Satellite Laser Ablation Propulsion Using Orbital Debris
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Solution Overview
Problem
Current satellite propulsion methods, such as chemical and electric propulsion, are costly and inefficient for orbit changes and debris removal, with high propellant costs and limited mission capabilities, while existing alternative solutions are either prohibitively expensive or technologically challenging.
Innovation Solution
A satellite equipped with a laser ablation propulsion system that uses orbital waste as a propellant reservoir, where a laser generates a force by vaporizing the surface of captured debris, allowing for efficient propulsion and mission execution without the need for pre-launched propellant, reducing mass and cost.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If chemical propulsion is used for orbit changes, then thrust is provided, but the specific impulse is low and the mass to be carried is very high
Solution Approach 1:
The satellite uses orbital debris as propellant, making the debris itself serve the propulsion function. The laser ablation system vaporizes the debris material, and the resulting plasma provides thrust without requiring separate propellant tanks or chemical fuel supplies.
Solution Approach 2:
The patent replaces chemical propulsion systems with laser ablation propulsion. Instead of using chemical reactions to generate thrust, a laser beam ablates the debris material directly, converting it to plasma that provides thrust through momentum ejection.
2Weight of moving object
If electric propulsion is used for orbit changes, then the specific impulse is higher reducing propellant mass, but the thrust is weaker and requires longer durations
Solution Approach 1:
The laser ablation system allows dynamic adjustment of propulsion parameters including laser power, pulse duration, and ablation rate. This enables the system to optimize between thrust magnitude and propellant consumption based on mission requirements, bridging the gap between chemical and electric propulsion characteristics.
3Force
If propellant is launched with the satellite for orbit changes, then propulsion capability is ensured, but the cost is prohibitive
Solution Approach 1:
The satellite converts harmful orbital debris into beneficial propellant material. The laser ablation system transforms the debris that poses collision risks into useful plasma for thrust generation, simultaneously addressing debris removal and propulsion needs while eliminating propellant launch costs.
4Quantity of substance
If orbital waste is used as propellant reservoir for laser ablation, then cost is reduced and multiple missions are enabled, but the debris must be captured and positioned
Solution Approach 1:
The captured orbital debris serves multiple functions: it provides propellant material for laser ablation propulsion, acts as reaction mass for thrust generation, and can be selectively targeted for specific mission objectives. This multi-functionality reduces the need for dedicated propellant supplies and enables versatile mission capabilities.
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
This approach significantly reduces the cost of orbit changes and debris removal by utilizing in-situ resources, minimizing the risk of debris to other satellites and enabling multiple missions with the gradual consumption of waste debris, thus transforming waste into a valuable propellant source.
Implementation Method 1
laser ablation propulsion device comprising at least one laser
Implementation Method 2
The impact of one or more lasers on a target space body generates a force by vaporizing the surface thereof
Implementation Method 3
the propulsion of the satellite is ensured by the ejection of matter in the form of plasma
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
A laser ablation-propelled satellite (1) comprising: - an attitude and orbit management device (5) for the satellite (1); - a capture and optional processing device (4) for the target space body (3); - an external communication device (7); - a laser ablation propulsion device (8) comprising one or more lasers (9) and a laser management module adapted to determine the laser beam(s) to be generated on the captured target space body (3) according to the desired displacement for the satellite (1); and - a visual inspection device (11) for the target space body (3).