VTOL Aircraft Ducted Rotor and Flaperon Integration

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Solution Overview

Problem

Current aircraft, particularly VTOL aircraft, face challenges in achieving efficient performance in both forward flight and vertical take-off and landing (VTOL) due to high drag and low airspeed issues, as well as weight and complexity penalties in existing designs.

Innovation Solution

The integration of fixed box wing, fixed Bi-Wing integrated ducting, fixed position Ducted Rotors, and Segmented, movable Flaperons to optimize thrust, lift, and control throughout all phases of flight, enabling improved VTOL capability and forward flight efficiency.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If helicopters are used for VTOL, then vertical take-off and landing capability is achieved, but drag increases and airspeed decreases in forward flight

Engineering Contradiction:

Improveairspeed in forward flightVSAvoiddrag in forward flight

Core Design Contradiction:

SpeedVSObject-affected harmful factors

Solution Approach 1:

The patent employs dynamic tilt-rotor mechanisms that allow the rotors to change orientation from vertical (for VTOL) to horizontal (for forward flight). This dynamic reconfiguration enables the aircraft to optimize its aerodynamic characteristics for each flight phase, reducing drag and increasing airspeed in forward flight while maintaining VTOL capability.

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The invention changes the operational parameters of the rotor system by varying the tilt angle according to flight phase. During VTOL, rotors are positioned vertically to generate lift; during forward flight, they tilt horizontally to generate thrust, similar to conventional aircraft. This parameter change resolves the contradiction between VTOL capability and forward flight performance.

Inventive Principle:

Principle #35Parameter changes

2Productivity

If shaft-driven tilt-rotor aircraft are used, then acceptable performance is achieved for limited applications, but weight and complexity increase significantly

Engineering Contradiction:

Improvemission viability for broader applicationsVSAvoidmechanical component transitions

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The patent replaces complex mechanical tilt mechanisms with a simplified system where the entire rotor assembly tilts as a unit. This reduces the number of moving parts and mechanical complexity while maintaining the ability to transition between VTOL and forward flight modes, thereby improving productivity for broader applications.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Productivity

If tilt-wings or partial tilt-wing mechanisms are used, then some improvement in performance is achieved, but not enough to achieve mission viability

Engineering Contradiction:

Improvemission viabilityVSAvoidmechanical component transitions

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The patent divides the aircraft into distinct functional modules: a fixed wing section for lift generation and a tilting rotor section for propulsion and VTOL capability. This segmentation allows each component to be optimized independently, improving overall mission viability while controlling complexity through modular design.

Inventive Principle:

Principle #1Segmentation

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 configuration enhances the aircraft's ability to transition seamlessly between VTOL and forward flight, achieving mission viability for a broader range of applications by minimizing mechanical component transitions and optimizing performance.

Implementation Method 1

The first right wing and first left wing including at least one ducted assembly including a fixedly positioned rotor to draw air from the forward direction through the ducted assembly and propel air out of the ducted assembly in the aft direction when powered

Methodology Applied

Scientific EffectThrust generation through air propulsion: Jet

Implementation Method 2

the rotor employing power from the power system to rotate

Methodology Applied

Scientific EffectElectromagnetic conversion to mechanical rotation: Electromagnetic Induction

Implementation Method 3

The wings also include a segmented moveable flaperon assembly positioned in the aft direction relative to the rotor to direct propelled air to provide substantially forward thrust and dynamic vertical lift in a first position and substantially vertical thrust and vertical lift in a second position

Methodology Applied

Scientific EffectThrust vectoring through flow direction control: Coanda Effect

Data Source

PatentUS11597509B1Vertical take-off and landing aircraft and methods of taking-off, landing, and aircraft control

Publication Date: 2023.03.07 ALFARO REYNALDO THOMAS

AI summary

An aircraft that closely integrates thrust and aerodynamics to achieve VTOL flight, forward flight, and smooth transitions from VTOL to forward flight. The invention combines a Box wing, Ducted Rotors and movable Flaperons for VTOL and sustained forward flight of an aircraft. In forward flight, the concept uses a plurality of fixed Ducted Rotors to not only provide thrust, but also enhance dynamic lift and controllability by interacting closely with the two fixed primary lifting bodies of each ducted wing section. In VTOL flight and transitioning to forward flight, the Ducted Rotors direct air through movable Flaperons attached to the trailing end of the ducted wings, providing smooth power, controllability, and aircraft orientation throughout transition. Throughout all phases of flight, differential actuation of Ducted Rotors and Flaperons provide control.