Multicopter Gas Turbine Engine Control for Power Efficiency
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Solution Overview
Problem
Existing aircraft propulsion systems lack sufficient improvement in power generation efficiency, particularly in multicopter systems where energy management during flight states like takeoff, cruising, and landing is inefficient.
Innovation Solution
A multicopter aircraft propulsion system that incorporates gas turbine engines (GTs) and a control device to optimize power generation efficiency by operating GTs within a defined efficient operating range, adjusting output based on flight states, and supplementing power from batteries when necessary, ensuring efficient energy use and stable flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If gas turbine engines operate at high power output to ensure sufficient power during flight states, then power availability is improved, but power generation efficiency deteriorates
Solution Approach 1:
The system dynamically adjusts the operating state of gas turbine engines based on real-time flight conditions. During takeoff and high-power phases, engines operate at high output; during cruising and low-power phases, engines operate at efficient operating points. This dynamic adaptation resolves the contradiction between power availability and efficiency by matching engine output to actual demand.
Solution Approach 2:
The control device changes operating parameters of the gas turbine engines based on flight states. It adjusts throttle position, fuel injection rate, and other parameters to optimize the balance between power output and thermal efficiency. This parameter optimization allows the system to achieve both sufficient power and improved efficiency under different operating conditions.
2Power
If gas turbine engines operate continuously to maintain power output, then power availability is improved, but energy consumption increases
Solution Approach 1:
The system implements periodic cycling of the gas turbine engines based on flight phases. Engines are activated during high-power需求的 phases (takeoff, climb, maneuvering) and reduced or shut down during low-power phases (cruising, gliding). This periodic operation pattern maintains power availability when needed while minimizing energy consumption during extended flight periods.
Solution Approach 2:
The propulsion system integrates energy recovery mechanisms where the gas turbine engines can operate as generators during efficient operating conditions to recharge battery systems. This self-service approach allows the system to replenish energy storage during efficient operation, effectively reducing net energy consumption while maintaining power output capability.
3Reliability
If multiple gas turbine engines operate simultaneously to provide redundant power, then reliability is improved, but power generation efficiency deteriorates
Solution Approach 1:
The propulsion system is segmented into multiple independent gas turbine engine units, each capable of operating independently. The control device intelligently distributes flight phases among these segments, allowing one engine to operate efficiently while another provides standby capability or operates at reduced power. This segmentation enables reliability through redundancy while maintaining efficiency by not requiring all segments to operate at full capacity simultaneously.
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
Improves power generation efficiency by optimizing GT operation within specific ranges, ensuring sufficient power during flight states and maintaining battery charge levels, thereby enhancing overall flight performance and energy management.
Implementation Method 1
a plurality of gas turbine engines (GTs) 60-1 and 60-2
Data Source
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AI summary
An aircraft propulsion system capable of improving power generation efficiency is provided. When a flight state of an aircraft (10) is a first state after a plurality of engines (60-1, 60-2) operate and the aircraft takes off, the aircraft propulsion system causes at least one engine among the plurality of engines (60-1, 60-2) to be stopped, causes another engine, which has not been stopped, to be operated in an operating range in which the other engine is able to operate efficiently, and causes a generator corresponding to the other engine to output power.