Anti-hooking protective cover and locking device of control moment gyro

Abstract

The application provides a kind of anti-hooking protective cover and locking device of control moment gyro in the technical field of spacecraft, including control moment gyro body, common interface locking washer and coaxial thin-wall protective cover.The coaxial thin-wall protective cover is arranged on the control moment gyro body, and multiple common interface locking washers are arranged in the four directions of the control moment gyro body.The application achieves the purpose of anti-hooking of control moment gyro on spacecraft through simple mechanical design, without additional interface, without changing the existing design of control moment gyro, and can also achieve frequency offset design by adjusting the thickness of coaxial thin-wall carbon fiber protective cover for the resonance and harmonic phenomenon of control moment gyro.The application has the characteristics of simple structure, light weight and high reliability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft, in particular, to a control moment gyro anti-hooking protective cover and locking device. BACKGROUND

[0002] With the development of spacecraft technology, the control accuracy of spacecraft is higher and higher, and spacecraft using control moment gyro for attitude control is increasingly widespread, and the cable network in the spacecraft is also more and more complex, involving more and more active cables, and the active cables are less constrained and more free in the absence of gravity, and the hooking of the control moment gyro and the cables seriously affects the service life and reliability of the spacecraft.

[0003] Active component anti-hooking needs to be considered from two aspects: first, the cables should be as fixed as possible to reduce active cables, but it is difficult to reduce active cables for many spacecrafts that need to be opened for electrical testing or have high integration; second, the control moment gyro is protected to avoid hooking, but the problem that follows is how to fix the protective components without increasing the interface or changing the product profile, and the fixing method should be reliable and effective, and can also avoid resonance or resonance phenomenon with the control moment gyro, while the resource demand on the spacecraft is minimized. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a control moment gyro anti-hooking protective cover and locking device.

[0005] According to the control moment gyro anti-hooking protective cover and locking device provided by the present application, the control moment gyro body, the common interface locking gasket and the coaxial thin-walled protective cover are included.

[0006] The coaxial thin-walled protective cover is arranged on the control moment gyro body, and a plurality of common interface locking gaskets are arranged in the four directions of the control moment gyro body.

[0007] The coaxial thin-walled protective cover is arranged on the control moment gyro body, and a plurality of common interface locking gaskets are arranged in the four directions of the control moment gyro body.

[0008] The control moment gyro body is provided with a mounting hole one, and a plurality of common interface locking gaskets are provided with a mounting hole two, and the mounting hole one and the mounting hole two are arranged in alignment.

[0009] The control moment gyro body is provided with a fitting surface, and a plurality of common interface locking gaskets are provided with ear pieces, and the fitting surface and the plurality of ear pieces are fitted.

[0010] In some embodiments, the coaxial thin-wall protective cover and the control moment gyro body are in close contact by inserting screws into the mounting hole one and the mounting hole two and tightening.

[0011] In some embodiments, the coaxial thin-wall protective cover is limited from translating arbitrarily by the abutment of the ears on the common interface locking gasket and the abutting surface on the coaxial thin-wall protective cover.

[0012] In some embodiments, the coaxial thin-wall protective cover is limited from rotating arbitrarily by the abutment of the abutting surface on the coaxial thin-wall protective cover and the frame on the control moment gyro body.

[0013] In some embodiments, the coaxial thin-wall protective cover is provided with semicircular notches at both ends, which are used to clamp the shaft ends on both sides of the control moment gyro body.

[0014] In some embodiments, multiple common interface locking gaskets are provided around the coaxial thin-wall protective cover.

[0015] In some embodiments, the convex surface of the coaxial thin-wall protective cover is provided in an inverted bowl shape, the abutting surface is provided around the convex surface on both sides, and the outward surface of the abutting surface is provided as an abutting surface, on which the ears are provided.

[0016] In some embodiments, the coaxial thin-wall protective cover comprises a coaxial thin-wall carbon fiber material protective cover.

[0017] Compared with the prior art, the present application has the following advantages:

[0018] The coaxial thin-wall protective cover is provided on the control moment gyro body, and multiple common interface locking gaskets are provided around the control moment gyro body.

[0019] The coaxial thin-wall protective cover is provided with an abutting surface, the control moment gyro body is provided with a frame, and the abutting surface and the frame are in alignment and installed.

[0020] The control moment gyro body is provided with a mounting hole one, and the multiple common interface locking gaskets are provided with a mounting hole two, which are in alignment and installed.

[0021] The control moment gyro body is provided with an abutting surface, and the multiple common interface locking gaskets are provided with ears, which are in abutment.

[0022] By adopting the above design scheme, the present application does not need additional interfaces and can solve the problem of anti-hooking of the movable rotating parts in the spacecraft without changing the existing structure of the control moment gyro.

[0023] Meanwhile, aiming at the resonance and harmonic resonance phenomenon of the control moment gyro, the thickness of the coaxial thin-wall carbon fiber protective cover can be adjusted to achieve the frequency offset design, so as to avoid the resonance and harmonic resonance phenomenon, and the design scheme has the characteristics of simple structure, light weight and high reliability. BRIEF DESCRIPTION OF DRAWINGS

[0024] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments thereof, read in conjunction with the accompanying drawings:

[0025] Figure 1 It is an appearance structure diagram of the control moment gyro anti-hooking protective cover and locking device of the present application;

[0026] Figure 2 It is a structure diagram of the control moment gyro body on the control moment gyro anti-hooking protective cover and locking device of the present application;

[0027] Figure 3 It is a structure diagram of the common interface locking gasket on the control moment gyro anti-hooking protective cover and locking device of the present application;

[0028] Figure 4 It is a structure diagram of the coaxial thin-wall protective cover on the control moment gyro anti-hooking protective cover and locking device of the present application.

[0029] LIST OF REFERENCE NUMERALS:

[0030] Control moment gyro body 1 ear piece 7

[0031] Common interface locking gasket 2 butt joint surface 8

[0032] Coaxial thin-wall protective cover 3 adhering surface 9

[0033] Frame 4 convex surface 10

[0034] Mounting hole one 5 semicircular notch 11

[0035] Mounting hole two 6 DETAILED DESCRIPTION

[0036] The present application will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that for those skilled in the art, without departing from the concept of the present application, a number of changes and improvements can be made. These all belong to the protection scope of the present application.

[0037] As Figures 1-4As shown, the present application comprises a control moment gyro body 1, a common interface locking washer 2, and a coaxial thin-walled protective cover 3. The coaxial thin-walled protective cover 3 is arranged on the control moment gyro body 1, and a plurality of common interface locking washers 2 are arranged in the four directions of the control moment gyro body 1. The coaxial thin-walled protective cover 3 is provided with a butt joint surface 8, the control moment gyro body 1 is provided with a frame 4, and the butt joint surface 8 is arranged in alignment with the frame 4. The control moment gyro body 1 is provided with a mounting hole one 5, and the plurality of common interface locking washers 2 are provided with mounting hole twos 6, and the mounting hole one 5 and the mounting hole two 6 are arranged in alignment. The control moment gyro body 1 is provided with a fitting surface 9, and the plurality of common interface locking washers 2 are provided with ear pieces 7, and the fitting surface 9 is arranged in fitting with the plurality of ear pieces 7.

[0038] The present application realizes the mutual compression arrangement of the coaxial thin-walled protective cover 3 and the control moment gyro body 1 by inserting screws into the mounting hole one 5 and the mounting hole two 6 and tightening the screws. The present application realizes the fitting arrangement of the ear pieces 7 on the common interface locking washer 2 and the fitting surface 9 on the coaxial thin-walled protective cover 3, which is used to limit the arbitrary translation of the coaxial thin-walled protective cover 3. The present application realizes the fitting arrangement of the butt joint surface 8 on the coaxial thin-walled protective cover 3 and the frame 4 on the control moment gyro body 1, which is used to limit the arbitrary rotation of the coaxial thin-walled protective cover 3. The coaxial thin-walled protective cover 3 is provided with semicircular notches 11 at both ends, which are used to clamp the shaft ends of the control moment gyro body 1. The plurality of common interface locking washers 2 are arranged on the periphery of the coaxial thin-walled protective cover 3. The convex surface 10 on the coaxial thin-walled protective cover 3 is arranged in an inverted bowl shape, the butt joint surface 8 is arranged on both sides of the convex surface 10, and one side of the butt joint surface 8 is arranged as the fitting surface 9, and the ear pieces 7 are arranged on the fitting surface 9.

[0039] Specifically, in this embodiment, the coaxial thin-walled protective cover 3 is made of a coaxial thin-walled carbon fiber material protective cover.

[0040] Specifically, in this embodiment, the silicon rubber should be pre-fixed on the butt joint surface 8 of the coaxial thin-walled carbon fiber protective cover 3 before the spacecraft is launched or before the mechanical test.

[0041] Specifically, in this embodiment, the mounting hole twos 6 of the four common interface locking washers 2 are aligned and mounted with the mounting hole one 5 of the control moment gyro body 1, at which time the ear pieces 7 of the common interface locking washers 2 are fitted with the surface of the fitting surface 9 of the coaxial thin-walled protective cover 3.

[0042] Specifically, in this embodiment, the coaxial thin-walled carbon fiber protective cover 3 and the control moment gyro body 1 are compressed by tightening the screws and elastic pads on the support or honeycomb plate of the control moment gyro, and after applying the tightening torque, the coaxial thin-walled carbon fiber protective cover 3 and the control moment gyro body 1 are compressed.

[0043] Working principle:

[0044] The application solves the anti-hooking problem of the movable rotating part in the spacecraft by using simple structure design, and the hooking problem has been a problem that greatly influences the reliability of the spacecraft. The application uses the universal ready-to-use interface design, the control moment gyro used in the spacecraft is mostly the type spectrum product, the appearance and the interface are determined, the application can use the existing interface of the control moment gyro for fixing, without additional interface, and without any modification to the type spectrum product. Because the existing control moment gyro itself often couples with the local spacecraft, resonance and harmonic resonance phenomenon occurs, therefore, the application can adjust and design the frequency by changing the wall thickness, to achieve the purpose of frequency error design.

[0045] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0046] The specific embodiments of the application are described above. It should be understood that the application is not limited to the specific implementation described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A hooking prevention shield for a control moment gyroscope with a locking device, characterized in that It comprises a control moment gyro body (1), a common interface locking gasket (2) and a coaxial thin-wall protective cover (3); The coaxial thin-wall protective cover (3) is arranged on the control moment gyro body (1), and a plurality of common interface locking gaskets (2) are arranged on the control moment gyro body (1) in the four directions. The coaxial thin-wall protective cover (3) is provided with a butt joint surface (8), the control moment gyro body (1) is provided with a frame (4), and the butt joint surface (8) is arranged in alignment with the frame (4). The control moment gyro body (1) is provided with a mounting hole one (5), a plurality of common interface locking gaskets (2) are provided with mounting hole two (6), and the mounting hole one (5) is arranged in alignment with the mounting hole two (6). The control moment gyro body (1) is provided with a fitting surface (9), and a plurality of common interface locking gaskets (2) are provided with ear pieces (7), and the fitting surface (9) is arranged in fitting with a plurality of ear pieces (7).

2. The anti-hooking protective cover of the control moment gyro with the locking device according to claim 1, wherein The coaxial thin-wall protective cover (3) and the control moment gyro body (1) are arranged in mutual compression by inserting screws into the mounting hole one (5) and the mounting hole two (6) and tightening.

3. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that The ear pieces (7) on the common interface locking gasket (2) and the fitting surface (9) on the coaxial thin-wall protective cover (3) are arranged in fitting, which is used for limiting the arbitrary translation of the coaxial thin-wall protective cover (3).

4. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that The butt joint surface (8) on the coaxial thin-wall protective cover (3) and the frame (4) on the control moment gyro body (1) are arranged in fitting, which is used for limiting the arbitrary rotation of the coaxial thin-wall protective cover (3).

5. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that The coaxial thin-wall protective cover (3) is provided with semicircular notches (11) at both ends, which are used for clamping the shaft ends of the control moment gyro body (1).

6. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that A plurality of common interface locking gaskets (2) are arranged on the coaxial thin-wall protective cover (3) in the four directions.

7. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that The convex surface (10) on the coaxial thin-wall protective cover (3) is arranged in inverted bowl shape, the butt joint surface (8) is arranged on both sides of the convex surface (10), and one side of the butt joint surface (8) is provided with a fitting surface (9), and the ear pieces (7) are arranged on the fitting surface (9).

8. The anti-hooking guard for a control moment gyroscope with locking device according to claim 1, characterized in that The coaxial thin-wall protective cover (3) comprises a coaxial thin-wall carbon fiber material protective cover.

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