Hybrid Aircraft Power Unit With Thermal Generator-Propeller Coupling
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Solution Overview
Problem
Flight vehicles with hybrid power systems require separate engines for generating power and thrust, leading to increased volume and weight, limiting equipment loading and maneuverability.
Innovation Solution
A power unit integrating an engine, power generator, and thrust generator, allowing selective operation based on temperature, with decoupling and coupling mechanisms via hooks and grooves, enabling a single engine to drive either generator or thrust generator.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate engines are provided for driving the generator and the propeller, then the power generation function and thrust generation function can be independently optimized, but the volume and weight of the flight vehicle increase
Solution Approach 1:
The single engine is designed to perform multiple functions: it can drive the generator to produce electricity, directly drive the propeller to generate thrust, or operate in both modes simultaneously. This multi-functionality eliminates the need for separate engines, reducing overall system volume and weight while maintaining independent optimization of power generation and thrust generation capabilities through selective operational modes
2Reliability
If separate engines are provided for driving the generator and the propeller, then the power generation function and thrust generation function can be independently optimized, but the weight of the flight vehicle increases
Solution Approach 1:
The single engine serves dual purposes by being capable of driving both the generator and the propeller. This eliminates the need for a second dedicated engine, thereby reducing the overall weight of the flight vehicle while maintaining the ability to independently optimize power generation and thrust generation through selective operational configurations
3Reliability
If separate engines are provided for driving the generator and the propeller, then the power generation function and thrust generation function can be independently optimized, but the equipment loading capacity is limited
Solution Approach 1:
The single engine can selectively drive either the generator or the propeller based on operational requirements. This flexibility frees up space and weight capacity that would otherwise be occupied by a second engine, thereby increasing the flight vehicle's equipment loading capacity while maintaining independently optimized power generation and thrust generation functions
4Volume of moving object
If the power generator and thrust generator are integrated, then the volume and weight are reduced, but the system complexity increases due to coupling and decoupling mechanisms
Solution Approach 1:
The power unit is segmented into modular components: the engine, the generator, and the propeller drive are distinct but integrable modules. The coupling and decoupling mechanisms are designed as separate, standardized interfaces that connect these modules, allowing the system to maintain reduced volume through integration while managing complexity through modular design and standardized connection protocols
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
Reduces volume and weight, enhances maneuverability, and optimizes energy use by selectively driving power or thrust generators based on temperature, improving flight vehicle performance.
Implementation Method 1
the hook may include a shape memory alloy
Implementation Method 2
the hook may include a first metal and a second metal that have thermal expansion coefficients different from each other
Data Source
AI summary
A power unit includes an engine including a driving shaft, a power generator provided on the driving shaft and configured to supply electric energy to a flight vehicle, and a thrust generator provided on an outer side of the power generator and configured to provide a propulsion force to the flight vehicle. When a temperature of the power generator is greater than or equal to a first temperature, the power generator and the thrust generator are decoupled from each other, and the power generator is driven by an output of the engine and supplies the electric energy to the flight vehicle. When the temperature of the power generator is less than the first temperature, the power generator and the thrust generator are coupled to each other, and the thrust generator is driven by the output of the engine and provides the propulsion force to the flight vehicle.