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Film spacecraft

A technology for spacecraft and thin-film sensors, which is applied in the direction of aerospace vehicles, antennas, aircraft, etc., and can solve the problems of not being able to better realize the high performance and long life requirements of spacecraft

Active Publication Date: 2020-08-18
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The main purpose of the present invention is to provide a thin-film spacecraft, which integrates thin-film propulsion, thin-film imaging, thin-film communication, thin-film power generation, etc. To better realize the spacecraft's demand for high performance and long life

Method used

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Embodiment Construction

[0052] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0053] Aiming at the requirements of long-duration and large-scale space missions for long-life and high-performance spacecraft, and at the same time meeting the higher requirements of space missions for response time and manufacturing costs, the invention is based on new aerospace thin-film structure technology and deep integration technology of structural loads , a thin-film spacecraft is proposed, which consists of a multifunctional body platform 1,...

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Abstract

The invention discloses a film spacecraft, and belongs to the technical field of spacecraft design. The thin-film spacecraft comprises a multifunctional body platform, a thin-film propelling device, athin-film camera, a thin-film antenna, a thin-film battery piece, a thin-film sensor, a thin-film actuator and the like. The thin film propelling device stretches the six thin film sails into a hugeregular hexagon sail surface in a supporting rod stretching mode, flight power is obtained under the action of sunlight pressure, and the thin film camera can conduct high-resolution imaging on an observed target. According to the film spacecraft, multiple functions of thin film propulsion, thin film imaging, thin film communication, thin film power generation, thin film sensing and actuation andthe like are integrated; the film spacecraft can complete long-term voyage and large-range space flight tasks, the advantages of a thin film structure technology and a multifunctional structure technology are fused, through depth integrated design of the structure and loads, weight reduction, energy increase and function ratio improvement of the spacecraft structure are further achieved, and the requirements of spacecrafts for high performance and long service life can be better met.

Description

technical field [0001] The invention belongs to the technical field of spacecraft structure design, and in particular relates to a thin-film spacecraft. Background technique [0002] With the continuous improvement of spacecraft performance requirements, the spacecraft has an urgent need for a larger scale and size of its own platform, solar array, and antenna structures. However, in order to meet the limitations of the current rocket launch capability While increasing in size, try to achieve lighter weight and smaller folded volume. Therefore, the large-scale, light-weight and small-volume reduction of the spacecraft structural platform has become the unremitting goal of spacecraft designers in various countries. The thin film structure has the characteristics of light weight, small storage volume, and easy realization of super-large space structures. It has good application prospects in spacecraft propulsion, communication, energy, etc., and has become a popular aerospace...

Claims

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Application Information

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IPC IPC(8): B64G1/22B64G1/44B64G1/66H01L31/0445H01L31/048H01Q1/28H01Q1/38H01Q21/00
CPCB64G1/22B64G1/443B64G1/66H01L31/048H01Q1/285H01Q1/38H01Q21/00H01L31/0445Y02E10/50
Inventor 李东旭刘望吴军
Owner NAT UNIV OF DEFENSE TECH
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