Engine-Mounted Rotor Layout for Long-Flight 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 systems.
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 the output distribution ratio of the sub rotor, combined with an electric power converter and capacitor for efficient energy management, and a belt-driven connection between the engine and main rotor.
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 through generators and power conditioners
Solution Approach 1:
The patent divides the rotor system into main rotors (directly driven by engine) and sub rotors (independently controlled), allowing separate optimization of energy transmission paths. The main rotors use direct mechanical coupling for high efficiency, while sub rotors handle orientation control with independent motors, resolving the contradiction between continuous flight time and energy efficiency.
Solution Approach 2:
The patent dynamically adjusts the output distribution ratio between main rotors and sub rotors based on operational requirements. During hovering, more power is allocated to main rotors for efficiency, while during orientation control, power distribution shifts to sub rotors, allowing the system to adapt between different operational states and resolve the energy efficiency contradiction.
2Productivity
If a hybrid autonomous flying device enhances operation efficiency, then productivity is improved, but orientation control stability deteriorates
Solution Approach 1:
The patent employs an arithmetic control device that continuously monitors and adjusts the output distribution ratio between main rotors and sub rotors based on real-time operational feedback. This feedback mechanism ensures stable orientation control while maintaining high operation efficiency by dynamically optimizing power distribution according to actual flight conditions.
Solution Approach 2:
The patent changes the output distribution ratio parameter dynamically based on operational mode. By adjusting this parameter, the system optimizes the balance between main rotor thrust and sub rotor orientation control, resolving the contradiction between productivity and orientation stability through parameter optimization.
3Ease of operation
If the output distribution ratio of sub rotor is increased for orientation control, then ease of operation is improved, but energy consumption increases
Solution Approach 1:
The patent applies partial action by allocating power to sub rotors only when needed for orientation control, rather than continuously. The output distribution ratio is adjusted to provide sufficient power for orientation maneuvers while minimizing energy consumption during steady-state flight, 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 a large payload and long continuous flight time with stable orientation control, reducing energy loss and vibration, and enabling precise orientation adjustments.
Implementation Method 1
a sub rotor (15) that controls orientation of the fuselage (19), wherein 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 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 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.