Hybrid-Electric Aircraft Drive With Tandem Twin-Cylinder Range Extension
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Solution Overview
Problem
Current electric aircraft have limited range due to low power density in battery technology and high space requirements, making them less efficient and less climate-friendly.
Innovation Solution
A hybrid-electric drive system incorporating a two-cylinder reciprocating-piston engine to generate electrical energy, with multiple generators and batteries connected in parallel for redundancy, allowing for extended flight duration and safe landing capabilities, while reducing weight and emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If battery technology with low power density is used in electric aircraft, then the aircraft can be operated emission-free, but the range is limited and space requirement on the ground is high
Solution Approach 1:
The drive system is segmented into multiple independent power sources: a combustion engine for generating electrical energy, multiple drive batteries for energy storage, and multiple electric motors for propulsion. This segmentation allows the combustion engine to extend range while batteries provide emission-free operation capability, resolving the contradiction between emissions and range.
Solution Approach 2:
The patent merges a combustion engine with an electrical drive system to create a hybrid configuration. The combustion engine generates electrical energy that charges batteries and directly powers electric motors, combining the high energy density of fossil fuels with the emission-free operation and high efficiency of electric drives, thereby extending range without sacrificing environmental benefits.
2Reliability
If multiple drive batteries and electric motors are connected in parallel for redundancy, then operational safety is improved, but device complexity increases
Solution Approach 1:
The drive system is divided into multiple independent, identical modules (drive batteries and electric motors). Each module can operate independently, and the system maintains functionality even if one module fails. This modular segmentation provides redundancy without requiring complex interconnections or control systems, as each module is a self-contained unit.
Solution Approach 2:
Each drive battery and electric motor is designed as an independent unit with its own control and connection to the combustion engine's electrical output. This local independence allows any single unit to fail without affecting the others, providing operational safety through simplicity rather than complex redundancy management.
3Duration of action of moving object
If a two-cylinder reciprocating-piston engine is used to generate electrical energy, then range is extended, but weight increases
Solution Approach 1:
The patent replaces a direct mechanical drive system with an electrical generation system. Instead of using the combustion engine to mechanically drive the aircraft, the engine generates electrical energy that is stored in batteries and used to power electric motors. This substitution allows for a lighter overall system architecture while extending range through the high energy density of the combustion engine.
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 hybrid-electric drive system increases the range and efficiency of electric aircraft, ensures safe operation by maintaining power in case of component failures, and reduces emissions and noise, enhancing climate-friendliness and operational safety.
Implementation Method 1
The power unit comprises a two-cylinder reciprocating-piston engine having two cylinder-piston units in tandem arrangement and comprises at least one generator for generating electrical energy, wherein each cylinder-piston unit has a crankshaft, and the crankshafts of the two cylinder-piston units are mechanically coupled to each other, and wherein at least one crankshaft, in particularly both crankshafts each, is mechanically connected to the at least one generator
Implementation Method 2
the drive system comprises a power unit, at least one drive battery and at least one electric motor, which draws electrical energy from the drive battery
Data Source
AI summary
The invention relates to an aircraft comprising a drive system having a power unit, at least one drive battery, and at least one electric motor drawing electrical energy from the at least one drive battery, wherein the power unit comprises a two-cylinder reciprocating-piston engine having two cylinder-piston units in tandem arrangement and comprises at least one generator for generating electrical energy, wherein each cylinder-piston unit has a crankshaft, and wherein the crankshafts are mechanically coupled to each other, and wherein at least one crankshaft is mechanically connected to the at least one generator. The invention also relates to additional improvements of the aircraft and to an operating method.