Asymmetrical Electrostatic Pressure Thruster for Propellant-Free Spacecraft
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Solution Overview
Problem
Current propulsion systems for spacecraft rely heavily on propellants, which are inefficient and limit the mission duration and capability of spacecraft, as they require significant mass for stored propellant and mechanical structures, and existing propellantless propulsion methods, such as the Biefeld-Brown Effect, face challenges in generating sufficient thrust in a vacuum environment without ion wind effects.
Innovation Solution
The development of an electrostatic pressure force (EPF) system that utilizes electrostatic pressure generated by voltage differences across electrically conductive surfaces to produce a net force on an object without expelling propellant, achieved through computational optimization of geometric arrangements and voltage applications to create asymmetrical electrostatic pressure distributions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If chemical or electrically enhanced chemical propulsion systems are used to provide physical thrust, then the spacecraft can achieve desired motion and maintain location, but the mass and volume dedicated to propulsion systems becomes extremely large (85% or more of total mass per volume budget)
Solution Approach 1:
The patent replaces chemical propulsion systems with an electrostatic propulsion system that uses electric fields to generate thrust. Instead of burning propellants to create chemical thrust, the system applies high voltage to asymmetrical electrode structures to create electrostatic pressure differences that propel the spacecraft, eliminating the need for large propellant tanks and chemical propulsion machinery.
Solution Approach 2:
The patent changes the fundamental parameter of propulsion from chemical energy conversion to electrostatic field energy conversion. By using high voltage electric fields applied to asymmetrical electrode configurations, the system generates thrust through electrostatic pressure rather than chemical combustion, fundamentally altering the energy-to-thrust conversion mechanism and reducing propulsion system mass.
2Duration of action of moving object
If stored propellant is used to determine mission capability, then the spacecraft can perform maneuvers and maintain precise location, but the spacecraft becomes space junk when propellant is exhausted, ending its operational life
Solution Approach 1:
The electrostatic propulsion system uses the spacecraft's own electrical power system to generate thrust continuously without consuming propellant mass. The system draws electrical energy from the spacecraft's power supply and converts it directly to mechanical thrust through electrostatic field interactions, allowing indefinite operation as long as electrical power is available, rather than being limited by finite propellant reserves.
Solution Approach 2:
The patent fundamentally changes the limiting parameter from propellant quantity to electrical energy availability. By replacing chemical propellant with electrostatic field-based propulsion, the system's operational duration is no longer constrained by the amount of stored propellant but by the spacecraft's electrical power generation and storage capabilities, which can be continuously replenished through solar panels or other power sources.
3Power
If complex systems for energy conversion to motion are used, then the spacecraft can generate physical thrust, but the system complexity, mass, and volume increase significantly
Solution Approach 1:
The patent replaces complex mechanical energy conversion systems with a direct electrostatic field-to-mechanical thrust conversion system. Instead of using engines, turbines, nozzles, and moving parts to convert chemical or electrical energy to mechanical motion, the system uses high voltage applied to asymmetrical electrodes to create electrostatic pressure differences that directly generate thrust, eliminating complex mechanical conversion components.
Solution Approach 2:
The patent extracts and eliminates the complex intermediate mechanical conversion stages from the energy-to-motion pathway. By using electrostatic propulsion, the system goes directly from electrical energy storage to mechanical thrust generation through field interactions, removing the need for combustion chambers, propellant flow systems, mechanical turbines, and other complex intermediate conversion components.
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 enables the generation of thrust without propellant, potentially increasing spacecraft mission duration and capability, and has been verified in laboratory tests to produce measurable forces, independent of ion wind effects.
Implementation Method 1
generates forces by voltages, or voltage differences, when such voltages or voltage differences are applied to electrically conductive surfaces in such a way as to generate electrostatic pressure forces
Data Source
AI summary
A system and method for generating a force from a voltage difference applied across at least one electrically conductive surface. The applied voltage difference creates an electric field resulting in an electrostatic pressure force acting on at least one surface of an object. Asymmetries in the resulting electrostatic pressure force vectors result in a net resulting electrostatic pressure force acting on the object. The magnitude of the net resulting electrostatic pressure force is a function of the geometry of the electrically conductive surfaces, the applied voltage, and the dielectric constant of any material present in the gap between electrodes. The invention may be produced on a nanoscale using nanostructures such as carbon nanotubes. The invention may be utilized to provide a motivating force to an object. A non-limiting use case example is the use of electrostatic pressure force apparatus as a thruster to propel a spacecraft through a vacuum.