Solar-sail spacecraft structure provided with distributed satellites for traction

A distributed and spacecraft technology, which is applied in the field of solar sail spacecraft configuration, can solve the problems that are difficult to apply to super large-area solar sails, and achieve the effect of high spin control efficiency and reduced weight requirements

Active Publication Date: 2017-02-15
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, the current spin-unfolded configuration is still diff

Method used

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  • Solar-sail spacecraft structure provided with distributed satellites for traction
  • Solar-sail spacecraft structure provided with distributed satellites for traction
  • Solar-sail spacecraft structure provided with distributed satellites for traction

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Example Embodiment

[0025] This embodiment is a configuration of a distributed satellite towed solar sail spacecraft.

[0026] Refer to Figure 1a , Figure 1b ~ Figure 4 In this embodiment, the distributed satellite traction solar sail spacecraft configuration consists of the distributed satellite 1, the central spacecraft 3, the solar sail film 6 and the connection and separation device 2, the liquid crystal reflector 4, the solar cell 5, the solar sail film 6. Tether 7 is composed. The central spacecraft 3 is connected with the distributed satellite 1 and the solar sail membrane 6 by a tether 7. The distributed satellite 1 is symmetrically distributed according to the central spacecraft 3 and is in the same plane. In this embodiment, there are four distributed satellites 1 and the four distributed satellites 1 have the same quality; each distributed satellite 1 can be three-axis stable, positioned relative to the central spacecraft 3, and carry different payloads. The solar sail film 6 is connec...

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Abstract

The invention discloses a solar-sail spacecraft structure provided with distributed satellites for traction. The solar-sail spacecraft structure provided with the distributed satellites for traction is composed of a central spacecraft, the distributed satellites and a square solar sail film. The distributed satellites are fixedly connected with the central spacecraft through connection and separation devices, and the distributed satellites are ejected to be separated from the central spacecraft through the connection and separation devices, so that the relative speed is obtained; and tied ropes are pulled to be controlled at the same time, so that the solar sail film is pulled out and unfolded. After the solar sail film is unfolded in place, a system is made to spin up through active acting force of the distributed satellites, and tensile force for keeping the solar sail film flat is generated. The multiple distributed satellites are used for providing traction force in the unfolding process, providing centrifugal force in the on-orbit flight process and serving as a distributed effective loading platform when a detection task is carried out. A thin-film solar cell and a liquid crystal reflection device are pasted onto the solar sail film; and electric energy converted by the solar cell is stored in a power source management system, serves as electric energy required for operation of satellite-borne equipment and is used for achieving posture control of the central spacecraft.

Description

technical field [0001] The invention relates to a spacecraft configuration, in particular, to a solar sail spacecraft configuration using distributed satellites to tow and deploy and using spin to keep the sail membrane tensioned. Background technique [0002] The solar sail spacecraft is a large-scale film-expanded spacecraft composed of a large-area sail membrane and a supporting structure. It uses the reflected light pressure of the sun on a large-area flat sail membrane to provide power for the spacecraft to fly. Chemical propulsion for aircraft in sustained flight. Compared with traditional spacecraft, solar sail spacecraft has great advantages. It does not need to consume fuel, so its service life in space is not restricted by limited fuel; using high-performance materials, the quality of the spacecraft structure itself is very light, reducing The small launch mass makes the launch cost lower; using the continuous acceleration provided by the sun's light pressure, aft...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/44
CPCB64G1/10B64G1/44
Inventor 徐超泮斌峰张一凡郑晓亚黄德东文丽华
Owner NORTHWESTERN POLYTECHNICAL UNIV
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