Performance-Ratio Thrust Allocation in Parallel Hybrid Aircraft
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Solution Overview
Problem
Optimized utilization of battery and fuel energy in parallel hybrid aircraft is challenging due to the complexity of battery capacity and varying thrust requirements during different flight phases, making real-time cost-effective operation difficult.
Innovation Solution
A system and method to determine and control motor and engine thrust using a performance thrust ratio, calculated based on user input, sensor information, aerodynamic, and battery models, to balance fuel and battery consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the total propulsion capability is sized for take-off and initial climb requirements, then the aircraft can meet maximum thrust demands, but the cruise and landing segments consume unnecessary fuel and battery charge
Solution Approach 1:
The patent implements dynamic thrust allocation that continuously adjusts the ratio of motor thrust to engine thrust based on real-time flight conditions. During take-off and initial climb, the system provides maximum combined thrust, but during cruise and landing segments, it dynamically reduces the thrust contribution from each source according to actual performance requirements, thereby avoiding energy waste while maintaining the capability to meet peak demands when needed
Solution Approach 2:
The system changes operational parameters by varying the thrust contribution ratio between the electric motor and combustion engine across different flight phases. The control system monitors flight conditions and adjusts the thrust allocation parameters in real-time, optimizing the energy mix to match the actual propulsion needs at each moment rather than maintaining a fixed capability ratio
2Use of energy by moving object
If the battery capacity is maximized to use entire capacity over the flight course, then electricity consumption increases, but fuel consumption decreases, creating complexity in real-time optimization
Solution Approach 1:
The patent employs a feedback control system that continuously monitors flight conditions, battery state of charge, and thrust requirements. Based on this feedback, the system dynamically adjusts the thrust allocation between motor and engine to optimize energy utilization. The feedback loop enables real-time decision-making about whether to use electric or fuel power, simplifying the control complexity by using sensor data and predefined optimization algorithms rather than requiring complex manual calculations
Solution Approach 2:
The system performs preliminary optimization by pre-calculating or pre-planning the optimal thrust allocation strategy based on known flight parameters and battery characteristics. This preliminary action allows the control system to anticipate energy requirements and adjust thrust mix proactively rather than reactively, reducing real-time computational complexity while maximizing electricity utilization throughout the flight
3Loss of energy
If motor thrust is increased during cruise segments, then electricity consumption increases, but overall flight cost decreases due to lower fuel costs
Solution Approach 1:
The system exploits parameter changes by varying the thrust allocation ratio between electric motor and combustion engine according to flight phase and energy cost considerations. During cruise segments where electricity is more cost-effective, the system increases motor thrust contribution and decreases engine thrust contribution, effectively using electricity to replace fuel consumption when economically advantageous
Data Source
AI summary
A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft. One or more sensors may be configured to monitor one or more flight parameters to generate sensor information. User input including one or more pilot estimates may be received. The sensor information may be obtained. A performance thrust ratio may be calculated based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model. The performance thrust ratio may be used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight. A first thrust setting for the motor and/or a second thrust setting for the engine may be determined based on the performance thrust ratio.