Articulated Electric VTOL Aircraft for Endurance-Efficient Transition Flight

Solution Overview

Problem

Current aircraft systems, particularly in the sub-25 kg weight class, face limitations in cost, complexity, endurance, and versatility for applications like precision survey and monitoring, lacking a configuration that balances VTOL capability with efficient energy use and modular scalability.

Innovation Solution

A configurable all-electric VTOL aircraft with a blended wing body design, utilizing articulated propellers/motors and thrust vectoring for control, which can transition between multi-rotor and fixed-wing flight, eliminating traditional flight control surfaces and incorporating modular energy solutions for enhanced performance and efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Use of energy by moving object

If traditional multi-rotor configuration is used for VTOL capability, then vertical take-off and landing is achieved, but endurance is limited due to high energy consumption

Engineering Contradiction:

Improveenergy consumptionVSAvoidendurance

Core Design Contradiction:

Use of energy by moving objectVSDuration of action of moving object

Solution Approach 1:

The aircraft employs dynamic reconfiguration of its propulsion system, transitioning from a multi-rotor configuration for vertical take-off and landing to a fixed-wing configuration for forward flight. This dynamic transformation allows the system to optimize energy consumption at different flight phases, using electric motors only when necessary for VTOL operations while leveraging aerodynamic lift during horizontal flight to extend endurance.

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If VTOL capability is implemented, then vertical take-off and landing is enabled, but device complexity increases

Engineering Contradiction:

ImproveVTOL capabilityVSAvoidsystem complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The aircraft integrates multiple flight modes (VTOL, hover, and fixed-wing forward flight) into a single platform, making the system universal for various operational requirements. The same propulsion system and airframe structure serve multiple functions: electric motors provide thrust for vertical operations, while the entire configuration enables efficient horizontal flight, reducing the need for separate specialized vehicles.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The aircraft employs dynamic reconfiguration of its propulsion system, transitioning from a multi-rotor configuration for vertical take-off and landing to a fixed-wing configuration for forward flight. This dynamic transformation allows the system to optimize energy consumption at different flight phases, using electric motors only when necessary for VTOL operations while leveraging aerodynamic lift during horizontal flight to extend endurance.

Inventive Principle:

Principle #15Dynamics

3Ease of manufacture

If all-electric propulsion is used, then operational cost is reduced, but power density and range are limited

Engineering Contradiction:

Improveoperational costVSAvoidpower density

Core Design Contradiction:

Ease of manufactureVSPower

Solution Approach 1:

The aircraft employs dynamic reconfiguration of its propulsion system, transitioning from a multi-rotor configuration for vertical take-off and landing to a fixed-wing configuration for forward flight. This dynamic transformation allows the system to optimize energy consumption at different flight phases, using electric motors only when necessary for VTOL operations while leveraging aerodynamic lift during horizontal flight to extend endurance.

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

The solution enables reduced operational and life-cycle costs, improved endurance, and versatility across various applications by maximizing electrical energy use and allowing seamless transitions between flight modes, enhancing hover efficiency and range while maintaining lift and control authority.

Implementation Method 1

articulated propeller/motors (rotors) that is designed to exploit the full potential of an aircraft with a relatively small gross weight

Methodology Applied

Scientific EffectThrust generation:

Implementation Method 2

Thrust vectored aerodynamic control

Methodology Applied

Scientific EffectThrust vectoring:

Implementation Method 3

blended wing body fixed-wing aircraft

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Data Source

PatentUS11724801B2VTOL aircraft having fixed-wing and rotorcraft configurations

Publication Date: 2023.08.15 TEXTRON SYSTEMS CORP

AI summary

An aircraft includes an airframe having a fixed-wing section and a plurality of articulated electric rotors, at least some of which are variable-position rotors having different operating configurations based on rotor position. A first operating configuration is a vertical-flight configuration in which the rotors generate primarily vertical thrust for vertical flight, and a second operating configuration is a horizontal-flight configuration in which the rotors generate primarily horizontal thrust for horizontal fixed-wing flight. Control circuitry independently controls rotor thrust and rotor orientation of the variable-position rotors to provide thrust-vectoring maneuvering. The fixed-wing section may employ removable wing panels so the aircraft can be deployed both in fixed-wing and rotorcraft configurations for different missions.