Coaxial Dual-Rotor UAV Layout Using Battery Offset Flight Control
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Solution Overview
Problem
Current aircraft with coaxial dual-rotor power systems have complex structures, poor impact resistance, and low reliability due to their four-axis or six-axis symmetrical layouts, which complicate flight operations and increase the number of motors and electronic speed controllers.
Innovation Solution
A centrally arranged coaxial multi-rotor power system with a single-axis dual-rotor design, utilizing counterweight blocks and center-of-gravity offset arrangements driven by electric actuators to control flight attitudes, reducing the number of motors and electronic speed controllers, and achieving stable flight through battery offset.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a four-axis or six-axis symmetrical layout is adopted for coaxial dual-rotor aircraft, then flight operations can be achieved, but the structure becomes complex, impact resistance deteriorates, and reliability decreases
Solution Approach 1:
The patent extracts and eliminates unnecessary axes from the traditional four-axis or six-axis symmetrical layout, retaining only the essential single-axis dual-rotor configuration. This extraction of redundant components simplifies the overall structure while maintaining flight capability through the coaxial arrangement of two rotors on a single axis.
Solution Approach 2:
The patent merges the control functions of multiple axes into a single-axis system. By combining the rotational control into one axis with dual rotors, the system achieves flight operations with fewer components, thereby reducing structural complexity while preserving operational effectiveness.
2Ease of operation
If a four-axis or six-axis symmetrical layout is adopted, then flight control is achieved, but the number of motors and electronic speed controllers increases
Solution Approach 1:
The patent extracts and removes redundant motors and electronic speed controllers from the traditional multi-axis configuration. By taking out the unnecessary components associated with four-axis or six-axis layouts, the system achieves flight control with only two motors and corresponding controllers, significantly reducing the quantity of components.
Solution Approach 2:
The patent applies multi-functionality to the single-axis dual-rotor system, where each motor and electronic speed controller performs multiple control functions that would traditionally require separate components in a four-axis or six-axis system. This universalization reduces the total number of components needed for flight control.
3Device complexity
If a single-axis dual-rotor design is adopted with counterweight offset, then structure is simplified and reliability improved, but flight control complexity increases due to center-of-gravity manipulation
Solution Approach 1:
The patent introduces counterweight blocks that can be offset from the center of gravity to manipulate the overall center of gravity position. This counterweight mechanism simplifies the structural design by replacing complex multi-axis motor control with a simpler mass distribution approach, while the flight control complexity is managed through the predictable gravitational effects of the counterweight arrangement.
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 simplified design results in a more reliable and efficient aircraft with fewer parts, allowing both motors to operate at rated power simultaneously, enhancing flight stability and reducing energy consumption, with a 27% higher maximum take-off weight capacity compared to four-axis symmetrical designs.
Implementation Method 1
counterweight blocks respectively to make an eccentric displacement, thereby shifting a center of gravity of the aerial vehicle and causing the entire aerial vehicle to deflect accordingly
Implementation Method 2
During ascent, the lift force is greater than the takeoff weight; during hovering, the lift equals the takeoff weight
Implementation Method 3
It only requires an electric actuator to control the displacement of the counterweight, changing the center of gravity of the counterweight
Data Source
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AI summary
An aerial vehicle, comprising a centrally-arranged coaxial multi-rotor power system, a chassis support assembly supporting the coaxial multi-rotor power system, counterweight blocks (100) arranged at the lower part of the chassis support assembly, and offset gravity center devices. The offset gravity center devices drive the counterweight blocks (100) to eccentrically shift, thereby shifting the center of gravity of the aerial vehicle and deflecting the whole aerial vehicle accordingly. The counterweight blocks are batteries (100), the batteries (100) and the offset gravity center devices being distributed centrally symmetrically about the axis of a rotor shaft. By adjusting positions of the batteries, the aerial vehicle is upright or inclined in the air. The aerial vehicle exhibits good anti-collision performance and saves electric energy.