Rocket Engine Ignition Using Atomized H2O2 Without a Catalyst Bed
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Solution Overview
Problem
Existing rotating detonation rocket engines (RDREs) face challenges with expensive, low-density fuels and oxidizers that require separate storage and cryogenic conditions, leading to inefficiencies and compatibility issues with solid fuels and oxidizers, and hydrogen peroxide necessitates a catalyst bed for decomposition, adding mass and volume.
Innovation Solution
A rocket engine configured to operate on liquid fuels and liquid hydrogen peroxide (H2O2) without a catalyst bed, utilizing high-pressure jets to atomize H2O2 and liquid fuel for ignition and continuous detonation, with a combustion chamber design that delivers finely atomized fuels and oxidizers for spontaneous ignition and detonation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hydrogen peroxide is decomposed on a catalyst bed, then decomposition is supported during flight, but mass and volume are significantly added to the rocket
Solution Approach 1:
The patent removes the catalyst bed from the rocket system entirely. Instead of carrying a catalyst bed for H2O2 decomposition, the system uses an external ground-based catalyst system. The H2O2 is decomposed before injection into the combustion chamber, extracting the decomposition function from the moving rocket mass and placing it in the stationary ground infrastructure.
Solution Approach 2:
The patent introduces an intermediary ground-based catalyst system that mediates the H2O2 decomposition process. Rather than the rocket carrying its own catalyst, the ground system acts as an intermediary that prepares the oxidizer (decomposes H2O2 into O2 and H2O) before it is injected into the rocket engine, thereby supporting decomposition without adding mass to the moving object.
2Quantity of substance
If cryogenic fuels and oxidizers are used, then high energy density is achieved, but continuous pressurization or refrigeration is required
Solution Approach 1:
The patent changes the temperature parameter of the oxidizer from cryogenic to ambient temperature. By using hydrogen peroxide at ambient temperature instead of cryogenic liquid oxygen or other cold oxidizers, the system achieves high energy density without requiring continuous refrigeration or complex pressurization systems, thus reducing device complexity while maintaining effective energy content.
3Productivity
If liquid hydrogen or liquid methane is used, then high efficiency is achieved, but cryogenic storage is required
Solution Approach 1:
The patent uses ground-based heating as an intermediary process. Liquid hydrogen or liquid methane is stored cryogenically on the ground, then heated to ambient temperature by ground-based heating systems before being injected into the rocket. This intermediary heating process allows the use of efficient cryogenic fuels without requiring the rocket itself to maintain cryogenic storage systems during flight.
4Ease of manufacture
If solid fuels and oxidizers are used, then storage simplicity is achieved, but the engine cannot be stopped and restarted
Solution Approach 1:
The patent employs liquid propellants (hydrogen peroxide and liquid fuel) that can be pumped and controlled through hydraulic systems. This allows the engine to be started, stopped, and restarted by controlling the liquid flow rates, providing adaptability and versatility that solid propellants cannot achieve, while still maintaining relatively simple storage requirements for liquids at ambient temperature.
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
Enables efficient, lightweight operation of RDREs using ambient-temperature fuels and oxidizers, eliminating the need for cryogenic storage and catalyst beds, and achieving continuous detonation with reduced mass and volume.
Implementation Method 1
we employ high-pressure jets of H2O2 impinging on a surface and/or impinging on jets of liquid fuel to provide sufficient kinetic energy to atomize the liquid H2O2 by conversion of the kinetic energy into increased surface area, surface energy, and smaller droplets
Implementation Method 2
When H2O2 at high concentrations is catalytically decomposed, the chemical energy of decomposition is sufficient to fully vaporize the H2O2 (and diluent water). Catalytic decomposition of hydrogen peroxide releases 2.877 MJ of energy per 1 kg of hydrogen peroxide and produces green products according to the following reaction: H2O2→H2O+1⁄2O2
Implementation Method 3
In operation, a fuel and an oxidizer are injected into the reaction channel, normally through small holes or slits, and detonation is initiated in the fuel/oxidizer mixture by an igniter. After the engine is started, detonation of the fuel/oxidizer mixture is self-sustaining.
Data Source
AI summary
A rocket engine configured to run on a liquid fuel and liquid hydrogen peroxide is started by impinging high pressure streams of a fuel and liquid H2O2 into a combustion chamber under pressure and temperature conditions sufficient to decompose the liquid H2O2 into hot water stream and oxidizer and achieve ignition.