Hybrid Rotor Power Split for Long-Endurance UAV Orientation Control
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Solution Overview
Problem
Autonomous flying devices face challenges in achieving a large payload and long continuous flight time due to energy efficiency limitations in battery-driven and series type configurations, and difficulty in stable orientation control in hybrid devices.
Innovation Solution
An engine-mounted autonomous flying device with a main rotor for thrust, a sub rotor for orientation control, and an arithmetic control device to adjust output distribution, utilizing an engine for main rotor rotation and electric power for sub rotor rotation, with a belt connection and a capacitor for energy storage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If a series type autonomous flying device uses an engine to generate electric power for rotors, then continuous flight time and payload are improved, but energy efficiency deteriorates due to energy loss in generators and power conditioners
Solution Approach 1:
The patent divides the autonomous flying device into two independent propulsion systems: a main rotor driven directly by the engine and sub rotors driven by electric motors. This segmentation allows the main rotor to provide efficient direct mechanical power transmission for sustained flight, while sub rotors handle orientation control with electric power, resolving the contradiction between continuous flight time and energy efficiency.
Solution Approach 2:
The engine serves multiple functions: it directly drives the main rotor for thrust and simultaneously drives generators to produce electric power for sub rotors and other systems. This multi-functionality allows the system to achieve long continuous flight time while maintaining reasonable energy efficiency by avoiding complete energy conversion through generators for all functions.
2Productivity
If a hybrid autonomous flying device enhances operation efficiency, then productivity is improved, but orientation control stability deteriorates
Solution Approach 1:
The patent implements dynamic output distribution control where the arithmetic control device adjusts the power distribution between the main rotor and sub rotors based on flight conditions. During orientation control, the system dynamically increases sub rotor output to maintain stability, while during normal operation it optimizes for efficiency, thus resolving the contradiction between productivity and orientation control stability.
3Ease of operation
If the sub rotor output is increased for orientation control, then ease of operation is improved, but energy consumption increases
Solution Approach 1:
The patent changes the operational parameters of the sub rotors dynamically based on flight phase. The arithmetic control device adjusts sub rotor output distribution ratio upward during orientation control maneuvers to improve ease of operation, and reduces it during steady-state flight to minimize energy consumption, thus resolving the contradiction between ease of operation and energy consumption.
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 device achieves increased payload and long flight time with stable orientation control by optimizing energy distribution and reducing energy loss, while minimizing weight and vibration through a belt-driven system and balanced piston configuration.
Implementation Method 1
an engine 30 that generates energy for rotating the main rotor 14 and the sub rotor 15
Implementation Method 2
the sub rotor 15 is rotated by a motor 21 driven by electric power generated from a generator 16 operated by the engine 30
Implementation Method 3
the sub rotor 15 is rotated by a motor 21 driven by electric power generated from a generator 16 operated by the engine 30
Implementation Method 4
the main rotor 14 is rotated by being drivingly connected to the engine 30
Data Source
AI summary
An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.