Large load cabin section of space station

Abstract

The invention discloses a space station large-scale load cabin section which comprises a cabin body structure, a two-degree-of-freedom optical load camera, a ground side separable beam type reinforcing structure, a sky side separable beam type reinforcing structure, an optical load rear end processing module and a floating type vibration isolation stabilizing system. The support is used for supporting other parts; the two ends of the two-degree-of-freedom optical load camera are connected with the cabin body structure through the floating type vibration isolation stabilizing system. The ground-side separable beam type reinforcing structure and the sky-side separable beam type reinforcing structure are respectively connected with the cabin body structure, are used for further reinforcing the cabin body structure and can be separated after orbit injection; the optical load rear-end processing module is mounted in the cabin structure; and the floating type vibration isolation stabilizing system is used for isolating on-orbit external vibration. The space station cabin section can provide a stable environment for installation and bearing of a large-aperture optical load, a large opening can be formed to make a view field space, and the strength and rigidity are guaranteed.

Description

Technical Field

[0001] The invention relates to the field of overall design of spacecraft, and in particular to a large payload compartment of a space station. Background Art

[0002] Space payloads, especially large-aperture optical payloads, are often large in size and heavy in weight, and have high requirements for installation pointing, accuracy and field of view. Therefore, general space optical payloads use dedicated spacecraft platforms and are designed as independent optical satellites or detectors, such as the famous Hubble telescope. In this way, the pointing of the optical camera can be achieved by adjusting the attitude of the spacecraft platform, and it is easy to achieve unobstructed field of view. However, the optical payload on the space station is only one of the many space payloads on the space station. Each payload has its own pointing requirements, and there are many external devices on the space station. Therefore, it is unlikely to point the camera through the attitude adjustment of the entire space station. Therefore, the optical payload of the space station itself needs to be equipped with a dual-degree-of-freedom pointing mechanism for independent pointing control. This brings another problem, that is, the large-aperture optical payload on the space station is generally installed inside the cabin. The dual-degree-of-freedom pointing and field of view requirements require a large opening in the cabin structure to make room for the camera's field of view, which causes a huge loss of structural strength and stiffness, making reinforcement design difficult.

[0003] In summary, how to adopt innovative designs so that the large-aperture optical payload cabin of the space station can not only provide a stable environment for installation and load-bearing, but also open a large opening to allow for the field of view and ensure strength and rigidity is a difficult problem with important practical significance. Summary of the invention

[0004] In order to overcome the deficiencies in the prior art, the present invention provides a large payload compartment for a space station, which can be used to install a large-aperture optical payload with an aperture of up to 2 meters and meet its pointing and field of view space requirements.

[0005] In order to achieve the above-mentioned invention object, the technical solution adopted to solve the technical problem is as follows: A large payload cabin section of a space station comprises a cabin structure, a dual-degree-of-freedom optical payload camera, a ground-side detachable beam-type reinforcement structure, a sky-side detachable beam-type reinforcement structure, an optical payload back-end processing module and a floating vibration isolation stabilization system, wherein: The cabin structure is the main load-bearing frame of the entire payload cabin section, and is used to support the dual-degree-of-freedom optical payload camera, the ground-side detachable beam-type reinforcement structure, the sky-side detachable beam-type reinforcement structure, the optical payload back-end processing module, and the floating vibration isolation stabilization system; Both ends of the dual-degree-of-freedom optical payload camera are respectively connected to the cabin structure through the floating vibration isolation stabilization system; The ground-side detachable beam-type reinforcement structure and the sky-side detachable beam-type reinforcement structure are respectively connected to the cabin structure for further strengthening the cabin structure and can be separated after entering orbit; The optical payload back-end processing module is installed in the cabin structure; The floating vibration isolation stabilization system is used to isolate the external vibration of the rail.

[0006] Furthermore, the dual-degree-of-freedom optical payload camera uses orthogonal dual degrees of freedom for spatial pointing, so as to realize ground and sky observation.

[0007] 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 the above manner, the camera body can generate dual-degree-of-freedom rotational motion.

[0008] 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 plate structure. The longitudinal beam structure and the transverse frame structure are the main body, and the wall plate structure is the outer wall of the cabin. Two large circumferential openings are respectively opened on the ground side and the sky side in the middle of the cabin structure to avoid the sky and ground field of view required by the dual-degree-of-freedom optical payload camera.

[0009] Furthermore, a detachable beam-type reinforcement structure for the ground side is installed at the large circumferential opening on the ground side, and a detachable beam-type reinforcement structure for the sky side is installed at the large circumferential opening on the sky side. The detachable beam-type reinforcement structure for the ground side and the detachable beam-type reinforcement structure for the sky side respectively use X-shaped beam-type reinforcement structures to reinforce the large circumferential opening, and have 5 connection positions with the cabin structure, respectively supporting 4 fixed positions and the middle position of the top of the large circumferential opening.

[0010] Furthermore, the detachable beam-type reinforcement structure on the ground side and the detachable beam-type reinforcement structure on the sky side are respectively connected to the cabin structure at the five connection positions through five separation nuts, so as to reinforce the two large circumferential openings of the cabin structure so as to ensure the strength and stiffness in the ascending section, and after the launch of the carrier rocket, the detachable beam-type reinforcement structure on the ground side and the detachable beam-type reinforcement structure on the sky side are separated from the cabin structure by unlocking the separation nuts.

[0011] Furthermore, the load compartment section is cylindrical as a whole.

[0012] Furthermore, the dual-degree-of-freedom optical payload camera and the optical payload back-end processing module are installed in a separate layout form inside the cabin structure along the cabin axis, with the dual-degree-of-freedom optical payload camera on one side and the wheeled optical payload back-end processing module on the other side.

[0013] Due to the adoption of the above technical solution, the present invention has the following advantages and positive effects compared with the prior art: The large payload compartment of the space station of the present invention can realize the installation of a 2-meter-diameter optical payload inside the space station compartment without blocking the field of view of other equipment in the space station; at the same time, it provides a stable load-bearing installation environment, and can open a large opening to make room for the field of view and ensure strength and rigidity. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work. In the drawings: Figure 1 This is a schematic diagram of the three-dimensional structure of a large payload compartment of a space station according to the present invention; Figure 2 This is a schematic diagram of the overall structure of a large payload compartment of a space station according to the present invention from a first perspective; Figure 3 This is a schematic diagram of the overall structure of a large payload compartment of a space station according to the present invention from a second viewing angle; Figure 4 This is a schematic diagram of the main components of a large payload compartment of a space station according to the present invention; Figure 5 This is a schematic diagram of a dual-degree-of-freedom optical payload camera for a large payload compartment of a space station according to the present invention; Figure 6 It is a schematic diagram of a cabin structure and a detachable beam-type reinforcement structure of a large payload cabin section of a space station according to the present invention; Figure 7 The present invention is a schematic diagram of the separation process of a detachable beam-type reinforcement structure of a large payload compartment of a space station.

[0015]

Explanation of main symbols

[0016] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0017] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0018] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0019] like Figure 1-Figure 7 As shown, this embodiment discloses a large payload cabin section of a space station, including a cabin structure 1, a dual-degree-of-freedom optical payload camera 2, a ground-side detachable beam-type reinforcement structure 3, a sky-side detachable beam-type reinforcement structure 4, an optical payload back-end processing module 5, and a floating vibration isolation stabilization system 6, wherein: The cabin structure 1 is the main load-bearing frame of the entire payload cabin section, and is used to support the dual-degree-of-freedom optical payload camera 2, the ground-side detachable beam-type reinforcement structure 3, the sky-side detachable beam-type reinforcement structure 4, the optical payload back-end processing module 5, and the floating vibration isolation stabilization system 6; Both ends of the dual-degree-of-freedom optical payload camera 2 are respectively connected to the cabin structure 1 through the floating vibration isolation stabilization system 6; The ground-side detachable beam-type reinforcement structure 3 and the sky-side detachable beam-type reinforcement structure 4 are respectively connected to the cabin structure 1 to further strengthen 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 stabilization system 6 is used to isolate the external vibration of the rail.

[0020] refer to Figure 5 The dual-degree-of-freedom optical payload camera 2 uses orthogonal dual degrees of freedom for spatial pointing, which is used to achieve ground and sky observations.

[0021] Furthermore, the dual-degree-of-freedom optical payload camera 2 is composed 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 an inner rotation axis; the inner frame 8 is installed in the outer frame 9 and can be driven by a motor to rotate around an outer rotation axis; in the above manner, the camera body 7 can generate dual-degree-of-freedom rotational motion.

[0022] See also Figure 6 The cabin structure 1 of this embodiment adopts an external load-bearing cylinder configuration, which is composed of a longitudinal beam structure 10, a transverse frame structure 11 and a wall plate structure 12. The longitudinal beam structure 10 and the transverse frame structure 11 are used as the main body, and the wall plate structure is used as the outer wall of the cabin. Two large circumferential openings with a size of about 4 meters × 2.8 meters are respectively opened on the ground side and the sky side in the middle of the cabin structure 1 to avoid the sky-ground field of view required by the dual-degree-of-freedom optical payload camera 2, which can meet the field of view requirements of the internal dual-degree-of-freedom optical payload camera 2 under pointing movement.

[0023] refer to Figure 1 , 2 , 4 and 6, a detachable beam-type reinforcement structure 3 for the ground side is installed at the large circumferential opening on the ground side, and a detachable beam-type reinforcement structure 4 for the sky side is installed at the large circumferential opening on the sky side. In this embodiment, since the cabin structure 1 has a large opening, the detachable beam-type reinforcement structure 3 for the ground side and the detachable beam-type reinforcement structure 4 for the sky side respectively adopt X-shaped beam-type reinforcement structures to reinforce the large circumferential opening, and have 5 connection positions with the cabin structure 1, which respectively support the 4 fixed positions and the middle position of the top of the large circumferential opening.

[0024] Furthermore, the detachable beam-type reinforcement structure 3 on the ground side and the detachable beam-type reinforcement structure 4 on the sky side are respectively connected to the cabin structure 1 at the five connection positions through five separation nuts 13, so as to reinforce the two large circumferential openings of the cabin structure 1 so as to ensure the strength and stiffness in the ascending section, and after the launch of the carrier rocket, the detachable beam-type reinforcement structure 3 on the ground side and the detachable beam-type reinforcement structure 4 on the sky side are separated from the cabin structure 1 by unlocking the separation nuts 13.

[0025] The large payload compartment of the space station is mainly composed of a cabin structure 1, which is cylindrical in shape. The dual-degree-of-freedom optical payload camera 2 and the optical payload back-end processing module 5 are installed in 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 wheeled optical payload back-end processing module 5 on the other side.

[0026] See also Figure 7 , the figure illustrates the separation process of the ground-side detachable beam-type reinforcement structure 3 and the sky-side detachable beam-type reinforcement structure 4 from the cabin structure 1 in this embodiment. The separation timing needs to be calculated and designed: after the launch of the carrier rocket, after the fairing is jettisoned, the separation timing is inferred by the estimated calculation based on the landing point of the ground-side detachable beam-type reinforcement structure 3 and the sky-side detachable beam-type reinforcement structure 4, and the ground-side detachable beam-type reinforcement structure 3 and the sky-side detachable beam-type reinforcement structure 4 are separated from the cabin structure 1 and fall by unlocking the separation nut 13. After the above separation process, the field of view requirements of the dual-degree-of-freedom optical payload camera 2 under pointing motion can be met in this embodiment during the on-orbit process. The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A large payload compartment of a space station, characterized in that: The system comprises a cabin structure (1), a dual-degree-of-freedom optical payload camera (2), a ground-side detachable beam-type reinforcement structure (3), a sky-side detachable beam-type reinforcement structure (4), an optical payload back-end processing module (5) and a floating vibration isolation stabilization system (6), wherein: The cabin structure (1) is the main load-bearing frame of the entire payload cabin section, and is used to support the dual-degree-of-freedom optical payload camera (2), the ground-facing detachable beam-type reinforcement structure (3), the sky-facing detachable beam-type reinforcement structure (4), the optical payload back-end processing module (5), and the floating vibration isolation stabilization system (6); Both ends of the dual-degree-of-freedom optical payload camera (2) are respectively connected to the cabin structure (1) via the floating vibration isolation stabilization system (6); The ground-side detachable beam-type reinforcement structure (3) and the sky-side detachable beam-type reinforcement structure (4) are respectively connected to the cabin structure (1) to further strengthen 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 stabilization system (6) is used to isolate the external vibration of the rail.

2. A large payload compartment of 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 ground and sky observations.

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

4. A large payload compartment for a space station according to claim 1, characterized in that: The cabin structure (1) adopts an external bearing cylinder configuration and is composed of a longitudinal beam structure (10), a transverse frame structure (11) and a wall plate structure (12). The longitudinal beam structure (10) and the transverse frame structure (11) are used as the main body, and the wall plate structure is used as the cabin outer wall. Two large circumferential openings (14) are respectively provided on the ground side and the sky side of the middle part of the cabin structure (1) to avoid the sky and ground field of view areas required by the dual-degree-of-freedom optical payload camera (2).

5. A large payload compartment of a space station according to claim 4, characterized in that: A separable beam-type reinforcement structure (3) facing the ground is installed at the large circumferential opening (14) facing the ground, and a separable beam-type reinforcement structure (4) facing the sky is installed at the large circumferential opening (14) facing the sky. The separable beam-type reinforcement structure (3) facing the ground and the separable beam-type reinforcement structure (4) facing the sky respectively use X-shaped beam-type reinforcement structures to reinforce the large circumferential opening (14), and have five connection positions with the cabin structure (1), respectively supporting four fixed positions and a top middle position of the large circumferential opening (14).

6. A large payload compartment of a space station according to claim 5, characterized in that: The ground-facing detachable beam-type reinforcement structure (3) and the sky-facing detachable beam-type reinforcement structure (4) are respectively connected to the cabin structure (1) at the five connection positions via five separation nuts (13), and are used to reinforce the two circumferential large openings (14) of the cabin structure (1) so as to ensure the strength and rigidity in the ascending section. After the launch vehicle is launched and the fairing is jettisoned, the ground-facing detachable beam-type reinforcement structure (3) and the sky-facing detachable beam-type reinforcement structure (4) are separated from the cabin structure (1) by unlocking the separation nuts (13).

7. A large payload compartment for a space station according to claim 1, characterized in that: The load compartment section is cylindrical as a whole.

8. A large payload compartment of a space station according to claim 7, characterized in that: The dual-degree-of-freedom optical payload camera (2) and the optical payload back-end processing module (5) are installed in a separate layout along the axis of the cabin as a whole inside the cabin structure (1), 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 wheeled manner on the other side.

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