Hybrid Rocket Engine Solid-Fluid Oxidizer Integration
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Solution Overview
Problem
Current rocket engines face challenges in achieving homogeneous ignition, high take-off thrust, controllable cruising thrust, and cost-effectiveness, with existing technologies either being non-reignitable and complex or limited by internal geometries and high costs.
Innovation Solution
A rocket engine design featuring a combustion chamber with a block of solid propellant comprising both solid fuel and oxidizer, where a fluid oxidizer is injected to facilitate ignition and regulate thrust, allowing for self-sustaining combustion and protection of critical components from combustion gases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If solid propellant engines are used, then ease of storage and high thrust are achieved, but restart capability and thrust control are lost
Solution Approach 1:
The patent combines solid propellant and liquid propellant systems into a hybrid rocket engine. The solid propellant block provides high thrust and ease of storage, while the liquid oxidizer injection system enables thrust control and restart capability. This merging of solid and liquid propulsion systems resolves the contradiction by integrating the advantages of both types into a single engine architecture.
Solution Approach 2:
The patent introduces a dynamic control system that regulates the injection rate of liquid oxidizer to control the combustion rate of solid propellant. The control device can dynamically adjust the thrust level and enable engine restart, transforming the static solid propellant system into a dynamically controllable propulsion system that maintains high thrust while gaining adaptability.
2Adaptability or versatility
If liquid propellant engines are used, then restart capability and thrust regulation are achieved, but cost and implementation complexity increase
Solution Approach 1:
The patent segments the propulsion system into distinct functional components: a solid propellant block for fuel, a liquid oxidizer storage system, an injection system, and a control device. This segmentation allows each component to be optimized independently and simplifies the overall implementation by clearly defining the role of each subsystem, reducing the complexity associated with traditional liquid propellant engines.
3Adaptability or versatility
If hybrid propulsion engines with pressurized liquid oxidizer injection are used, then restart capability and thrust regulation are achieved, but homogeneous ignition is not achieved and internal geometries become complex
Solution Approach 1:
The patent incorporates solid oxidizer grains within the solid propellant block before ignition. This preliminary inclusion of oxidizer in the solid fuel matrix ensures homogeneous distribution of fuel and oxidizer, enabling uniform ignition across the propellant surface. This preliminary action eliminates the need for complex internal geometries to achieve homogeneous combustion, while still allowing thrust regulation through liquid oxidizer injection control.
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 design enables uniform ignition, increased thrust, and precise thrust regulation, enhancing mission flexibility and reducing costs by using a combination of solid and fluid oxidizers, while protecting components from erosion and damage.
Implementation Method 1
The oxidizer is configured so that, after ignition by an igniter, it reacts chemically with the solid fuel, causing the solid propellant block to burn
Implementation Method 2
Injecting a fluid oxidizer, in addition to the solid oxidizer already present in the solid propellant block, intensifies combustion within the block, thus increasing the engine's thrust
Data Source
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AI summary
rocket engine (1) comprising a combustion chamber (10) opening onto a nozzle (14), at least one first solid propellant block disposed in the combustion chamber (10), the first solid propellant block comprising a solid fuel and a solid oxidizer, at least one injector (30) configured to inject a fluid oxidizer into the combustion chamber (10), a control element (44) for regulating the flow rate of fluid oxidizer injection into the combustion chamber (10), a second solid propellant block (70) disposed in the combustion chamber (10) so as to define a cavity (12) opening onto the nozzle (14), the first block being encapsulated between an internal wall of the combustion chamber (10) and the second solid propellant block (70), the first solid propellant block (60) having a lower solid oxidizer content than the second solid propellant block (70).