Wireless energy transmission based spacecraft charging method

A space vehicle and charging method technology, applied in secondary battery charging/discharging, electrical components, circuit devices, etc., can solve problems such as long-term on-orbit, achieve the effects of reducing launch costs, reducing mass scale, and improving attitude control accuracy

Active Publication Date: 2014-02-19
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, to carry out debris capture operations, the aircraft needs to have a high attitude control capability, which has a greater impact on the aircraft carrying large flexible devices...

Method used

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  • Wireless energy transmission based spacecraft charging method
  • Wireless energy transmission based spacecraft charging method
  • Wireless energy transmission based spacecraft charging method

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Embodiment Construction

[0042] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0043] The space charging aircraft based on wireless energy transmission is based on the space charging aircraft (OPSV), and the charging aircraft carries large-scale solar panels and battery packs. The aircraft adopts electric propulsion to maximize its on-orbit maintenance capability. The charging aircraft carries a space wireless energy transmitter, which can provide energy supply for the charged aircraft by means of electromagnetic induction, microwave and laser. Debris removal vehicles carry standard power receivers and battery packs capable of maintaining power usage between refuelings.

[0044] For space wireless energy transmission, in order to improve energy transmission efficiency, it is necessary to carry out space wireless energy transmission track optimization design for flight mission planning. OPSV first maneuvers to stay in orb...

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Abstract

The invention relates to a wireless energy transmission based spacecraft charging method, and the charging method comprises the following steps: (1) a to-be-charged spacecraft sends a charging request command to a ground command center, and the ground command center, according to the needed charging amount and energy transmission efficiency, calculates the wireless energy transmission time; (2) charging and to-be-charged spacecraft tracks and the charging time are taken as constraints for track rendezvous calculation, a charging spacecraft is guided to performing track rendezvous with a to-be-charged spacecraft by using a C-W guidance strategy according to track calculation results; (3) an energy transmission channel is established, the relative position and relative attitude of the charging spacecraft and the to-be-charged spacecraft are confirmed; (4) energy is transmitted to the to-be-charged spacecraft by a laser or microwave way. The charging method can effectively reduce the spacecraft mass scale, reduce launch costs of small spacecrafts such as a debris removal spacecraft and the like, and improve the feasibility of development of an initiative space debris removal task.

Description

technical field [0001] The invention belongs to the technical field of active removal of space debris, and relates to a space vehicle charging method based on wireless energy transmission. Background technique [0002] Space debris is various wastes and their derivatives produced by human beings in space activities. With the gradual deepening of space resources development and the expansion of space applications, especially the emergence and development of small satellites and satellite constellations, the more spacecraft that enter space orbit, the more space debris will be generated. Space debris not only seriously threatens the safety of orbiting spacecraft, but also poses a serious threat to limited space orbit resources as the number continues to increase, especially when the density of space debris at a certain orbital altitude reaches a critical value When , the chain collision process between debris will cause permanent damage to orbital resources. Therefore, it is...

Claims

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Application Information

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IPC IPC(8): H01M10/44H02J17/00H02J50/20H02J50/30
CPCH01M10/44H02J17/00Y02E60/10
Inventor 唐超高朝辉唐庆博张旭辉申麟刘伟
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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