VTOL Wing Transition Locking for Stable Mode Switching

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Solution Overview

Problem

Hybrid aircrafts face challenges in efficiently transitioning between vertical and horizontal flight modes due to differing stabilization requirements, with wind conditions exacerbating instability during vertical takeoff and landing (VTOL) and forward flight, and existing wing locking solutions add weight and inefficiency.

Innovation Solution

A device and method that controllably locks and unlocks aircraft wings based on flight mode, using lightweight actuators and aerodynamic control to align wings for optimal positioning, allowing efficient transitions between vertical and horizontal flight.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stability of the object's composition

If existing wing locking solutions are used to stabilize horizontal flight, then flight stability is improved, but aircraft weight increases

Engineering Contradiction:

Improveflight stabilityVSAvoidaircraft weight

Core Design Contradiction:

Stability of the object's compositionVSWeight of moving object

Solution Approach 1:

The patent replaces heavy mechanical locking mechanisms with a control system that uses aerodynamic forces and active control surfaces to stabilize the aircraft during horizontal flight, eliminating the need for substantial mechanical wing locks and reducing overall aircraft weight

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The system dynamically adjusts flight parameters such as angle of attack, roll pitch, and yaw moments through controlled manipulation of aerodynamic forces, allowing the aircraft to transition smoothly between vertical and horizontal modes without heavy mechanical reconfiguration

Inventive Principle:

Principle #35Parameter changes

2Productivity

If the aircraft uses fixed wing configuration for horizontal flight, then forward flight efficiency is improved, but vertical flight stability deteriorates in windy conditions

Engineering Contradiction:

Improveforward flight efficiencyVSAvoidvertical flight stability

Core Design Contradiction:

ProductivityVSStability of the object's composition

Solution Approach 1:

The aircraft employs dynamic control of flight surfaces and aerodynamic forces, allowing the wing configuration to adapt between fixed and flexible states based on flight mode requirements, enabling stable vertical flight in winds while maintaining efficient horizontal flight performance

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The system changes aerodynamic parameters including angle of attack, wing flexure, and control surface deflection to optimize performance for the current flight mode, transitioning from vertical to horizontal flight through controlled manipulation of aerodynamic forces rather than mechanical reconfiguration

Inventive Principle:

Principle #35Parameter changes

3Ease of operation

If the aircraft uses multirotor configuration for vertical flight, then vertical maneuvering capability is improved, but forward flight efficiency deteriorates

Engineering Contradiction:

Improvevertical maneuvering capabilityVSAvoidforward flight efficiency

Core Design Contradiction:

Ease of operationVSProductivity

Solution Approach 1:

The aircraft integrates multiple rotor units that can function both as vertical propulsion elements and as aerodynamic surfaces for forward flight, allowing the same structural components to provide vertical maneuvering capability when needed and efficient forward flight performance when operating in horizontal mode

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The system dynamically adjusts rotor speed, orientation, and aerodynamic parameters to optimize performance for the current flight mode, enabling efficient transition between vertical and horizontal flight through controlled manipulation of aerodynamic forces and rotor characteristics

Inventive Principle:

Principle #35Parameter changes

4Speed

If the aircraft transitions quickly between flight modes, then operational responsiveness is improved, but control stability deteriorates

Engineering Contradiction:

Improvetransition speedVSAvoidcontrol stability

Core Design Contradiction:

SpeedVSStability of the object's composition

Solution Approach 1:

The aircraft employs feedback control systems that continuously monitor flight parameters and adjust aerodynamic forces and rotor characteristics in real-time during mode transitions, maintaining control stability while enabling quick and responsive transitions between vertical and horizontal flight modes

Inventive Principle:

Principle #23Feedback

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

Enables safe, efficient, and quick transitions between vertical and horizontal flight modes by optimizing wing positioning for both flight types, enhancing stability and reducing weight and power consumption.

Implementation Method 1

using lightweight actuators and aerodynamic control to align wings for optimal positioning

Methodology Applied

Scientific EffectAerodynamic control: Aerofoil

Data Source

PatentUS20260054864A1Device and method for flight mode transitioning in a VTOL aircraft

Publication Date: 2026.02.26 COLUGO SYSTEMS LTD

AI summary

A flight mode transitioning device, method and system configured to facilitate transitioning between vertical flight mode and horizontal flight mode in a vertical take-off and landing (VTOL) aircraft, the device comprising at least one actuator mediated member capable of limiting the movement the aircraft wing so as to enable both forward fight and vertical flight.