High Power Electric Propulsion System for Rapid Orbit Maneuvers
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Solution Overview
Problem
Existing electric propulsion systems for space vehicles are not powerful enough to escape a planet's gravitational force or change orbits quickly, especially to avoid foreign objects, due to limitations in power levels and efficiency.
Innovation Solution
A high power electric propulsion system with energy storage capability, combining electric rocket engines with energy capture and storage mechanisms, such as lithium-ion batteries or flywheels, to provide sustained power for efficient orbit transfers and maneuvering, enabling Hohmann orbit transfers and rapid avoidance of debris.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If conventional electric propulsion systems are used, then power consumption is reduced, but thrust capability and orbit change speed are insufficient
Solution Approach 1:
The system performs preliminary energy accumulation by capturing solar energy during orbit and storing it in batteries. This stored energy is then released during thruster activation to provide high-power bursts for orbit changes, resolving the contradiction between needing high thrust and limiting power consumption.
Solution Approach 2:
The propulsion system operates in periodic cycles: energy capture phase during orbital flight, energy storage phase charging batteries, and thrust phase utilizing stored energy for brief high-power operations. This periodic operation allows the system to achieve high thrust capability while maintaining average power consumption within acceptable limits.
2Speed
If high power electric propulsion is implemented, then orbit change speed increases, but energy storage requirements increase
Solution Approach 1:
The system changes the temporal distribution of power delivery parameters, delivering energy in high-intensity pulses rather than continuous flow. This allows achieving high orbit change speeds during thrust phases while the average energy storage requirements remain manageable, as the batteries only need to store enough energy for brief high-power bursts.
3Speed
If chemical propulsion is used for orbit changes, then maneuvering speed is high, but propellant consumption increases
Solution Approach 1:
The system replaces chemical propulsion mechanics with electric propulsion mechanics. Electric thrusters provide sustained thrust over longer periods with much higher efficiency, achieving comparable maneuvering speeds while consuming minimal propellant (electricity from stored energy rather than chemical propellant).
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 solution increases the maneuverability and agility of spacecraft, reducing propellant usage and time to change orbits, allowing for more efficient and responsive in-orbit maneuvers with minimal propellant, and providing higher thrust capabilities than conventional systems.
Implementation Method 1
an energy storage device operably connected to the electric propulsion thruster
Implementation Method 2
an electric propulsion thruster having a thrust rating capable of maneuvering the spacecraft into another orbit via multi-burn transfer
Data Source
AI summary
An electric propulsion module coupled to a spacecraft capable of providing thrust at a level required for multi-burn orbit transfer is disclosed herein. The electric propulsion system includes an electric propulsion thruster, a propellant tank and an energy storage device. In one form the energy storage device is a battery operable to provide sufficient power to maneuver the spacecraft quickly to avoid space debris and/or move to a different orbit through a multi-burn thrust procedure.