A large payload module for a space station

Abstract

This invention discloses a large payload module for a space station, comprising a module structure, a two-degree-of-freedom optical payload camera, a separable beam-type reinforcement structure on the Earth-facing side, a separable beam-type reinforcement structure on the Space-facing side, an optical payload back-end processing module, and a floating vibration isolation and stabilization system. The module structure serves as the main load-bearing frame for the entire payload module, supporting other components. The two ends of the two-degree-of-freedom optical payload camera are connected to the module structure via the floating vibration isolation and stabilization system. The separable beam-type reinforcement structures on the Earth-facing and Space-facing sides are connected to the module structure to further strengthen it and can be separated after orbit insertion. The optical payload back-end processing module is installed within the module structure. The floating vibration isolation and stabilization system isolates external vibrations in orbit. This invention allows the space station module to provide a stable environment for the installation and support of large-aperture optical payloads while allowing for large openings to provide a field of view and ensuring strength and stiffness.

Description

Technical Field

[0001] This invention relates to the field of spacecraft overall design, and in particular to a large payload module for a space station. Background Technology

[0002] Space payloads, especially large-aperture optical payloads, are often large and heavy, and have high requirements for installation, pointing accuracy, and field of view. Therefore, space optical payloads are generally designed as independent optical satellites or detectors on dedicated spacecraft platforms, such as the famous Hubble Telescope. In this way, the pointing of the optical camera can be achieved through attitude adjustment of the spacecraft platform, and an unobstructed field of view is easily achieved. However, optical payloads on a space station are just one of many space payloads, each with its own pointing requirements. Furthermore, the space station has numerous external devices, making it impractical to adjust the camera pointing through attitude adjustment of the entire space station. Therefore, the space station's optical payloads need to be equipped with a two-degree-of-freedom pointing mechanism for independent pointing control. This leads to another problem: large-aperture optical payloads on the space station are generally installed inside the cabin. The two-degree-of-freedom pointing and field-of-view requirements necessitate large openings in the cabin structure to allow space for the camera's field of view, resulting in significant losses in structural strength and stiffness, and making reinforcement design difficult.

[0003] In conclusion, how to adopt innovative design to enable the large-aperture optical payload module of the space station to not only provide a stable environment for installation and support, but also to open large openings to allow for a field of view while ensuring strength and rigidity is a challenging problem of significant practical importance. Summary of the Invention

[0004] To overcome the shortcomings of the prior art, the present invention provides a large payload module for a space station that can install and carry large-aperture optical payloads with an aperture of up to 2 meters, and meet their pointing and field of view requirements.

[0005] To achieve the aforementioned objectives of the invention, the technical solution adopted to solve its technical problems is as follows:

[0006] A large payload module for a space station includes a module structure, a two-degree-of-freedom optical payload camera, a separable beam-type reinforcement structure on the ground side, a separable beam-type reinforcement structure on the space side, an optical payload back-end processing module, and a floating vibration isolation and stabilization system, wherein:

[0007] The cabin structure is the main load-bearing frame of the entire payload compartment, used to support the dual-degree-of-freedom optical payload camera, the ground-side separable beam-type reinforcement structure, the sky-side separable beam-type reinforcement structure, the optical payload back-end processing module, and the floating vibration isolation and stabilization system.

[0008] The two ends of the dual-degree-of-freedom optical payload camera are respectively connected to the cabin structure through the floating vibration isolation and stabilization system;

[0009] The detachable beam-type reinforcement structure on the ground side and the detachable beam-type reinforcement structure on the space side are respectively connected to the cabin structure to further strengthen the cabin structure, and can be separated after entering orbit;

[0010] The optical payload back-end processing module is installed in the cabin structure;

[0011] The floating vibration isolation and stabilization system is used to isolate external vibrations from the track.

[0012] Furthermore, the dual-degree-of-freedom optical payload camera employs orthogonal dual degrees of freedom for spatial pointing, enabling observation of both the Earth and the sky.

[0013] Furthermore, the dual-degree-of-freedom optical payload camera consists of a camera body, an inner frame, and an outer frame. The camera body is installed in the inner frame and can be driven by a motor to rotate around an inner rotation axis. The inner frame is installed in the outer frame and can be driven by a motor to rotate around an outer rotation axis. In this way, the camera body can generate dual-degree-of-freedom rotational motion.

[0014] Furthermore, the cabin structure adopts an external load-bearing cylinder configuration, which is composed of a longitudinal beam structure, a transverse frame structure, and a wall panel structure. The longitudinal beam structure and the transverse frame structure are the main body, and the wall panel structure is the outer wall of the cabin. Two large circumferential openings are opened in the middle of the cabin structure on the ground side and the sky side, respectively, to avoid the sky and ground field of view required by the dual-degree-of-freedom optical payload camera.

[0015] Furthermore, a separable beam-type reinforcement structure is installed at the large circumferential opening on the ground side, and a separable beam-type reinforcement structure is installed at the large circumferential opening on the sky side. The separable beam-type reinforcement structures on the ground side and the sky side respectively adopt X-shaped beam-type reinforcement structures to reinforce the large circumferential opening, and have 5 connection points with the cabin structure, respectively supporting 4 fixed points and the middle position of the top of the large circumferential opening.

[0016] Furthermore, the ground-side detachable beam reinforcement structure and the space-side detachable beam reinforcement structure are respectively connected to the cabin structure at the five connection points via five separation nuts. These connections are used to reinforce the two large circumferential openings of the cabin structure, thereby ensuring the strength and rigidity during the ascent phase. After the fairing is jettisoned after the launch vehicle has completed its launch, the separation nuts are used to unlock and separate the ground-side detachable beam reinforcement structure and the space-side detachable beam reinforcement structure from the cabin structure.

[0017] Furthermore, the load compartment is cylindrical in shape.

[0018] Furthermore, the dual-degree-of-freedom optical payload camera and the optical payload back-end processing module are installed as a whole inside the cabin structure along the cabin axis in a separate layout, with the dual-degree-of-freedom optical payload camera on one side and the optical payload back-end processing module distributed in a wheel-like manner on the other side.

[0019] By employing the above technical solutions, this invention has the following advantages and positive effects compared with the prior art:

[0020] The large payload module for space stations of the present invention can enable the installation of 2-meter diameter optical payloads inside the space station module without obstructing the field of view of other equipment on the space station; at the same time, it provides a stable load-bearing installation environment, and can open a large opening to give up the field of view space while ensuring strength and rigidity. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0022] Figure 1 This is a three-dimensional structural diagram of a large payload module for a space station according to the present invention.

[0023] Figure 2 This is a first-view schematic diagram of the overall structure of a large payload module of a space station according to the present invention.

[0024] Figure 3 This is a second-view schematic diagram of the overall structure of a large payload module of a space station according to the present invention;

[0025] Figure 4 This is an exploded view of the main components of a large payload module for a space station according to the present invention.

[0026] Figure 5 This is a schematic diagram of a dual-degree-of-freedom optical payload camera for a large payload module of a space station according to the present invention.

[0027] Figure 6 This is a schematic diagram of the body structure and separable beam-type reinforcement structure of a large payload module for a space station according to the present invention.

[0028] Figure 7 This is a schematic diagram illustrating the separation process of a separable beam-type reinforcement structure for a large payload module of a space station according to the present invention.

[0029] [Explanation of Key Symbols]

[0030] 1- Cabin structure;

[0031] 2-Two-DOF optical payload camera;

[0032] 3- Separable beam-type reinforcement structure on the ground side;

[0033] 4-Separable beam-type reinforcement structure on the top side;

[0034] 5- Optical payload back-end processing module;

[0035] 6-Floating vibration isolation and stabilization system;

[0036] 7-Camera body;

[0037] 8-Inner frame;

[0038] 9-Outer frame;

[0039] 10-Longitudinal beam structure;

[0040] 11- Horizontal frame structure;

[0041] 12-Panel structure;

[0042] 13-Separation nut;

[0043] 14-Zhou Xiang large opening. Detailed Implementation

[0044] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0045] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for 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 the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0046] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0047] like Figures 1-7 As shown, this embodiment discloses a large payload module for a space station, including a module structure 1, a dual-degree-of-freedom optical payload camera 2, a separable beam-type reinforcing structure on the ground side 3, a separable beam-type reinforcing structure on the space side 4, an optical payload back-end processing module 5, and a floating vibration isolation and stabilization system 6, wherein:

[0048] The cabin structure 1 is the main load-bearing frame of the entire payload cabin section, used to support the dual-degree-of-freedom optical payload camera 2, the ground-side separable beam-type reinforcing structure 3, the sky-side separable beam-type reinforcing structure 4, the optical payload back-end processing module 5, and the floating vibration isolation and stabilization system 6.

[0049] The two ends of the dual-degree-of-freedom optical payload camera 2 are respectively connected to the cabin structure 1 through the floating vibration isolation and stabilization system 6;

[0050] The ground-side separable beam-type reinforcing structure 3 and the space-side separable beam-type reinforcing structure 4 are respectively connected to the cabin structure 1 to further reinforce the cabin structure 1, and can be separated after entering orbit;

[0051] The optical payload back-end processing module 5 is installed in the cabin structure 1;

[0052] The floating vibration isolation and stabilization system 6 is used to isolate external vibrations that are in orbit.

[0053] refer to Figure 5 The dual-degree-of-freedom optical payload camera 2 uses orthogonal dual degrees of freedom for spatial pointing, and is used to realize observation of the earth and the sky.

[0054] Furthermore, the dual-degree-of-freedom optical payload camera 2 consists of a camera body 7, an inner frame 8, and an outer frame 9. The camera body 7 is installed in the inner frame 8 and can be driven by a motor to rotate around the inner rotation axis. The inner frame 8 is installed in the outer frame 9 and can be driven by a motor to rotate around the outer rotation axis. In this way, the camera body 7 can generate dual-degree-of-freedom rotational motion.

[0055] See also Figure 6In this embodiment, the cabin structure 1 adopts an external load-bearing cylinder configuration, which is composed of a longitudinal beam structure 10, a transverse frame structure 11, and a wall panel structure 12. The longitudinal beam structure 10 and the transverse frame structure 11 are the main body, and the wall panel structure is the outer wall of the cabin. Two large circumferential openings of approximately 4 meters × 2.8 meters are opened in the middle of the cabin structure 1 on the ground side and the sky side, respectively, to avoid the sky and ground field of view required by the dual-degree-of-freedom optical payload camera 2, and to meet the field of view requirements of the internal dual-degree-of-freedom optical payload camera 2 under pointing motion.

[0056] refer to Figure 1 , 2 4 and 6, a separable beam-type reinforcement structure 3 is installed at the large circumferential opening on the ground side, and a separable beam-type reinforcement structure 4 is installed at the large circumferential opening on the sky side. In this embodiment, because the cabin structure 1 has a large opening, the separable beam-type reinforcement structure 3 on the ground side and the separable beam-type reinforcement structure 4 on the sky side respectively adopt an X-shaped beam-type reinforcement structure to reinforce the large circumferential opening, and have 5 connection positions with the cabin structure 1, respectively supporting 4 fixed positions and the top middle position of the large circumferential opening.

[0057] Furthermore, the ground-side separable beam reinforcement structure 3 and the space-side separable beam reinforcement structure 4 are respectively connected to the cabin structure 1 at the five connection points via five separation nuts 13. These connections are used to reinforce the two large circumferential openings of the cabin structure 1, thereby ensuring the strength and rigidity during the ascent phase. After the fairing is jettisoned after the launch vehicle has completed its launch, the separation nuts 13 are used to unlock and separate the ground-side separable beam reinforcement structure 3 and the space-side separable beam reinforcement structure 4 from the cabin structure 1.

[0058] The aforementioned large payload module of the space station has a main force transmission structure 1, and the payload module is cylindrical in shape. The dual-degree-of-freedom optical payload camera 2 and the optical payload back-end processing module 5 are installed separately inside the module 1 along the module axis, with the dual-degree-of-freedom optical payload camera 2 on one side and the optical payload back-end processing module 5 on the other side in a wheel-like arrangement.

[0059] See also Figure 7The figure illustrates the separation process of the ground-side detachable beam reinforcement structure 3 and the space-side detachable beam reinforcement structure 4 from the cabin structure 1 in this embodiment. The separation timing requires calculation and design: after the launch vehicle launches and the fairing is jettisoned, the separation timing is calculated and deduced based on the estimated landing points of the ground-side and space-side detachable beam reinforcement structures 3 and 4. The separation nuts 13 are then used to unlock and separate the ground-side and space-side detachable beam reinforcement structures 3 and 4 from the cabin structure 1, allowing them to fall. Through this separation process, this embodiment can meet the field-of-view requirements of the dual-degree-of-freedom optical payload camera 2 under pointing motion during its on-orbit operation.

[0060] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A large payload module for a space station, characterized in that, The system includes a cabin structure (1), a dual-degree-of-freedom optical payload camera (2), a separable beam-type reinforcement structure on the ground side (3), a separable beam-type reinforcement structure on the sky side (4), an optical payload back-end processing module (5), and a floating vibration isolation and stabilization system (6), wherein: The cabin structure (1) is the main load-bearing frame of the entire payload cabin section, used to support the dual-degree-of-freedom optical payload camera (2), the ground-side separable beam-type reinforcing structure (3), the sky-side separable beam-type reinforcing structure (4), the optical payload back-end processing module (5), and the floating vibration isolation and stabilization system (6). The two ends of the dual-degree-of-freedom optical payload camera (2) are connected to the cabin structure (1) through the floating vibration isolation and stabilization system (6); The ground-side separable beam-type reinforcing structure (3) and the space-side separable beam-type reinforcing structure (4) are respectively connected to the cabin structure (1) to further reinforce the cabin structure (1) and can be separated after entering orbit; The optical payload back-end processing module (5) is installed in the cabin structure (1); The floating vibration isolation and stabilization system (6) is used to isolate external vibrations on the track; The cabin structure (1) adopts an external load-bearing cylinder configuration, which is composed of a longitudinal beam structure (10), a transverse frame structure (11) and a wall panel structure (12). The longitudinal beam structure (10) and the transverse frame structure (11) are the main body, and the wall panel structure is the outer wall of the cabin. Two large circumferential openings (14) are opened on the ground side and the sky side in the middle of the cabin structure (1) to avoid the sky and ground field of view required by the dual-degree-of-freedom optical payload camera (2). A separable beam-type reinforcement structure (3) is installed at the circumferential large opening (14) on the ground side, and a separable beam-type reinforcement structure (4) is installed at the circumferential large opening (14) on the sky side. The separable beam-type reinforcement structure (3) on the ground side and the separable beam-type reinforcement structure (4) on the sky side are respectively reinforced by X-shaped beam-type reinforcement structures for the circumferential large opening (14), and have 5 connection positions with the cabin structure (1), respectively supporting 4 fixed positions and the top middle position of the circumferential large opening (14).

2. A large payload module for a space station according to claim 1, characterized in that, The dual-degree-of-freedom optical payload camera (2) uses orthogonal dual degrees of freedom for spatial pointing, and is used to achieve observation of the earth and the sky.

3. A large payload module for a space station according to claim 2, characterized in that, The dual-degree-of-freedom optical payload camera (2) consists of a camera body (7), an inner frame (8), and an outer frame (9). The camera body (7) is installed in the inner frame (8) and can be driven by a motor to rotate around the inner rotation axis. The inner frame (8) is installed in the outer frame (9) and can be driven by a motor to rotate around the outer rotation axis. In this way, the camera body (7) can generate a dual-degree-of-freedom rotational motion.

4. A large payload module for a space station according to claim 1, characterized in that, The ground-side separable beam reinforcement structure (3) and the space-side separable beam reinforcement structure (4) are connected to the cabin structure (1) at the five connection points by five separation nuts (13), respectively. These nuts are used to reinforce the two large circumferential openings (14) of the cabin structure (1) to ensure the strength and stiffness during the ascent. After the fairing is jettisoned after the launch vehicle is launched, the separation nuts (13) are used to unlock and separate the ground-side separable beam reinforcement structure (3) and the space-side separable beam reinforcement structure (4) from the cabin structure (1).

5. A large payload module for a space station according to claim 1, characterized in that, The load compartment is cylindrical in shape.

6. A large payload module for a space station according to claim 5, characterized in that, The dual-degree-of-freedom optical payload camera (2) and the optical payload back-end processing module (5) are installed in the interior of the cabin structure (1) along the cabin axis in a separate layout, with the dual-degree-of-freedom optical payload camera (2) on one side and the optical payload back-end processing module (5) distributed in a wheel-like manner on the other side.

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