Oriented Wire Electrostatic Radiation Protection for Spacecraft
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current radiation protection systems for spacecraft, such as physical barriers and hydrogen/water shields, are impractical due to high mass requirements and operational limitations during solar particle events, making interplanetary travel hazardous for both occupants and equipment.
Innovation Solution
An oriented wire electrostatic radiation protection system that deploys positively and negatively charged wires to deflect solar particles via electrostatic repulsion, creating a shielded region around the spacecraft with reduced mass and power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If physical barriers or solar particle radiation absorbing material are used to protect spacecraft, then radiation protection effectiveness is improved, but mass increases significantly exceeding 40 g/cm2
Solution Approach 1:
The patent replaces the mechanical/physical barrier system (massive radiation-absorbing materials) with an electrostatic field system. Charged wires generate electric fields that deflect charged solar particles through electrostatic forces, eliminating the need for massive physical shields while maintaining radiation protection effectiveness.
Solution Approach 2:
The patent changes the state of matter from solid/rigid radiation-absorbing materials to charged particles suspended in space. By ionizing gas or using charged wires, the system creates an electrostatic field that dynamically responds to incoming solar particles, providing protection with minimal mass compared to static physical barriers.
2Reliability
If hydrogen or water shields are used for radiation protection, then radiation protection effectiveness is improved, but mass and volume requirements increase
Solution Approach 1:
The patent substitutes the bulk material shielding approach (hydrogen or water tanks) with an electrostatic field generation system. Charged wires or ionized gas create electric fields that deflect charged particles, replacing the need for large quantities of shielding material with a field-based protection mechanism.
Solution Approach 2:
The patent introduces charged wires or ionized gas as an intermediary between the solar particles and the spacecraft. This intermediary creates an electrostatic field that interacts with incoming charged particles, deflecting them before they reach the spacecraft, thereby protecting the spacecraft without requiring massive hydrogen or water shields.
3Reliability
If occupants are confined in a small capsule during solar particle events, then radiation protection effectiveness is improved, but operational capability deteriorates
Solution Approach 1:
The patent establishes a radiation protection field around the entire spacecraft before solar particle events occur. The wire management system deploys and charges protective wires in advance, creating a persistent electrostatic shield that protects all spacecraft and occupants without requiring confinement, allowing normal operations to continue during solar events.
Solution Approach 2:
The patent creates a universal protection field that covers the entire spacecraft and all its occupants simultaneously, rather than providing localized protection in a small capsule. The electrostatic field generated by charged wires protects all equipment and personnel throughout the spacecraft, enabling full operational capability while maintaining radiation protection.
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 system effectively protects spacecraft from solar particle radiation with lower mass and power usage compared to traditional methods, enabling safer interplanetary travel by deflecting charged particles and maintaining charge balance.
Implementation Method 1
When the approaching solar particles travel in parallel and alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion
Data Source
AI summary
There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.