Spacecraft Laser Control for Remote Debris Removal
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Solution Overview
Problem
Existing methods for removing space debris are inefficient, as they either face challenges with rotating debris, risk of collision, and high costs due to incineration of the debris-removing satellite, or require close proximity to apply force, increasing the risk of collision.
Innovation Solution
A spacecraft equipped with a laser apparatus that converges and controls laser irradiation to change the orbit or attitude of space debris from a distance, using a focusing unit and irradiation control system to determine optimal laser output and position, reducing collision risks and costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the debris-removing artificial satellite approaches the rotating debris to adhere to it, then the debris can be removed by incineration, but the risk of collision increases and the satellite itself is incinerated leading to high costs
Solution Approach 1:
The patent replaces the mechanical approach of physically approaching and adhering to debris with a laser-based remote removal system. The laser apparatus emits laser beams to heat and vaporize debris from a distance, eliminating the need for close proximity operations and thereby reducing collision risk while maintaining debris removal effectiveness
Solution Approach 2:
The patent introduces laser beams as an intermediary medium to transfer energy from the satellite to the debris remotely. This intermediary approach allows energy transfer and debris removal without direct physical contact, solving the collision risk problem while achieving the desired debris removal outcome
2Reliability
If gas is ejected from the artificial satellite to apply force to the debris, then the debris orbit can be changed, but the satellite must approach the debris which increases collision risk
Solution Approach 1:
The patent replaces the mechanical gas ejection method with a laser-based remote force application system. By emitting laser beams at the debris from a distance, the system applies thermal stress and radiation pressure to change the debris orbit without requiring close proximity, thereby eliminating the collision risk associated with mechanical approaches
3Reliability
If the laser output is increased to change the orbit or attitude of the target, then the orbital control effectiveness improves, but the risk of uncontrolled heating or damage increases
Solution Approach 1:
The patent implements dynamic control of laser output by the control unit, which adjusts the laser beam intensity based on real-time detection information from the detection unit. This dynamic adjustment allows the system to apply sufficient energy for orbital control while preventing excessive heating through continuous monitoring and adaptive response
Solution Approach 2:
The patent employs a feedback mechanism where the detection unit continuously monitors the target's state and feeds this information to the control unit, which then adjusts the laser output accordingly. This closed-loop control ensures that the laser energy remains within safe parameters while achieving the desired orbital or attitude change
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution allows for safe and efficient change of space debris orbit or attitude, reducing collision risks and costs by enabling remote operation and precise laser control, even for small debris, and can be used for both orbit adjustment and attitude control.
Implementation Method 1
a laser apparatus (106) configured to generate the laser
Implementation Method 2
a focusing unit (107) configured to converge the laser
Implementation Method 3
by irradiating the target with a laser... can change the orbit or the attitude of the target by emitting the laser from a distant position
Data Source
AI summary
A spacecraft for changing an orbit or an attitude of a target in outer space by irradiating the target with a laser, the spacecraft includes: a laser apparatus configured to generate the laser; a focusing unit configured to converge the laser; a detecting unit configured to acquire detection information including a distance between the spacecraft and the target; and an irradiation control unit configured to control the focusing unit on the basis of the distance so that the laser converges on the target.