Solar Aircraft Variable Geometry Wing Optimization
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Solution Overview
Problem
Solar powered aircraft face challenges in achieving long duration flights at high altitudes and high latitudes due to limitations in energy collection at low sun angles, structural fragility, and increased power requirements, which hinder their viability as a replacement for satellites in telecommunications networks.
Innovation Solution
A solar powered aircraft with a rigid, molded construction and segmented wing that adjusts dihedral angles to optimize photovoltaic cell orientation towards the horizon, combined with a robust airframe and energy storage devices for extended flight durations, enabling operation at high altitudes and latitudes beyond 20° N and S.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If solar powered aircraft use extremely flexible structures to achieve low weight and high altitude, then weight is reduced and altitude is improved, but structural strength and reliability deteriorate
Solution Approach 1:
The patent applies flexible membrane structures for the wing envelope and skin, which provide the necessary flexibility for weight reduction while maintaining adequate structural strength through careful material selection and structural design. The flexible skin is tensioned over a rigid or semi-rigid framework to achieve the desired balance between weight and strength.
Solution Approach 2:
The patent utilizes composite materials combining lightweight materials (such as aluminum alloys, composite structures) with flexible membrane materials to create a structure that achieves both low weight and sufficient strength. The composite construction allows optimization of different structural components for their specific functional requirements.
2Adaptability or versatility
If solar powered aircraft operate at high latitudes and low sun angles, then geographic coverage is improved, but photovoltaic cell efficiency deteriorates
Solution Approach 1:
The patent implements adjustable or flexible wing surfaces that can dynamically change their orientation or angle relative to the sun's position. This allows the photovoltaic cells to maintain optimal incidence angles even when the sun is at low angles in the sky, thereby maintaining high efficiency across various geographic locations and times of day.
Solution Approach 2:
The patent changes the operational parameters of the photovoltaic system by adjusting the wing's geometric configuration or surface orientation to optimize energy collection. This may include variable dihedral angles, adjustable panel orientations, or flexible skin tensioning to present the solar cells at optimal angles to incident sunlight.
3Area of stationary object
If solar powered aircraft fly at high altitudes for long duration, then communications coverage area is improved, but power availability deteriorates due to solar energy being diffuse
Solution Approach 1:
The patent divides the power generation system into multiple segmented photovoltaic panels distributed across the wing surfaces. This segmentation allows each panel to be independently oriented or adjusted to maximize solar capture, and the distributed arrangement increases the total effective collecting area without concentrating weight in one location.
Solution Approach 2:
The patent utilizes the three-dimensional surface area of the aircraft structure, particularly the curved and multi-faceted wing surfaces, to mount photovoltaic cells. By exploiting the dimensional complexity of the aircraft geometry, the system increases the effective solar collection area beyond what would be available on a simple planar surface.
4Duration of action of moving object
If solar powered aircraft use large lifting surface area to achieve low wing loading, then altitude and endurance are improved, but device complexity increases
Solution Approach 1:
The patent designs the wing structure to serve multiple functions simultaneously: it provides the primary lifting surface for flight, supports and positions the photovoltaic power generation panels, and may also serve as the aircraft skin or envelope. This multi-functionality reduces the need for separate structural components, thereby reducing overall device complexity despite the large surface area requirement.
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 aircraft achieves flight durations of 2 months to 5 years at altitudes over 50,000 feet and latitudes between 40° N and 40° S, providing continuous coverage and competitive cost per communication data rate with geosynchronous satellites.
Implementation Method 1
The wing supports a segmented configuration of photovoltaic cells for power generation
Implementation Method 2
combined with a robust airframe and energy storage devices for extended flight durations
Data Source
AI summary
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. A telecommunications network incorporating such aircraft is also discussed.