Flexible-Wing UAV Control Using Fuselage Rotation and Weight Shift
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Solution Overview
Problem
Existing UAVs lack the flexibility and cost-effectiveness to perform a wide range of missions, requiring advanced autonomy and control systems to navigate obstacles and environmental conditions effectively.
Innovation Solution
A flexible wing aircraft system utilizing a combination of sensors, electronics, mechanical controls, and payload systems, featuring weight-shift control mechanisms that allow the aircraft to autonomously adjust its wing shape and center of mass for optimal aerodynamic control, enabling efficient navigation and mission versatility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional rigid-wing UAV designs are used, then structural stability is maintained, but mission flexibility and adaptability are reduced
Solution Approach 1:
The patent implements a flexible wing structure that can dynamically change its shape and configuration during flight. The wing includes flexible materials and mechanisms that allow it to adapt to different flight conditions and mission requirements, transforming the static rigid structure into a dynamic adaptable one while maintaining stability through controlled flexibility.
Solution Approach 2:
The patent utilizes weight-shift control mechanisms that change the center of gravity position and wing camber parameters to achieve different flight modes and missions. By varying these physical parameters, the UAV can transition between different operational states while maintaining structural integrity.
2Extent of automation
If advanced autonomous control systems are added to UAVs, then navigation capability improves, but system complexity and cost increase
Solution Approach 1:
The patent implements autonomous navigation capabilities where the UAV can independently sense its environment, process navigation data, and execute flight commands without continuous human intervention. The system serves itself by integrating sensors, processors, and actuators that work together autonomously to complete missions.
Solution Approach 2:
The patent designs a multi-functional control system that handles various tasks including navigation, obstacle avoidance, mission execution, and communication through a unified platform. This universal system reduces overall complexity by consolidating multiple specialized subsystems into an integrated architecture.
3Adaptability or versatility
If flexible wing structures are used, then mission versatility improves, but manufacturing precision requirements increase
Solution Approach 1:
The patent employs flexible wing structures made from thin film materials that can be manufactured with standard tolerances. The flexibility is inherent in the material selection and structural design, allowing the wing to adapt its shape without requiring precision manufacturing of moving parts or joints.
Solution Approach 2:
Rather than manufacturing precise rigid structures with moving parts, the patent uses dynamically adaptable flexible materials that achieve their functional shape through material properties and aerodynamic forces during flight, reducing manufacturing precision requirements while maintaining mission versatility.
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 system enables the UAV to perform complex missions with enhanced autonomy, adaptability, and cost-effectiveness by using sensors and actuators to adjust wing shape and center of mass, improving navigation and mission success rates.
Implementation Method 1
a flexible wing structure which is controlled by moving the center of gravity
Implementation Method 2
a primary sensor network comprised of a plurality of sensors which detect physical quantities
Data Source
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AI summary
Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.