Rocket Thrust Vectoring With Parallel Electrodes and No Moving Parts
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Solution Overview
Problem
Existing rocket thrust vectoring systems are prone to mechanical failures, add significant weight, reduce propulsion efficiency, and are not suitable for both atmospheric and deep space operations, particularly for medium to high-thrust applications.
Innovation Solution
A method and system using parallel electrodes distributed circumferentially around a rocket nozzle to generate a strong electric field that deflects an ionized exhaust jet laterally, allowing for vectoring without moving parts, utilizing a high-voltage DC supply to control the electric field intensity and pair voltage for precise azimuth steering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical means such as gimballing engine nozzle or pivoting thrust vanes are used for thrust vectoring, then trajectory correction is achieved, but engine weight increases by up to one-third and propulsion efficiency reduces by 3% or more
Solution Approach 1:
The patent replaces mechanical thrust vectoring systems (gimbals, pivoting vanes) with an electromagnetic system using ionized exhaust particles. Electromagnetic coils generate magnetic fields that interact with the ionized propellant to deflect the exhaust jet, eliminating heavy mechanical moving parts while achieving the same trajectory correction function.
Solution Approach 2:
The patent changes the physical state of the propellant by ionizing it before exhaust, transforming neutral propellant molecules into charged ions. This parameter change enables electromagnetic interaction for thrust vectoring, allowing control without mechanical components and reducing engine weight while maintaining reliability.
2Reliability
If mechanical means such as gimballing engine nozzle are used for thrust vectoring, then trajectory correction is achieved, but propulsion efficiency reduces by 3% or more
Solution Approach 1:
The patent replaces mechanical thrust vectoring systems with an electromagnetic system using ionized exhaust particles. Electromagnetic coils generate magnetic fields that interact with the ionized propellant to deflect the exhaust jet, eliminating heavy mechanical moving parts while achieving the same trajectory correction function.
Solution Approach 2:
The patent changes the physical state of the propellant by ionizing it before exhaust, transforming neutral propellant molecules into charged ions. This parameter change enables electromagnetic interaction for thrust vectoring, allowing control without mechanical components and reducing engine weight while maintaining reliability.
3Speed
If electric or ion thruster is used to accelerate ionized atoms, then specific impulse increases to 20-100 km/s, but thrust force reduces to only millinewtons to a few newtons
Solution Approach 1:
The patent merges the advantages of chemical propulsion (high thrust) with electric propulsion (high specific impulse) by ionizing a portion of the chemical propellant exhaust and using electromagnetic fields to accelerate both ionized and neutral particles together, achieving high thrust while maintaining high exhaust velocity.
Solution Approach 2:
The electromagnetic propulsion system serves multiple functions: it ionizes propellant, accelerates ionized particles to high velocities, and simultaneously drags neutral particles along through electromagnetic interaction, creating a unified propulsion system that achieves both high thrust and high specific impulse.
4Adaptability or versatility
If extraction grid is mechanically repositioned for deflecting exhaust jet, then vectoring capability is achieved, but engine weight increases
Solution Approach 1:
The patent replaces mechanical extraction grid repositioning systems with electromagnetic field control. Coils generate magnetic fields that interact with ionized propellant to deflect the exhaust jet electrically, eliminating mechanical moving parts while maintaining full vectoring capability.
Solution Approach 2:
The patent uses dynamically controllable electromagnetic fields to achieve exhaust deflection. By varying the current in different coil segments, the magnetic field direction and strength can be changed in real-time, providing adaptive thrust vectoring without mechanical movement.
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
Achieves lightweight, efficient, and reliable thrust vectoring capable of deflecting the exhaust jet by up to ±10° without mechanical complexity, suitable for both atmospheric and deep space missions, including chemical and electric propulsion systems.
Implementation Method 1
The electrodes may be energized with a high-voltage DC supply for impressing a strong electric field across the exhaust jet
Implementation Method 2
Positively charged particles in the exhaust jet may be accelerated laterally toward a negatively charged side of the one or more electrode pairs
Data Source
AI summary
There is disclosed a method of vectoring a rocket propulsion system producing a partly ionized exhaust jet along a longitudinal jet axis and through a nozzle. One or more pairs of electrodes may straddle the exhaust jet inside the nozzle or at a nozzle exit. A high-voltage DC supply may energize one or more of the electrode pairs with a strong electric field. A field intensity of the electric field may be scaled by the DC supply to proportionately deflect the exhaust jet away the longitudinal axis by a desired vectoring angle. The particular pair voltages sent to each pair of electrodes by the DC supply may be weighted for establishing a desired azimuth for the deflection. The strong electric field may laterally accelerate positively charged particles in the exhaust jet toward a negatively charged side of the one or more electrode pairs, thereby achieving the desired deflection and azimuth.