Pivoting eVTOL Thrust Units With Nested Propeller Blades
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Solution Overview
Problem
VTOL aircraft require significantly more thrust for takeoff and landing than for regular forward flight, and existing thrust units often incur excessive drag during transitions between vertical and horizontal flight.
Innovation Solution
Aerial vehicles with pivoting thrust units that can rotate from vertical to horizontal thrust positions and stow propeller blades into a nested configuration, using electric motors and articulated linkages to minimize drag and power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If propeller blades are deployed for vertical thrust during takeoff and landing, then thrust capability is improved, but drag increases during forward flight
Solution Approach 1:
The propeller blades are designed to nest within the propeller hub when not in use. The blades fold back and store inside the hub structure, creating a compact configuration that minimizes drag during forward flight while allowing full deployment when vertical thrust is required for takeoff and landing operations.
2Force
If multiple thrust units are used for vertical takeoff, then thrust capability is improved, but power consumption increases during horizontal flight
Solution Approach 1:
The thrust units are designed with dynamic blade deployment and retraction capabilities. During horizontal flight, the blades are retracted into the hub to eliminate drag, allowing the system to consume minimal power. The blades are deployed only when vertical thrust is required, enabling the system to adapt its power consumption to the actual flight phase and requirements.
3Object-generated harmful factors
If propeller blades are stowed in nested configuration during forward flight, then drag is reduced, but thrust capability is lost
Solution Approach 1:
The system employs dynamic control of blade deployment and retraction based on flight phase requirements. The blades can be rapidly transitioned between stowed and deployed configurations, allowing the aircraft to optimize for low drag during horizontal flight while maintaining the capability to generate full thrust when vertical takeoff or landing is required.
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 system allows for efficient vertical takeoff and landing with reduced drag and power usage during forward flight, enabling quick thrust adjustments and impact resistance through blade coupling mechanisms.
Implementation Method 1
An electric motor is coupled to the propeller
Implementation Method 2
A propeller blade is coupled to a propeller hub such that centrifugal force moves the blade from a first position to a second position as the propeller rotates
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 aerial vehicle may be powered with electric motors.