Multi-Drive Aircraft Propulsion With Hybrid Engine Backup
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Solution Overview
Problem
Existing aircraft propulsion systems with gas turbine engines and electric motors lack efficient redundancy and power management, leading to potential power loss during engine failures.
Innovation Solution
A propulsion system with integrated electric machines and thermal engines, featuring a clutch and fuse link mechanism, allows for seamless power transfer and backup operation, enabling hybrid power operation and efficient redundancy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional gas turbine engines are used without hybrid electric backup, then the propulsion system is simpler, but the reliability deteriorates due to lack of redundancy during engine failures
Solution Approach 1:
The propulsion system is segmented into independent drive units, each with its own electric machine and thermal engine. This segmentation allows one drive unit to fail while the other continues to provide power, thereby improving reliability without requiring a completely complex integrated system. Each segment can operate independently or in combination with the other.
Solution Approach 2:
The system changes the operational parameters of the drive units based on flight conditions. During normal operation, both thermal engines and electric machines may contribute power. During engine failure, the system transitions to using only the electric machine or the remaining thermal engine, adapting the power configuration to maintain reliability while managing complexity.
2Power
If larger gas turbine engines are used to provide sufficient power, then the power availability is improved, but the weight increases
Solution Approach 1:
The system merges thermal engine power with electric machine power in a hybrid configuration. By combining these two power sources, the aircraft can achieve the necessary total power output without requiring a single oversized thermal engine, thereby reducing the weight of moving objects while maintaining power availability.
Solution Approach 2:
The propulsion system dynamically adjusts the contribution of each power source based on operational requirements. During takeoff and high-power需求的 phases, both thermal engines and electric machines can operate together to provide maximum power. During cruise or lower power phases, the system can rely more on the electric machines or reduce thermal engine operation, optimizing the weight-power balance dynamically.
3Reliability
If redundant backup systems are added to the propulsion system, then the reliability during engine failure is improved, but the device complexity increases
Solution Approach 1:
The electric machines serve multiple functions: they act as motors during normal operation to supplement thermal engine power, and they serve as backup power sources during thermal engine failure. This multi-functionality provides reliability without requiring separate dedicated backup systems, thereby limiting the increase in device complexity.
Solution Approach 2:
The system uses its own electric machines and power storage components to provide backup power during engine failure, rather than requiring external or additional specialized backup systems. The hybrid electric components serve their primary function while also providing redundancy, allowing the system to be self-sufficient and reducing overall complexity.
4Adaptability or versatility
If hybrid electric propulsion with multiple drive units is implemented, then the power management flexibility is improved, but the device complexity increases
Solution Approach 1:
The control system dynamically adjusts the power distribution between multiple drive units based on real-time operational conditions, aircraft performance requirements, and component status. This dynamic control provides flexible power management for various flight phases while using automated control logic to manage the complexity of coordinating multiple independent drive units.
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
Enhances system reliability by providing backup power during engine failures, reduces weight and cost through downsizing engines, and optimizes power distribution for various flight conditions.
Implementation Method 1
an electric machine (54) selectively configurable as an electric motor and/or an electric generator
Implementation Method 2
a thermal engine (56) configured to rotate a rotating assembly (58) within the thermal engine
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A system (20) is provided for an aircraft (22). This aircraft system (20) includes a propulsion system (26), and the propulsion system (26) includes a first thermal engine (56A), a second thermal engine (56B) and a first electric machine (54A). The propulsion system (20) is configured to operate the first thermal engine (56A) and the second thermal engine (56B), without operating the first electric machine (54A), during a first mode of operation to provide aircraft (22) thrust. The propulsion system (26) is configured to operate the first electric machine (54A) and the second thermal engine (56B), without operating the first thermal engine, during a second mode of operation to provide the aircraft thrust.