Dual-Rotor UAV Pivot Arm Structure for Stable Long-Endurance Flight
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Solution Overview
Problem
Traditional dual-rotor unmanned flight systems have complex structures, low transmission efficiency, and short flight durations, making them difficult to assemble and maintain, with limited improvements in flight duration due to battery technology limitations.
Innovation Solution
A dual-rotor unmanned flight system with a lift mechanism featuring rotor assembly arm structures that provide stability through a pivotable rotor assembly, motor base, and servo motor system, allowing for adjustable angles and positions to enhance flight stability and efficiency, along with an obstacle detection and avoidance system for improved navigation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If traditional multi-rotor configurations (4, 6, or 8 rotors) are used, then flight control algorithms and motion forms are simpler, but the size of the unmanned flight system becomes relatively large and power consumption increases
Solution Approach 1:
The patent merges multiple rotor functions into a dual-rotor configuration where each rotor can independently control both lift and thrust vectors through variable pitch angles, eliminating the need for multiple separate rotors while maintaining flight control capability
Solution Approach 2:
The patent employs dynamic pitch angle adjustment of rotor blades during flight, allowing the same dual-rotor structure to perform multiple functions (vertical flight, horizontal flight, attitude control) that would traditionally require different rotor configurations
2Use of energy by moving object
If larger rotors are used to achieve the same lifting power, then power consumption is reduced and efficiency is improved, but the overall structure becomes more complex
Solution Approach 1:
The patent segments the rotor assembly into independently controllable modules with variable pitch mechanisms, allowing each rotor to be optimized for efficiency while maintaining structural modularity that simplifies assembly
Solution Approach 2:
The dual-rotor design with variable pitch capability makes each rotor universally functional, capable of providing both vertical lift and horizontal thrust, eliminating the need for specialized rotor configurations for different flight modes
3Productivity
If existing dual-rotor configurations are used, then flight efficiency is improved, but the structure becomes complicated and assembly becomes troublesome
Solution Approach 1:
The patent employs pre-assembled rotor modules with integrated pitch control mechanisms that can be installed as complete units, reducing on-site assembly complexity while maintaining the high-performance dual-rotor configuration
Solution Approach 2:
The patent uses adjustable pitch angles as a key parameter to achieve different flight modes and performance characteristics without changing the physical structure, allowing a single simplified configuration to replace multiple complex fixed-configuration designs
4Productivity
If existing dual-rotor configurations are used, then flight efficiency is improved, but transmission efficiency remains relatively low and flight duration cannot be effectively extended
Solution Approach 1:
The patent optimizes the transmission system to minimize energy losses and maintain continuous efficient power delivery to the rotors, ensuring that battery energy is converted to lift and thrust with maximum efficiency throughout the entire flight duration
Solution Approach 2:
The patent converts the limitation of fixed battery capacity into an advantage by optimizing the entire power transmission chain to minimize waste, thereby extracting maximum flight duration from the available energy supply
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 achieves faster horizontal flight speeds, longer flight times, simpler assembly, and improved maintenance, while maintaining vertical takeoff and landing capabilities, and enhances flight stability and navigation through advanced control systems.
Implementation Method 1
the rotor assembly arm structure can provide a moment to overcome the tilting of the unmanned flight system, thereby improving the flight stability
Data Source
AI summary
The present disclosure provides an unmanned flight system and a control system for an unmanned flight system. The unmanned flight system comprises: a body and a lift mechanism connected to the body, wherein the lift mechanism includes two rotor assembly arm structures respectively provided on two sides of the body, wherein each of the rotor assembly arm structures respectively includes: an arm, a pivotable rotor assembly, a motor for driving the rotor assembly to pivot about a pivot axis, and a motor base for mounting the motor, wherein one end of the arm is pivotally connected to one side of the body, the motor base is pivotally provided on the other end of the arm, and a rotational axis of the motor base is higher than a center of gravity of the unmanned flight system. The unmanned flight system according to the present disclosure can achieve a longer flight time, a simple rotor assembly structure, and easier overall assembly and maintenance.