Hybrid UAV Propulsion System for Extended Flight and Low Signatures
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Solution Overview
Problem
Current UAV propulsion systems face limitations in energy efficiency and operational versatility, particularly for larger UAVs, with purely electric propulsion being unsuitable for high power and long flight durations, and existing internal combustion engines generating significant thermal and acoustic signatures.
Innovation Solution
A hybrid propulsion system combining a diesel or kerosene internal combustion engine with an electric motor and energy storage, utilizing a charger device that leverages exhaust gas energy for charging and features a controller to manage power based on flight parameters, allowing for efficient and versatile operation across various altitudes and power requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If purely electric propulsion is used for UAVs, then thermal and acoustic signatures are reduced, but flight duration and power output are limited
Solution Approach 1:
The patent combines an internal combustion engine and an electric motor into a hybrid propulsion system. The internal combustion engine provides sustained power for extended flight durations, while the electric motor can operate independently to reduce thermal and acoustic signatures when stealth is required. This merging of two propulsion systems allows the UAV to achieve both long flight duration and reduced detectability depending on operational requirements.
Solution Approach 2:
The hybrid propulsion system dynamically switches between different operating modes: pure internal combustion engine mode for maximum power and duration, pure electric motor mode for reduced signatures, and combined mode for optimized performance. This dynamic adaptability allows the system to optimize between flight duration and signature reduction based on real-time operational needs.
2Power
If internal combustion engines are used for larger UAVs, then power output and flight duration are sufficient, but thermal and acoustic signatures increase
Solution Approach 1:
The propulsion system is segmented into two independent power sources: an internal combustion engine for high power output requirements and an electric motor for low-signature operation. This segmentation allows the system to divide operational requirements between the two sources, using the internal combustion engine only when high power is needed and switching to electric motor when reduced signatures are required.
Solution Approach 2:
The hybrid system employs periodic switching between different propulsion modes based on operational requirements. The controller periodically evaluates flight conditions, power demands, and signature concerns to determine whether to operate the internal combustion engine, electric motor, or both together, creating a rhythmic pattern of mode transitions that optimizes both power output and signature management.
3Adaptability or versatility
If hybrid propulsion with multiple chargers is used, then energy efficiency and operational versatility are improved, but device complexity increases
Solution Approach 1:
The hybrid propulsion system is designed with multi-functionality to handle diverse operational requirements. The controller can manage multiple charging modes (exhaust gas-driven, mechanical, electrical), switch between different propulsion modes, and adapt to various flight conditions. This universal design allows a single system to perform multiple functions that would otherwise require separate systems, justifying the increased complexity through enhanced versatility.
Solution Approach 2:
The system incorporates self-service capabilities through the controller that automatically manages the complex interactions between the internal combustion engine, electric motor, and multiple chargers. The controller monitors system state and autonomously determines optimal operating modes, charge management strategies, and power distribution, reducing the need for manual intervention and simplifying operation despite the underlying system complexity.
Data Source
AI summary
An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.