Solar Cell Module for UAV Fuselage Vertical Mounting
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Solution Overview
Problem
Conventional unmanned aerial vehicles (UAVs), especially rotorcraft designs, face challenges in powering long-term flights due to limited battery life and lack of suitable placement for solar cells, which interfere with air flow or have no horizontal surface for solar panel arrangement.
Innovation Solution
A solar cell module comprising a carrier base with solar cells attached, optimized for rotorcraft UAVs with a power-to-weight ratio ≥0.1 W/g, weight-to-solar cell module ratio ≥1.5, and surface area-to-weight ratio ≥7 cm2/g, featuring adjustable tilt angles and flexible, foldable designs to minimize air resistance and maximize energy generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If solar cells are arranged on fixed-wing UAV wings, then sufficient power can be generated, but the solar cells interfere with engine air flow and require runways for takeoff and landing
Solution Approach 1:
The patent transitions from horizontal wing-mounted solar cells to vertical fuselage-mounted solar cells. This dimensional change allows the solar cells to be positioned where they do not interfere with engine air flow while still capturing sufficient sunlight for power generation. The vertical arrangement on the fuselage represents a spatial reconfiguration that resolves the conflict between power generation and aerodynamic performance.
2Duration of action of moving object
If battery capacity is increased to extend flight time, then longer flight duration is achieved, but the weight of the UAV increases significantly
Solution Approach 1:
The patent implements a hybrid power system where solar cells mounted on the fuselage serve as a self-sufficient power source that continuously generates electricity during flight. This self-service mechanism reduces dependence on battery capacity, allowing extended flight times without proportionally increasing battery weight. The solar power supplementation enables the system to maintain longer operational duration while keeping the overall weight increase minimal.
3Power
If solar cells are mounted on rotorcraft UAVs, then power generation is achieved, but the solar cells increase air resistance and lack proper mounting surface
Solution Approach 1:
The patent positions solar cells vertically on the fuselage rather than horizontally on wings or rotor blades. This vertical orientation presents a streamlined profile that minimizes air resistance while still providing adequate surface area for solar cell mounting and power generation. The fuselage mounting location offers both structural support and aerodynamic efficiency.
Solution Approach 2:
The patent optimizes the tilt angle of solar cells to balance two competing requirements: maximizing sunlight absorption for power generation while minimizing air resistance. By adjusting the inclination angle parameter, the system achieves an optimal compromise between energy capture efficiency and aerodynamic drag reduction.
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
Enables UAVs to fly for extended periods with sufficient electricity, maintaining balance and control while reducing weight and air resistance, and includes a backup battery system for varying sunlight conditions.
Implementation Method 1
The solar cell unit comprises a plurality of solar cells attached to the carrier base
Implementation Method 2
The heavier-than-air unmanned aerial vehicles can push air or gas downwards so that a reaction occurs to push the aircraft upwards
Data Source
AI summary
A solar cell module for an unmanned aerial vehicle is disclosed. The solar cell module includes a carrier base and a solar cell unit. The carrier base is disposed on the unmanned aerial vehicle. The solar cell unit has a plurality of solar cells attached to the carrier body. A ratio of the power provided by the solar cell unit to the weight of the solar cell module is equal to or greater than 0.1 (W/g).