Segmented Solar Wing Dihedral Control for High-Altitude UAVs
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Solution Overview
Problem
Solar powered aircraft face challenges in achieving long duration flights at high altitudes and latitudes due to fragile structures, limited energy collection at low sun angles, and high power requirements, which restrict their operational viability and safety record.
Innovation Solution
A rigid, molded solar powered aircraft with a segmented wing capable of adjusting dihedral angles, utilizing hinges to orient photovoltaic cells towards the horizon for efficient energy collection, and incorporating a controller for autonomous flight to minimize active control surface usage, ensuring robustness and reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If extremely flexible structures are used to achieve low weight and high altitude, then aircraft weight is reduced and altitude record is improved, but structural strength and reliability deteriorate
Solution Approach 1:
The aircraft structure is divided into multiple rigid segments (wing sections, fuselage modules) that can be assembled in space. Each segment maintains structural integrity while the overall configuration allows for reduced weight compared to a fully rigid structure of equivalent span.
Solution Approach 2:
The patent employs composite materials combining rigid structural elements with lightweight materials to achieve optimal strength-to-weight ratio. The rigid portions provide necessary structural strength while minimizing overall weight through advanced material composition.
2Use of energy by moving object
If solar cells are oriented perpendicular to wing surface for maximum power collection, then energy collection efficiency is improved, but performance at low sun angles deteriorates
Solution Approach 1:
The solar cell panels are mounted on adjustable supports that allow them to dynamically change orientation relative to the wing surface. This enables the solar cells to track the sun's position and maintain optimal angle of incidence throughout the day and across different latitudes, resolving the contradiction between fixed perpendicular mounting and adaptability to varying sun angles.
Solution Approach 2:
The solar array system serves multiple functions: it generates electrical power while also acting as a controllable surface that can adjust its orientation. The universal design allows the same structure to optimize energy collection across diverse operational conditions including different latitudes, times of day, and seasonal variations.
3Stability of the object's composition
If active control surfaces are used frequently for flight control, then flight stability is improved, but mechanical wear and reliability deteriorate
Solution Approach 1:
The aircraft is designed with inherent aerodynamic stability features that allow it to maintain stable flight without continuous active control input. The control surfaces are sized and positioned to provide sufficient stability margin, enabling the aircraft to self-correct minor deviations and reducing the frequency and intensity of actuator operations, thereby minimizing mechanical wear.
Solution Approach 2:
The control system is designed to apply control authority beyond what is minimally required for stability. This excessive control capability ensures that the aircraft maintains robust stability margins while allowing the actuators to operate less frequently, as the system can rely on aerodynamic damping and stability features for routine corrections.
4Area of stationary object
If aircraft fly at high altitude for large coverage area, then communications coverage is improved, but power requirements increase
Solution Approach 1:
The aircraft employs multiple distributed propulsors along the wingspan rather than a single large propulsion system. This segmentation allows for efficient power distribution and reduces the power required per unit of thrust, enabling high-altitude flight with reduced overall power consumption while maintaining the large wing area needed for communications coverage.
Solution Approach 2:
The aircraft utilizes variable speed propulsion and adjustable propeller pitch to optimize power consumption across different flight conditions. By dynamically changing operational parameters such as propeller blade angle and rotational speed, the system minimizes power requirements while maintaining the altitude and speed necessary for effective communications coverage.
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 continuous flight durations of 2 months to 5 years at altitudes over 50,000 feet and latitudes between 40° N and 30° S, providing robust and efficient solar energy collection and stable flight operations, even in inclement weather.
Implementation Method 1
The wing segments are joined by hinges adjustable to positive and negative dihedral angles during flight to orient photovoltaic cells towards the horizon
Data Source
AI summary
Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.