Pivoting eVTOL Drive Unit Control for Yaw and Roll Stability
Find Innovative SolutionsGenerate Solutions
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 by determining and superimposing vertical and horizontal control parameters using specific algorithms and actuation parameters, allowing for precise control of yaw and roll angles through continuous calculation and power adjustments based on pivot angles.
Engineering Contradictions & Design Principles
Engineering 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 the actuation requirements differ between flight phases
Solution Approach 1:
The control method dynamically adapts between vertical and horizontal flight modes by continuously monitoring the pivot angle of drive units. When pivot angles indicate vertical flight configuration, vertical flight control parameters are applied; when horizontal flight configuration is detected, horizontal flight control parameters are applied. This dynamic adaptation enables precise control for each flight phase without requiring a completely separate control system for each mode.
Solution Approach 2:
The control method changes control parameters based on the detected flight phase. Different control algorithms and parameter sets are used for vertical versus horizontal flight positions. By monitoring pivot angles and determining the current flight phase, the system switches between appropriate control parameter sets, maintaining high control precision across different operating conditions while using a single unified control system.
2Adaptability or versatility
If drive units are pivotable to achieve both vertical and horizontal flight positions, then adaptability is improved, but device complexity increases due to additional pivot mechanisms and control requirements
Solution Approach 1:
The drive units are designed with pivot capability that enables them to serve multiple functions: they can operate in vertical flight position for take-off and hovering, and in horizontal flight position for forward flight. The same drive unit structure and control system handle both flight modes by adjusting pivot angles, eliminating the need for separate mechanisms for different flight phases and reducing overall system complexity.
Solution Approach 2:
The pivotable drive units dynamically adjust their orientation based on flight phase requirements. The control system monitors pivot angles and commands appropriate position changes to transition between vertical and horizontal flight configurations. This dynamic reconfiguration capability provides flight phase adaptability while using a single versatile mechanism rather than multiple fixed mechanisms.
Data Source
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.