VTOL Drive Unit Control for Yaw and Roll Transition Stability

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Solution Overview

Problem

Existing control methods for vertical take-off aircraft fail to effectively manage yaw and roll angles during both vertical and horizontal flight transitions, leading to inefficiencies and unstable flight behavior.

Innovation Solution

A control method that adapts power generated by drive units based on determined yaw and roll control parameters, using superimposed actuation parameters calculated from vertical and horizontal flight parameters, allowing for precise control of yaw and roll angles by adjusting power distribution across drive units.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Device complexity

If a single control method is used for both vertical and horizontal flight positions, then device complexity is reduced, but control precision deteriorates because different control parameters are needed for different flight phases

Engineering Contradiction:

Improvecontrol method complexityVSAvoidcontrol precision

Core Design Contradiction:

Device complexityVSMeasurement precision

Solution Approach 1:

The control method dynamically adapts between vertical control parameters and horizontal control parameters based on the current flight phase. The system transitions from using vertical control parameters (g1, r1) during vertical flight to horizontal control parameters (g2, r2) during horizontal flight, allowing optimal control precision for each phase without requiring a completely separate control system

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The invention changes the control parameters according to the flight position. Vertical control parameters are used when the drive units are in vertical flight position, while horizontal control parameters are used when the drive units are in horizontal flight position. This parameter adaptation resolves the contradiction by maintaining control precision through parameter optimization while avoiding the need for multiple complete control systems

Inventive Principle:

Principle #35Parameter changes

2Measurement precision

If separate control parameters are determined for vertical and horizontal flight positions, then control precision is improved, but device complexity increases due to multiple control parameter sets

Engineering Contradiction:

Improvecontrol precisionVSAvoidcontrol method complexity

Core Design Contradiction:

Measurement precisionVSDevice complexity

Solution Approach 1:

The control system dynamically selects and switches between vertical control parameters and horizontal control parameters based on the current flight phase. This dynamic adaptation allows the system to maintain high control precision for each specific flight position while using a unified control architecture that manages both parameter sets, thereby avoiding excessive complexity

Inventive Principle:

Principle #15Dynamics

3Stability of the object's composition

If drive units are positioned for optimal vertical flight control, then vertical flight stability is improved, but horizontal flight efficiency deteriorates due to suboptimal positioning

Engineering Contradiction:

Improvevertical flight stabilityVSAvoidhorizontal flight efficiency

Core Design Contradiction:

Stability of the object's compositionVSUse of energy by moving object

Solution Approach 1:

The drive units are designed to be pivotable between vertical and horizontal flight positions. During vertical flight, the drive units are positioned optimally for vertical stability control. During horizontal flight, the drive units pivot to positions optimized for horizontal flight efficiency. This dynamic repositioning resolves the contradiction by allowing optimal positioning for each flight phase

Inventive Principle:

Principle #15Dynamics

Solution Approach 2:

The spatial parameters of the drive units are changed according to the flight phase. The pivot angle and positioning of drive units are adjusted to match the optimal configuration for the current flight mode, enabling both vertical flight stability and horizontal flight efficiency at different times without compromise

Inventive Principle:

Principle #35Parameter changes

4Use of energy by moving object

If drive units are positioned for optimal horizontal flight control, then horizontal flight efficiency is improved, but vertical flight stability deteriorates due to suboptimal positioning

Engineering Contradiction:

Improvehorizontal flight efficiencyVSAvoidvertical flight stability

Core Design Contradiction:

Use of energy by moving objectVSStability of the object's composition

Solution Approach 1:

The drive units are designed with pivot capability that allows them to switch between horizontal and vertical configurations. When horizontal flight is required, the drive units are positioned to maximize efficiency. When vertical flight is required, they pivot to positions that maximize vertical stability. This dynamic adaptability resolves the contradiction by allowing optimal positioning for each flight phase

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS11994877B2Control method for controlling a yaw angle and a roll angle of a vertical take-off aircraft

Publication Date: 2024.05.28 WINGCOPTER GMBH

AI summary

A control method for controlling a yaw angle γz and a roll angle γx of a vertical take-off aircraft comprising at least two drive groups arranged in opposite side regions of the aircraft so as to be spaced apart from a fuselage of the aircraft is presented. Each drive group comprises at least one first drive unit. The first drive unit is arranged so as to be spaced apart from the fuselage to pivot about a pivot angle α into a horizontal flight position and a vertical flight position.