Distributed control moment gyroscope group mounting device

Abstract

The application provides a distributed control moment gyro group mounting device for spacecraft configuration and layout design, which comprises micro-vibration suppression supports, control moment gyro elements and a moment gyro mounting plate; the micro-vibration suppression supports are provided in plurality, the moment gyro mounting plate provides mounting interfaces for the micro-vibration suppression supports, the plurality of micro-vibration suppression supports are arranged on the moment gyro mounting plate through the mounting interfaces, the control moment gyro elements are provided in plurality, the micro-vibration suppression supports provide interfaces for the control moment gyro elements, the micro-vibration suppression supports suppress the interference of the micro-vibration response of the control moment gyro elements on sensitive loads, and the plurality of control moment gyro elements are arranged on the plurality of micro-vibration suppression supports through the interfaces. The mounting mode has the advantages of good heat dissipation, convenient precision control and convenient operation, the interference of the micro-vibration response of the control moment gyro elements on sensitive loads is suppressed, and the stability, reliability and safety of high-precision sensitive loads on the satellite during on-orbit operation are ensured.

Description

Technical Field

[0001] This invention relates to the configuration and layout design of spacecraft, and more specifically, to a distributed control moment gyroscope group installation device. Background Technology

[0002] A control moment gyroscope (CMG) is an actuator widely used in high-resolution observation satellites. It generates a reaction torque by changing the direction of the angular momentum vector of a high-speed rotor. However, while generating a large torque, internal imbalances or noise within the CMG can cause vibrations in the satellite structure, making the CMG a significant source of vibration disturbance on the satellite. Currently, the installation method for control moment gyroscope clusters is relatively simple, employing a centralized, integrated installation. The main problem with this method is poor heat dissipation, which fails to meet the thermal environment requirements of the moment gyroscope.

[0003] A search of existing technologies revealed Chinese invention patent publication number CN1974326, which discloses an integrated magnetic levitation control torque gyroscope control platform. This platform provides integrated control of a magnetic levitation control torque gyroscope system and primarily comprises an application layer, a system layer, a fieldbus, and a control layer. The application layer, built upon the system layer, mainly performs signal data acquisition, complex algorithm calculations, and monitoring functions, including a status acquisition module, a monitoring module, a communication module, and a human-machine interface module. This patent addresses the aforementioned issues and is applicable to integrated magnetic levitation control torque gyroscope control platforms. This patent primarily focuses on the integrated control of magnetic levitation control torque gyroscope systems.

[0004] A search of existing technologies revealed Chinese invention patent publication number CN103603916B, which discloses a vibration isolation device for a control moment gyroscope. This device includes at least one upper platform, at least one vibration isolation component, and at least one lower platform, wherein the vibration isolation component is fixed between the upper and lower platforms. The vibration isolation component includes a housing element, a vibration isolation spring, a first limiting sleeve, a second limiting sleeve, a first base, a second base, and four sets of damping elements. The vibration isolation spring is disposed on the housing element. The first limiting sleeve, the first base, and the housing element form a first housing portion and a second housing portion. The second limiting sleeve, the second base, and the housing element form a third housing portion and a fourth housing portion. The four sets of damping elements are respectively disposed in the first, second, third, and fourth housing portions. This patented technology suffers from the aforementioned problems, specifically concerning the design of the control moment gyroscope vibration isolation device itself. It exhibits poor heat dissipation and fails to meet the thermal environment requirements of the moment gyroscope.

[0005] To address the aforementioned problems, the present invention aims to provide a distributed control moment gyroscope group installation method. This installation method features good heat dissipation, convenient precision control, and easy operation, suppressing the interference of moment gyroscope micro-vibration response on sensitive loads and ensuring the stability, reliability, and safety of high-precision sensitive loads on the satellite during on-orbit operation. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a distributed control torque gyroscope group installation device.

[0007] A distributed control torque gyroscope group mounting device according to the present invention includes a micro-vibration suppression bracket, a control torque gyroscope component, and a torque gyroscope mounting plate;

[0008] Multiple micro-vibration suppression brackets are provided, and the torque gyroscope mounting plate provides an installation interface for the micro-vibration suppression brackets. Multiple micro-vibration suppression brackets are mounted on the torque gyroscope mounting plate through the installation interface. Multiple control torque gyroscopes are provided, and the micro-vibration suppression brackets provide an interface for the control torque gyroscopes. The micro-vibration suppression brackets suppress the interference of the micro-vibration response of the control torque gyroscopes on the sensitive load. Multiple control torque gyroscopes are correspondingly mounted on multiple micro-vibration suppression brackets through the interface.

[0009] In some embodiments, a partition is fixedly provided on the torque gyroscope mounting plate. The partition provides operating space for the control torque gyroscope component. Multiple partitions are provided, and the multiple partitions are respectively arranged between adjacent control torque gyroscope components.

[0010] In some embodiments, the torque gyroscope mounting plate has a slot with a circular cross-section, and a plurality of control torque gyroscope components are arranged circumferentially around the slot on the torque gyroscope mounting plate.

[0011] In some embodiments, the micro-vibration suppression bracket includes a first end face and a second end face. The first end face is fixedly disposed on the torque gyroscope mounting plate. One end of the first end face is fixedly disposed with one end of the second end face. The second end face is obliquely disposed on the first end face. The control torque gyroscope is mounted on the second end face.

[0012] In some embodiments, five control torque gyroscopes are provided, including a first torque gyroscope, a second torque gyroscope, a third torque gyroscope, a fourth torque gyroscope, and a fifth torque gyroscope, which are arranged sequentially around the slot circumferentially.

[0013] In some embodiments, the partition is provided between the third torque gyroscope and the first torque gyroscope, the partition is provided on the other side of the third torque gyroscope, the partition is provided between the fourth torque gyroscope and the second torque gyroscope, and the partition is provided between the second torque gyroscope and the fifth torque gyroscope.

[0014] In some embodiments, the centerline of the first moment gyroscope forms an angle of 72° with the centerlines of the second and fifth moment gyroscopes on the projection plane; the centerline of the second moment gyroscope forms an angle of 72° with the centerline of the third moment gyroscope; the centerline of the third moment gyroscope forms an angle of 72° with the centerline of the fourth moment gyroscope; and the centerline of the fourth and fifth moment gyroscopes forms an angle of 72° on the projection plane.

[0015] In some embodiments, the partition uses an M55J-6K carbon fiber frame and has a hollow structure, with the base material of the frame being Ag80.

[0016] In some embodiments, the second end face is tilted at an angle of 63.43° above the first end face.

[0017] In some embodiments, the torque gyroscope mounting plate is a sandwich panel made of aluminum alloy material panel and honeycomb core. The thickness of the sandwich panel is 30 mm, the thickness of the panel is 0.3 mm, the honeycomb core is aluminum honeycomb core material, the wall thickness of the honeycomb core is 0.03 mm, the cell side length of the honeycomb core is 5 mm, and the honeycomb core is bonded to the panel with J47 adhesive film, the thickness of the adhesive film being 0.1 mm.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. This invention sets up a control torque gyroscope component, which is mounted on the torque gyroscope mounting plate via a micro-vibration suppression bracket. This mounting method has advantages such as good heat dissipation, easy precision control, and convenient operation. It suppresses the interference of the torque gyroscope's micro-vibration response on sensitive loads, ensuring the stability, reliability, and safety of high-precision sensitive loads on the satellite during on-orbit operation.

[0020] 2. This invention sets up a micro-vibration suppression bracket and a control torque gyroscope. The angle between two adjacent control torque gyroscopes on the projection plane is 72°. The tilt angle of the control torque gyroscope through the micro-vibration suppression bracket is 63.43°. The torque gyroscope mounting plate has no direct connection with the sensitive load and is far away from the sensitive load, thus ensuring the micro-vibration working environment of the sensitive load. Attached Figure Description

[0021] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0022] Figure 1 This is a schematic diagram of the structure of the distributed control torque gyroscope group installation device of the present invention;

[0023] Figure 2 This is a schematic diagram of the layout of the torque gyroscope group in the distributed control torque gyroscope group installation device of the present invention;

[0024] Figure 3 This is a schematic diagram of the micro-vibration suppression stent of the present invention;

[0025] Figure 4 This is a schematic diagram of the structure of the partition of the present invention;

[0026] Figure labels;

[0027] Detailed Implementation

[0028] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0029] like Figure 1 The diagram shows the structure of a distributed control torque gyroscope group device, including a micro-vibration suppression bracket 1, control torque gyroscope components 2, and torque gyroscope mounting plates 4. Multiple micro-vibration suppression brackets 1 are provided, and the torque gyroscope mounting plates 4 provide mounting interfaces for the micro-vibration suppression brackets 1. Multiple micro-vibration suppression brackets are mounted on the torque gyroscope mounting plates 4 through these mounting interfaces. Multiple control torque gyroscope components 2 are provided, and the micro-vibration suppression brackets 1 provide interfaces for them. The micro-vibration suppression brackets 1 suppress the interference of the micro-vibration response of the control torque gyroscope components 2 on sensitive loads. Multiple control torque gyroscope components 2 are correspondingly mounted on multiple micro-vibration suppression brackets 1 through their interfaces.

[0030] A partition 3 is fixedly installed on the torque gyroscope mounting plate 4. The partition 3 provides operating space for the control torque gyroscope component 2. Multiple partitions 3 are provided, and each partition 3 is positioned between adjacent control torque gyroscope components 2. Figure 4The diagram shows the structure of partition 3. Partition 3 uses an M55J-6K carbon fiber frame and has a hollow structure. The base material of the frame is Ag80. The frame is laid up manually with pre-impregnated non-woven fabric. The layup is quasi-isotropic, and the layers are cured by heating and pressurizing in an autoclave. The required precision is ensured by machining.

[0031] A slot 41 is formed on the torque gyroscope mounting plate 4. The slot 41 has a circular cross-section, and multiple control torque gyroscopes 2 are arranged circumferentially around the slot 41 on the torque gyroscope mounting plate 4. The torque gyroscope mounting plate 4 is a sandwich panel made of aluminum alloy panel and honeycomb core. The thickness of the sandwich panel is 30 mm, the thickness of the panel is 0.3 mm, the honeycomb core is aluminum honeycomb core material, the wall thickness of the honeycomb core is 0.03 mm, the cell side length of the honeycomb core is 5 mm, and the honeycomb core is bonded to the panel with J47 adhesive film, the thickness of which is 0.1 mm. The torque gyroscope mounting plate 4 provides an interface for the control torque gyroscopes 2 and suppresses the interference of the micro-vibration response of the control torque gyroscopes 2 on sensitive loads.

[0032] like Figure 3 The diagram shows the structure of the micro-vibration suppression bracket 1. The micro-vibration suppression bracket 1 includes a first end face and a second end face. The first end face is fixedly mounted on the torque gyroscope mounting plate 4. One end of the first end face is fixedly mounted to one end of the second end face. The second end face is inclinedly mounted on the first end face. The control torque gyroscope 2 is mounted on the second end face. In this embodiment, the second end face is inclined at an angle of 63.43° above the first end face.

[0033] like Figure 3 As shown, the micro-vibration suppression bracket 1 also includes eight sets of vibration isolation components and four sets of unlocking components. During the launch phase, the unlocking components secure the control moment gyroscope 2 to the micro-vibration suppression bracket 1 to ensure stiffness requirements and that the control moment gyroscope 2 meets the active phase response requirements. During the on-orbit flight phase, a remote unlocking command is sent according to the flight procedure. After the unlocking components unlock, the control moment gyroscope 2 is connected to the micro-vibration suppression bracket 1 only through the vibration isolation components. The vibration isolation components then begin to work, suppressing the transmission of micro-vibrations of the control moment gyroscope 2 to the satellite and sensitive loads, thus ensuring the micro-vibration working environment of the sensitive loads.

[0034] like Figure 2 The diagram shows the layout of the torque gyroscope group in the distributed control torque gyroscope group device. There are five control torque gyroscope components 2, including a first torque gyroscope 5, a second torque gyroscope 6, a third torque gyroscope 7, a fourth torque gyroscope 8, and a fifth torque gyroscope 9. The fourth torque gyroscope 8, the second torque gyroscope 6, the fifth torque gyroscope 9, the first torque gyroscope 5, and the third torque gyroscope 7 are arranged circumferentially around the slot 41 in sequence.

[0035] A partition 3 is provided between the third torque gyroscope 7 and the first torque gyroscope 5. A partition 3 is provided on the other side of the third torque gyroscope 7. A partition 3 is provided between the fourth torque gyroscope 8 and the second torque gyroscope 6. A partition 3 is provided between the second torque gyroscope 6 and the fifth torque gyroscope 9.

[0036] The centerline of the first torque gyroscope 5 forms an angle of 72° with the centerlines of the second torque gyroscope 6 and the fifth torque gyroscope 9 on the projection plane. Similarly, the centerlines of the second torque gyroscope 6 and the third torque gyroscope 7, the third torque gyroscope 7 and the fourth torque gyroscope 8, and the fourth torque gyroscope 8 and the fifth torque gyroscope 9 all form an angle of 72° on the projection plane. The configuration accuracy of the five control torque gyroscopes 2 is guaranteed by the overall machining accuracy of the torque gyroscope mounting plate 4. It is required that the installation deviation between the reference of the control torque gyroscope 2 and the overall satellite mounting reference after installation is less than or equal to 3′.

[0037] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "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 application 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 application.

[0038] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A distributed control torque gyroscope group installation device, characterized in that, It includes a micro-vibration suppression bracket (1), a control torque gyroscope component (2), and a torque gyroscope mounting plate (4); The micro-vibration suppression bracket (1) is provided in multiple ways. The torque gyroscope mounting plate (4) provides an installation interface for the micro-vibration suppression bracket (1). The multiple micro-vibration suppression brackets are mounted on the torque gyroscope mounting plate (4) through the installation interface. The control torque gyroscope (2) is provided in multiple ways. The micro-vibration suppression bracket (1) provides an interface for the control torque gyroscope (2). The micro-vibration suppression bracket (1) suppresses the interference of the micro-vibration response of the control torque gyroscope (2) on the sensitive load. The multiple control torque gyroscopes (2) are correspondingly mounted on the multiple micro-vibration suppression brackets (1) through the interface. A partition (3) is fixedly installed on the torque gyroscope mounting plate (4). The partition (3) provides operating space for the control torque gyroscope component (2). There are multiple partitions (3), and the multiple partitions (3) are respectively arranged between adjacent control torque gyroscope components (2). The micro-vibration suppression bracket (1) includes a first end face and a second end face. The first end face is fixedly mounted on the torque gyroscope mounting plate (4). One end of the first end face is fixedly mounted on one end of the second end face. The second end face is inclinedly mounted on the first end face. The control torque gyroscope (2) is mounted on the second end face. The second end face is tilted at an angle of 63.43° and is positioned above the first end face. The control torque gyroscope (2) is provided in five parts, including a first torque gyroscope (5), a second torque gyroscope (6), a third torque gyroscope (7), a fourth torque gyroscope (8), and a fifth torque gyroscope (9). The center line of the first torque gyroscope (5) forms an angle of 72° with the center line of the second torque gyroscope (6) and the center line of the fifth torque gyroscope (9) on the projection plane. The center line of the second torque gyroscope (6) forms an angle of 72° with the center line of the third torque gyroscope (7) on the projection plane. The center line of the third torque gyroscope (7) forms an angle of 72° with the center line of the fourth torque gyroscope (8) on the projection plane. The center line of the fourth torque gyroscope (8) forms an angle of 72° with the center line of the fifth torque gyroscope (9) on the projection plane.

2. The distributed control torque gyroscope group installation device according to claim 1, characterized in that, The torque gyroscope mounting plate (4) has a slot (41) with a circular cross-section. Multiple control torque gyroscope components (2) are arranged circumferentially around the slot (41) on the torque gyroscope mounting plate (4).

3. The distributed control torque gyroscope group installation device according to claim 2, characterized in that, The fourth torque gyroscope (8), the second torque gyroscope (6), the fifth torque gyroscope (9), the first torque gyroscope (5), and the third torque gyroscope (7) are arranged circumferentially around the slot (41) in sequence.

4. The distributed control torque gyroscope group installation device according to claim 3, characterized in that, The partition (3) is provided between the third torque gyroscope (7) and the first torque gyroscope (5), and the partition (3) is provided on the other side of the third torque gyroscope (7). The partition (3) is provided between the fourth torque gyroscope (8) and the second torque gyroscope (6), and the partition (3) is provided between the second torque gyroscope (6) and the fifth torque gyroscope (9).

5. The distributed control torque gyroscope group installation device according to claim 1, characterized in that, The partition (3) adopts an M55J-6K carbon fiber frame and the partition (3) adopts a hollow structure. The base material of the frame is Ag80.

6. The distributed control torque gyroscope group installation device according to claim 2, characterized in that, The torque gyroscope mounting plate (4) is a sandwich panel made of aluminum alloy material panel and honeycomb core. The thickness of the sandwich panel is 30 mm, the thickness of the panel is 0.3 mm, the honeycomb core is aluminum honeycomb core material, the wall thickness of the honeycomb core is 0.03 mm, the cell side length of the honeycomb core is 5 mm, and the honeycomb core is bonded to the panel by J47 adhesive film with a thickness of 0.1 mm.

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