Dual-Propeller VTOL Clutch Layout for Low-Drag Flight Transition
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing vertical take-off and landing (VTOL) aircraft face inefficiencies due to mismatched power requirements between vertical take-off and horizontal flight modes, with high thrust needed for VTOL exceeding that required for forward flight, leading to compromised performance and drag.
Innovation Solution
Aerial vehicles with wing-mounted thrust-producing elements and tail-mounted rotors that transition between configurations for vertical take-off and horizontal flight, utilizing rotors that stow and nest to reduce drag and adjust power delivery, incorporating directional clutches for efficient thrust distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If high thrust is provided for vertical take-off, then vertical lift capability is improved, but drag increases during horizontal flight
Solution Approach 1:
The rotor blades are designed to dynamically change their configuration between vertical and horizontal flight modes. During vertical take-off, the rotors are positioned vertically to generate high thrust. During horizontal flight, the rotors transition to a horizontal configuration where they generate less drag while still providing necessary thrust for forward motion and control.
Solution Approach 2:
The same rotor system serves multiple functions across different flight phases: providing vertical lift during take-off and landing, transitioning to provide forward thrust during horizontal flight, and enabling control in all flight modes. This multi-functionality eliminates the need for separate propulsion systems optimized for each flight phase.
2Power
If rotor configuration is optimized for vertical take-off, then vertical lift is improved, but performance deteriorates in horizontal flight mode
Solution Approach 1:
The rotor system dynamically reconfigures between vertical and horizontal orientations based on flight phase requirements. The ability to change rotor orientation allows the same power system to deliver optimal performance in both vertical lift and horizontal flight modes without compromise.
Solution Approach 2:
The system changes key operational parameters including rotor orientation, blade pitch angle, and rotational speed to optimize performance for the current flight phase. These parameter adjustments allow the same hardware to deliver different performance characteristics suited for vertical versus horizontal flight.
3Device complexity
If single power delivery system is used, then system simplicity is maintained, but efficiency is compromised across different flight modes
Solution Approach 1:
A single power delivery system is made dynamically adaptable through variable rotor orientation and blade pitch control. This allows the system to maintain simplicity in hardware while achieving mode-specific optimization through dynamic parameter adjustment, thereby improving energy efficiency across different flight phases without adding complex separate propulsion systems.
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 solution enables efficient power usage and reduced drag across flight modes, allowing for balanced thrust distribution and improved performance by altering rotor configurations and power delivery paradigms.
Implementation Method 1
The motor may use directional clutches such that when the motor direction determines which of the blade sets is powered.
Data Source
AI summary
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The deployment mechanisms deploy the rotor forward and up as they deploy from a forward flight configuration to a vertical thrust configuration. A single motor may drive two co-axial propellers, with a first propeller driven when the motor spins in a first direction, and a second propeller driven when the motor spins in a second direction.