VTOL Flying Car Wing Reconfiguration for Road Integration

Solution Overview

Problem

Current Vertical Take-off and Landing (VTOL) aircraft designs have not successfully transitioned to forward flight and lack integration with road and parking infrastructure, failing to effectively address traffic congestion and short to mid-range commute needs.

Innovation Solution

A small personal VTOL aircraft with a rectangular wing configuration, featuring asymmetrical and reflexed airfoils, symmetrical vertical wing sections, elevons, and a propulsion system with electric propellers, designed for vertical take-off, transition to forward flight, and landing, with a support frame and carbon fiber construction for stability and weight reduction.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If VTOL aircraft use traditional helicopter designs, then vertical take-off and landing capability is achieved, but forward flight capability and integration with road infrastructure are lost

Engineering Contradiction:

Improvedual-mode flight capabilityVSAvoidaircraft configuration

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The aircraft employs dynamic reconfiguration of its propulsion system, transitioning from a quadcopter configuration with four rotors for vertical flight to a forward flight configuration where rotors are repositioned and reconfigured as pusher propellers. This dynamic transformation enables the same aircraft structure to perform both vertical take-off/landing and forward flight efficiently

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The aircraft is divided into modular components including the fuselage, four rotors, and a transformable wing structure. Each rotor can be independently positioned and configured, allowing the system to reconfigure from a vertical flight platform to a forward flight aircraft with conventional wing-based lift and propeller-based thrust

Inventive Principle:

Principle #1Segmentation

2Speed

If VTOL aircraft prioritize vertical flight capability, then take-off and landing are achieved, but transition to forward flight and aerodynamic stability are compromised

Engineering Contradiction:

Improveforward flight speedVSAvoidflight stability

Core Design Contradiction:

SpeedVSReliability

Solution Approach 1:

The aircraft employs dynamic reconfiguration of its propulsion system, transitioning from a quadcopter configuration with four rotors for vertical flight to a forward flight configuration where rotors are repositioned and reconfigured as pusher propellers. This dynamic transformation enables the same aircraft structure to perform both vertical take-off/landing and forward flight efficiently

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The aircraft utilizes carbon fiber composite materials for the fuselage and wing structure, providing high strength-to-weight ratio and structural integrity. This enables the aircraft to maintain aerodynamic stability during forward flight while keeping overall weight low for efficient vertical take-off and landing

Inventive Principle:

Principle #40Composite materials

3Use of energy by moving object

If VTOL aircraft use asymmetrical airfoils for forward flight, then aerodynamic efficiency is improved, but structural complexity and manufacturing difficulty increase

Engineering Contradiction:

Improveaerodynamic efficiencyVSAvoidwing construction

Core Design Contradiction:

Use of energy by moving objectVSEase of manufacture

Solution Approach 1:

The aircraft utilizes carbon fiber composite materials for the fuselage and wing structure, providing high strength-to-weight ratio and structural integrity. This enables the aircraft to maintain aerodynamic stability during forward flight while keeping overall weight low for efficient vertical take-off and landing

Inventive Principle:

Principle #40Composite materials

Solution Approach 2:

The wing structure serves multiple functions: providing aerodynamic lift during forward flight through asymmetrical airfoil sections, structural support for the propulsion system, and contributing to overall aircraft stability. The transformable wing can also serve as a mounting structure for the rotors during vertical flight phase

Inventive Principle:

Principle #6Universality (Multi-functionality)

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 design enables efficient vertical take-off and landing, stable forward flight, and integration with road infrastructure, potentially reducing traffic congestion by providing a viable solution for short to mid-range commutes while maintaining aerodynamic efficiency and structural integrity.

Implementation Method 1

an upper wing section having an upper wing cross section with a first asymmetrical airfoil shape configured to cause lift when in forward flight

Methodology Applied

Scientific EffectLift: Aerofoil

Implementation Method 2

each of the right vertical wing section and the left vertical wing section having a vertical wing cross section with a symmetrical shape to cause yaw directional stability when in forward flight

Methodology Applied

Scientific EffectYaw directional stability:

Implementation Method 3

The upper wing section and the lower wing section may be reflexed-type airfoils to provide stabilization of the pitch moment

Methodology Applied

Scientific EffectPitch moment stabilization:

Implementation Method 4

The asymmetrical airfoil shape may have a camber line that curves back up near the trailing edge to add a positive pitching moment and to create positive longitudinal stability

Methodology Applied

Scientific EffectPositive pitching moment:

Data Source

PatentUS11485489B2Systems and methods for functionality and controls for a VTOL flying car

Publication Date: 2022.11.01 ALEF AERONAUTICS INC

AI summary

A vertical take-off and landing (VTOL) aircraft has a first drivable configuration in which the pilot seat is positioned between the wings and facing the direction of forward travel. The VTOL may be driven in the first configuration as a normal automobile. In the first configuration the wings are aligned with the direction of forward travel and their surfaces are vertically oriented. In the first configuration, the VTOL may also attain altitude and be maneuvered using thrust from propulsion sources. In a second configuration, the pilot seat is rotated 90 degrees from the direction of forward travel to a direction of forward flight. Forward flight is achieved using thrust to rotate the wings from the vertical orientation to a lift-providing orientation. In concert with the rotation of the wings, the pi lot seat is counter-rotated to maintain the seat facing the direction of forward flight.