Tilt-Wing UAV Wing-Locking Mechanism for Drag Reduction

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Solution Overview

Problem

Tilt-wing UAVs face reduced aerodynamic properties and increased drag due to maximum wing surface exposure in vertical positions during hover and vertical take-off and landing, leading to reduced lift effects.

Innovation Solution

The UAV design features detachable wings with rotating shafts and rotor propellers that can switch between a first flight mode where wings rotate freely to minimize drag and a second mode where wings are fixed for conventional lift, using a wing-locking mechanism to adjust pitch and stabilize the aircraft.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If the wings are positioned vertically in hover mode and vertical take-off and landing, then the aircraft can achieve vertical flight capability, but the surface area of the wing is at maximum exposure to crossover winds which reduces the aerodynamic properties and increases drag

Engineering Contradiction:

Improvevertical flight capabilityVSAvoiddrag

Core Design Contradiction:

SpeedVSObject-generated harmful factors

Solution Approach 1:

The patent applies the dynamics principle by making the wings movable rather than fixed. The wings can rotate around their longitudinal axis to change their orientation relative to the fuselage. During hover and vertical take-off/landing operations, the wings automatically adjust to a more streamlined position that reduces their exposure to crossover winds, thereby minimizing drag while maintaining vertical flight capability. This dynamic adjustment resolves the contradiction between achieving vertical flight and reducing aerodynamic drag.

Inventive Principle:

Principle #15Dynamics

2Speed

If the wings are fixed in a lift generation position for forward flight, then conventional forward flight capability is maintained, but the aircraft cannot achieve hover or vertical take-off and landing

Engineering Contradiction:

Improveforward flight capabilityVSAvoidflight mode flexibility

Core Design Contradiction:

SpeedVSAdaptability or versatility

Solution Approach 1:

The patent employs the dynamics principle by enabling the wings to rotate around their longitudinal axes independently. This allows the aircraft to adapt its wing configuration for different flight modes: during forward flight, the wings are positioned at optimal angles for lift generation; during hover and vertical operations, the wings can reposition to reduce drag. This dynamic reconfiguration capability provides both forward flight performance and flight mode versatility without compromise.

Inventive Principle:

Principle #15Dynamics

3Force

If the rotor propellers are used to generate lift in vertical position, then hover and vertical take-off and landing are enabled, but the wings experience maximum exposure to crossover winds reducing aerodynamic efficiency

Engineering Contradiction:

Improvelift generation in vertical positionVSAvoidaerodynamic efficiency

Core Design Contradiction:

ForceVSLoss of energy

Solution Approach 1:

The patent applies dynamics by allowing the wings to independently rotate around their longitudinal axes. When the rotor propellers are operating in vertical positions for hover and vertical take-off/landing, the wings automatically adjust their orientation to present a reduced profile to crossover winds. This dynamic adjustment maintains the necessary lift generation capability while significantly improving aerodynamic efficiency and reducing energy loss during vertical flight operations.

Inventive Principle:

Principle #15Dynamics

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 design enhances aerodynamic properties by reducing drag in hover and VTOL modes while maintaining conventional forward flight capabilities, improving lift and stability through adjustable wing positions and rotor propeller angles.

Implementation Method 1

rotor propellers arranged on either side of the fuselage on the one or more rotating shafts... configured to rotate around the rotating shafts... capable of hovering, as well as being suitable for vertical take-off and landing (VTOL)

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Implementation Method 2

one or more wings on either side of the fuselage arranged on the rotating shaft, so that the wings rotate with regards to the fuselage around the rotating shaft

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Implementation Method 3

the downstream flow generated by the rotor propeller, which produces a rotary movement along the transversal longitudinal axis

Methodology Applied

Scientific EffectDownstream flow: Drag

Data Source

PatentUS11772787B2Unmanned aerial vehicle with different flight modes

Publication Date: 2023.10.03 FUVEX CIVIL SL

AI summary

The unmanned aerial vehicle, UAV, has a fuselage (1) with at least one rotating shaft (2) and one wing (3) positioned on the rotating shaft (2), protruding from either side of the fuselage (1). Preferably, the UAV has at least one rotor propeller (4) arranged on each rotating shaft (2), on either side of the fuselage (1), with one or more rotor blades (4a) and a housing (4b), which includes an actuator. The UAV is capable of shifting between a first flight mode using rotatable wings that rotate freely around the rotating shaft (2) only due to a direction and strength of wind impinging against a surface of the wings (3) and a downstream flow generated by the rotor propellers (4), and a second flight mode using fixed wings, kept in a predetermined position by a wing-locking mechanism, preferably a substantially horizontal position.