Polar Cusp Plasma Redirection for Space Debris Removal
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Solution Overview
Problem
Current methods for removing space debris from near-Earth orbits are inadequate, as they often rely on high-mass and high-energy systems that can contribute to the debris problem and do not effectively address smaller debris particles, leading to potential catastrophic collisions and the Kessler Syndrome.
Innovation Solution
The PRRISM (Platform for Redirecting and Removing Inert Space Material) Satellite system utilizes the solar wind's electromagnetic forces by positioning a satellite at the northern and southern Polar Cusps to redirect and streamline solar plasma, creating a pressure wave that can deflect and de-orbit small debris particles without adding to the debris population.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If high-mass and high-energy systems are used to remove space debris, then the debris removal capability is improved, but the risk of contributing to the debris problem increases
Solution Approach 1:
The patent replaces traditional mechanical debris removal systems (nets, harpoons, tethers) with an electromagnetic field-based system. The electromagnetic launcher uses magnetic fields to accelerate a projectile without mechanical contact, eliminating the need for heavy mechanical structures that would become additional debris. The electromagnetic field acts remotely on the debris through electromagnetic forces, avoiding physical interaction that could generate fragments.
Solution Approach 2:
The patent introduces an electromagnetic projectile as an intermediary carrier. Instead of directly launching heavy debris-removal equipment into orbit, a lightweight electromagnetic projectile is launched and then used to transfer momentum to the debris through electromagnetic forces. This intermediary approach allows debris removal without deploying large masses that would become additional space debris.
2Device complexity
If natural decay forces are relied upon to remove debris, then the system complexity is reduced, but the debris removal time increases to many years
Solution Approach 1:
The patent applies preliminary action by launching an electromagnetic projectile into orbit in advance, positioning it strategically before debris removal operations begin. This pre-positioned electromagnetic launcher can then rapidly accelerate debris removal operations, achieving fast debris removal without requiring complex real-time control systems. The preliminary deployment of the electromagnetic system enables rapid intervention when debris collisions are detected.
3Measurement precision
If existing debris tracking and monitoring systems are used, then the measurement capability for large debris is improved, but the detection of smaller debris particles remains insufficient
Solution Approach 1:
The patent replaces traditional mechanical sensing systems (radars, optical telescopes) with an electromagnetic field-based detection and interaction system. The electromagnetic launcher can detect and interact with small debris particles through electromagnetic forces, which are effective at much smaller scales than mechanical or gravitational sensing. This allows the system to detect and remove debris down to micrometer scales, vastly expanding the size range of detectable debris.
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 provides a sustainable and efficient method to remove small space debris from low Earth orbit by leveraging the solar wind's energy to change the debris' orbital velocity, thereby preventing collisions and mitigating the growth of debris in near-Earth orbits.
Implementation Method 1
utilizes the solar wind's electromagnetic forces by positioning a satellite at the northern and southern Polar Cusps to redirect and streamline solar plasma, creating a pressure wave that can deflect and de-orbit small debris particles
Implementation Method 2
The PRRISM (Platform for Redirecting and Removing Inert Space Material) Satellite system utilizes the solar wind's electromagnetic forces
Implementation Method 3
an antenna directs a local electromagnetic wave to interact with the solar EM wave at the entry point of the polar cusp
Data Source
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AI summary
A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.