Nonlinear Fly-By-Wire Control for Rotorcraft Overcorrection Limits
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Solution Overview
Problem
Traditional fly-by-wire systems for rotorcrafts are less than optimal due to their linear translation of control inputs, which can lead to overcorrection and system failure, especially in dynamic flight conditions, as they do not adequately account for multiple variables such as airspeed, yaw, pitch, roll, and aircraft loading.
Innovation Solution
A flight control computer system that uses a multi-dimensional lookup table and circuitry to nonlinearly translate control inputs into flight geometry outputs, incorporating a virtual hardstop mechanism that adjusts based on flight conditions and variables like airspeed and acceleration, ensuring the aircraft operates within safe performance parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If linear translation of control inputs is used in fly-by-wire systems, then system simplicity is maintained, but overcorrection and system failure occur in dynamic flight conditions
Solution Approach 1:
The patent implements dynamic control translation where the relationship between control inputs and flight geometry outputs changes based on flight conditions. The system adjusts translation parameters in real-time according to variables such as airspeed, yaw, pitch, roll, and aircraft loading, transforming the static linear translation into a dynamic adaptive process that prevents overcorrection while maintaining system reliability
Solution Approach 2:
The system modifies control translation parameters based on multiple flight condition variables including airspeed, yaw, pitch, roll, and aircraft loading. By changing these parameters dynamically, the system adapts the control response to current flight conditions, preventing overcorrection without requiring a complete redesign of the control architecture
2Adaptability or versatility
If multiple flight variables are incorporated into control translation, then accuracy and adaptability improve, but computational complexity increases
Solution Approach 1:
The patent extends the control translation from a simple one-dimensional input-output relationship to a multi-dimensional space that incorporates flight control inputs, airspeed, yaw, pitch, roll, and aircraft loading. This dimensional expansion allows the system to consider multiple flight variables simultaneously, improving adaptability while managing complexity through structured data organization
3Reliability
If virtual hardstop mechanism is implemented, then safety is improved, but response time may be reduced
Solution Approach 1:
The system pre-establishes virtual hardstop boundaries based on safe operational parameters before flight conditions require intervention. By defining these limits in advance and continuously monitoring flight parameters, the system can prevent unsafe conditions before they occur, maintaining safety without requiring reactive time delays
Data Source
AI summary
There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier.