eVTOL Pivoting Thrust Units With Nested Blades for Low-Drag Flight
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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 stow propeller blades into a nested configuration during forward flight, utilizing electric motors for rapid thrust adjustments and reducing drag by nesting blades in nacelles.
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 nacelle structure during forward flight, with each blade fitting into a corresponding recess or cavity in the nacelle body. This nesting configuration minimizes the projected area and eliminates the harmful drag that would be generated by deployed propeller blades during horizontal flight, while allowing full blade deployment when vertical thrust is required for takeoff and landing operations.
2Use of energy by moving object
If thrust units are idled during horizontal forward flight, then power consumption is reduced, but thrust response time increases when vertical thrust is needed
Solution Approach 1:
The thrust units are designed with dynamic control capabilities that allow individual blades to be pitched or feathered to minimal angles during forward flight, maintaining a ready state without requiring full power operation. The system can rapidly transition from this low-power state to full thrust production when vertical lift is needed, eliminating the delay associated with starting idle engines while still reducing power consumption during horizontal flight phases.
3Force
If propeller blades are fully extended for maximum thrust, then thrust production is improved, but structural stress increases during impact
Solution Approach 1:
The nacelle structure incorporates impact-absorbing elements and energy-dissipating features positioned to cushion blows to the propeller blades before they reach critical structural components. These pre-positioned cushioning elements, such as elastomeric dampers or deformable structures, absorb impact energy during bird strikes or debris contact, protecting the blade root attachments and shaft from catastrophic failure while allowing the blades to remain in their high-thrust extended position during normal operation.
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 achieves efficient thrust transitions, reduces drag, and conserves power by minimizing thrust requirements during horizontal flight while maintaining rapid response capabilities.
Implementation Method 1
utilizing electric motors for rapid thrust adjustments
Implementation Method 2
pivoting thrust units that stow propeller blades into a nested configuration
Implementation Method 3
reduces drag by nesting blades in nacelles
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 have rear mounted rotors 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 be powered with electric motors.