A rocket cabin section with an integrated structure design

Abstract

This application relates to a rocket module with an integrated structural design. It includes a one-piece molded bulkhead, an inertial navigation system (INS) support beam, a grid rib, an antenna window, a single-unit mounting interface, an INS aiming port, and an operating port. The INS support beam and grid rib are located inside the bulkhead, while the antenna window, single-unit mounting interface, INS aiming port, and operating port are all located on the bulkhead. The antenna window and single-unit mounting interface are thickened to form bosses, which are connected in series with the grid ribs. Its advantages are: the integrated design of the module shell and single-unit support results in a simple structure, high reliability, and high structural efficiency; the grid rib design of the shell results in a thinner skin, and the thickened bosses at the single-unit mounting points, connected in series with the grid ribs, improves local strength; fewer components reduce assembly steps and lower assembly errors and omissions; and the use of aluminum alloy casting results in a lighter overall weight and lower manufacturing cost.

Description

Technical Field

[0001] This invention belongs to the aerospace field and relates to the design of rocket modules, specifically an integrated structural design for a rocket module. Background Technology

[0002] In recent years, commercial spaceflight has developed rapidly, with low cost and high reliability being its primary development requirements. Solid-propellant launch vehicle structures generally consist of various modules, a satellite-rocket adapter, and a propulsion system. Module materials are divided into metallic and composite materials, with aluminum alloys being the most common type of metallic material. Rocket module shell assemblies typically consist of a shell, reinforcing ribs, single-unit supports, socket supports, and fasteners.

[0003] The existing rocket compartments have complex structures, numerous components, and cumbersome and complicated assembly processes. The assembly workload is large, the assembly efficiency is low, and the assembly error is large. Summary of the Invention

[0004] To address the shortcomings or improvement needs of existing technologies, this invention provides an integrated rocket module design that fuses the module shell with the individual unit support frame. This integrated design utilizes low-cost aluminum alloy casting, followed by machining of the individual unit mounting holes to improve positioning accuracy, reduce assembly errors and inaccuracies, and increase assembly efficiency. The shell employs a mesh reinforcement design with a thinner skin. Thickened bosses are formed at individual unit mounting points, connected in series with the mesh reinforcement to enhance local strength. This results in a lighter overall weight and higher structural efficiency. This invention solves the technical problems of existing rocket modules having numerous components, complex assembly processes, high workload, low efficiency, and large assembly errors.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A rocket module with an integrated structural design includes an integrally formed bulkhead, an inertial navigation system (INS) support beam, a grid rib, an antenna window, a single-unit mounting interface, an INS aiming port, and an operating port.

[0007] The inertial navigation system support beam and grid ribs are located on the inner side of the bulkhead, and the antenna window, single-unit installation interface, inertial navigation system aiming port and operation port are all opened on the bulkhead.

[0008] Both the antenna window and the single-unit mounting interface are thickened to form protrusions, and the protrusions are connected in series with the mesh reinforcement to form a whole.

[0009] Preferably, the inertial navigation system support beams consist of 1-3 beams with a thickness of 25-30 mm.

[0010] Preferably, it also includes a transfer platform disposed on the inertial navigation system support beam, the transfer platform being integrally formed with the bulkhead or machined.

[0011] Preferably, the adapter platform is provided with multiple mounting holes.

[0012] Preferably, it also includes diagonal bracing on both sides of the transfer platform, the diagonal bracing being integrally formed with the bulkhead.

[0013] Preferably, there are multiple antenna windows, and the multiple antenna windows are square, with the flatness of their mounting surfaces and the accuracy of their holes being ensured by machining.

[0014] Preferably, there are multiple single-machine mounting interfaces, and the multiple single-machine mounting interfaces are circular. The flatness of their mounting surfaces and the accuracy of their holes are ensured by machining. Each single-machine mounting interface is provided with a mounting hole.

[0015] Preferably, it also includes a camera bracket fixedly mounted on the outer wall of the bulkhead.

[0016] Preferably, the operating port is thickened to form a boss, and the operating port is also provided with a cover mounting interface.

[0017] Preferably, the bulkhead is made of cast aluminum alloy.

[0018] In summary, the above-mentioned one or more technical solutions provided in this application can produce at least the following beneficial effects or advantages:

[0019] 1. The compartment shell and the single-unit support are integrated into a design, which is simple in structure, highly reliable and efficient. At the same time, it reduces the problems of assembly accuracy and stress distribution that exist when assembling many parts and components in traditional compartments.

[0020] 2. The shell adopts a mesh reinforcement design, the skin is relatively thin, and the mounting points of individual units are thickened to form bosses. The bosses are connected in series with the mesh reinforcement, which improves the local strength.

[0021] 3. The inertial navigation system (INS) mounting location is reinforced with diagonal bracing to improve local stiffness and INS accuracy;

[0022] 4. Fewer components reduce assembly steps, lower assembly errors and omissions, shortening assembly time and improving the design efficiency of the compartment.

[0023] 5. It is made of aluminum alloy casting, which makes it lightweight and reduces manufacturing costs. Attached Figure Description

[0024] Figure 1 This is a structural schematic diagram A of a rocket module with an integrated structural design in one embodiment of this application;

[0025] Figure 2 This is a structural schematic diagram B of a rocket module with an integrated structural design in one embodiment of this application;

[0026] Figure 3 This is a cross-sectional view of a rocket compartment with an integrated structural design in one embodiment of this application;

[0027] Figure 4 This is a schematic diagram of the structure of the adapter in one embodiment of this application.

[0028] In all the accompanying drawings, the same reference numerals are used to denote the same elements or structures, wherein:

[0029] 1-Diagonal tie rod, 2-Inertial navigation system support beam, 3-Grid reinforcement, 4-Bushead, 5-Operating port, 6-Camera bracket, 7-Antenna window, 8-Adapter, 9-Inertial navigation system aiming port, 10-Single unit installation interface, 101-Mounting surface, 11-Mounting hole. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0031] In the description of this invention, it should be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. In addition, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0032] like Figures 1 to 3 As shown, the present invention provides an integrated structural design for a rocket module, comprising an aluminum alloy bulkhead integrally formed by casting, and inertial navigation system (INS) support beams, grid ribs, antenna windows, unit mounting interfaces, INS aiming ports, and operating ports distributed along the bulkhead. The INS support beams and grid ribs are located on the inner side of the bulkhead, while the antenna windows, unit mounting interfaces, INS aiming ports, and operating ports are all located on the bulkhead. The antenna windows and unit mounting interfaces are circumferentially thickened into the interior of the module to form protrusions, and all protrusions are connected in series with the grid ribs on the bulkhead to improve local and overall strength.

[0033] The inertial navigation system (INS) support beams consist of 1-3 beams, each 25-30 mm thick. In this embodiment, there are 2 INS support beams, each 27 mm thick. Figure 4 As shown, to facilitate the installation of the inertial navigation system (INS), a transfer platform is provided on the INS support beam. In this embodiment, the transfer platform is integrally formed with the bulkhead and the INS support beam; in another embodiment, the transfer platform is machined and fixed to the INS support beam with screws. Meanwhile, multiple threaded mounting holes are provided on the transfer platform to facilitate the installation of the INS and the transfer platform.

[0034] To make the transfer platform more stable and reliable, a set of diagonal braces is provided on each side of the transfer platform to improve local rigidity, thereby improving the stability of the inertial navigation system on the transfer platform and ensuring the accuracy of the inertial navigation system. The diagonal braces are integrally formed with the bulkhead. In this embodiment, the diagonal braces are right-angled triangular structures, with the two right-angled sides respectively set on the inner side of the bulkhead and on the inertial navigation system support beam.

[0035] To ensure the installation of multiple antennas, multiple antenna windows are provided as needed, running radially along the bulkhead. Each antenna window is a square that matches the antenna, with the edges of the square protruding inward to form a boss. The thickness of the boss is not less than 5mm. The flatness of the antenna window mounting surface and the accuracy of the holes are ensured by machining.

[0036] To ensure the installation of multiple individual units, multiple installation interfaces are provided as needed. Each installation interface is a circular boss protruding into the compartment from the bulkhead. Each circular boss has a mounting hole at its center. In this embodiment, the mounting holes are all threaded holes. The mounting surface of the installation interface is the end face of the boss, and its flatness and hole position accuracy are guaranteed by machining.

[0037] To facilitate camera installation, camera brackets are fixed to the outer wall of the compartment for camera mounting.

[0038] In this embodiment, the inertial navigation system (INS) aiming port is the INS prism's improved aiming window.

[0039] To improve local strength, the circumferential side of the operating port is thickened to form a boss on the inner side of the compartment. The thickness of the boss is not less than 5mm. An operating port cover installation interface is also provided at the operating port to facilitate the installation of the operating port cover.

[0040] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the scope of protection of this application.

Claims

1. A rocket module with an integrated structural design, characterized in that, It includes a one-piece molded bulkhead, inertial navigation system support beam, mesh reinforcement, antenna window, single-unit mounting interface, inertial navigation system aiming port, and operating port; The inertial navigation system support beam and grid ribs are located on the inner side of the bulkhead, and the antenna window, single-unit installation interface, inertial navigation system aiming port and operation port are all opened on the bulkhead. A transfer platform is provided on the inertial navigation system support beam, and the transfer platform is integrally formed with the bulkhead. The adapter is provided with diagonal bracing on both sides, and the diagonal bracing is integrally formed with the bulkhead. Both the antenna window and the single-unit mounting interface are thickened to form protrusions, and the protrusions are connected in series with the mesh reinforcement to form a whole; The bulkhead is made of cast aluminum alloy.

2. The rocket module with an integrated structural design according to claim 1, characterized in that: The inertial navigation system support beam consists of 1-3 beams, each with a thickness of 25-30 mm.

3. The rocket module with an integrated structural design according to claim 1, characterized in that: The adapter platform is provided with multiple mounting holes.

4. The rocket module with an integrated structural design according to claim 1, characterized in that: The antenna window is multiple, and the multiple antenna windows are square. The flatness of the mounting surface and the accuracy of the holes are guaranteed by machining.

5. The rocket module with an integrated structural design according to claim 1, characterized in that: The single-machine mounting interface is multiple, and each single-machine mounting interface is a circular boss. The flatness of the mounting surface and the accuracy of the hole position are guaranteed by machining. Each single-machine mounting interface is provided with a mounting hole.

6. The rocket module with an integrated structural design according to claim 1, characterized in that: It also includes a camera bracket that is fixedly installed on the outer wall of the bulkhead.

7. The rocket module with an integrated structural design according to claim 1, characterized in that: The operating port is thickened to form a boss, and the operating port is also provided with a cover installation interface.

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