Hybrid Power System for VTOL Aircraft Using Segmented Gas Generators
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Solution Overview
Problem
Traditional aircraft power systems, particularly in VTOL aircraft, are inefficient due to weight and fuel inefficiencies caused by oversized engines for hover and takeoff, and lack sufficient specific power for maneuvers like takeoff, landing, and engine failure scenarios.
Innovation Solution
A hybrid power system comprising a first power source for forward flight and a second power source with an auxiliary gas generator, such as a combustion, decomposition, or cool gas generator, coupled to a turbine, providing high specific power for altitude adjustment modes like hover, transition, and engine failure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a conventional turbine engine is sized to provide power in hover mode, then sufficient power is available for vertical flight, but the engine becomes much larger and heavier than required for forward flight
Solution Approach 1:
The power system is divided into two separate power sources: a first power source (conventional turbine engine) sized for forward flight, and a second power source (auxiliary gas generator with turbine) providing high specific power for hover and altitude adjustment. This segmentation allows each component to be optimized for its specific function rather than one oversized engine handling all modes.
Solution Approach 2:
The hybrid power system combines two different power sources to achieve multi-functionality: the first power source handles forward flight efficiently, while the second power source provides supplemental power for hover, transition, and engine failure scenarios. Together they create a universal power system capable of all flight modes.
2Power
If a conventional turbine engine is sized for peak power in hover mode, then sufficient power is available for takeoff and landing, but the engine operates at a small fraction of maximum during forward flight, reducing efficiency
Solution Approach 1:
The power delivery is segmented between two sources: the first power source operates at efficient levels during forward flight, while the second power source provides peak power during hover and altitude adjustment. This eliminates the need for one engine to operate inefficiently at partial load.
Solution Approach 2:
The system changes the operational parameters by introducing a second power source with different characteristics (high specific power, shorter duration) to complement the first power source, allowing optimal parameter selection for each flight mode rather than compromising with a single engine size.
3Weight of moving object
If chemical or electrical power systems are used in hybrid systems, then weight is reduced, but they do not provide sufficient specific power for takeoff, landing, and hovering
Solution Approach 1:
The auxiliary gas generator acts as an intermediary power source that bridges the gap between lightweight but low-power chemical/electrical systems and heavy high-power conventional engines. It provides the necessary high specific power for critical maneuvers while being more compact and lighter than a conventional engine sized for the same power output.
Solution Approach 2:
The hybrid power system combines two different types of power sources (conventional combustion and auxiliary gas generator) into a composite system that achieves properties neither component alone could provide: sufficient specific power for hover combined with reduced overall system weight and complexity.
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 hybrid power system offers high specific power and energy efficiency, reducing weight and fuel consumption while enabling sufficient power for critical maneuvers, and providing a lightweight, compact solution for VTOL aircraft.
Implementation Method 1
the auxiliary gas generator includes at least one of the following: a combustion gas generator
Implementation Method 2
the auxiliary gas generator includes at least one of the following: a decomposition gas generator
Implementation Method 3
an auxiliary gas generator coupled to a turbine and a drive system
Data Source
AI summary
A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.