Hypersonic Power Module Fuel System Integration
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Solution Overview
Problem
Hypersonic vehicles with scramjet engines face challenges in generating electrical and hydraulic power without rotational components, necessitating auxiliary power units that require carrying dedicated fuel, which increases weight and reduces payload capacity.
Innovation Solution
A power module system that utilizes a scramjet engine connected to a propellant selector valve through a bleed air conduit, with a stored energy module and gas generator, allowing the vehicle to generate power using either stored energy or scramjet engine bleed air, reducing the need for onboard fuel and enhancing power generation efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If an auxiliary power unit with dedicated fuel supply is used to generate power, then power generation capability is ensured, but vehicle weight increases and payload capacity decreases
Solution Approach 1:
The patent merges the auxiliary power unit with the scramjet engine fuel system. The APU shares the main fuel supply system, eliminating the need for separate dedicated fuel tanks and reducing overall fuel carriage requirements. The power generation system integrates with existing engine components rather than operating as a completely separate unit.
Solution Approach 2:
The fuel system serves multiple functions: it supplies fuel to the scramjet engine for propulsion and to the auxiliary power unit for electricity generation. This multi-functional approach allows the same fuel resource to support both propulsion and power generation needs, reducing the total amount of fuel required.
2Duration of action of moving object
If dedicated fuel supply for APU is carried, then continuous power generation is possible, but fuel consumption increases
Solution Approach 1:
The APU fuel supply is merged with the main engine fuel system. Both systems draw from the same fuel reservoir, allowing continuous operation without requiring separate fuel storage while reducing total fuel quantity needed.
Solution Approach 2:
The system can dynamically adjust fuel allocation between the scramjet engine and APU based on operational requirements. During phases where propulsion demand is lower, more fuel can be directed to the APU for power generation, optimizing overall fuel utilization.
3Reliability
If separate fuel system for APU is used, then power generation reliability is improved, but device complexity increases
Solution Approach 1:
The fuel delivery systems for the scramjet engine and APU are merged into a single integrated system with common fuel tanks, filtration, and control mechanisms. This reduces the number of separate systems while maintaining reliable power generation through shared infrastructure.
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 the generation of electrical and hydraulic power without an external source of mechanical rotation, reducing the amount of fuel needed for power generation and optimizing power production across various flight regimes, thereby increasing payload capacity and range.
Implementation Method 1
the gas generator comprises a decomposition chamber for decomposing a mono-propellant
Implementation Method 2
the gas generator comprises a combustion chamber for combusting a bi-propellant with an oxidizer
Implementation Method 3
a turbine operatively associated with the permanent magnet generator and configured to receive the high pressure gases from the gas generator or the scramjet engine and communicate mechanical rotation to the permanent magnet generator
Implementation Method 4
a permanent magnet generator configured to convert the mechanical rotation communicated to the permanent magnet generator by the turbine into electrical power
Implementation Method 5
a pressurization gas contained within the pressure vessel, the pressurization gas pressurizing the mono-propellant to urge the mono-propellant toward the propellant selector valve
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
A power module includes a turbo-generator (104) with a propellant selector valve (106), a stored energy module (208) connected to the propellant selector valve, and bleed air conduit (118). The bleed air conduit is connected to the propellant selector valve, wherein the propellant selector valve has a first position, wherein the stored energy tank is in fluid communication with the turbo-generator, and a second position, wherein the bleed air conduit is in fluid communication with the turbo-generator. Vehicles and methods of generating electrical power are also described.