Hybrid Rocket Thruster Motor and Fuel System
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Hybrid rocket thrusters face challenges with low weight ratios due to the need for extensive fluid fuel storage, limiting the amount of equipment that can be carried on a rocket.
Innovation Solution
A motor and fuel-powered hybrid system with a central processing system, compressor, fluid fuel injector, and igniter, which adjusts fuel output and thrust stages based on altitude information to optimize kinetic energy use, reducing the volume of fluid fuel required.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If fluid fuel is stored on the rocket body for lift-off, then the rocket can achieve sufficient thrust for lift-off, but the space for equipment installation is reduced and the weight ratio of carried objects becomes extremely low
Solution Approach 1:
The patent divides the fuel storage into multiple separate tanks (first tank, second tank, third tank) arranged in sequence along the rocket body. Each tank has specific functions: the first tank stores compressed air, the second tank stores fluid fuel, and the third tank serves as the combustion chamber. This segmentation allows optimized space utilization and reduces the volume required for equipment installation while maintaining sufficient thrust through staged fuel delivery.
Solution Approach 2:
The patent pre-compresses air in the first tank before lift-off using a compressor powered by an electric motor. This preliminary compression of air prepares the oxidizer in advance, eliminating the need to carry large volumes of both fuel and oxidizer in liquid form during launch. The pre-compressed air is then delivered to the combustion chamber during flight, reducing the overall fuel storage volume required on the rocket body.
2Power
If fluid fuel is stored on the rocket body for lift-off, then the rocket can achieve sufficient thrust for lift-off, but the weight ratio of carried objects becomes extremely low
Solution Approach 1:
The system pre-compresses air in the first tank before lift-off using a compressor powered by an electric motor. This preliminary compression of air prepares the oxidizer in advance, eliminating the need to carry large volumes of both fuel and oxidizer in liquid form during launch. The pre-compressed air is then delivered to the combustion chamber during flight, reducing the overall fuel storage volume and weight required on the rocket body.
Solution Approach 2:
The patent replaces the traditional mechanical system of carrying large quantities of liquid oxidizer with a compressed air storage system. The electric motor-driven compressor mechanically compresses atmospheric air into the first tank before launch, substituting the need for heavy liquid oxidizer storage. This mechanical substitution significantly reduces the weight of fuel storage systems while maintaining thrust capability.
3Ease of operation
If the mixing of fluid fuel and solid fuel is used for propulsion, then thrust control is improved, but the amount of fluid fuel required increases and requires more storage space
Solution Approach 1:
The patent implements periodic action through staged fuel delivery in three distinct phases: (1) Before lift-off: The electric motor drives the compressor to compress air into the first tank; (2) During lift-off and ascent: Compressed air from the first tank is delivered to the combustion chamber to mix with fluid fuel from the second tank; (3) After fuel depletion: The system transitions to using only the pre-compressed air from the first tank for propulsion. This periodic operation allows precise thrust control while minimizing fluid fuel consumption by using compressed air as the primary oxidizer source during critical flight phases.
Solution Approach 2:
The system changes the physical state parameter of the oxidizer from liquid (traditional rocket oxidizer) to compressed gas. By compressing air into the first tank before launch and delivering it to the combustion chamber during flight, the system achieves thrust control through parameter changes in pressure and flow rate of the compressed air, rather than relying on large quantities of fluid fuel. This parameter change reduces the quantity of fluid fuel required while maintaining ease of thrust 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 system increases the rocket's load ratio by minimizing fluid fuel storage needs, allowing more equipment to be carried while maintaining efficient propulsion through staged thrust adjustments.
Implementation Method 1
a compressor that is power connected to the central processing system
Implementation Method 2
an igniter disposed in the third tank and controllingly connected to the processing unit, and being used for igniting fluid fuel
Implementation Method 3
a fluid fuel injector disposed on the casing, controllingly connected to the processing unit, and including an injection head extending into the second tank, and the injection head being arranged toward the third tank to spray fluid fuel
Data Source
AI summary
A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.