VTOL Flight Control with Decoupled Stick Inputs Across Flight Modes
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Solution Overview
Problem
Existing VTOL aircraft require pilots to adapt complex control strategies across different airspeed regimes, increasing mental workload and necessitating multiple control elements, which complicates transitions between vertical and forward flight.
Innovation Solution
A flight control system with two manually operated stick members, each pivotable around multiple axes, connected to a flight control computer that eliminates cross-coupling between motion directions, allowing for unified control inputs across flight phases without additional levers or pedals, ensuring intuitive and simplified piloting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If different control strategies are used for vertical and forward flight, then the aircraft can be controlled in all flight modes, but the pilot's mental workload increases and control complexity increases
Solution Approach 1:
The patent implements a universal control system where two stick members serve multiple functions across all flight modes. The same control elements (two sticks) are used for both vertical and forward flight, eliminating the need for mode-specific controls. The flight control computer automatically adapts the control response based on the current flight phase, providing consistent pilot interface while maintaining adaptability to different aerodynamic regimes.
Solution Approach 2:
The patent merges the control functions for vertical and forward flight into a unified system. Instead of separate control mechanisms for different flight modes, the invention combines all control functions into two stick members that operate continuously across all phases. The flight control computer integrates the control signals and automatically adjusts the control law based on flight phase, merging what would otherwise require separate control systems.
2Adaptability or versatility
If multiple control elements are provided for different flight phases, then comprehensive control is achieved, but the device complexity increases
Solution Approach 1:
The control system uses only two stick members that perform all control functions across all flight modes. These universal controls replace what would traditionally require multiple specialized control elements (collective, cyclic, throttle, mixture levers, etc.). The flight control computer provides the adaptive behavior that would otherwise require additional physical controls, maintaining comprehensive control coverage while minimizing hardware complexity.
Solution Approach 2:
The patent replaces complex mechanical control systems with an electronically controlled system. Instead of having separate mechanical linkages for different flight modes, the invention uses electronic sensors on the two stick members and a flight control computer to provide mode-appropriate control responses. This substitution of mechanical complexity with electronic control systems achieves comprehensive control coverage with fewer physical elements.
3Measurement precision
If control inputs must be adapted between vertical and forward flight, then precise control is maintained, but the ease of operation decreases
Solution Approach 1:
The flight control computer dynamically adjusts the control law based on the detected flight phase. The system continuously monitors flight conditions and automatically modifies how the two stick members map to control outputs. This dynamic adaptation maintains precise control responses appropriate for each aerodynamic regime while presenting a consistent, unchanged interface to the pilot, eliminating the need for manual control strategy changes.
Solution Approach 2:
The system uses feedback from flight sensors to automatically determine the current flight phase and adjust control responses accordingly. The flight control computer receives continuous feedback about aircraft state and uses this information to adapt the control law in real-time. This feedback mechanism ensures precise control adaptation without requiring the pilot to manually adjust control inputs based on flight mode.
Data Source
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AI summary
The present invention relates to a flight control system for a VTOL aircraft (10) defining an aircraft reference frame with a roll axis (Xb), a pitch axis (Yb) and a yaw axis (Zb), the flight control system comprising a first and a second manual control apparatus for inputting control commands by an operator, wherein the first manual control apparatus comprises a first stick member, wherein the first stick member is pivotable around first and second control axes with respect to a first neutral position, wherein the second manual control apparatus comprises a second stick member, wherein the second stick member is pivotable around third and fourth control axes with respect to a second neutral position, a flight control computer, which is connected to the first and second manual control apparatuses and configured to output flight control instructions based on pivot positions of the first and second stick members with respect to the first to fourth control axes, wherein the flight control computer is adapted to derive and output flight control instructions, while at least partially eliminating cross-coupling between the individual directions of motion for longitudinal motion control based on the pivot position of the first stick member with respect to the first control axis, for lateral motion control based on the pivot position of the first stick member with respect to the second control axis, for vertical motion control based on the pivot position of the second stick member with respect to the third control axis, and for directional motion control based on the pivot position of the second stick member with respect to the fourth control axis. The invention further relates to a VTOL aircraft (10) comprising such a flight control system.