A multi-spine rocket instrument compartment

Abstract

This invention discloses a multi-spindle rocket instrument compartment, belonging to the field of launch vehicle technology. It includes an instrument compartment skin, a web, and an engine frame for mounting the engine. The instrument compartment skin is a cylindrical structure open at both ends. The internal cavity of the instrument compartment skin serves as a mounting cavity. The web is fixedly disposed within the mounting cavity and is fixedly connected to the inner wall of the instrument compartment skin. The engine frame is fixedly disposed within the instrument compartment skin via the web. This invention achieves lightweight instrument compartment design and improves rocket carrying capacity while providing a sufficient number of mounting interfaces.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, and in particular to a multi-spindle rocket instrument compartment. Background Technology

[0002] As a key component of a rocket, the instrument compartment must meet at least the following functional requirements: first, it must have sufficient load-bearing capacity; second, it must provide enough installation interfaces for avionics equipment while ensuring that the noise environment for each device meets operational requirements; and third, it must meet lightweight requirements to maximize payload capacity. Therefore, the optimization and design of the instrument compartment is a crucial technology in rocket structural design.

[0003] With the continuous development of commercial space technology, the demand for rocket carrying capacity is increasing, and the existing instrument compartments can no longer meet the requirements.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0005] To address the aforementioned technical issues, this application provides a multi-slab rocket instrument compartment that can achieve lightweighting of the instrument compartment and improve rocket carrying capacity while providing a sufficient number of installation interfaces.

[0006] A multi-spine rocket instrument compartment includes: an instrument compartment skin, a belly plate, and an engine frame for fixing the engine;

[0007] The instrument compartment skin is a cylindrical structure with openings at both ends; the internal cavity of the instrument compartment skin is a mounting cavity.

[0008] The web plate is fixedly disposed in the mounting cavity and is fixedly connected to the inner wall of the instrument compartment skin.

[0009] The engine frame is fixed within the instrument compartment skin via the web plate.

[0010] Preferably, the web includes a first web arranged laterally and a second web arranged longitudinally, the first web and the second web forming a "well" shaped structure.

[0011] Preferably, the central frame of the "well"-shaped structure formed by the first web plate and the second web plate serves as the mounting interface for installing the engine; the engine is fixed within the central frame of the "well"-shaped structure formed by the first web plate and the second web plate.

[0012] Preferably, the first web plate is distributed in 8 locations; the second web plate is distributed in 8 locations.

[0013] The two web plates mentioned above form a group. The web plates in the same group are adjacent and collinear. The web plates in adjacent groups are perpendicular to each other, forming a rectangular frame.

[0014] The two No. 1 web plates are grouped together, and the No. 1 web plates in the same group are perpendicular to each other and connected at their ends; the end connection line of the No. 1 web plates in the same group coincides with the edge line of the rectangular frame; the No. 1 web plate and the No. 2 web plate are arranged collinearly or perpendicularly.

[0015] Preferably, the engine frame is fixed within the rectangular frame; the engine is fixedly connected to the instrument compartment skin via the engine frame and the web plate; the engine shaft center coincides with the instrument compartment skin shaft center.

[0016] Preferably, the engine frame includes a frame body and an engine mounting hole disposed in the frame body; the engine is disposed in the engine mounting hole and fixedly connected to the frame body.

[0017] Preferably, the web plate further includes a third web plate; the third web plate is disposed at the connection point of the second web plate in the same group; one end of the third web plate is perpendicularly disposed to the second web plate to which it is connected, and the other end of the third web plate is fixedly connected to the interior of the instrument compartment skin.

[0018] Preferably, it also includes instrument cabin stringers fixed to the outer surface of the instrument cabin skin; the instrument cabin stringers are arranged parallel to the axis of the instrument cabin skin.

[0019] Preferably, it further includes an upper frame and a lower frame of the instrument compartment; the upper frame of the instrument compartment is fixedly disposed at one end of the instrument compartment skin and is fixedly connected to the outer wall of the instrument compartment skin; the lower frame of the instrument compartment is fixedly disposed at the other end of the instrument compartment skin and is fixedly connected to the outer wall of the instrument compartment skin.

[0020] Preferably, the multi-spindle rocket instrument compartment further includes an inertial navigation system (INS) support; the INS support is fixedly connected to the inner wall of the instrument compartment skin.

[0021] Compared with the prior art, this application has at least the following beneficial effects:

[0022] 1. This invention can achieve lightweight instrument compartment and improve rocket carrying capacity while providing a sufficient number of installation interfaces.

[0023] 2. The invention employs a multi-web structure, which can provide sufficient installation interfaces for the equipment. Avionics equipment does not need to be installed on the bulkhead, and the noise environment requirements for instruments and equipment are relatively low.

[0024] 3. In the multi-web structure adopted in this invention, the webs can be connected by ring plates, which can make the instrument cabin as a whole have good torsional stiffness. Attached Figure Description

[0025] The following sections will describe some specific embodiments of the invention in detail by way of example and not limitation, with reference to the accompanying drawings. The same reference numerals in the drawings denote the same or similar parts or portions. Those skilled in the art should understand that these drawings are not necessarily drawn to scale. In the drawings:

[0026] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0027] The above figures include the following reference numerals:

[0028] 1. Instrument cabin skin; 2. Upper frame of instrument cabin; 3. Instrument cabin stringers; 4. Lower frame of instrument cabin; 5. No. 1 web plate; 6. No. 3 web plate; 7. No. 2 web plate; 8. Engine frame; 9. Engine; 10. Inertial navigation system support. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0030] like Figure 1 As shown, a multi-spindle rocket instrument compartment includes: an instrument compartment skin 1, a web, and an engine frame 8 for fixing an engine 9. The instrument compartment skin 1 is a cylindrical structure with openings at both ends; the internal cavity of the instrument compartment skin 1 is a mounting cavity; the web is fixedly installed in the mounting cavity and is fixedly connected to the inner wall of the instrument compartment skin 1; the engine frame 8 is fixedly installed in the instrument compartment skin 1 through the web.

[0031] The web consists of a first web 5 arranged laterally and a second web 7 arranged longitudinally, forming a "well" shaped structure. The "well" shaped structure of the web provides a sufficient number of mounting interfaces, ensuring that the instrument has enough mounting positions.

[0032] The central frame of the "well"-shaped structure formed by the first web plate 5 and the second web plate 7 serves as the mounting interface for the engine 9; the engine 9 is fixed within the central frame of the "well"-shaped structure formed by the first web plate 5 and the second web plate 7.

[0033] The engine frame 8 is fixed within the rectangular frame; the engine 9 is fixedly connected to the instrument compartment skin 1 through the engine frame 8 and the web plate, and the axis of the engine 9 coincides with the axis of the instrument compartment skin 1.

[0034] The engine frame 8 includes a frame body and an engine mounting hole disposed in the frame body; the engine 9 is disposed in the engine mounting hole and fixedly connected to the frame body.

[0035] In this embodiment, the first web plate 5 is distributed at 8 locations, and the second web plate 7 is distributed at 8 locations. Two locations of the second web plate 7 form a group, with the second web plates 7 within the same group being adjacent and collinear. Second web plates 7 in adjacent groups are perpendicular to each other, forming a rectangular frame. Two locations of the first web plate 5 form a group, with the first web plates 5 within the same group being perpendicular to each other and connected at their ends; the end connection line of the first web plates 5 in the same group coincides with the edge line of the rectangular frame; the first web plate 5 and the second web plate 7 are arranged collinearly or perpendicularly.

[0036] In another embodiment of the present invention, the web plate includes a third web plate 6; the third web plate 6 is disposed at the connection of the second web plate 7 in the same group; one end of the third web plate 6 is perpendicularly disposed to the second web plate 7 connected thereto, and the other end of the third web plate 6 is fixedly connected to the interior of the instrument cabin skin 1.

[0037] In another embodiment of the invention, provided the instrument compartment meets design requirements, the first web plate 5 and the second web plate 7 form a "well" shaped structure. However, the first web plate 5 and the second web plate 7 are not set in eight locations, but rather fewer than that. For example, the first web plate 5 is set in four locations, where the first web plate 5 in the same group is made from a single sheet and bent at corresponding positions to ensure the corresponding structure and vertical arrangement. Similarly, the second web plate 7 is made from a single sheet and welded at both ends to form a ring structure, and bent and shaped at corresponding positions to form a rectangular frame. This method can achieve a "well" shaped web plate structure while reducing the number of the first web plate 5 and / or the second web plate 7, effectively improving the processing efficiency of the web plates and reducing processing costs.

[0038] In another embodiment of the present invention, a multi-spindle rocket instrument compartment further includes an instrument compartment stringer 3 fixed to the outer surface of the instrument compartment skin 1; the instrument compartment stringer 3 is arranged parallel to the axis of the instrument compartment skin 1.

[0039] In another embodiment of the present invention, a multi-spindle rocket instrument compartment further includes an upper instrument compartment frame 2 and a lower instrument compartment frame 4; the upper instrument compartment frame 2 is fixedly disposed at one end of the instrument compartment skin 1 and is fixedly connected to the outer wall of the instrument compartment skin 1; the lower instrument compartment frame 4 is fixedly disposed at the other end of the instrument compartment skin 1.

[0040] Preferably, the upper frame 2 and the lower frame 4 of the instrument compartment are externally mounted and flipped outwards, that is, both the upper frame 2 and the lower frame 4 of the instrument compartment are fixedly connected to the outer wall of the instrument compartment skin 1.

[0041] In another embodiment of the present invention, a multi-spindle rocket instrument compartment further includes an inertial navigation system (INS) support 10 for fixing the INS, the INS support 10 being fixedly connected to the inner wall of the instrument compartment skin 1.

[0042] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0043] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0044] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in sequences other than those illustrated or described herein.

[0045] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A multi-spindle rocket instrument compartment, characterized in that, include: The instrument compartment skin (1), the web plate, and the engine frame (8) for fixing the engine (9) are included. The instrument compartment skin (1) is a cylindrical structure with openings at both ends. The internal cavity of the instrument compartment skin (1) is a mounting cavity. The web plate is fixedly installed in the mounting cavity and is fixedly connected to the inner wall of the instrument compartment skin (1). The engine frame (8) is fixedly installed in the instrument compartment skin (1) through the web plate. The web includes a first web (5) arranged laterally and a second web (7) arranged longitudinally, the first web (5) and the second web (7) forming a "well" shaped structure; The central frame of the "well" shaped structure formed by the first web plate (5) and the second web plate (7) serves as the mounting interface for the engine (9); the engine (9) is fixed within the central frame of the "well" shaped structure formed by the first web plate (5) and the second web plate (7). The first web plate (5) is set in 4 places. The first web plate (5) in the same group is made of a whole plate and is bent at the corresponding position to ensure the corresponding structure and vertical setting. Similarly, the second web plate (7) is made of a whole plate and is welded at the beginning and end to form a ring structure. It is bent and shaped at the corresponding position to form a rectangular frame. The engine frame (8) is fixedly installed within the rectangular frame; the engine (9) is fixedly connected to the instrument compartment skin (1) through the engine frame (8) and the web plate; the axis of the engine (9) coincides with the axis of the instrument compartment skin (1); The engine frame (8) includes a frame body and an engine mounting hole disposed in the frame body; the engine (9) is disposed in the engine mounting hole and fixedly connected to the frame body; The web includes a third web (6); the third web (6) is located at the connection point of the second web (7) in the same group; one end of the third web (6) is perpendicular to the second web (7) connected to it, and the other end of the third web (6) is fixedly connected to the interior of the instrument cabin skin (1).

2. The multi-spindle rocket instrument compartment as described in claim 1, characterized in that, It also includes instrument cabin stringers (3) fixed to the outer surface of the instrument cabin skin (1); the instrument cabin stringers (3) are arranged parallel to the axis of the instrument cabin skin (1).

3. The multi-spindle rocket instrument compartment as described in claim 1, characterized in that, It also includes an upper frame (2) and a lower frame (4) for the instrument compartment; the upper frame (2) is fixed to one end of the instrument compartment skin (1) and is fixedly connected to the outer wall of the instrument compartment skin (1); the lower frame (4) is fixed to the other end of the instrument compartment skin (1) and is fixedly connected to the outer wall of the instrument compartment skin (1).

4. The multi-spindle rocket instrument compartment as described in claim 1, characterized in that, The multi-spindle rocket instrument compartment also includes an inertial navigation system (INS) support (10); the INS support (10) is fixedly connected to the inner wall of the instrument compartment skin (1).

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