial bottom end of the auxiliary auxiliary rod is connected to the ring plate; 3 main auxiliary rods and 3 auxiliary auxiliary rods are distributed at intervals; 2 main rods are symmetrically installed on both sides of each main auxiliary rod; the tops of the 2 main rods are connected to the hexagonal frame corner points corresponding to the main auxiliary rods. Point connection; the bottoms of the two main rods are separated into a triangular shape, and the bottoms of the two main rods are connected to the ring plate; two ear seats are symmetrically installed on the tops of the corner points of the hexagonal frame corresponding to the sub-auxiliary rods; two sub-rods are symmetrically installed on both sides of each sub-auxiliary rod; the tops of the two sub-rods are connected to the corner points of the hexagonal frame corresponding to the sub-auxiliary rods; the bottoms of the two sub-rods are separated into a triangular shape, and the bottoms of the two sub-rods are connected to the ring plate; an upper joint is installed at the lower ends of adjacent main rods and sub-rods, which are fixed to the top of the external rocket box through the upper joint.

[0008] In the above-mentioned lightweight three-engine parallel engine rack, an engine is installed on the top of the hexagonal frame corner point corresponding to each main auxiliary rod; the thrust generated by the three parallel engines is transmitted to the main rod and the main auxiliary rod through the hexagonal frame; a servo mechanism is installed corresponding to each ear seat; the servo mechanism force is transmitted to the hexagonal frame through the ear seat and then to the auxiliary rod and the auxiliary auxiliary rod; the thrust on the main rod and the servo force on the auxiliary rod are then transmitted to the upper joint; the thrust on the main auxiliary rod and the servo force on the auxiliary auxiliary rod are then transmitted to the ring plate; the upper joint and the ring plate then evenly transmit the force to the bottom of the rocket box, achieving the overall control box bottom deformation requirement.

[0009] In the above-mentioned lightweight three-engine parallel engine rack, the hexagonal frame includes an I-beam, three main joint seats, three auxiliary joint seats, three tie rods and a support plate;

[0010] The main structure of the hexagonal frame is composed of three pairs of vertical I-beams; each pair of two vertical I-beams is connected by a main joint seat; the three main joint seats are located on the same circle and are distributed in an equilateral triangle; the three pairs of vertical I-beams are connected to each other through a secondary joint seat; the secondary joint seat is the servo force application point, and two ear seats are installed on the top of each secondary joint. The centers of the three secondary joint seats are located on the same circle and are distributed in an equilateral triangle; the three secondary joint seats are supported by an equilateral triangle composed of three tie rods to strengthen the radial stiffness of the hexagonal frame; a support plate is installed between the I-beams on both sides of the main joint seat.

[0011] In the above-mentioned lightweight three-engine parallel engine rack, one end of every two adjacent main rods is connected to a main joint seat in a hexagonal frame, and the other ends of the two main rods are connected to two adjacent upper joints; the main rods are the main bearing rods of the engine thrust; the three main rods are evenly distributed around the rack axis, and the angles between the three main rods and the rack axis are equal. The three main rods realize uniform transmission of the thrust acting on the main joint seat, thereby reducing deformation of the rocket engine rack.

[0012] In the above-mentioned lightweight three-machine parallel engine rack, one end of each two adjacent auxiliary rods is connected to a auxiliary joint seat in a hexagonal frame, and the other ends of the two auxiliary rods are connected to two adjacent upper joints; the end of the auxiliary rod connected to the upper joint is connected to the upper joint together with one end of the adjacent main rod; the three auxiliary rods are evenly distributed around the rack axis, and the angles between the three auxiliary rods and the rack axis are equal. The three auxiliary rods can evenly transmit the servo force acting on the auxiliary joint seat, thereby reducing the deformation of the rocket engine rack.

[0013] In the above-mentioned lightweight three-engine parallel engine rack, one end of the main auxiliary rod is connected to the adjacent main joint seat, and the other end is connected to the ring plate; the three main auxiliary rods are evenly distributed around the rack axis, and the angles between the three main auxiliary rods and the rack axis are equal.

[0014] In the above-mentioned lightweight three-engine parallel engine frame, one end of the auxiliary rod is connected to the adjacent auxiliary joint seat, and the other end is connected to the ring plate; the ends of the three auxiliary rods connected to the ring plate are evenly distributed on the ring plate.

[0015] In the above-mentioned lightweight three-engine parallel engine rack, one side of the upper joint is connected to the adjacent main rod and auxiliary rod at the same time, and the other side of the upper joint is connected to the bottom of the rocket box through bolts; the upper joint transmits the adjacent thrust or servo force through the connected main rod or auxiliary rod.

[0016] In the above-mentioned lightweight three-engine parallel engine frame, the ring plate is welded to the upper joint and installed together on the bottom of the rocket box; the thrust generated by the engine directly acts on the bottom of the rocket box through the ring plate.

[0017] In the above-mentioned lightweight three-machine parallel engine rack, the number of ear seats is the same as the number of servo mechanisms, and the ear seats are used to install the servo mechanisms; the ear seats are installed on the auxiliary joints of the hexagonal frame, and two ear seats are installed on one auxiliary joint seat 13 at the same time.

[0018] The beneficial effects of the present invention compared with the prior art are:

[0019] (1) The lightweight three-engine parallel engine frame of the present invention adopts a hexagonal frame + rod system + ring structure layout design; it has the characteristics of advanced structure, uniform force, strong load-bearing capacity, and light weight;

[0020] (2) In the present invention, one end of each of two adjacent main rods is connected to a main joint seat in a hexagonal frame, and the other ends of the two main rods are connected to two adjacent upper joints. The main rod is the main bearing rod of the engine thrust. The multiple main rods are evenly distributed around the axis of the frame, and the angles between the multiple main rods and the axis of the frame are equal. The multiple main rods can evenly transmit the thrust acting on the main joint seat, thereby reducing the deformation of the rocket engine frame;

[0021] (3) In the present invention, one end of each of two adjacent secondary rods is connected to a secondary joint seat in a hexagonal frame, and the other ends of the two secondary rods are connected to two adjacent upper joints; the end of the secondary rod connected to the upper joint is connected to the end of the adjacent main rod. The multiple secondary rods are evenly distributed around the frame axis, and the angles between the multiple secondary rods and the frame axis are equal. The multiple secondary rods can evenly transmit the servo force acting on the secondary joint seat, thereby reducing the deformation of the rocket engine frame.

[0022] (4) The auxiliary auxiliary rod of the present invention has one end connected to the adjacent auxiliary joint seat and the other end connected to the ring plate; the ends of the auxiliary auxiliary rods connected to the ring plate are evenly distributed on the ring plate. The main auxiliary rod and the auxiliary auxiliary rods are mainly used to improve the deformation uniformity of the interface between the lightweight three-engine parallel engine frame and the rocket box. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is an overall schematic diagram of the lightweight three-engine parallel engine frame of the present invention;

[0024] Figure 2 This is a top view of the hexagonal frame of the present invention. DETAILED DESCRIPTION

[0025] The present invention will be further described below in conjunction with the embodiments.

[0026] The present invention provides a lightweight three-engine parallel engine frame, which is used to connect a rocket engine and a rocket body, and has the characteristics of advanced structure, uniform force, strong load-bearing capacity, and light weight.

[0027] Lightweight three-engine parallel engine frame, such as Figure 1 As shown, it specifically includes a hexagonal frame 1, a main rod 2, a secondary rod 3, three main auxiliary rods 4, three secondary auxiliary rods 5, an upper joint 6, a ring plate 7, and six ear seats 8.

[0028] Among them, the ring plate 7 is placed horizontally on the top of the external rocket box; the hexagonal frame 1 is concentrically arranged above the ring plate 7; the axial top of the main auxiliary rod 4 is connected to a corner point of the hexagonal frame 1, and the axial bottom end of the main auxiliary rod 4 is connected to the ring plate 7; the axial top of the auxiliary auxiliary rod 5 is connected to a corner point of the hexagonal frame 1, and the axial bottom end of the auxiliary auxiliary rod 5 is connected to the ring plate 7; the three main auxiliary rods 4 and the three auxiliary auxiliary rods 5 are distributed at intervals; two main rods 2 are symmetrically installed on both sides of each main auxiliary rod 4; the tops of the two main rods 2 are connected to the corner points of the hexagonal frame 1 corresponding to the main auxiliary rod 4 Point connection; the bottoms of the two main rods 2 are separated into a triangular shape, and the bottoms of the two main rods 2 are connected to the ring plate 7; two ear seats 8 are symmetrically installed on the tops of the corner points of the hexagonal frame 1 corresponding to the sub-auxiliary rods 5; two sub-rods 3 are symmetrically installed on both sides of each sub-auxiliary rod 5; the tops of the two sub-rods 3 are connected to the corner points of the hexagonal frame 1 corresponding to the sub-auxiliary rods 5; the bottoms of the two sub-rods 3 are separated into a triangular shape, and the bottoms of the two sub-rods 3 are connected to the ring plate 7; an upper joint 6 is installed at the lower ends of adjacent main rods 2 and sub-rods 3, which are fixed to the top of the external rocket box through the upper joint 6.

[0029] An engine is installed at the top of the corner point of the hexagonal frame 1 corresponding to each main auxiliary rod 4; the thrust generated by the three parallel engines is transmitted to the main rod 2 and the main auxiliary rod 4 through the hexagonal frame 1; a servo mechanism is installed corresponding to each ear seat 8; the servo mechanism force is transmitted to the hexagonal frame 1 through the ear seat 8 and then to the auxiliary rod 3 and the auxiliary auxiliary rod 5; the thrust on the main rod 2 and the servo force on the auxiliary rod 3 are then transmitted to the upper joint 6; the thrust on the main auxiliary rod 4 and the servo force on the auxiliary auxiliary rod 5 are then transmitted to the ring plate 7; the upper joint 6 and the ring plate 7 then evenly transmit the force to the bottom of the rocket box, achieving the requirement of overall control of the box bottom deformation.

[0030] like Figure 2 As shown, the hexagonal frame 1 includes an I-beam 11 , three main joint seats 12 , three auxiliary joint seats 13 , three tie rods 14 and a support plate 15 .

[0031] The main structure of the hexagonal frame 1 is composed of three pairs of vertical I-beams 11; each pair of vertical I-beams 11 is connected by a main joint seat 12; the three main joint seats 12 are located on the same circle and are distributed in an equilateral triangle; the three pairs of vertical I-beams 11 are connected to each other through a secondary joint seat 13; the secondary joint seat 13 is the servo force application point, and two ear seats 8 are installed on the top of each secondary joint 13. The centers of the three secondary joint seats 13 are located on the same circle and are distributed in an equilateral triangle; the three secondary joint seats 13 are supported by three tie rods 14 to form an equilateral triangle, so as to strengthen the radial stiffness of the hexagonal frame 1; a support plate 15 is installed between the I-beams 11 on both sides of the main joint seat 12.

[0032] One end of every two adjacent main rods 2 is connected to a main joint seat 12 in a hexagonal frame 1, and the other ends of the two main rods 2 are connected to two adjacent upper joints 6; the main rod 2 is the main bearing rod of the engine thrust; the three main rods 2 are evenly distributed around the axis of the frame, and the angles between the three main rods 2 and the axis of the frame are equal. The three main rods 2 realize uniform transmission of the thrust acting on the main joint seat 12, thereby reducing the deformation of the rocket engine frame.

[0033] One end of every two adjacent secondary rods 3 is connected to a secondary joint seat 13 in a hexagonal frame 1, and the other ends of the two secondary rods 3 are connected to two adjacent upper joints 6; one end of the secondary rod 3 connected to the upper joint 6 and one end of the adjacent main rod 2 are commonly connected to the upper joint 6; the three secondary rods 3 are evenly distributed around the axis of the frame, and the angles between the three secondary rods 3 and the axis of the frame are equal. The three secondary rods 3 can evenly transmit the servo force acting on the secondary joint seat 13, thereby reducing the deformation of the rocket engine frame.

[0034] One end of the main auxiliary rod 4 is connected to the adjacent main joint seat 12, and the other end is connected to the ring plate 7; the three main auxiliary rods 4 are evenly distributed around the frame axis, and the angles between the three main auxiliary rods 4 and the frame axis are equal.

[0035] One end of the auxiliary auxiliary rod 5 is connected to the adjacent auxiliary joint seat 13 , and the other end is connected to the ring plate 7 ; the ends of the three auxiliary auxiliary rods 5 connected to the ring plate 7 are evenly distributed on the ring plate 7 .

[0036] One side of the upper joint 6 is connected to the adjacent main rod 2 and auxiliary rod 3 at the same time, and the other side of the upper joint 6 is connected to the bottom of the rocket box through bolts; the upper joint 6 transmits the adjacent thrust or servo force through the connected main rod 2 or auxiliary rod 3.

[0037] The ring plate 7 is welded to the upper joint 6 and installed together on the bottom of the rocket box; the thrust generated by the engine acts directly on the bottom of the rocket box through the ring plate 7.

[0038] The number of the ear seats 8 is the same as that of the servo mechanisms, and the ear seats 8 are used to install the servo mechanisms; the ear seats 8 are installed on the auxiliary joints 13 of the hexagonal frame 1, and two ear seats 8 are installed on one auxiliary joint seat 13 at the same time.

[0039] In the present invention, the thrust generated by the three parallel engines is transmitted to the main rod 2 and the main auxiliary rod 4 through the hexagonal frame 1, and the servo mechanism force is transmitted to the hexagonal frame 1 through the ear seat 8 and then to the auxiliary rod 3 and the auxiliary auxiliary rod 5. The thrust on the main rod 2 and the servo force on the auxiliary rod 3 are then transmitted to the upper joint 6, and the thrust on the main auxiliary rod 4 and the servo force on the auxiliary auxiliary rod 5 are then transmitted to the ring plate 7. The upper joint 6 and the ring plate 7 then evenly transmit the force to the bottom of the rocket box, meeting the requirements of overall control of the box bottom deformation.

[0040] The hexagonal frame 1 primarily consists of an I-beam 11, a primary joint block 12, a secondary joint block 13, tie rods 14, and support plates 15. The main structure of the hexagonal frame 1 is composed of three pairs of mutually perpendicular I-beams 11. Multiple reinforcing ribs are located between the flanges and webs of each I-beam 11 to increase its rigidity.

[0041] The intersection of the three perpendicular I-beams 11 forms the main joint seat 12, with the center of the main joint seat 12 serving as the thrust application point. The main joint seat 12 has a number of bolt holes distributed across its mating surface, connecting to the engine gimbal via bolts. The centers of the three main joint seats 12 lie on the same circle, forming an equilateral triangle.

[0042] The remaining three intersections of the I-beam 11 serve as auxiliary joints 13. The centers of these joints 13 serve as the servo force application points. Each joint 13 connects to two lugs 8, and the centers of the three joints 13 lie on the same circle, forming an equilateral triangle. Three tie rods 14 form an equilateral triangle between the joints 13, reinforcing the radial rigidity of the hexagonal frame.

[0043] The circle where the main joint seat 12 is located and the circle where the auxiliary joint seat 13 is located are concentric circles, which ensures the symmetry of the entire frame and more uniform force.

[0044] The support plate 15 is connected to two adjacent I-beams 11. It is used to connect the front bracket of the hydrogen and oxygen pump of the engine.

[0045] There are multiple main rods 2, each of which has one end connected to a main joint seat 11 within a hexagonal frame 1. The other ends of the two main rods 2 are connected to two adjacent upper joints 6. The main rods 2 are the primary bearings of the engine thrust. The multiple main rods 2 are evenly distributed around the frame axis, and the angles between them and the frame axis are equal. This allows for uniform transfer of thrust acting on the main joint seat 12, minimizing deformation of the rocket engine frame.

[0046] The number of secondary rods 3 is equal to the number of primary rods 2. One end of every two adjacent secondary rods 3 is connected to a secondary joint seat 13 in a hexagonal frame 1, and the other ends of the two secondary rods 3 are connected to two adjacent upper joints 6. The end of the secondary rod 3 connected to the upper joint 6 is connected to the end of the adjacent primary rod 2, which is also connected to the upper joint 6. The multiple secondary rods 3 are evenly distributed around the frame axis, and the angles between the multiple secondary rods 3 and the frame axis are equal. The multiple secondary rods 3 can evenly transmit the servo force acting on the secondary joint seat 13, reducing deformation of the rocket engine frame.

[0047] There are multiple main auxiliary rods 4, one end of each main auxiliary rod 4 is connected to the adjacent main joint seat 12, and the other end is connected to the ring plate 7. The ends of the multiple main auxiliary rods 4 connected to the ring plate 7 are evenly distributed on the ring plate 4. The multiple main auxiliary rods 4 are evenly distributed around the frame axis, and the angles between the multiple main auxiliary rods 4 and the frame axis are equal.

[0048] The number of auxiliary rods 5 is equal to the number of main auxiliary rods 4. One end of each auxiliary rod 5 is connected to the adjacent auxiliary connector 13, and the other end is connected to the ring plate 7. The ends of the auxiliary rods 5 connected to the ring plate 7 are evenly distributed on the ring plate 7. The main auxiliary rods 4 and auxiliary rods 5 are primarily used to improve the deformation uniformity of the interface between the lightweight three-engine parallel engine frame and the rocket body.

[0049] There are multiple upper joints 6, one side of which is connected to the adjacent main rod 2 and auxiliary rod 3, and the other side of which is connected to the bottom of the rocket box through bolts. The upper joint 6 transmits the adjacent thrust or servo force through the connected main rod 2 or auxiliary rod 3.

[0050] Ring plate 7 is welded with the upper joint 6 and is installed on the bottom of the rocket box together. The thrust generated by the engine acts directly on the bottom of the rocket box through the ring plate 7.

[0051] The number of the ear seats 8 is the same as the number of the servo mechanisms, and the ear seats 8 are used to install the servo mechanisms. The ear seats 8 are installed on the auxiliary joints 13 of the hexagonal frame 1, and two ear seats 8 are installed on one auxiliary joint seat 13 at the same time.

[0052] The lightweight three-engine parallel engine frame adopts a hexagonal frame + rod system + circular ring structural layout design.

[0053] In the lightweight three-engine parallel engine frame, high-strength TC4 pipes are used as the main load-bearing rods of the frame.

[0054] The lightweight three-engine parallel engine frame is entirely welded with titanium alloy material.

[0055] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A lightweight three-engine parallel engine frame, characterized by: It comprises a hexagonal frame (1), a main rod (2), a secondary rod (3), three main auxiliary rods (4), three secondary auxiliary rods (5), an upper joint (6), a ring plate (7), and six ear seats (8); The ring plate (7) is horizontally placed on the top of the external rocket box; the hexagonal frame (1) is concentrically arranged above the ring plate (7); the axial top end of the main auxiliary rod (4) is connected to a corner point of the hexagonal frame (1), and the axial bottom end of the main auxiliary rod (4) is connected to the ring plate (7); the axial top end of the auxiliary auxiliary rod (5) is connected to a corner point of the hexagonal frame (1), and the axial bottom end of the auxiliary auxiliary rod (5) is connected to the ring plate (7); three main auxiliary rods (4) and three auxiliary auxiliary rods (5) are distributed at intervals; two main rods (2) are symmetrically installed on both sides of each main auxiliary rod (4); the tops of the two main rods (2) are connected to the corners of the hexagonal frame (1) corresponding to the main auxiliary rod (4); Point connection; the bottoms of the two main rods (2) are separated into a triangular shape, and the bottoms of the two main rods (2) are connected to the ring plate (7); two ear seats (8) are symmetrically installed on the tops of the corner points of the auxiliary rod (5) corresponding to the hexagonal frame (1); two auxiliary rods (3) are symmetrically installed on both sides of each auxiliary rod (5); the tops of the two auxiliary rods (3) are connected to the corner points of the hexagonal frame (1) corresponding to the auxiliary rod (5); the bottoms of the two auxiliary rods (3) are separated into a triangular shape, and the bottoms of the two auxiliary rods (3) are connected to the ring plate (7); an upper joint (6) is installed on the lower ends of adjacent main rods (2) and auxiliary rods (3), and is fixedly connected to the top of the external rocket box through the upper joint (6); An engine is installed at the top of the corner point of the hexagonal frame (1) corresponding to each main auxiliary rod (4); the thrust generated by the three parallel engines is transmitted to the main rod (2) and the main auxiliary rod (4) through the hexagonal frame (1); a servo mechanism is installed corresponding to each ear seat (8); the servo mechanism force is transmitted to the hexagonal frame (1) through the ear seat (8) and then to the auxiliary rod (3) and the auxiliary auxiliary rod (5); the thrust on the main rod (2) and the servo force on the auxiliary rod (3) are then transmitted to the upper joint (6); the thrust on the main auxiliary rod (4) and the servo force on the auxiliary auxiliary rod (5) are then transmitted to the ring plate (7); the upper joint (6) and the ring plate (7) then evenly transmit the force to the bottom of the rocket box, thereby achieving the requirement of overall control of the box bottom deformation.

2. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: The hexagonal frame (1) comprises an I-beam (11), three main joint seats (12), three auxiliary joint seats (13), three tie rods (14) and a support plate (15); The main structure of the hexagonal frame (1) is composed of three pairs of vertical I-beams (11); each pair of two vertical I-beams (11) are connected by a main joint seat (12); the three main joint seats (12) are located on the same circle and are distributed in an equilateral triangle; the three pairs of vertical I-beams (11) are connected to each other through a secondary joint seat (13); the secondary joint seat (13) is a servo force application point, and two ear seats (8) are installed on the top of each secondary joint seat (13). The centers of the three secondary joint seats (13) are located on the same circle and are distributed in an equilateral triangle; the three secondary joint seats (13) are supported by three tie rods (14) to form an equilateral triangle, so as to strengthen the radial stiffness of the hexagonal frame (1); a support plate (15) is installed between the I-beams (11) on both sides of the main joint seat (12).

3. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: One end of each of two adjacent main rods (2) is connected to a main joint seat (12) in a hexagonal frame (1), and the other ends of the two main rods (2) are connected to two adjacent upper joints (6); the main rod (2) is a main bearing rod for the engine thrust; the three main rods (2) are evenly distributed around the axis of the frame, and the angles between the three main rods (2) and the axis of the frame are equal. The three main rods (2) realize uniform transmission of the thrust acting on the main joint seat (12), thereby reducing deformation of the rocket engine frame.

4. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: One end of each two adjacent auxiliary rods (3) is connected to an auxiliary joint seat (13) in a hexagonal frame (1), and the other ends of the two auxiliary rods (3) are connected to two adjacent upper joints (6); one end of the auxiliary rod (3) connected to the upper joint (6) and one end of the adjacent main rod (2) are commonly connected to the upper joint (6); three auxiliary rods (3) are evenly distributed around the frame axis, and the angles between the three auxiliary rods (3) and the frame axis are equal. The three auxiliary rods (3) can evenly transmit the servo force acting on the auxiliary joint seat (13), thereby reducing the deformation of the rocket engine frame.

5. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: One end of the main auxiliary rod (4) is connected to the adjacent main joint seat (12), and the other end is connected to the ring plate (7); the three main auxiliary rods (4) are evenly distributed around the axis of the frame, and the angles between the three main auxiliary rods (4) and the axis of the frame are equal.

6. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: One end of the auxiliary auxiliary rod (5) is connected to the adjacent auxiliary joint seat (13), and the other end is connected to the ring plate (7); the ends of the three auxiliary auxiliary rods (5) connected to the ring plate (7) are evenly distributed on the ring plate (7).

7. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: One side of the upper joint (6) is simultaneously connected to the adjacent main rod (2) and auxiliary rod (3), and the other side of the upper joint (6) is connected to the bottom of the rocket box through bolts; the upper joint (6) transmits adjacent thrust or servo force through the connected main rod (2) or auxiliary rod (3).

8. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: The ring plate (7) and the upper joint (6) are welded and installed together on the bottom of the rocket box; the thrust generated by the engine directly acts on the bottom of the rocket box through the ring plate (7).

9. The lightweight three-engine parallel engine frame according to claim 1, characterized in that: The number of the ear seats (8) is consistent with that of the servo mechanism, and the ear seats (8) are used to install the servo mechanism; the ear seats (8) are installed on the auxiliary joint seat (13) of the hexagonal frame (1), and two ear seats (8) are installed on one auxiliary joint seat (13) at the same time.

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