Hybrid Aircraft Power Switching for One-Fail-Safe Propulsion
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Solution Overview
Problem
Current electrically-propelled vertical take-off and landing aircrafts face challenges in achieving a one-fail-safe solution while maintaining reasonable costs, as existing solutions require redundant systems that increase weight and reduce flight capacity, and previous energy management and power generation approaches do not fully satisfy the redundancy requirements.
Innovation Solution
A hybrid power source system with two horizontal drive thrusters, four pairs of vertical take-off/landing rotors, and four power sources, where each vertical drive unit can connect to a horizontal drive unit via a switch, and power generation sources can recharge batteries, ensuring passive control and complementary power supply based on flight requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant systems are implemented to achieve one-fail-safe operations, then reliability is improved, but weight increases and flight capacity is reduced
Solution Approach 1:
The power generation source is designed to serve multiple functions: it can power horizontal thrusters during cruise flight, recharge battery packs when excess power is available, and provide backup power if a battery fails. This multi-functionality eliminates the need for dedicated redundant battery systems while maintaining one-fail-safe capability.
Solution Approach 2:
The system enables self-service through automatic power management where the power generation source automatically recharges battery packs during flight when power demand is low, and automatically switches to battery power or direct power generation when a failure occurs. This self-regulating system maintains reliability without requiring additional active redundancy components.
2Reliability
If redundant systems are implemented to achieve one-fail-safe operations, then reliability is improved, but device complexity increases
Solution Approach 1:
The power generation source serves as a universal power supply that can directly power horizontal thrusters, recharge battery packs, or provide backup power for vertical rotors. This consolidates multiple potential redundant systems into a single multi-functional unit, reducing overall system complexity while maintaining one-fail-safe operations.
Solution Approach 2:
The invention merges the functions of primary power supply, backup power supply, and energy storage management into an integrated hybrid power system. The power generation source, battery packs, and control system work as a unified ensemble, simplifying the architecture compared to separate redundant systems.
3Duration of action of moving object
If power generation sources are used to power horizontal thrusters, then range and endurance are improved, but reliability is insufficient for one-fail-safe operations
Solution Approach 1:
The system implements beforehand cushioning by maintaining charged battery packs that can immediately take over power supply if the power generation source or its connection fails. The battery packs are kept as a pre-charged backup ready to compensate for any failure, ensuring one-fail-safe operations while allowing the power generation source to extend endurance during normal operation.
Solution Approach 2:
The battery packs serve as an intermediary energy buffer between the power generation source and the motors. They decouple the power generation from power consumption, allowing the system to maintain reliable backup power while extending endurance through efficient energy management during cruise flight.
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
This architecture provides redundancy for one-fail-safe operations while optimizing element sizing, minimizing additional costs, and allowing batteries to act as energy buffers, ensuring continuous flight and efficient power management.
Implementation Method 1
at least two power generation sources, each connected on the one hand to each of the power supply buses by a respective input of the corresponding vertical drive unit
Implementation Method 2
at least four pairs of vertical take-off/landing rotors each powered by a respective electric motor, and at least two horizontal drive units each comprising a respective electric motor
Implementation Method 3
the power sources supplying electricity according to the difference between the power requirements of the vertical drive units and/or of the horizontal drive units and the power emitted by the power generation sources
Data Source
AI summary
An aircraft having a hybrid power source includes two horizontal drive units, four vertical drive units, a vertical drive unit comprising a power supply bus the output of which may be connected to a single horizontal drive unit which may be connected to at least two vertical drive units via a switch, two power generation sources connected, on the one hand, to each of the power supply buses by a respective input of the corresponding vertical drive unit and, on the other hand, to each horizontal drive unit via the respective output of each vertical drive unit, and a power supply command arranged to send a power command to the power generation sources according to the power requirements of the vertical drive units and/or horizontal drive units. The power generation sources are also suitable for recharging power sources of the vertical drive units.