M-Wing VTOL Propeller Layout for Low-Drag Flight Transition
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Solution Overview
Problem
Existing VTOL aircraft face inefficiencies due to separate rotors for vertical lift and forward thrust, leading to increased motor weight, drag, and design complexity, as well as ineffective lift during forward flight.
Innovation Solution
A VTOL aircraft transitions from vertical takeoff using stacked propellers for lift to cruise mode using wings for lift, with rotating wingtip propellers and hinged control surfaces, allowing for efficient thrust and lift distribution during different flight phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If separate non-articulating rotors are used for vertical lift and forward thrust, then vertical lift capability is achieved, but motor weight and aircraft drag increase
Solution Approach 1:
The stacked propeller assembly is designed to perform multiple functions: during vertical flight, the lower propeller provides lift while the upper propeller provides thrust; during forward flight, the entire assembly tilts to provide both lift and thrust components. This multi-functionality eliminates the need for separate dedicated lift and thrust rotors, reducing overall motor weight while maintaining full vertical lift capability.
Solution Approach 2:
The propeller assembly incorporates articulation mechanisms that allow dynamic reconfiguration of propeller orientation and stacking position based on flight phase. The assembly can tilt collectively to transition between vertical and forward flight, and the stacked propellers can rotate relative to each other to optimize thrust vectoring. This dynamic adaptability enables a single assembly to replace multiple static components.
2Force
If separate non-articulating rotors are used for vertical lift and forward thrust, then vertical lift is provided, but aircraft drag increases
Solution Approach 1:
The stacked propeller assembly dynamically reconfigures its orientation based on flight phase. During forward flight, the entire assembly tilts forward and the propellers rotate to align with the direction of motion, minimizing drag. During vertical flight, the assembly transitions to a vertical configuration to maximize lift. This dynamic repositioning ensures that propellers are always optimally oriented relative to the airflow, reducing parasitic drag compared to fixed separate rotors.
Solution Approach 2:
The invention extracts the thrust-generation function from separate dedicated rotors and integrates it into the lift propeller system through stacking and articulation. By consolidating lift and thrust functions into a single integrated assembly that can be reconfigured, the design eliminates the drag penalties associated with multiple separate rotor systems operating simultaneously.
3Force
If separate rotors are used for vertical lift and forward thrust, then lift and thrust are provided, but design complexity increases
Solution Approach 1:
The invention merges the lift rotor and thrust rotor into a single stacked propeller assembly that performs both functions through coordinated operation of the upper and lower propellers. The assembly includes integrated mounting structures, control linkages, and articulation mechanisms that combine what would otherwise be separate systems. This consolidation reduces the number of independent components, simplifies structural support requirements, and reduces overall system complexity while maintaining full lift and thrust capability.
4Force
If stacked propellers are deployed for vertical lift, then vertical takeoff capability is achieved, but aircraft drag increases during forward flight
Solution Approach 1:
The stacked propeller assembly is designed with dynamic reconfiguration capability that allows it to transition from a vertical stacked configuration during takeoff to a forward-tilted, unfolded configuration during cruise. The articulation mechanisms enable the entire assembly to tilt forward, and the propellers can rotate to align with the airflow direction. This dynamic repositioning minimizes the assembly's projected area and drag contribution during forward flight while maintaining vertical lift capability during takeoff.
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
This configuration reduces drag, motor weight, and design complexity while maintaining efficient lift and thrust capabilities across various flight modes, enhancing the aircraft's ability to transport passengers and cargo.
Implementation Method 1
rotating wingtip propellers on the nacelles are pitched upward at a 90-degree angle and stacked lift propellers are deployed from the wing and tail booms to provide lift
Implementation Method 2
nacelles rotate downward to a zero-degree position, allowing the wingtip propellers to provide forward thrust
Implementation Method 3
The hinged control surfaces on the wings, tail boom, and tail may tilt during takeoff and landing to yaw the vehicle
Implementation Method 4
the stacked propellers are redeployed from the wing booms and the tail boom and begin to rotate along the wings and tail to generate the lift required for descent
Data Source
AI summary
A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.