Tilting Wing Airframe for Stable VTOL-to-Forward Flight Transition
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing airframes with high aspect ratio fixed wings face challenges in maneuverability at slow speeds, require runways for takeoff and landing, suffer from aerodynamic drag, and struggle with stability during transitions between flight modes, necessitating improved designs for efficient forward flight and vertical takeoff and landing.
Innovation Solution
The airframe employs a unique configuration of tilting wings and propulsion units that pivot on a slanted axis, allowing seamless transitions between hovering and forward flight configurations, with thrust redirection between vertical and horizontal orientations, and includes a folding wing structure to reduce inertia and storage space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If high aspect ratio fixed wings are used for efficient forward flight, then forward flight efficiency is improved, but maneuverability at slow speeds deteriorates and runway requirement increases
Solution Approach 1:
The patent applies the dynamics principle by making the wings movable rather than fixed. The wings can pivot between a horizontal configuration for forward flight and a vertical configuration for vertical takeoff and landing. This dynamic reconfiguration allows the aircraft to optimize its wing orientation based on the flight mode, resolving the contradiction between forward flight efficiency and slow speed maneuverability.
Solution Approach 2:
The patent changes the orientation parameter of the wings from fixed to variable. By allowing the wings to change their angle relative to the fuselage (from horizontal to vertical), the aircraft can adapt its aerodynamic characteristics to suit different flight regimes, thereby maintaining both forward flight efficiency and slow speed maneuverability.
2Force
If high aspect ratio fixed wings are used, then forward flight lift generation is improved, but aerodynamic drag during maneuvering increases
Solution Approach 1:
The patent employs dynamic wing orientation to minimize aerodynamic drag. During vertical takeoff and landing maneuvers, the wings are positioned vertically, presenting their edge-on to the airflow, thereby reducing drag. During forward flight, the wings are positioned horizontally to maximize lift generation, thus resolving the contradiction between lift generation and drag reduction.
3Productivity
If long fixed wings are used, then forward flight efficiency is improved, but moment of inertia during VTOL operation increases
Solution Approach 1:
The patent applies dynamic reconfiguration of the wing position to manage moment of inertia. During vertical takeoff and landing, the wings are folded vertically along the fuselage, bringing the mass closer to the center of gravity and reducing the moment of inertia. This allows for better control and maneuverability during VTOL operations while maintaining the benefit of long wings for forward flight efficiency.
4Volume of moving object
If wing folding mechanisms are used for ground storage, then storage space is reduced, but operability during flight for VTOL is limited
Solution Approach 1:
The patent implements a universal wing folding mechanism that serves multiple functions. The same folding mechanism that reduces storage space on the ground also enables vertical takeoff and landing operations. The wings can be folded vertically for compact storage and then deployed to the horizontal position for forward flight, providing versatility across different operational modes.
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 stable and efficient operation across a wide range of speeds, reducing aerodynamic drag and moment of inertia, facilitating smooth transitions and versatile flight modes, suitable for various scales from drones to large aircraft.
Implementation Method 1
a plurality of engines mounted on the pair of opposed wings
Implementation Method 2
the weight of the aircraft can be substantially supported by the lift generated from the wings
Implementation Method 3
long fixed wings can be difficult to maneuver during STOL or VTOL operation due to a large moment of inertia created by their mass being extended away from a center of gravity of the aircraft
Data Source
Figure 1
Figure 2
Figure 3
AI summary
Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.