Folded Wing VTOL UAS for Regime Transition
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Solution Overview
Problem
Traditional unmanned aircraft systems are limited to operating in either a powered flight regime or a vertical flight regime, restricting their range, endurance, altitude, and overall performance, as they lack the capability for efficient transition between these regimes.
Innovation Solution
A Vertical Takeoff and Landing (VTOL) unmanned aircraft system with a unique folded wing design, featuring a center wing, foldable wings, and a ducted fan or propeller engine configuration, allowing for vertical takeoff and landing while transitioning to powered flight and back, utilizing vectored thrust for control and stability in both regimes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional unmanned aircraft systems operate in only one flight regime (powered or vertical), then the system structure can be simplified, but the range, endurance, and altitude capabilities are limited
Solution Approach 1:
The patent implements dynamic reconfigurability where the wings can rotate between a horizontal configuration for powered flight and a vertical configuration for VTOL operations. This dynamic structural change allows the single aircraft to adapt between two flight regimes, resolving the contradiction between versatility and complexity by using one adjustable structure instead of two separate systems
Solution Approach 2:
The aircraft design integrates multiple flight capabilities into a single platform that can perform both powered forward flight and vertical takeoff/landing operations. The universal wing structure serves dual purposes: horizontal extension for aerodynamic lift during powered flight, and vertical rotation for thrust vectoring during VTOL, eliminating the need for separate specialized aircraft
2Reliability
If traditional VTOL systems use complex thrust vectoring systems and rotating engines, then vertical flight control is maintained, but endurance in powered flight regime is limited
Solution Approach 1:
The system dynamically reconfigures the wing position rather than relying on continuous thrust vectoring. During VTOL, wings are vertical providing structural support and stability. During powered flight, wings rotate to horizontal position to generate aerodynamic lift, reducing dependence on thrust vectoring and enabling sustained endurance operation
Solution Approach 2:
The patent extracts the thrust vectoring function from the engine/propeller system and transfers it to the wing configuration itself. The wings become the primary control element for flight regime transition, while the propulsion system focuses solely on providing thrust, simplifying the control system and improving powered flight efficiency
3Length of moving object
If wings are extended for powered flight, then range and altitude capabilities increase, but vertical takeoff and landing capability is lost
Solution Approach 1:
The wing assembly is designed with rotational capability around the fuselage, allowing it to transition between horizontal extension (maximizing span for powered flight) and vertical orientation (enabling VTOL). This dynamic reconfiguration resolves the contradiction by making the wing span adaptable rather than fixed
Solution Approach 2:
The wing configuration operates in two dimensional states: horizontally extended along the lateral axis for powered flight, and vertically oriented along the longitudinal axis for VTOL operations. This dimensional switching allows the same structure to fulfill both contradictory requirements at different operational phases
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 controlled flight in both VTOL and powered flight regimes, increasing endurance and performance by utilizing the folded wing configuration for vertical takeoff and landing and powered flight for extended range and altitude capabilities.
Implementation Method 1
A Vertical Takeoff and Landing (VTOL) unmanned aircraft system with a unique folded wing design, featuring a center wing, foldable wings, and a ducted fan or propeller engine configuration
Implementation Method 2
utilizing vectored thrust for control and stability in both regimes
Implementation Method 3
transitioning to powered flight and back, utilizing vectored thrust for control and stability in both regimes
Data Source
AI summary
A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.