Multi-web rocket instrument cabin

Abstract

The invention discloses a multi-web rocket instrument cabin, which belongs to the technical field of carrier rockets, and comprises an instrument cabin skin, webs and an engine frame for fixing an engine, the instrument cabin skin is of a cylindrical structure with two open ends; an inner cavity of the instrument cabin skin is a mounting cavity; the web plate is fixedly arranged in the mounting cavity and is fixedly connected with the inner wall of the instrument cabin skin; and the engine frame is fixedly arranged in the instrument cabin skin through the web plate. On the premise of providing enough mounting interfaces, the light weight of the instrument cabin is realized, and the carrying capacity of a rocket is improved.

Description

Technical Field

[0001] The invention relates to the technical field of launch vehicles, in particular to a multi-web rocket instrument cabin. Background Art

[0002] As one of the key compartments of the rocket, the instrument cabin has at least the following functional requirements: first, it must have sufficient carrying capacity; second, it must provide sufficient installation interfaces for avionics equipment, while ensuring that the noise environment of each device installation meets the use requirements; third, it must meet the lightweight requirements to maximize the carrying capacity. Therefore, the optimization and scheme design of the instrument cabin is a key technology in rocket structural design.

[0003] With the continuous development of commercial aerospace technology, the demand for rocket carrying capacity is increasing, and the existing instrument cabin 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] In order to solve the above-mentioned technical problems, the present application provides a multi-belt rocket instrument cabin, which can achieve lightweight instrument cabin and improve rocket carrying capacity under the premise of providing sufficient installation interfaces.

[0006] A multi-belt rocket instrument cabin, comprising: an instrument cabin skin, a belly plate and an engine frame for fixing an engine; The instrument cabin skin is a cylindrical structure with openings at both ends; the inner cavity of the instrument cabin skin is a mounting cavity; The web is fixedly arranged in the installation cavity and is fixedly connected to the inner wall of the instrument cabin skin; The engine frame is fixed in the instrument compartment skin via the web.

[0007] Preferably, the web includes a web No. 1 disposed transversely and a web No. 2 disposed longitudinally, and the web No. 1 and the web No. 2 form a "well"-shaped structure.

[0008] Preferably, the center frame of the "well"-shaped structure formed by the first web and the second web serves as an installation interface for installing the engine; the engine is fixedly arranged in the center frame of the "well"-shaped structure formed by the first web and the second web.

[0009] Preferably, the first web is distributed at 8 locations; the second web is distributed at 8 locations; The second webs at 2 locations form a group, the second webs in the same group are adjacent and collinear, and the second webs in adjacent groups are perpendicular to each other to form a rectangular frame; The No. 1 webs at 2 locations form a group, the No. 1 webs in the same group are perpendicular to each other and connected at the ends; the end connection lines of the No. 1 webs in the same group coincide with the edge lines of the rectangular frame; the No. 1 web and the No. 2 web are colinearly or vertically arranged.

[0010] Preferably, the engine frame is fixed in the rectangular frame; the engine is fixedly connected to the instrument compartment skin via the engine frame and the belly plate; the engine axis coincides with the axis of the instrument compartment skin.

[0011] Preferably, the engine frame includes a frame body and an engine mounting hole arranged in the frame body; the engine is arranged in the engine mounting hole and fixedly connected to the frame body.

[0012] Preferably, the web also includes a No. 3 web; the No. 3 web is arranged at the connection of the No. 2 web in the same group; one end of the No. 3 web is perpendicularly arranged to the No. 2 web connected to it, and the other end of the No. 3 web is fixedly connected to the inside of the instrument cabin skin.

[0013] Preferably, it also includes an instrument cabin purlin fixedly mounted on the outer surface of the instrument cabin skin; the instrument cabin purlin is arranged parallel to the axis of the instrument cabin skin.

[0014] Preferably, it also includes an upper end frame and a lower end frame of the instrument cabin; the upper end frame of the instrument cabin is fixedly arranged at one end of the instrument cabin skin and fixedly connected to the outer wall of the instrument cabin skin; the lower end frame of the instrument cabin is fixedly arranged at the other end of the instrument cabin skin and fixedly connected to the outer wall of the instrument cabin skin.

[0015] Preferably, the multi-web rocket instrument cabin also includes an inertial group bracket; the inertial group bracket is fixedly connected to the inner wall of the instrument cabin skin.

[0016] Compared with the prior art, this application has at least the following beneficial effects: 1. The present invention can realize lightweight instrument cabin and improve rocket carrying capacity under the premise of providing enough installation interfaces.

[0017] 2. The multi-web structure adopted in the present invention can provide sufficient installation interfaces for the equipment, and the avionics equipment does not need to be installed on the bulkhead, and the noise environment requirements of the equipment are relatively low.

[0018] 3. In the multi-web structure adopted in the present invention, the webs can be connected by ring plates, so that the instrument cabin as a whole has better torsional rigidity. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings: Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0020] The above drawings include the following reference numerals: 1. Instrument cabin skin; 2. Instrument cabin upper frame; 3. Instrument cabin girders; 4. Instrument cabin lower frame; 5. No. 1 belly plate; 6. No. 3 belly plate; 7. No. 2 belly plate; 8. Engine frame; 9. Engine; 10. Inertial group bracket. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0022] like Figure 1 As shown, a multi-belt rocket instrument cabin comprises: an instrument cabin skin 1, a belly plate and an engine frame 8 for fixing an engine 9. The instrument cabin skin 1 is a cylindrical structure with two ends open; the inner cavity of the instrument cabin skin 1 is a mounting cavity; the belly plate is fixed in the mounting cavity and fixedly connected to the inner wall of the instrument cabin skin 1; the engine frame 8 is fixed in the instrument cabin skin 1 through the belly plate.

[0023] The webs include a first web 5 arranged transversely and a second web 7 arranged longitudinally, and the first web 5 and the second web 7 form a "well"-shaped structure. The webs of the "well"-shaped structure can provide enough installation interfaces to ensure that the instrument has enough installation positions.

[0024] The center frame of the "well"-shaped structure formed by the first web 5 and the second web 7 serves as an installation interface for installing the engine 9; the engine 9 is fixedly arranged in the center frame of the "well"-shaped structure formed by the first web 5 and the second web 7.

[0025] The engine frame 8 is fixed in the rectangular frame; the engine 9 is fixedly connected to the instrument compartment skin 1 through the engine frame 8 and the belly plate, and the axis of the engine 9 coincides with the axis of the instrument compartment skin 1.

[0026] The engine frame 8 includes a frame body and an engine mounting hole arranged in the frame body; the engine 9 is arranged in the engine mounting hole and fixedly connected to the frame body.

[0027] In this embodiment, the No. 1 webs 5 are distributed at 8 locations, and the No. 2 webs 7 are distributed at 8 locations. Among them, 2 No. 2 webs 7 form a group, and the No. 2 webs 7 in the same group are adjacent and collinear, and the No. 2 webs 7 in adjacent groups are perpendicular to each other, forming a rectangular frame. 2 No. 1 webs 5 form a group, and the No. 1 webs 5 in the same group are perpendicular to each other and connected at the ends; the end connection lines of the No. 1 webs 5 in the same group coincide with the edge lines of the rectangular frame; the No. 1 webs 5 and the No. 2 webs 7 are collinearly arranged or perpendicularly arranged.

[0028] In another embodiment of the present invention, the web also includes a No. 3 web 6; the No. 3 web 6 is arranged at the connection of the No. 2 web 7 of the same group; one end of the No. 3 web 6 is vertically arranged to the No. 2 web 7 connected to it, and the other end of the No. 3 web 6 is fixedly connected to the inside of the instrument cabin skin 1.

[0029] In another embodiment of the present invention, under the premise that the instrument cabin meets the design requirements, the No. 1 web 5 and the No. 2 web 7 form a "well"-shaped structure, but the No. 1 web 5 and the No. 2 web 7 are not set to 8 locations, but less than that number. For example, the No. 1 web 5 is set to 4 locations, wherein the No. 1 web 5 of the same group is made of a whole plate and is bent at corresponding positions to ensure the corresponding structure and vertical setting. Similarly, the No. 2 web 7 is made of a whole plate and is welded at the head and tail to form a ring structure, and is bent and shaped at corresponding positions to form a rectangular frame. This method can not only realize the web structure of the "well"-shaped structure, but also reduce the number of the No. 1 web 5 and / or the No. 2 web 7, which can effectively improve the processing efficiency of the web and reduce the processing cost.

[0030] In another embodiment of the present invention, a multi-web rocket instrument cabin also includes an instrument cabin stringer 3 fixed to the outer surface of the instrument cabin skin 1; the instrument cabin stringer 3 is arranged parallel to the axis of the instrument cabin skin 1.

[0031] In another embodiment of the present invention, a multi-web rocket instrument cabin also includes an instrument cabin upper end frame 2 and an instrument cabin lower end frame 4; the instrument cabin upper end frame 2 is fixedly arranged at one end of the instrument cabin skin 1 and is fixedly connected to the outer wall of the instrument cabin skin 1; the instrument cabin lower end frame 4 is fixedly arranged at the other end of the instrument cabin skin 1.

[0032] Preferably, the upper end frame 2 of the instrument cabin and the lower end frame 4 of the instrument cabin are placed outward and turned outward, that is, the upper end frame 2 of the instrument cabin and the lower end frame 4 of the instrument cabin are fixedly connected to the outer wall of the instrument cabin skin 1.

[0033] In another embodiment of the present invention, a multi-web rocket instrument cabin further includes an inertial group bracket 10 for fixing the inertial group, and the inertial group bracket 10 is fixedly connected to the inner wall of the instrument cabin skin 1.

[0034] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0035] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0036] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0037] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A multi-web rocket instrument cabin, characterized in that: include: An instrument cabin skin (1), a belly plate, and an engine frame (8) for fixing an engine (9); the instrument cabin skin (1) is a cylindrical structure with openings at both ends; the internal cavity of the instrument cabin skin (1) is a mounting cavity; the belly plate is fixedly arranged in the mounting cavity and is fixedly connected to the inner wall of the instrument cabin skin (1); the engine frame (8) is fixedly arranged in the instrument cabin skin (1) via the belly plate.

2. The multi-web rocket instrument cabin according to claim 1, characterized in that: The web plate comprises a first web plate (5) arranged transversely and a second web plate (7) arranged longitudinally, wherein the first web plate (5) and the second web plate (7) form a "well"-shaped structure.

3. The multi-web rocket instrument cabin as claimed in claim 2, characterized in that: The center frame of the "well"-shaped structure formed by the first web (5) and the second web (7) serves as a mounting interface for mounting the engine (9); the engine (9) is fixedly mounted in the center frame of the "well"-shaped structure formed by the first web (5) and the second web (7).

4. The multi-web rocket instrument cabin according to claim 3, characterized in that: The first webs (5) are distributed at 8 locations; the second webs (7) are distributed at 8 locations; The second webs (7) at 2 locations form a group, the second webs (7) in the same group are adjacent and collinear, and the second webs (7) in adjacent groups are perpendicular to each other to form a rectangular frame; The No. 1 webs (5) at the two locations form a group, the No. 1 webs (5) in the same group are perpendicular to each other and connected at the ends; the end connection lines of the No. 1 webs (5) in the same group coincide with the edge lines of the rectangular frame; the No. 1 webs (5) and the No. 2 webs (7) are arranged in the same line or perpendicularly.

5. The multi-web rocket instrument cabin according to claim 4, characterized in that: The engine frame (8) is fixedly arranged in the rectangular frame; the engine (9) is fixedly connected to the instrument cabin skin (1) via the engine frame (8) and the web; the axis of the engine (9) coincides with the axis of the instrument cabin skin (1).

6. The multi-web rocket instrument cabin according to claim 5, characterized in that: The engine frame (8) comprises a frame body and an engine mounting hole arranged in the frame body; the engine (9) is arranged in the engine mounting hole and fixedly connected to the frame body.

7. The multi-web rocket instrument cabin as claimed in claim 2, characterized in that: The webs also include a third web (6); the third web (6) is arranged at a connection with the second web (7) in the same group; one end of the third web (6) is arranged perpendicular to the second web (7) connected thereto, and the other end of the third web (6) is fixedly connected to the inside of the instrument cabin skin (1).

8. The multi-web rocket instrument cabin according to claim 7, characterized in that: It also comprises an instrument cabin beam (3) fixedly arranged on the outer surface of the instrument cabin skin (1); the instrument cabin beam (3) is arranged parallel to the axis of the instrument cabin skin (1).

9. The multi-web rocket instrument cabin according to claim 1, characterized in that: It also comprises an instrument cabin upper end frame (2) and an instrument cabin lower end frame (4); the instrument cabin upper end frame (2) is fixedly arranged at one end of the instrument cabin skin (1) and is fixedly connected to the outer wall of the instrument cabin skin (1); the instrument cabin lower end frame (4) is fixedly arranged at the other end of the instrument cabin skin (1) and is fixedly connected to the outer wall of the instrument cabin skin (1).

10. The multi-web rocket instrument cabin according to claim 1, characterized in that: The multi-web rocket instrument cabin also includes an inertial group bracket (10); the inertial group bracket (10) is fixedly connected to the inner wall of the instrument cabin skin (1).

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