A space station truss system

Abstract

The application provides a space station truss system. The system is composed of an upper truss structure (1), a lower truss structure (2), an unfolding driving assembly (3), a base structure (4), an integrated double-degree-of-freedom driving mechanism (5), a large-area flexible solar wing (6), an exposed load adapter (7) and the like. The system is launched into orbit together with a space station cabin. After being launched into orbit, the upper truss structure and the lower truss structure are synchronously and reversely rotated by 90 degrees around the axis of the rotating shaft assembly under the driving of the unfolding assembly, and the unfolding assembly is locked after being positioned, thereby forming a fixed structure system. At least four large-area solar wings can be carried by one-time launching, and no less than 16 exposed load stations are provided. The system can be applied to a space station, is simple in form, compact in structure, strong in single-cabin launching capacity and good in expandability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft overall design, in particular to a space station truss system. BACKGROUND

[0002] A space station is a large orbiting spacecraft, typically like the "Peace" space station, the International Space Station, and China's "Tiangong" space station, which is generally composed of multiple cabin sections and large structures. There are long-term astronauts living and working on the space station, and there are numerous platform instruments and devices and payloads in operation.

[0003] Space stations generally require a large energy demand. The energy system commonly used by spacecraft is a solar cell array photovoltaic power generation system. Due to the large energy demand of the space station, a large area of solar wings is often equipped, such as the total area of the solar wings of the International Space Station reaching an astonishing 2500 square meters. Large-area solar wings, whether rigid solar wings (such as the "Peace" space station) or flexible solar wings (such as the International Space Station and China's "Tiangong" space station), generally have two major problems: one is the launch space problem, limited by the fairing envelope constraint of the launch vehicle, the solar wings need to be folded during launch, and even when folded, the large-area solar wings still occupy a very large volume and are very heavy; the second is that after launch into orbit, the solar wings need to be deployed and move in a sun-oriented manner, requiring a support structure (such as the large truss structure of the International Space Station) with sufficient strength and stiffness. Due to the heavy weight and large volume, the solar wings and their support structures often need to be launched multiple times, such as the International Space Station having 9 launches related to this, resulting in a long construction period and high cost.

[0004] As a space laboratory in orbit, a space station needs to provide enough experimental stations exposed to the outer space environment to support experiments that need to utilize the space environment. These exposed payload stations are preferably arranged in a centralized manner to provide various mechanical, electrical, and thermal interfaces and to facilitate centralized management. However, the cabin sections of a space station are generally cylindrical or conical in shape, making it difficult to provide a large number of centralized stations, and the outer wall of the cabin body needs to be arranged with various sensors, antennas, and other equipment, so the periphery cannot be arranged with other equipment to avoid blocking the working field of view.

[0005] In summary, how to use innovative design to make the solar wing and its support structure layout compact, and to increase the number of solar wings as much as possible in one launch, significantly reducing the construction period and cost of a space station, while also providing a large number of exposed payload stations in a centralized manner to achieve greater application benefits, is a difficult problem of great practical significance. SUMMARY

[0006] The space station truss system can carry at least four large-area solar wings in one launch, and can also provide a large number of (not less than 16) exposed load stations

[0007] In order to achieve the above technical effects, the technical scheme of the present application is to provide a space station truss system, characterized in that it comprises an upper truss structure 1, a lower truss structure 2, an unfolding driving assembly 3, a base structure 4, an integrated two-degree-of-freedom driving mechanism 5, a large-area flexible solar wing 6, and an exposed load adapter 7.

[0008] The upper truss structure 1 and the lower truss structure 2 adopt a cuboid configuration, and the cross section is a square, four long rectangular sides of which are used for installing equipment, among which the side facing the sky and the side facing the ground are used for installing the exposed load adapter 7 as a concentrated arrangement area of the space station exposed load station; the side of the upper truss structure 1 and the lower truss structure 2 close to the outer side of the space station main body is used for installing the large-area flexible solar wing 6; the large-area flexible solar wing 6 realizes two-dimensional sun orientation by using the integrated two-degree-of-freedom driving mechanism 5, so that the large-area flexible solar wing 6 can realize higher light efficiency.

[0009] Further, the main structure of the truss system is composed of the upper truss structure 1 and the lower truss structure 2 in a parallel manner; the upper truss structure 1 and the lower truss structure 2 are connected with the base structure 4 through the unfolding driving assembly 3, so as to form a whole and be launched into orbit together with the cabin section; after being launched into orbit, the upper truss structure 1 and the lower truss structure 2 are synchronously and reversely rotated by 90° around the axis of the rotation shaft assembly under the driving of the unfolding driving assembly 3, and are locked after being positioned, so as to form a fixed structure system.

[0010] Further, the truss system is arranged at the tail of the space station transverse cabin section and is connected with the space station transverse cabin section tail structure through the base structure 3; the space station transverse direction refers to the direction orthogonal to the flight direction, the sky-facing direction and the ground-facing direction.

[0011] Further, the upper truss structure 1 and the lower truss structure 2 can be extended along the front-rear direction parallel to the flight direction, and the extension of the whole space station does not increase the lateral size and has small attitude control disturbance to the space station.

[0012] The space station truss system provided by the present application has the following beneficial effects:

[0013] 1. Four large-area solar wings can be carried in one launch, which greatly improves the solar wing launch capacity and the space station construction efficiency;

[0014] 2. One launch can provide more than 16 exposure payload positions, greatly improving the support capability of the exposure payload cabin out-of-orbit test in the initial construction stage of the space station, and the exposure payloads can be managed collectively, improving the on-orbit care efficiency;

[0015] 3. The solar wing is arranged on the lateral side of the space station, and does not block the field of view of various sensitive sensors, antennas and other equipment of the space station;

[0016] 4. The solar wing and its supporting truss can be expanded in the front-back direction parallel to the flight direction of the space station, and the lateral size is not increased after expansion, and the attitude control disturbance to the space station is small.

[0017] The space station truss system of the present application can be applied to a space station, has a simple form, compact structure, strong single-cabin launch capability, and good scalability. BRIEF DESCRIPTION OF DRAWINGS

[0018] The application will be further described below in combination with the drawings:

[0019] Figure 1 The figure is a schematic diagram of the launch and folding state of the preferred embodiment of the present application;

[0020] Figure 2 The figure is a schematic diagram of the on-orbit expansion process of the preferred embodiment of the present application;

[0021] Figure 3 The figure is a schematic diagram of the on-orbit movement form of the solar wing of the preferred embodiment of the present application;

[0022] Figure 4 The figure is a schematic diagram of a typical space station using the preferred embodiment of the present application. DETAILED DESCRIPTION

[0023] The space station truss system of the present application will be further described in detail below in combination with the drawings and specific embodiments. The advantages and features of the present application will be clearer according to the following description and claims. It should be noted that the drawings are very simplified and use non-precise ratios, only to facilitate and clearly assist in explaining the purpose of the embodiments of the present application.

[0024] Figures 1-3The figure is a schematic diagram of launching and on-orbit deployment, motion state of the preferred embodiment of the present application. The truss system includes upper truss structure 1, lower truss structure 2, deployment driving assembly 3, base structure 4, integrated two-degree-of-freedom driving mechanism 5, large-area flexible solar wing 6, exposed load adapter 7 and other parts. The upper truss structure 1 and the lower truss structure 2 adopt cuboid configuration, and the cross section is square. Four rectangular sides are used to install equipment, and the top and the ground are used to install the exposed load adapter 7, which is arranged as a centralized area of the space station exposed load station. The outer side of the upper truss structure 1 and the lower truss structure 2 is used to install the large-area flexible solar wing 6. The large-area flexible solar wing 6 realizes two-dimensional sun orientation by using the integrated two-degree-of-freedom driving mechanism 5, so that the large-area flexible solar wing 6 can realize higher light efficiency. The main structure of the truss system is composed of the upper truss structure 1 and the lower truss structure 2 in a parallel manner. The upper truss structure 1 and the lower truss structure 2 are connected with the base structure 4 through the deployment driving assembly 3, thereby forming a whole and being launched into orbit together with the cabin section. After being launched into orbit, the upper truss structure 1 and the lower truss structure 2 are synchronously and reversely rotated by 90° around the rotation shaft assembly axis under the driving of the deployment driving assembly 3, and are locked after being positioned, thereby forming a fixed structure system.

[0025] Figure 4 The figure is a schematic diagram of a typical space station applying the preferred embodiment of the present application. The truss system can be arranged at the tail of the transverse cabin section of the space station (the direction perpendicular to the flight direction, the direction perpendicular to the sky and the ground), and is connected with the tail structure of the transverse cabin section of the space station through the base structure 3. The upper truss structure 1 and the lower truss structure 2 can be expanded along the front-rear direction parallel to the flight direction, and can realize that the transverse dimension of the entire space station is not increased after expansion, and the attitude control disturbance of the space station is small.

[0026] The contents not described in detail in the specification belong to the prior art known to those skilled in the art. It is obvious for those skilled in the art that the present application is not limited to the details of the above exemplary embodiments, and the present application can be realized in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, the embodiments should be regarded as exemplary and non-limiting, and the scope of the present application is defined by the appended claims rather than the above description, and all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application.

Claims

1. A space station truss system, characterized by, The truss system comprises an upper truss structure (1), a lower truss structure (2), an unfolding driving assembly (3), a base structure (4), an integrated two-degree-of-freedom driving mechanism (5), a large-area flexible solar wing (6) and an exposed load adapter (7). The upper truss structure (1) and the lower truss structure (2) adopt a cuboid configuration, and the cross section is square, four rectangular sides of which are used for mounting equipment, wherein the side facing the sky and the side facing the ground are used for mounting the exposed load adapter (7) as a space station exposed load station centralized arrangement area; the side close to the outer side of the space station main body of the upper truss structure (1) and the lower truss structure (2) is used for mounting the large-area flexible solar wing (6); the large-area flexible solar wing (6) adopts the integrated two-degree-of-freedom driving mechanism (5) to realize two-dimensional sun orientation, so that the large-area flexible solar wing (6) can realize higher light efficiency. The main structure of the truss system is composed of the upper truss structure (1) and the lower truss structure (2) in a parallel manner; the upper truss structure (1) and the lower truss structure (2) are connected with the base structure (4) through the unfolding driving assembly (3), so as to form a whole and be launched into orbit together with the cabin section; after being launched into orbit, the upper truss structure (1) and the lower truss structure (2) are synchronously and reversely rotated by 90° around the rotation shaft assembly axis under the driving of the unfolding driving assembly (3) to be unfolded, and the unfolding assembly is locked after being in place to form a fixed structure system. The truss system is arranged at the tail of the space station transverse cabin section and connected with the space station transverse cabin section tail structure through the base structure (4); the space station transverse direction refers to the direction orthogonal to the flight direction, the sky-facing direction and the ground-facing direction.

2. The space station truss system of claim 1, wherein, The upper truss structure (1) and the lower truss structure (2) can be expanded along the front-rear direction parallel to the flight direction, and the entire space station can be expanded without increasing the lateral size and causing small attitude control disturbance to the space station.

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