UAV Rotor Layout Balancing Motor Cooling and Flight Drag
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Solution Overview
Problem
Fixed-wing aerial vehicles face limitations in use environments due to the need for runways and special takeoff/landing methods, and exposed motors cause flight resistance and heat dissipation issues during horizontal flight.
Innovation Solution
An unmanned aerial vehicle design with dual spiral power systems and rotor assemblies, partially exposing motors within accommodating cavities for heat dissipation and reducing flight resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If motors are completely exposed outside the body for heat dissipation, then heat dissipation effect is improved, but flight resistance increases during horizontal flight
Solution Approach 1:
The patent applies local quality by making different parts of the motor have different exposure levels. Specifically, the stator is partially exposed outside the body while the rotor remains inside, creating zones with different thermal and aerodynamic characteristics. This allows the exposed stator to dissipate heat effectively while minimizing the overall aerodynamic drag compared to complete exposure.
Solution Approach 2:
The patent implements nesting by placing the rotor inside the stator structure. The rotor is positioned within the accommodating cavity while the stator extends partially outside. This nested arrangement allows compact integration of motor components while optimizing the balance between heat dissipation surface area and aerodynamic profile during horizontal flight.
2Object-affected harmful factors
If motors are completely enclosed in the body for streamlined shape, then flight resistance is reduced, but heat dissipation capability deteriorates
Solution Approach 1:
The patent applies local quality by making different parts of the motor have different exposure levels. Specifically, the stator is partially exposed outside the body while the rotor remains inside, creating zones with different thermal and aerodynamic characteristics. This allows the exposed stator to dissipate heat effectively while minimizing the overall aerodynamic drag compared to complete exposure.
3Adaptability or versatility
If all rotor assemblies are mounted on wings for vertical lift, then vertical takeoff and landing capability is improved, but structural complexity increases
Solution Approach 1:
The patent applies universality by designing rotor assemblies that serve multiple functions. The first and second rotor assemblies mounted on the wings provide both vertical lift during takeoff and landing, and contribute to horizontal thrust during forward flight. This multi-functionality reduces the need for separate dedicated vertical lift mechanisms, thereby simplifying the overall structure while maintaining versatility.
Solution Approach 2:
The patent implements merging by integrating the vertical lift rotor assemblies with the wing structure. Instead of having separate vertical lift devices, the rotor assemblies are mounted directly on the wings, combining the functions of the wing support structure and the vertical lift mechanism into a unified system.
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
Improves flight performance by reducing resistance and ensuring effective heat dissipation, enabling efficient vertical takeoff, landing, and horizontal flight.
Implementation Method 1
a third rotor assembly, including a third motor and a third propeller connected to the third motor
Implementation Method 2
the third motor being mounted in the first accommodating cavity and being partially exposed to the body
Implementation Method 3
ensuring effective heat dissipation
Data Source
AI summary
An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.