Large-opening load cabin of space station

Abstract

The invention provides a large-opening load cabin of a space station. The large-opening load cabin is composed of a cabin body structure (1), a load module (2), a load supporting seat (3), a load auxiliary support (4), a mechanical arm (5) and a guide rail (6). The load cabin is cylindrical and can be used as a part of an independent cabin section of the space station, various load modules can be mounted in the load cabin, and a large opening is formed in one transverse side of the load cabin to ensure that the load modules can enter and exit from the cabin safely. The load module is further connected with the cabin body through a mechanical arm and used for pushing the load module out of / withdrawing the load module into the cabin body and conducting positioning and pointing on the load module. The mechanical arm is installed on a guide rail on one side of a large opening of the cabin structure and moves on the guide rail to position different positions of the load module so as to expand the movement range of the load module. The load cabin can meet the requirement that the space station view field pointing type effective load can meet the fairing envelope limitation and cannot be shielded by view fields of other structures and equipment on the space station.

Description

Technical Field

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

[0002] Among all kinds of spacecraft payloads, there is a type that has field of view requirements and needs to be positioned and pointed in different directions. Typically, such as space optical payloads, especially large-aperture cameras, which are large in size and heavy in weight, there are high requirements for installation pointing, accuracy and field of view. Therefore, this type of payload is generally designed as an independent spacecraft. In this way, the pointing of the payload can be achieved by adjusting the attitude of the spacecraft platform, and it is easy to achieve unobstructed field of view. However, for the payloads on the space station, it is difficult to use the attitude adjustment of the entire space station to point the camera. Because there are many payloads on the space station, each payload has different requirements, different working times and durations, and it is impossible to adjust the attitude of the entire space station for the needs of a single payload. Therefore, the payloads on the space station themselves need to be equipped with pointing mechanisms for independent pointing control. However, there are many extravehicular equipment on the space station, and large payloads are installed in limited space outside the cabin, and are limited by the fairing envelope during launch. However, if installed in the cabin, the payload field of view is blocked by the cabin structure, resulting in performance loss.

[0003] Therefore, innovative designs are needed to ensure that the space station's field of view pointing payloads can meet the fairing envelope limitations while not being blocked by the field of view of other structures and equipment on the space station. Summary of the invention

[0004] The purpose of the present invention is to provide a large-opening payload cabin for a space station, so that the field-of-view pointing payload of the space station can meet the fairing envelope limitation while not being blocked by the field of view of other structures and equipment on the space station.

[0005] In order to achieve the above technical effects, the technical solution of the present invention is: to provide a large-opening payload cabin for a space station, comprising a cabin structure 1, a payload module 2, a payload support seat 3, a payload auxiliary support 4, a mechanical arm 5, and a guide rail 6;

[0006] The payload cabin is cylindrical in shape, with a large opening on one lateral side of the payload cabin, and a guide rail 6 for use by the robotic arm 5 is installed on the longitudinal beam structure on one side of the large opening; when the payload cabin is launched with the space station module, the lower end of the payload module 2 is installed on the payload support seat 3 and is fixed by a strap connection unlocking device; the upper end of the payload module 2 is connected by a load auxiliary support 4 and is fixed by an explosive bolt.

[0007] Furthermore, the payload module 2 is also connected to the payload cabin through the robotic arm 5; after the payload cabin is launched into orbit, the strap connection unlocking device at the lower end of the payload module 2 and the explosive bolt at the upper end are unlocked, and the payload module 2 and the cabin body are only connected by the robotic arm 5, and the payload module moves and adjusts its posture with the support of the robotic arm 5.

[0008] Furthermore, the size of the large opening is designed according to the cross-sectional size of the payload to ensure that the payload can enter and exit the cabin safely.

[0009] Furthermore, the cabin structure 1 adopts a wall plate type external load-bearing cylinder configuration, and the large opening is reinforced with a longitudinal beam structure and a transverse frame structure.

[0010] Furthermore, the robotic arm 5 is a dedicated robotic arm for the payload module 2 , and is used to push the payload module out or retract it into the cabin, and to position and point the payload module 2 .

[0011] Furthermore, by moving the mechanical arm 5 on the guide rail, the payload module 2 can be positioned at different positions to expand the motion range of the payload module.

[0012] The beneficial effects achieved by the large-opening payload cabin of the space station provided by the present invention are:

[0013] 1. It can accommodate large payloads in the space station cabin, does not occupy additional fairing envelope during launch, and can be extended out of the cabin when in use after entering orbit;

[0014] 2. The payload is supported by a robotic arm outside the space station cabin, which can achieve independent multi-degree-of-freedom pointing and a wide field of view, and can also be retracted into the cabin by the robotic arm when the payload is not in use.

[0015] The large-opening payload cabin of the space station of the present invention can provide sufficient space and has a compact structure, which can meet the requirements of the space station's field of view pointing type payloads while meeting the fairing envelope restrictions and not being blocked by the field of view of other structures and equipment on the space station. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The invention will be further described below in conjunction with the accompanying drawings:

[0017] Figure 1 It is a schematic diagram of the overall and system composition of a preferred embodiment of the present invention;

[0018] Figure 2 It is a schematic diagram of the main components of a preferred embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram of the payload module working outside the cabin according to a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0020] The space station large opening payload cabin proposed by the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following description and claims. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise ratios, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0021] Figure 1 , Figure 2 Shown is an overall schematic diagram of a preferred embodiment of the present invention and a schematic diagram of the main components being decomposed.

[0022] See also Figure 1 , which is an overall schematic diagram of a preferred embodiment of the present invention.

[0023] See also Figure 2 The present embodiment is divided into a cabin structure 1, a load module 2, a load support seat 3, a load auxiliary support 4, a mechanical arm 5, and a guide rail 6, and each part is assembled as follows Figure 1 The above-mentioned component classification does not represent the actual assembly sequence, but is only for the convenience of description.

[0024] The cabin structure 1 of this embodiment is composed of a wall plate structure, and a large opening is opened on one lateral side of the cabin. The size of the large opening is designed according to the cross-sectional size of the payload to ensure that the payload can safely enter and exit the cabin.

[0025] On the basis of the above-mentioned cabin structure 1, the large opening of the cabin is reinforced with a longitudinal beam structure and a transverse frame structure.

[0026] On the basis of the aforementioned cabin structure 1, the longitudinal beam on the side of the large opening of the cabin can be used as a guide rail for the dedicated mechanical arm of the payload module.

[0027] In this embodiment, the lower end of the load module 2 is mounted on the load support seat 3 and fixed by an initiating device, and the upper end is connected to the load auxiliary support 4 by an initiating device.

[0028] On the basis of the aforementioned fixed load module 2, the load module 2 is also connected to the cabin through a mechanical arm 5. After the load cabin is launched into orbit, the pyrotechnic devices of the load support seat 3 and the load auxiliary support 4 are detonated and unlocked, and the load module is only connected to the cabin through the mechanical arm. The mechanical arm realizes the functions of exiting the cabin, recovery, and orientation of the load module.

[0029] See also Figure 3 The figure shows the working range of the payload module after the payload module is pushed out of the cabin by the payload module dedicated mechanical arm in this embodiment. The payload module dedicated mechanical arm can translate on the guide rail, and according to the design of the payload module dedicated mechanical arm, the payload module can realize multi-axis and multi-angle rotation to expand the working range of the payload module.

[0030] The contents not described in detail in this specification belong to the prior art known to those skilled in the art. It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention.

Claims

1. A space station large opening payload cabin, characterized in that: It comprises a cabin structure (1), a load module (2), a load support seat (3), a load auxiliary support (4), a mechanical arm (5), and a guide rail (6); The payload cabin is cylindrical in shape, with a large opening on one lateral side of the payload cabin, and a guide rail (6) for use by the robotic arm (5) is installed on a longitudinal beam structure on one side of the large opening; when the payload cabin is launched with the space station cabin section, the lower end of the payload module (2) is installed on the payload support seat (3) and is fixed by a strap connection unlocking device; the upper end of the payload module (2) is connected by a load auxiliary support (4) and is fixed by an explosive bolt.

2. The space station large opening payload cabin according to claim 1, characterized in that: The payload module (2) is also connected to the payload cabin via a mechanical arm (5); after the payload cabin is launched into orbit, the strap connection unlocking device at the lower end of the payload module (2) and the explosive bolt at the upper end are unlocked, and the payload module (2) is connected to the cabin body only via the mechanical arm (5), and the payload module moves and adjusts its posture with the support of the mechanical arm (5).

3. The space station large opening payload cabin according to claim 1, characterized in that: The size of the large opening is designed according to the cross-sectional size of the payload to ensure that the payload can enter and exit the cabin safely.

4. The space station large opening payload cabin according to claim 1, characterized in that: The cabin structure (1) adopts a wall plate type external load-bearing cylinder configuration, and the large opening is reinforced with a longitudinal beam structure and a transverse frame structure.

5. The space station large opening load cabin as claimed in claim 1, characterized in that: The mechanical arm (5) is a dedicated mechanical arm for the payload module (2), and is used to push the payload module out or retract it into the cabin, and to position and point the payload module (2).

6. The space station large opening load cabin as claimed in claim 1, characterized in that: By moving the mechanical arm (5) on the guide rail, positioning of the load module (2) at different positions is achieved, thereby expanding the movement range of the load module.

Images