Debris Removal Satellite for Rapid Congested-Orbit Interception
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Solution Overview
Problem
Existing debris removal technologies, such as towing satellites, do not effectively prevent debris from intruding into congested orbits, increasing the risk of collisions with operational satellites.
Innovation Solution
A debris removal satellite equipped with a capture device, propulsion system, and solar array wing is pre-launched with propellant loaded upon receiving an intrusion alarm, capturing debris at a higher altitude and maneuvering it to prevent entry into congested orbits.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If debris is captured and removed from congested orbits using existing towing satellite technology, then the debris is extracted from the congested region, but the debris may still intrude into congested orbits during its trajectory, increasing collision risk
Solution Approach 1:
The debris removal satellite is prepared in advance with propellant loaded in the propellant tank before launch. When a debris intrusion alarm is issued, the satellite can be immediately launched and operational without requiring propellant loading time, enabling rapid response to prevent debris from intruding into congested orbits
Solution Approach 2:
The debris removal satellite acts as an intermediary between the debris and the congested orbit region. By capturing the debris at higher orbital altitude and using the propulsion device to maneuver it, the satellite prevents direct intrusion into congested regions while maintaining control over the debris trajectory
2Speed
If the debris removal satellite is launched immediately upon receiving an intrusion alarm, then the response time is minimized and debris intrusion is prevented, but propellant must be pre-loaded which increases pre-launch preparation requirements
Solution Approach 1:
The satellite is built in advance with propellant pre-loaded in the propellant tank during manufacturing or before launch. This preliminary preparation eliminates the need for time-consuming propellant loading operations after the intrusion alarm is received, enabling immediate launch and rapid debris capture at higher orbital altitude
Solution Approach 2:
The debris removal satellite is designed as a modular system with distinct functional components: capture device for capturing debris, propulsion device with separately identifiable thruster and propellant tank, and solar array wing for power generation. This segmentation allows for standardized manufacturing and assembly while maintaining rapid deployment capability
3Reliability
If debris is captured at higher orbital altitude, then the solar array wing can operate effectively and the debris is kept away from congested regions, but the propulsion device requires more energy to maneuver the debris
Solution Approach 1:
The solar array wing generates electrical energy periodically as the satellite orbits Earth at higher altitude where solar illumination is more consistent. This electrical energy is stored and used by the propulsion device to provide periodic thrust maneuvers for capturing and maneuvering debris, reducing the need for continuous high-energy propulsion
Solution Approach 2:
The propulsion device uses electrical propulsion (ion thruster or Hall thruster) that converts electrical energy from the solar array wing into thrust through electromagnetic fields. This replaces traditional chemical propulsion, providing more efficient energy utilization for maneuvering debris at higher orbital altitude where solar power is abundant
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
Prevents debris from entering congested orbits by actively deorbiting it, reducing collision risks and protecting the space environment.
Implementation Method 1
a solar array wing that is operable in an orbit at an orbital altitude higher than a congested orbit region
Implementation Method 2
a propulsion device including a thruster of a chemical propulsion method and a propellant tank to store chemical fuel
Implementation Method 3
causes the propulsion device to operate with the capture-target debris being captured, so as to prevent the capture-target debris from intruding into the congested orbit region
Data Source
AI summary
A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.