Aircraft Hybrid Propulsion Power Sharing for VTOL Failure Handling
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Solution Overview
Problem
Existing hybrid propulsion systems for vehicles, particularly aircraft, face inefficiencies in power distribution and operational flexibility, especially in transitioning between different modes of propulsion such as vertical takeoff and forward flight, and in handling failures of propulsion components.
Innovation Solution
A hybrid propulsion system with a power sharing module that controls the ratio of mechanical energy from a gas turbine engine to drive propulsors and generate electrical energy, incorporating series and parallel propulsion units, allowing for adjustable power distribution and independent control of propulsion modules to optimize efficiency and safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the gas turbine engine mechanically drives the propulsor directly, then propulsion efficiency is improved, but the system loses flexibility in power distribution and cannot rapidly adapt to component failures
Solution Approach 1:
The system dynamically switches between mechanical direct-drive mode (for propulsion efficiency) and electrical power distribution mode (for flexibility and fault tolerance). The power sharing module and electrical machine enable the gas turbine engine to adapt its power output distribution based on operational requirements, resolving the contradiction between efficiency and adaptability.
Solution Approach 2:
The electrical machine acts as an intermediary between the gas turbine engine and the propulsor. It can operate in motor mode to provide electrical propulsion or in generator mode to convert mechanical energy to electrical energy, enabling flexible power distribution while maintaining the ability to drive the propulsor directly when efficiency is prioritized.
2Reliability
If the system uses complex power distribution controls to handle failures, then reliability is improved, but device complexity increases
Solution Approach 1:
The system automatically detects and responds to component failures through the controller and power sharing module, which continuously monitor system state and reconfigure power distribution without manual intervention. This self-service capability improves reliability while avoiding the need for complex manual override systems.
Solution Approach 2:
The electrical machine serves multiple functions: it can drive the propulsor as a motor, generate electrical energy from the gas turbine engine, and enable flexible power distribution during normal and fault conditions. This multi-functionality improves reliability across various operational scenarios without requiring separate dedicated systems for each function.
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 peak efficiency, reduced noise levels, and safe operation by allowing flexible power distribution and rapid adaptation to component failures, enhancing the vehicle's ability to transition between flight modes.
Implementation Method 1
A combustor may add fuel to the compressed fluid and combust the fuel/fluid combination
Implementation Method 2
an electrical machine configured to generate, for output via the one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine
Implementation Method 3
each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses
Data Source
AI summary
An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.