Propellant-less Propulsion System Using Synchronized Counter-Rotating Rotors
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Solution Overview
Problem
Current spacecraft propulsion systems rely on chemical propellants, leading to increased complexity, cost, and limited scalability, as well as limitations in bi-directional thrust and reaction wheel torque, which restrict the operational life and design flexibility of spacecraft.
Innovation Solution
A propellant-less propulsion system utilizing synchronized counter-rotating rotors with permanent magnets and electromagnets, allowing for bi-directional thrust generation and reaction wheel control, which simplifies spacecraft architecture and enhances scalability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If chemical propellant-based propulsion systems are used, then thrust generation is achieved, but spacecraft mass increases due to fuel tanks, fuel lines, valves, and flow gauges
Solution Approach 1:
The patent extracts and eliminates the chemical propellant system (fuel tanks, fuel lines, valves, flow gauges) from the spacecraft propulsion system. Instead of using chemical propellants, the invention employs electromagnetic fields generated by electromagnets and permanent magnets to produce thrust directly, removing the need for propellant storage and delivery systems while maintaining thrust generation capability
Solution Approach 2:
The patent replaces the mechanical chemical propulsion system with an electromagnetic field-based system. The electromagnets and permanent magnets create electromagnetic forces that directly propel the spacecraft without mechanical propellant delivery mechanisms, substituting electromagnetic interaction for chemical combustion and mechanical fuel delivery
2Force
If chemical propellant systems are used, then propulsion capability is provided, but system complexity increases due to additional components
Solution Approach 1:
The patent removes complex propellant management components (fuel tanks, fuel lines, valves, flow gauges) from the system while retaining propulsion capability through electromagnetic field interaction. The simplified system uses only electromagnets, permanent magnets, and power supply components
Solution Approach 2:
The electromagnetic propulsion system serves multiple functions: it provides thrust generation, attitude control, and potentially reaction wheel functionality through the same electromagnet and permanent magnet assemblies. This multi-functionality reduces overall system complexity compared to separate dedicated systems for each function
3Ease of operation
If traditional reaction wheels are used for attitude control, then angular orientation control is achieved, but torque production is limited when flywheels reach maximum speed
Solution Approach 1:
The patent replaces the mechanical reaction wheel flywheel system with an electromagnetic torque generation system. Electromagnets interact with permanent magnets mounted on rotors to produce torque directly through electromagnetic forces, eliminating the mechanical inertia-based torque limitation of traditional reaction wheels. This allows continuous torque production regardless of rotational speed
Solution Approach 2:
The patent changes the fundamental parameter for torque generation from mechanical inertia (flywheel mass and speed) to electromagnetic field strength (current through electromagnets). By controlling the electrical current to the electromagnets, torque can be adjusted independently of rotational speed, allowing full torque production even at maximum rotor speeds
4Force
If propellant-based propulsion systems are used, then thrust is generated in one direction, but bi-directional thrust capability is limited
Solution Approach 1:
The patent implements bi-directional thrust capability by using electromagnets that can reverse the polarity of their magnetic fields. By inverting the current direction through the electromagnets, the direction of the electromagnetic force is reversed, allowing thrust in opposite directions without requiring separate thruster assemblies for each direction
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 provides efficient, scalable, and bi-directional propulsion and attitude control, reducing launch mass and operational costs while extending the operational life of spacecraft by eliminating propellant dependency and addressing reaction wheel torque limitations.
Implementation Method 1
at least one permanent magnet of a first of the pair of synchronized rotors is attracted to at least one permanent magnet of a second of the pair of synchronized rotors
Implementation Method 2
providing one or more electromagnets located proximate to the pair of synchronized rotors, wherein the one or more electromagnets are aligned with the plurality of permanent magnets such that a rotational force is imparted on the pair of synchronized rotors
Implementation Method 3
net positive linear momentum is generated through ball bearing traction
Data Source
AI summary
A method of de-spinning a rotor of a propulsion system includes providing one or more spinning rotors rotatably mounted on a frame with a bearing having a bearing outer race, bearing balls, and bearing inner race; providing a force mechanism coupled with the one or more spinning rotors for applying a load to the one or more spinning rotors; and loading an outer portion of the outer bearing race, bearing ball, and inner bearing race of the bearing, a load on the outer portion of the bearing race, bearing ball, and inner bearing race of the bearing corresponding to a force applied to the one or more spinning rotors by the drive mechanism. The one or more spinning rotors de-spin at a rate corresponding to the load on the bearing balls.