Electron Propulsion Engine With Recycled Electrons for Spacecraft Thrust
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Solution Overview
Problem
Current propulsion systems for spacecraft rely on combustion engines that require large amounts of fuel/oxidant, limiting payload capacity, while electric propulsion engines lack sufficient thrust for wide-ranging applications.
Innovation Solution
An electron propulsion engine utilizing accelerated charged particles in space to emit electromagnetic radiation, which decelerates and recycles electrons, reducing fuel loss and balancing momentum through a symmetric configuration of two mirror engine modules.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If combustion engines are used to propel spacecraft, then sufficient thrust can be generated, but large amounts of fuel/oxidant are required, limiting payload capacity
Solution Approach 1:
The patent replaces the combustion-based mechanical propulsion system with an electromagnetic propulsion system. Electrons are accelerated through magnetic fields to generate thrust via electromagnetic radiation emission, eliminating the need for chemical fuel and oxidant while maintaining sufficient thrust capability for spacecraft propulsion
Solution Approach 2:
The patent changes the fundamental operating parameters from chemical combustion to electromagnetic acceleration. By accelerating electrons to high velocities in magnetic fields and controlling their deceleration, the system generates thrust through electromagnetic radiation pressure without consuming propellant mass, fundamentally altering the propulsion mechanism from chemical to physical/electromagnetic processes
2Loss of energy
If electric propulsion engines are used to reduce fuel consumption, then fuel efficiency improves, but thrust generation is insufficient for wide-ranging spacecraft applications
Solution Approach 1:
The patent introduces magnetic fields as an intermediary mechanism to couple electromagnetic energy with mechanical thrust generation. The magnetic fields accelerate and control electron beams, converting electromagnetic energy into directed kinetic energy and radiation pressure that produces thrust, thereby bridging the gap between electric propulsion efficiency and sufficient thrust generation
Solution Approach 2:
The patent employs periodic acceleration and deceleration of electron beams to generate continuous thrust. Electrons are periodically accelerated to high velocities and then decelerated to emit electromagnetic radiation, creating a pulsed thrust mechanism that accumulates to provide sustained propulsion force while maintaining high energy efficiency
3Loss of energy
If electrons are accelerated to emit electromagnetic radiation for propulsion, then thrust is generated with minimal fuel loss, but rotational momentum must be balanced
Solution Approach 1:
The patent employs asymmetric magnetic field configurations and electron beam trajectories to generate directional thrust while managing momentum. By carefully designing the asymmetry in electron acceleration paths and magnetic field distributions, the system produces net thrust in the desired direction while the overall symmetric arrangement of engine modules balances rotational momentum
Solution Approach 2:
The patent uses symmetrically arranged engine modules that produce equal and opposite rotational moments to balance each other. Each module generates thrust and associated rotational momentum, but the symmetric configuration ensures that rotational momenta cancel out, eliminating the need for additional momentum compensation mechanisms
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 electron propulsion engine efficiently propels spacecraft with minimal fuel consumption by recycling electrons, achieving thrust through electromagnetic radiation emission and balancing momentum, overcoming traditional propulsion limitations.
Implementation Method 1
When negatively charged particles (electrons) are accelerated in space, the accelerating electrons emit electromagnetic waves into space which in turn causes the electrons to lose momentum
Implementation Method 2
the present invention balances rotational momentum resulting from the acceleration/deceleration of electrons by implementing a symmetric configuration of two electric engines that operate simultaneously
Data Source
AI summary
An electron propulsion engine utilizes the acceleration of electrons to propel a spacecraft through space. The acceleration of the electrons in space emits electromagnetic radiation which can be used to propel the spacecraft. The radiation emission also decelerates the electrons, which allows the decelerated electrons to be recycled for reuse by the electron propulsion engine. The electron propulsion engine includes a first engine module, a second engine module, and an engine control system. The first engine module and the second engine module correspond to two mirror structures that form the electron propulsion engine. The engine control system facilitates the automatic control of the operation of the electron propulsion engine. The first engine module and the second engine module each includes a vacuum housing. The vacuum housing of each engine module is a D-shaped structure that facilitates the acceleration of the electrons and the resulting radiation emission to propel the spacecraft.