M-Wing VTOL Aircraft with Tilting Rotor Assemblies
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Solution Overview
Problem
Current VTOL aircraft face inefficiencies in vertical takeoff and landing due to downwash and control complexities, and fixed-wing aircraft require long runways for takeoff and landing, limiting their versatility in congested or remote areas.
Innovation Solution
An aircraft design featuring M-wings with swept forward and backward portions and propulsion assemblies that can tilt to generate variable thrust vectors, allowing for both vertical takeoff and landing, and forward flight modes, with a flight control system to independently control each propulsion assembly for efficient thrust vectoring.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If fixed-wing aircraft use wings to generate lift during takeoff and landing, then they can achieve efficient forward flight, but they require long runways that are hundreds or thousands of feet long
Solution Approach 1:
The aircraft employs rotatable wings that can dynamically change their orientation from a horizontal configuration during forward flight to a vertical configuration during takeoff and landing. This dynamic reconfiguration allows the same wings to serve dual purposes: generating forward thrust when horizontal and generating vertical lift when vertical, thereby eliminating the need for long runways while maintaining efficient forward flight capability
Solution Approach 2:
The rotatable wings serve multiple functions across different flight phases. During forward flight, they function as traditional horizontal wings generating lift. During takeoff and landing, they rotate to become vertical propellers generating thrust. This multi-functionality allows a single component to replace what would traditionally require separate systems, resolving the contradiction between forward flight efficiency and runway length requirements
2Ease of operation
If tiltrotor aircraft use fixed wings with rotating proprotors, then they can achieve vertical takeoff and landing, but they suffer from downwash inefficiencies due to interference from the fixed wing
Solution Approach 1:
The wings rotate dynamically from a horizontal position during forward flight to a vertical position during takeoff and landing. When vertical, the wings function as proprotors with their airfoils aligned vertically, allowing the slipstream to strike the wing on its smallest dimension. This dynamic reconfiguration eliminates the fixed wing interference problem that plagues tiltrotor designs, as the wing that would normally cause interference is now oriented vertically and functioning as the propulsion element itself
Solution Approach 2:
The design merges the functions of the wing and the proprotor into a single integrated component. The rotatable wing serves both as the lifting surface during forward flight and as the propulsion element during vertical flight. By combining these functions into one component rather than having separate fixed wings and rotating proprotors, the design eliminates the downwash interference problem that occurs when separate components interact
3Loss of energy
If tiltwing aircraft rotate the wing to vertical orientation for takeoff and landing, then they improve vertical thrust efficiency, but they become more difficult to control during hover due to large surface area exposed to crosswinds
Solution Approach 1:
The aircraft employs multiple independent propulsion assemblies distributed across the rotatable wings rather than a single centralized propulsion system. Each propulsion assembly can be independently controlled, providing multiple thrust vectors that can be adjusted to counteract crosswind effects during hover. This segmentation of the propulsion system into multiple controllable units enhances hover control capability while maintaining the vertical thrust efficiency benefits of the rotated wing configuration
Solution Approach 2:
The flight control system dynamically adjusts the tilt angle of individual propulsion assemblies and their rotational speeds to optimize performance across different flight phases. During hover, the system can make fine adjustments to the tilt angles of multiple propulsion units to maintain stability against crosswinds. During takeoff and landing, the same system optimizes for maximum vertical thrust efficiency by coordinating the propulsion assemblies to work together as an integrated vertical propulsion system
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 efficient transition between vertical takeoff and landing, and forward flight modes, improving versatility and reducing the need for long runways, while maintaining stability and control through variable thrust vectoring and M-wing design.
Implementation Method 1
The propulsion assemblies each have a rotor assembly with a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors.
Implementation Method 2
Fixed-wing aircraft, such as airplanes, are capable of flight using wings that generate lift responsive to the forward airspeed of the aircraft, which is generated by thrust from one or more jet engines or propellers. The wings generally have an airfoil cross section that deflects air downward as the aircraft moves forward, generating the lift force to support the airplane in flight.
Implementation Method 3
In the vertical takeoff and landing flight mode, the aircraft operates responsive to thrust-borne lift from the propulsion system.
Implementation Method 4
A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors.
Data Source
AI summary
An aircraft has a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings having first and second pylons extending therebetween, each M-wing forming a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors. In the vertical takeoff and landing fight mode, the aircraft operates responsive to thrust-borne lift from the propulsion system. In the forward flight mode, the aircraft operates responsive to wing-borne lift in a biplane orientation.