VTOL Rotor Deployment Mechanism for Drag Reduction

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Solution Overview

Problem

Existing VTOL aircraft require significantly more thrust for takeoff and landing than for regular forward flight, and current designs struggle to efficiently transition between vertical and horizontal flight modes while minimizing drag.

Innovation Solution

The use of pivoting thrust units with propellers that can rotate from a vertical to a horizontal thrust configuration, and the ability to stow propeller blades completely into a nested configuration during forward flight, allowing for efficient transition and reduced drag.

Engineering Contradictions & Design Principles

VSEngineering 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

Engineering Contradiction:

Improvethrust capabilityVSAvoiddrag during forward flight

Core Design Contradiction:

ForceVSObject-affected harmful factors

Solution Approach 1:

The propeller blades are designed to be dynamically deployable and stowable. During vertical takeoff and landing, the blades are deployed to provide necessary thrust. During forward flight, the blades are stowed into a nested configuration within the thrust unit housing, transforming the thrust unit into a streamlined fairing that minimizes drag. This dynamic reconfiguration allows the system to adapt its structure based on flight phase requirements.

Inventive Principle:

Principle #15Dynamics

2Force

If multiple thrust units are used for vertical flight, then vertical thrust is improved, but device complexity increases

Engineering Contradiction:

Improvevertical thrustVSAvoidthrust unit configuration

Core Design Contradiction:

ForceVSDevice complexity

Solution Approach 1:

Each thrust unit is designed as a universal, multi-functional module that can operate in multiple configurations. The same thrust unit provides vertical thrust during takeoff and landing, transitions to provide horizontal thrust during forward flight, and stows its propeller blades to minimize drag. This multi-functionality reduces the need for separate specialized components for different flight phases, thereby managing complexity while maintaining versatile performance.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Object-affected harmful factors

If propeller blades are stowed during forward flight, then drag is reduced, but thrust capability is lost

Engineering Contradiction:

Improvedrag during forward flightVSAvoidthrust capability

Core Design Contradiction:

Object-affected harmful factorsVSForce

Solution Approach 1:

The propeller blade deployment and stowing operates periodically based on flight phase requirements. During vertical takeoff and landing phases, the blades are deployed to provide thrust. During forward flight phases, the blades are stowed to reduce drag. The system transitions between these states periodically as the aircraft moves between different flight modes, optimizing performance for each phase while maintaining overall system efficiency.

Inventive Principle:

Principle #19Periodic action

Data Source

PatentUS12263943B2Rotor deployment mechanism for vertical take-off and landing aircraft

Publication Date: 2025.04.01 JOBY AERO INC

AI summary

A deployment mechanism for use on an aerial vehicle adapted for vertical takeoff and landing using deployable thrust producing elements for takeoff and landing. The deployment mechanism may use linear actuation of a linkage assembly to deploy thrust producing rotor assemblies from a vertical thrust hove configuration to a horizontal thrust forward flight configuration. The aerial vehicle may include left side rotor assemblies and right side rotor assemblies which may be deployed by deployment mechanisms.