Truss device for separated dual-degree-of-freedom solar orientation system of spacecraft

Abstract

The present invention discloses a truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft, comprising: a truss body, a circular flange, a curved 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 stopper support, and a cable fixing bracket; the circular flange, the curved flange, the high-power equipment mounting plate, the handrail, the foot stopper support, and the cable fixing bracket are mounted on the large column section of the truss body; the control equipment mounting plate, the extended solar wing mounting plate, the extended controller mounting plate, and the extended 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. The truss device of the present invention not only meets the requirements of separated dual-degree-of-freedom solar orientation, but also meets the requirements of equipment layout, high-power transmission, equipment heat dissipation, astronaut on-orbit operation, and on-orbit equipment expansion.

Description

Technical Field

[0001] The present 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 for the separated dual-degree-of-freedom solar orientation system for a spacecraft. Background Art

[0002] With the development of aerospace technology, spacecraft are placing higher demands on energy. To ensure optimal lighting conditions for solar panels and achieve high power generation capacity, they require dual-degree-of-freedom solar orientation. Implementing a dual-degree-of-freedom solar orientation solution requires first considering how to securely install the dual-degree-of-freedom solar orientation system. Existing technologies lack a solution to this problem. Summary of the Invention

[0003] The technology of the present invention solves the problem: it overcomes the shortcomings of the existing technology and provides a truss device for a separate 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, and at the same time meet the requirements of separate dual-degree-of-freedom solar orientation, equipment layout, high-power transmission, equipment heat dissipation, astronaut on-orbit operation, and on-orbit expansion 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 for a spacecraft, comprising: a truss body, a circular flange, a curved 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 curved 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; and 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: two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices and several cables; among them, the two β solar orientation mechanisms, one α solar orientation mechanism, the two high-power devices and the six control devices are connected by several cables to achieve electrical connection between the various mechanisms and devices; the two β solar orientation mechanisms, the one α solar orientation mechanism, the two high-power devices, the six control devices and the 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, which are symmetrically installed in the middle of the left and right sides of the large column section. They serve as the installation area for the β-solar orientation mechanism and are used to install two β-solar orientation mechanisms. The two β-solar orientation mechanisms are connected to the two circular flanges with screws and are symmetrically installed on the left and right sides of the truss device.

[0009] There are four curved flanges in total. These are installed at the bottom of the large column, perpendicular to the circular flange, and serve as the mounting area for the α-solar orientation mechanism. The α-solar orientation mechanism is connected to the four curved flanges via screws and is installed at the bottom of the truss assembly.

[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 and α solar orientation mechanisms;

[0011] The high-power equipment mounting plate is installed on the front side of the large column section and serves as a high-power equipment heat dissipation area for mounting two high-power devices. The two high-power devices 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 two control device mounting plates, which are symmetrically installed in the groove areas on the left and right sides of the small column section as control device mounting areas for installing six control devices. Among them, three control devices are installed on one control device mounting plate with screws, and the other three control devices are installed on the other control device mounting plate with 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 to route and bind the cables inside the truss device, and then lead 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 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, the extended solar wing mounting plate and the 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 two 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 a 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, the 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 spacecraft separated dual-degree-of-freedom solar orientation system. The truss device meets the functional requirements of the spacecraft separated dual-degree-of-freedom solar orientation system, such as high-power transmission path connection and high-power heat dissipation, and ultimately realizes the normal operation of the spacecraft separated dual-degree-of-freedom solar orientation system 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 the relevant control equipment under specific space conditions in the on-orbit dual-degree-of-freedom solar orientation mission of the solar wing, and integrates the functions of 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 according to an embodiment of the present invention;

[0024] Figure 2 This is a schematic structural diagram of another direction of a truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft according to 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 the 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 described in further detail below with reference to the accompanying drawings.

[0028] One of the core concepts of this invention is to design a truss assembly for a spacecraft's detachable, dual-degree-of-freedom solar orientation system, based on constraints such as the extended mission, astronaut operational capabilities, and vehicle equipment layout and installation. This truss assembly offers excellent on-orbit maintainability, reducing the maintenance burden on astronauts; provides excellent heat dissipation, ensuring the equipment operates at an appropriate temperature while meeting high-power transmission requirements in the extravehicular environment; and features a precise design that adapts to the actual length requirements of the solar array 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, a curved 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 limiter support 11 and a cable fixing bracket 12. Figure 3 As shown, the truss body 1 consists of two parts: a large column section 101 and a small column section 102. The circular flange 2, curved flange 3, high-power equipment mounting plate 4, handrail 10, foot stop support 11, and cable fixing bracket 12 are screwed to the large column section 101. The control device mounting plate 5, extended solar wing mounting plate 6, extended controller mounting plate 7, and extended cable protection bracket 8 are also screwed to the small column section 102; the plume protection frame 9 is also screwed to the high-power equipment mounting plate 4.

[0030] In this embodiment, the spacecraft's separate dual-DOF solar orientation system primarily includes two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices, and several cables. The two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, and six control devices are connected by several cables to achieve electrical connectivity between the mechanisms and devices. The two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices, six control devices, and several cables are mounted and secured using a truss assembly.

[0031] Preferably, the operating principle of the spacecraft's separated dual-degree-of-freedom solar orientation system, consisting 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, with the A-axis required to be perpendicular to the B-axis. A solar wing is mounted on each of the two β-solar orientation mechanisms. Under the control of the control device, the β-solar orientation mechanism drives the solar wing to rotate 360°, achieving single-degree-of-freedom solar orientation for the solar wing. Simultaneously, under the control of the control device, the α-solar orientation mechanism drives the truss device and the two β-solar orientation mechanisms to rotate 360° as a whole, achieving dual-degree-of-freedom solar orientation for the solar wing.

[0032] In this embodiment, the shape-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-direction-to-the-sun mechanism installation area 21, α-direction-to-the-sun 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] Two circular flanges 2 are symmetrically mounted in the middle of the left and right sides of the main column section 101, forming the β-solar orientation mechanism mounting area 21 for mounting two β-solar orientation mechanisms. The two β-solar orientation mechanisms are connected to the two circular flanges 2 with screws and are symmetrically mounted on the left and right sides of the truss assembly.

[0034] Four curved flanges 3 are mounted at the bottom of the main column section 101, forming the α-solar orientation mechanism mounting area 22 for mounting the α-solar orientation mechanism. These four curved flanges 3 collectively form the α-solar orientation mechanism mounting area 22, reducing the weight of the truss assembly and providing more space for equipment installation. The α-solar orientation mechanism is connected to the four curved flanges 3 via screws and mounted at the bottom of the truss assembly. The curved flanges 3 are perpendicular to the circular flange 2, thus satisfying the requirement that the A-axis and the B-axis be perpendicular in the spacecraft's separated dual-degree-of-freedom solar orientation system.

[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 the 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, serving as a high-power equipment heat dissipation zone 24 for mounting two high-power devices, each meeting the heat dissipation requirement of 300W. The two high-power devices are screwed to the high-power equipment mounting plate 4, located on the front side of the truss assembly. Two plume protection frames 9 are installed on the bottom side of the high-power equipment mounting plate 4 to provide plume protection for the cables connecting the high-power devices to the α-solar orientation mechanism, preventing plume damage to the high-power devices.

[0037] Two control device mounting plates 5 are symmetrically mounted in the recessed areas on the left and right sides of the small column section 102, forming a control device mounting area 25 for mounting six control devices. Three of the control devices are screwed to one of the control device mounting plates, while the remaining three are screwed to the other. The location of the control device mounting area 25 in the recessed area of ​​the small column section 102 helps reduce the weight of the truss assembly and the envelope size after the control devices are installed.

[0038] Four cable fixing brackets 12 are installed inside the main column section 101, forming the transmission cable installation area 29. These brackets are used to route and bundle cables within the truss assembly before routing them outside to connect to various devices. The cable fixing brackets 12 bundle and bundle the cables, preventing them from sliding in mechanical environments and preventing heat loss from concentrating and potentially burning them. The transmission cable installation area 29 is located within the main column section 101, allowing the cables to be routed within the section to avoid the effects of the spatial environment.

[0039] The extended solar wing mounting plate 6 and the extended controller mounting plate 7 are mounted on top of the small column section 102, forming the on-orbit extension mounting area 26. These are used to install the extended solar wing and the extended controller, enabling the aircraft to achieve on-orbit energy expansion. 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, each used to install the extended controller on-orbit.

[0040] An expansion cable protection bracket 8 is mounted on the front side of the small column section 102, serving as an expansion cable reserve area 27 for securing the reserved expansion cables launched with the aircraft. The expansion cable protection bracket 8 protects the reserved expansion cables. The expansion cable reserve area 27 is located near the on-orbit expansion installation area 26, facilitating on-orbit connection of the expansion solar panels and expansion controllers with the reserved expansion cables. Securing the reserved expansion cables launched with the aircraft with the expansion cable protection bracket 8 prevents them from moving in a mechanical environment.

[0041] The handrails 10 and foot restraint supports 11 are installed on the rear side of the main column section 101, serving as the astronaut operating area 28 for installing the extended solar wing and expansion controller in orbit. There are four handrails 10, distributed around the rear side of the main column section 101, for astronauts to grip and climb. The foot restraint support 11, located near the rear bottom of the main column section 101, is used to install the astronaut's foot restraint and secure the astronaut.

[0042] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions 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 solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

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

Claims

1. A truss device for a separated dual-degree-of-freedom solar orientation system for a spacecraft, characterized in that: include: A truss body (1), a circular flange (2), an arc-shaped 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-shaped 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 spacecraft separated dual-degree-of-freedom solar orientation system according to claim 1, characterized in that: The truss device includes nine 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 a spacecraft separated dual-degree-of-freedom solar orientation system 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 several cables; wherein the two β solar orientation mechanisms, one α solar orientation mechanism, two high-power devices and six control devices are connected by several 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 several 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 connected to the two circular flanges (2) by screws, respectively, 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). They 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), which is used to install the 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 in 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 the cables inside the truss device and then leading them out to the outside of the truss device to connect with 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 the extended solar wing and the extended controller on-track; wherein the extended solar wing mounting plate (6) is used for mounting the extended solar wing on-track; and there are two extended controller mounting plates (7) for mounting the extended controller on-track.

7. The truss device for a spacecraft separated dual-degree-of-freedom solar orientation system according to claim 2, characterized in that: An 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 a reserved extension cable launched with the aircraft, and the reserved extension cable is protected by the extension cable protection bracket (8).

8. The truss device for a spacecraft separated dual-degree-of-freedom solar orientation system 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 4 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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