Truss device for separated two-degree-of-freedom sun-oriented system of spacecraft

Abstract

The invention discloses a truss device for a separated two-degree-of-freedom sun-oriented system of a spacecraft. Comprising a truss body, a circular flange, an arc-shaped flange, a high-power equipment mounting plate, a control equipment mounting plate, an extended solar wing mounting plate, an extended controller mounting plate, an extended cable protection bracket, a plume protection frame, a handrail, a foot limiter support and a cable fixing bracket, the circular flange, the arc-shaped flange, the high-power equipment mounting plate, the handrail, the foot limiter support and the cable fixing bracket are mounted on the large column section of the truss body; the control equipment mounting plate, the expansion solar wing mounting plate, the expansion controller mounting plate and the expansion cable protection bracket are mounted on the small column section of the truss body; and the plume protection frame is mounted on the high-power equipment mounting plate. According to the truss device, the requirements of equipment layout, high-power transmission, equipment heat dissipation, astronaut on-orbit operation, on-orbit equipment expansion and the like are met while the requirement for separated two-degree-of-freedom sun orientation is met.

Description

Technical Field

[0001] The invention belongs to the technical field of research and development of a separated dual-degree-of-freedom solar orientation system for a spacecraft, and in particular relates to a truss device used for a separated dual-degree-of-freedom solar orientation system for a spacecraft. Background Art

[0002] With the development of aerospace technology, spacecraft has put forward higher requirements for energy. In order to make the solar wing have good lighting conditions to meet the large power generation capacity, the solar wing needs to be oriented to the sun with two degrees of freedom. The first problem to be considered in the implementation of the two-degree-of-freedom solar orientation solution is how to install and fix the two-degree-of-freedom solar orientation system. In the existing technology, there is no technical solution to solve this problem. Summary of the invention

[0003] The technology of the present invention solves the problem: overcomes the shortcomings of the prior art and provides a truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft, which can realize the installation and fixation of the dual-degree-of-freedom solar orientation system, while meeting the requirements of separated dual-degree-of-freedom solar orientation, and meeting the requirements of equipment layout, high-power transmission, equipment heat dissipation, astronaut on-orbit operation, and on-orbit expansion of equipment.

[0004] In order to solve the above technical problems, the present invention discloses a truss device for a separated dual-degree-of-freedom solar orientation system of a spacecraft, comprising: a truss body, a circular flange, an arc flange, a high-power equipment mounting plate, a control equipment mounting plate, an extended solar wing mounting plate, an extended controller mounting plate, an extended cable protection bracket, a plume protection frame, a handrail, a foot limiter support and a cable fixing bracket; wherein, the truss body comprises: a large column section and a small column section; the circular flange, the arc flange, the high-power equipment mounting plate, the handrail, the foot limiter support and the cable fixing bracket are installed on the large column section by screws; the control equipment mounting plate, the extended solar wing mounting plate, the extended controller mounting plate, and the extended cable protection bracket are installed on the small column section by screws; the plume protection frame is installed on the high-power equipment mounting plate by screws.

[0005] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of the spacecraft, the truss device includes 9 functional areas: β solar orientation mechanism installation area, α solar orientation mechanism installation area, mechanism heat dissipation area, high-power equipment heat dissipation area, control equipment installation area, on-orbit expansion installation area, expansion cable reserved area, astronaut operation area and transmission cable installation area.

[0006] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft, the separated dual-degree-of-freedom solar orientation system of a spacecraft includes: 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices, 6 control devices and several cables; among them, the 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices and 6 control devices are connected by several cables to realize the electrical connection between each mechanism and device; the 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices, 6 control devices and several cables are installed and fixed by the truss device.

[0007] In the above truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft,

[0008] There are two circular flanges in total, which are symmetrically installed at the middle of the left and right sides of the large column section as the β-solar orientation mechanism installation area, and are used to install two β-solar orientation mechanisms; wherein the two β-solar orientation mechanisms are respectively connected to the two circular flanges by screws, and are symmetrically installed on the left and right sides of the truss device;

[0009] There are 4 arc flanges in total. The 4 arc flanges are installed at the bottom of the large column section, perpendicular to the circular flange, and serve as the α sun-directing mechanism installation area for installing the α sun-directing mechanism. The α sun-directing mechanism is connected to the 4 arc flanges by screws and installed at the bottom of the truss device.

[0010] The area between the two circular flanges on the left and right sides and the bottom surface of the large column section is the mechanism heat dissipation area, which is used to install the heat dissipation plates of the β-solar orientation mechanism and the α-solar orientation mechanism;

[0011] The high-power equipment mounting plate is installed on the front side of the large column section as a high-power equipment heat dissipation area for mounting two high-power equipment; wherein the two high-power equipment are mounted on the high-power equipment mounting plate by screws and are located on the front side of the truss device;

[0012] There are 2 control device mounting plates in total. The 2 control device mounting plates are symmetrically mounted in the groove areas on the left and right sides of the small column section as control device mounting areas for mounting 6 control devices; 3 control devices are mounted on one of the control device mounting plates by screws, and the other 3 control devices are mounted on the other control device mounting plate by screws;

[0013] There are 4 cable fixing brackets in total. The 4 cable fixing brackets are installed inside the large column section as the transmission cable installation area. They are used for routing and binding the cables inside the truss device, and then leading them out to the outside of the truss device to connect with various equipment.

[0014] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft, there are two plume protection frames, which are installed at the bottom of the side of the high-power equipment mounting plate to provide plume protection for the cables between the high-power equipment and the α solar orientation mechanism.

[0015] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft, an extended solar wing mounting plate and an extended controller mounting plate are installed on the top of the small column section as an on-orbit extended mounting area for installing the extended solar wing and the extended controller on-orbit; among them, the extended solar wing mounting plate is used for installing the extended solar wing on-orbit; there are 2 extended controller mounting plates in total, which are used for installing the extended controller on-orbit.

[0016] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of the spacecraft, an extended cable protection bracket is installed on the front side of the small column section as an extended cable reserved area, which is used to fix the reserved extended cable launched with the aircraft, and the reserved extended cable is protected by the extended cable protection bracket.

[0017] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of the spacecraft, the armrest and foot limiter supports are installed on the rear side of the large column section as the astronaut operation area for astronauts to install extended solar wings and extended controllers in orbit.

[0018] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of the spacecraft, there are four handrails distributed around the rear side of the large column section for astronauts to grasp and climb.

[0019] In the above-mentioned truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft, a foot limiter support is arranged near the rear bottom of the large column section for installing the astronaut's foot limiter to fix the astronaut.

[0020] The present invention has the following advantages:

[0021] (1) The present invention discloses a truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft. The truss device meets the functional requirements of high-power transmission path connection and high-power heat dissipation of the separated dual-degree-of-freedom solar orientation system for a spacecraft, and ultimately realizes the normal operation of the separated dual-degree-of-freedom solar orientation system for a spacecraft in orbit.

[0022] (2) The present invention discloses a truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft, which solves the difficulty of arranging relevant control equipment under specific space conditions in the on-orbit dual-degree-of-freedom solar orientation mission of a solar wing, and integrates functions such as power transmission, heat dissipation and astronaut operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a structural schematic diagram of one direction of a truss device used in a separated dual-degree-of-freedom solar orientation system for a spacecraft in an embodiment of the present invention;

[0024] Figure 2 This is a schematic structural diagram of another direction of a truss device used in a separated dual-degree-of-freedom solar orientation system for a spacecraft in an embodiment of the present invention;

[0025] Figure 3 is a structural schematic diagram of a truss body in an embodiment of the present invention;

[0026] Figure 4 The present invention is a schematic diagram of functional area division of a truss device used in a separated dual-degree-of-freedom solar orientation system for a spacecraft in an embodiment of the present invention. DETAILED DESCRIPTION

[0027] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0028] One of the core ideas of the present invention is to design a truss device for a spacecraft separated dual-degree-of-freedom solar orientation system based on the constraints of extended missions, astronauts' operating capabilities, aircraft equipment layout, equipment and devices, etc. The truss device has good on-orbit maintainability, reducing the maintenance burden of astronauts; has good heat dissipation conditions, ensuring that the equipment works at a suitable temperature on the basis of meeting high-power transmission in the extravehicular environment; and has a precise shape design that can adapt to the actual length requirements of the solar wing transmission cable.

[0029] Reference Figures 1-2 In this embodiment, the truss device for the spacecraft separated dual-degree-of-freedom solar orientation system includes: a truss body 1, a circular flange 2, an arc flange 3, a high-power device mounting plate 4, a control device mounting plate 5, an extended solar wing mounting plate 6, an extended controller mounting plate 7, an extended cable protection bracket 8, a plume protection bracket 9, a handrail 10, a foot stopper support 11 and a cable fixing bracket 12. Among them, Figure 3 As shown, the truss body 1 includes two parts: a large column section 101 and a small column section 102. The circular flange 2, the arc flange 3, the high-power equipment mounting plate 4, the handrail 10, the foot stopper support 11 and the cable fixing bracket 12 are installed on the large column section 101 by screws. The control device mounting plate 5, the extended solar wing mounting plate 6, the extended controller mounting plate 7, and the extended cable protection bracket 8 are installed on the small column section 102 by screws; the plume protection frame 9 is installed on the high-power equipment mounting plate 4 by screws.

[0030] In this embodiment, the spacecraft separated dual-degree-of-freedom solar orientation system mainly includes: 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices, 6 control devices and several cables. Among them, the 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices and 6 control devices are connected by several cables to achieve electrical connection between the mechanisms and devices; the 2 β solar orientation mechanisms, 1 α solar orientation mechanism, 2 high-power devices, 6 control devices and several cables are installed and fixed by a truss device.

[0031] Preferably, the working principle of the separated dual-degree-of-freedom solar orientation system for a spacecraft composed of "two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices and several cables" is as follows: the two β solar orientation mechanisms are provided with a rotating B axis, and the α solar orientation mechanism is provided with a rotating A axis, and the A axis needs to be perpendicular to the B axis. A solar wing is installed on each of the two β solar orientation mechanisms, and the β solar orientation mechanism drives the solar wing to rotate 360° under the control of the control device, thereby realizing the single-degree-of-freedom solar orientation of the solar wing. At the same time, the α solar orientation mechanism drives the truss device and the two β solar orientation mechanisms to rotate 360° as a whole under the control of the control device, thereby realizing the dual-degree-of-freedom solar orientation of the solar wing.

[0032] In this embodiment, the appearance function division method is adopted to divide the truss device into multiple functional areas according to different functions. Figure 4 As shown, the truss device mainly includes 9 functional areas: β-directed solar orientation mechanism installation area 21, α-directed solar orientation mechanism installation area 22, mechanism heat dissipation area 23, high-power equipment heat dissipation area 24, control equipment installation area 25, on-orbit expansion installation area 26, expansion cable reserved area 27, astronaut operation area 28 and transmission cable installation area 29. Among them:

[0033] There are two circular flanges 2, which are symmetrically installed at the middle of the left and right sides of the large column section 101, as the β-solar orientation mechanism installation area 21, for installing two β-solar orientation mechanisms. The two β-solar orientation mechanisms are connected to the two circular flanges 2 by screws, and are symmetrically installed on the left and right sides of the truss device.

[0034] There are 4 arc flanges 3, which are installed at the bottom of the large column section 101 as the α sun orientation mechanism installation area 22 for installing the α sun orientation mechanism; the 4 arc flanges 3 together form the α sun orientation mechanism installation area 22, which is conducive to reducing the weight of the truss device and providing more equipment installation space. Among them, the α sun orientation mechanism is connected to the 4 arc flanges 3 by screws and installed at the bottom of the truss device. The arc flange 3 is arranged perpendicular to the circular flange 2, thereby meeting the requirement that the A axis must be perpendicular to the B axis in the separated dual-degree-of-freedom sun orientation system of the spacecraft.

[0035] The area between the two circular flanges 2 on the left and right sides and the bottom surface of the large column section 101 is a mechanism heat dissipation area 23, which is used to install the heat dissipation plates of the β-solar orientation mechanism and the α-solar orientation mechanism.

[0036] The high-power equipment mounting plate 4 is installed on the front side of the large column section 101 as a high-power equipment heat dissipation area 24, which is used to install two high-power equipment to meet the heat dissipation requirements of 300W heat consumption of each large-power equipment. Among them, the two high-power equipment are installed on the high-power equipment mounting plate 4 by screws, located on the front side of the truss device. There are two plume protection frames 9, which are installed at the bottom of the side of the high-power equipment mounting plate 4 to provide plume protection for the cables between the high-power equipment and the α-directed solar orientation mechanism to prevent the plume from acting on the high-power equipment and causing damage to it.

[0037] There are two control device mounting plates 5, which are symmetrically mounted on the groove areas on the left and right sides of the small column section 102 as the control device mounting area 25 for mounting six control devices. Among them, three control devices are mounted on one of the control device mounting plates by screws, and the other three control devices are mounted on the other control device mounting plate by screws. The control device mounting area 25 is located in the groove area of ​​the small column section 102, which is conducive to reducing the weight of the truss device and the envelope size after the control devices are installed.

[0038] There are 4 cable fixing brackets 12 in total, and the 4 cable fixing brackets 12 are installed inside the large column section 101 as the transmission cable installation area 29, which is used for routing and bundling the cables inside the truss device, and then leading them out to the outside of the truss device to connect with various devices. Among them, the cable fixing brackets 12 bundle and bundle the cables to prevent the cables from sliding in a mechanical environment, and at the same time avoid the heat loss of the cables from being concentrated and burning the cables. The transmission cable installation area 29 is located inside the large column section 101, and the cables are routed inside the large column section 101 to avoid the influence of the space environment on the cables.

[0039] The extended solar wing mounting plate 6 and the extended controller mounting plate 7 are mounted on the top of the small column section 102 as the on-orbit extended mounting area 26, which is used to install the extended solar wing and the extended controller on-orbit, so that the aircraft can achieve the on-orbit energy expansion function. Among them, the extended solar wing mounting plate 6 is used to install the extended solar wing on-orbit; there are two extended controller mounting plates 7, which are used to install the extended controller on-orbit.

[0040] The extension cable protection bracket 8 is installed at the front side of the small column section 102 as an extension cable reserved area 27, which is used to fix the reserved extension cable launched with the aircraft, and the reserved extension cable is protected by the extension cable protection bracket 8. Among them, the extension cable reserved area 27 is arranged close to the on-orbit extension installation area 26, which is convenient for the expansion of the solar wing and the expansion controller to be connected with the reserved extension cable on-orbit. The reserved extension cable launched with the aircraft is fixed by the extension cable protection bracket 8, which can prevent the reserved extension cable from moving in a mechanical environment.

[0041] The handrail 10 and the foot stopper support 11 are installed on the rear side of the large column section 101 as the astronaut operation area 28, which is used for astronauts to install the extended solar wing and the extended controller in orbit. Among them, there are 4 handrails 10, which are distributed around the rear side of the large column section 101 for astronauts to grasp and climb. The foot stopper support 11 is set near the rear bottom of the large column section 101, and is used to install the astronaut foot stopper to fix the astronaut.

[0042] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0043] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A truss device for a separated dual-degree-of-freedom solar orientation system of a spacecraft, characterized in that: include: A truss body (1), a circular flange (2), an arc flange (3), a high-power device mounting plate (4), a control device mounting plate (5), an extended solar wing mounting plate (6), an extended controller mounting plate (7), an extended cable protection bracket (8), a plume protection frame (9), a handrail (10), a foot stopper support (11) and a cable fixing bracket (12); wherein the truss body (1) comprises: a large column section (101) and a small column section (102); the circular flange (2), the arc flange (3), the high-power device mounting plate (4), the handrail (10), the foot stopper support (11) and the cable fixing bracket (12) are mounted on the large column section (101) by screws; the control device mounting plate (5), the extended solar wing mounting plate (6), the extended controller mounting plate (7) and the extended cable protection bracket (8) are mounted on the small column section (102) by screws; and the plume protection frame (9) is mounted on the high-power device mounting plate (4) by screws.

2. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 1, characterized in that: The truss device includes 9 functional areas: a β-solar orientation mechanism installation area (21), an α-solar orientation mechanism installation area (22), a mechanism heat dissipation area (23), a high-power equipment heat dissipation area (24), a control equipment installation area (25), an on-orbit expansion installation area (26), an expansion cable reserved area (27), an astronaut operation area (28) and a transmission cable installation area (29).

3. The truss device for the separated dual-degree-of-freedom solar orientation system of a spacecraft according to claim 2, characterized in that: A separated dual-degree-of-freedom solar orientation system for a spacecraft comprises: two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices and a number of cables; wherein the two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices and six control devices are connected by a number of cables to achieve electrical connection between the mechanisms and devices; the two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices and a number of cables are installed and fixed by a truss device.

4. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 3, characterized in that: There are two circular flanges (2) in total. The two circular flanges (2) are symmetrically mounted on the middle of the left and right sides of the large column section (101) to serve as a β-solar orientation mechanism mounting area (21) for mounting two β-solar orientation mechanisms. The two β-solar orientation mechanisms are respectively connected to the two circular flanges (2) by screws and are symmetrically mounted on the left and right sides of the truss device. There are four arc-shaped flanges (3) in total. The four arc-shaped flanges (3) are installed at the bottom of the large column section (101) and are perpendicular to the circular flange (2) to serve as an α-solar orientation mechanism installation area (22) for installing the α-solar orientation mechanism. The α-solar orientation mechanism is connected to the four arc-shaped flanges (3) by screws and is installed at the bottom of the truss device. The area between the two circular flanges (2) on the left and right sides and the bottom surface of the large column section (101) is a mechanism heat dissipation area (23) for installing heat dissipation plates of the β-solar orientation mechanism and the α-solar orientation mechanism; A high-power device mounting plate (4) is mounted on the front side of the large column section (101) as a high-power device heat dissipation area (24) for mounting two high-power devices; wherein the two high-power devices are mounted on the high-power device mounting plate (4) by screws and are located on the front side of the truss device; There are two control device mounting plates (5) in total. The two control device mounting plates (5) are symmetrically mounted on the groove areas on the left and right sides of the small column section (102) as control device mounting areas (25) for mounting six control devices; three of the control devices are mounted on one of the control device mounting plates by screws, and the other three control devices are mounted on the other control device mounting plate by screws; There are four cable fixing brackets (12) in total. The four cable fixing brackets (12) are installed inside the large column section (101) as a transmission cable installation area (29) for routing and binding cables inside the truss device and then leading them out to the outside of the truss device to be connected to various devices.

5. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 4, characterized in that: There are two plume protection frames (9), which are installed at the bottom of the side of the high-power equipment installation plate (4) to provide plume protection for the cables between the high-power equipment and the α-sun orientation mechanism.

6. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 2, characterized in that: An extended solar wing mounting plate (6) and an extended controller mounting plate (7) are mounted on the top of the small column section (102) as an on-track extended mounting area (26) for mounting an extended solar wing and an extended controller on-track; wherein the extended solar wing mounting plate (6) is used for mounting an extended solar wing on-track; and there are two extended controller mounting plates (7) for mounting an extended controller on-track.

7. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 2, characterized in that: The extension cable protection bracket (8) is installed on the front side of the small column section (102) as an extension cable reserved area (27) for fixing the reserved extension cable launched with the aircraft. The reserved extension cable is protected by the extension cable protection bracket (8).

8. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 2, characterized in that: The handrail (10) and the foot stopper support (11) are installed on the rear side of the large column section (101) as an astronaut operation area (28) for astronauts to install the extended solar wing and the extended controller on orbit.

9. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 8, characterized in that: There are four handrails (10) distributed around the rear side of the large column section (101) for astronauts to grasp and climb.

10. The truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to claim 8, characterized in that: The foot stopper support (11) is arranged near the rear bottom of the large column section (101) and is used for installing the astronaut's foot stopper to fix the astronaut.

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