Rocket Engine With Plasma-Assisted Combustion And Acceleration
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Solution Overview
Problem
Existing rocket engines face limitations in efficiency and thrust due to thermodynamic processes in chemical engines and high energy demand in electric engines, necessitating a more efficient propulsion system.
Innovation Solution
A rocket engine with a convergent-divergent nozzle, ionization device, and plasma propulsion accelerator, utilizing multiple ionization stations and electromagnetic fields to enhance combustion stability and control propellant velocity, reducing fuel consumption and improving specific impulse.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If chemical reaction processes are used in rocket engines, then high thrust is generated, but efficiency is limited by thermodynamic processes
Solution Approach 1:
The patent changes the physical state of the propellant from neutral to ionized plasma, fundamentally altering how the propellant interacts with electromagnetic fields. This parameter change enables the propellant to be accelerated more efficiently by electromagnetic forces while maintaining the high thrust characteristics of chemical reactions, thus resolving the contradiction between thrust generation and energy efficiency
Solution Approach 2:
The patent replaces purely mechanical/thermal chemical propulsion with a hybrid system that uses electromagnetic fields for propellant acceleration. By substituting some of the mechanical energy conversion processes with electromagnetic acceleration, the system achieves higher efficiency while maintaining the thrust benefits of chemical reactions
2Use of energy by moving object
If electromagnetic fields are used for propellant acceleration, then fuel consumption is reduced, but thrust is limited by high energy demand per unit mass
Solution Approach 1:
The patent applies preliminary action by ionizing the propellant before it enters the acceleration zone. This pre-ionization process prepares the propellant to respond more effectively to electromagnetic fields, enabling efficient acceleration with lower energy demand per unit mass while generating sufficient thrust for space vehicle propulsion
3Stability of the object's composition
If plasma is generated in the reaction chamber, then combustion stability is improved, but maintaining plasma stability under high pressure is difficult
Solution Approach 1:
The patent applies local quality by creating different plasma conditions in different regions of the reaction chamber. By tailoring the ionization level and plasma density to specific local requirements within the chamber, the system maintains combustion stability in the reaction zone while managing plasma stability challenges in the high-pressure environment
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 system achieves improved combustion stability, reduced fuel consumption, and enhanced propulsion performance by leveraging plasma-assisted combustion and controlled propellant acceleration, maintaining plasma stability under high pressure.
Implementation Method 1
an ionization device, which is configured to ionize the propellant and comprises at least one first ionization station arranged in the area of the reaction chamber
Implementation Method 2
a reaction chamber arranged upstream of the convergent-divergent nozzle and in which the propellant is subject to a chemical reaction that generates energy in the form of heat
Implementation Method 3
chemical rocket engines are based on a chemical reaction of the propellant and are characterized by the high thrusts generated due to the capacity to eject large quantities of mass generated by exothermic processes
Implementation Method 4
Electric engines are based on the use of electromagnetic fields for acceleration of the propellant
Implementation Method 5
a convergent-divergent nozzle having a minimum passage section configured to guide a flow of propellant in a given direction
Implementation Method 6
The phenomenon of 'plasma assisted combustion' improves the stability of the flame, catalyzes the combustion processes, allows more stable and rapid combustion reactions to be obtained
Data Source
Figure 1~3
Figure 2
AI summary
A rocket engine (2) for vehicles, in particular for space vehicles, has: - a convergent-divergent nozzle (12) configured to guide a propellant flow in a given direction (D1) and having a minimum passage section (Smin); - a reaction chamber (5) arranged upstream of the convergent-divergent nozzle (12) and in which the propellant is subject to a chemical reaction that generates energy in the form of heat; - an ionization device (6), which is configured to ionize the propellant and comprises at least a first ionization station arranged in the area of the reaction chamber (5); and - a plasma propulsion engine accelerator (7) downstream of the convergent-divergent nozzle (12).