Hybrid Aircraft Propulsion with Generator-Fed Electric Thrust
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Solution Overview
Problem
Existing flying devices face challenges in efficiently managing energy flows for long-distance transportation of heavy payloads without the need for large batteries, leading to increased weight and complexity, and struggle with responsiveness and maneuverability due to the use of combustion engines and electric motors.
Innovation Solution
A hybrid propulsion system combining combustion engines and electric motors, where the electric motors are powered directly by generators coupled to the combustion engines, allowing for optimized energy management without large batteries, enhancing responsiveness and maneuverability by controlling thrust vectors and energy transfer through circuits with converters and storage elements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a battery is dimensioned to carry out all flight manoeuvres with a safety minimum, then the battery provides sufficient energy for maneuvers, but the battery size and weight increase excessively
Solution Approach 1:
The energy storage system is segmented into two distinct components: a compact battery for maneuvering energy and a fuel tank for cruise energy. This segmentation allows each component to be optimized independently - the battery can be small since it only needs to handle maneuvers, while the fuel tank provides additional range without impacting maneuverability or adding excessive weight to the critical battery system.
2Ease of operation
If electric motors are used for flexibility and responsiveness, then maneuverability improves, but the requirement for large batteries increases weight and complexity
Solution Approach 1:
The propulsion system is segmented into two independent powertrain systems: electric motors for maneuvering and combustion engines for cruise flight. This segmentation allows the electric motors to maintain flexibility and responsiveness without requiring a large, complex battery system, since the battery only needs to provide power for maneuvers rather than entire flight sequences.
3Use of energy by moving object
If combustion engines are used for long-distance travel with heavy payloads, then fuel efficiency improves, but responsiveness and maneuverability decrease
Solution Approach 1:
The flight operations are segmented into two distinct phases with dedicated propulsion systems: electric motor operation for maneuvering phases requiring responsiveness, and combustion engine operation for cruise phases requiring fuel efficiency. This temporal and functional segmentation allows the system to optimize for the dominant requirement of each phase without compromise.
Solution Approach 2:
The system dynamically transitions between two propulsion modes based on flight phase requirements. The hybrid architecture enables smooth switching between electric and combustion power sources, allowing the vehicle to adapt its propulsion characteristics to match the instantaneous operational needs - whether prioritizing rapid response or fuel-efficient sustained flight.
4Ease of operation
If thrust vectors are placed on either side of the main body for attitude control, then maneuverability improves, but the mechanical complexity of the propulsion system increases
Solution Approach 1:
The attitude control system is segmented into independent thrust vector control for each propulsion unit. Each motor (electric or combustion) can independently adjust its thrust magnitude and direction, providing six-degree-of-freedom control capability. This segmented control architecture simplifies the mechanical design compared to complex linkage systems, as each unit operates independently while collectively providing full attitude control.
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
The system improves the responsiveness and maneuverability of flying devices by directly powering electric motors with generators, reducing the need for large batteries and optimizing energy distribution, enabling efficient long-distance transportation of heavy payloads.
Implementation Method 1
The first electric generator is mechanically coupled to the first combustion engine in order to be driven by the latter
Implementation Method 2
a first electric motor arranged to create a first thrust vector
Implementation Method 3
a first combustion engine and a first electric motor fixed to a main body of the flying device
Data Source
AI summary
A flying device includes a main body, to which a combustion engine, an electric motor, an electricity generator and an electrical energy transfer circuit are attached. The combustion engine and electric motor are arranged to create thrust vectors and are placed on either side of the main body in order to create thrust vectors on each side of a plane of separation of said body. The electricity generator is mechanically coupled to the combustion engine in order to be driven thereby. The electrical energy transfer circuit is connected between the electricity generator and the electric motor, the energy transfer circuit being configured to create mechanical resistance that slows the combustion engine and to produce electrical energy in order to power the electric motor.