Aircraft Flight Control System with Reaction Force Actuator
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Solution Overview
Problem
Current aircraft flight control systems lack effective mechanisms to prevent overrunning operation limitations, especially when pilots operate flight control devices quickly, which can lead to instability and reduced performance.
Innovation Solution
A flight control system that includes sensors to detect flight conditions, a limitation flight control position calculating section, a reaction force generating command calculating section, and an inner loop command calculating section, which together generate and adjust reaction forces and control surface commands to prevent exceeding operation limitations by adjusting the flight control device's position and control surface actuation based on real-time parameters and predictions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a pilot operates the flight control device quickly to respond to changing flight conditions, then the response speed and productivity are improved, but the aircraft may overrun operation limitations and become unstable
Solution Approach 1:
The system calculates a limitation flight control position in advance based on current flight parameters (speed, altitude, angle of attack, etc.) before the pilot's input would cause an overrun. This predetermined limitation position is used to generate reaction force commands that prevent exceeding safe operating limits, thus maintaining reliability while allowing rapid pilot responses.
Solution Approach 2:
The system continuously monitors flight parameters and dynamically adjusts the limitation flight control position based on real-time aircraft state. The reaction force generating actuator provides continuous feedback to the pilot through the control device, creating a closed-loop system that prevents overrunning limitations while maintaining responsiveness.
2Ease of operation
If a mechanical spring is used to provide tactile cues for operation limitations, then the pilot receives clear tactile feedback, but the preset level cannot be changed once installed
Solution Approach 1:
The patent replaces the mechanical spring system with an electronically controlled reaction force generating actuator. This substitution allows the limitation level to be dynamically adjusted through software-based calculation of the limitation flight control position, enabling adaptability to different flight conditions while maintaining tactile feedback through controlled reaction forces.
Solution Approach 2:
The system transitions from a static mechanical spring with fixed characteristics to a dynamic electronic system that continuously adjusts the reaction force based on real-time flight parameters. The limitation flight control position is recalculated as flight conditions change, providing adaptive tactile cues that match current operational limits.
3Stability of the object's composition
If the inner loop actuator drives the control surface based on inner loop command, then the aircraft stability is improved, but the system complexity increases
Solution Approach 1:
The patent integrates the reaction force generation function with the existing inner loop control system. The reaction force generating command calculating section uses the same flight parameters and limitation calculations as the inner loop command, merging safety limitation enforcement with stability control in a unified electronic control architecture.
Data Source
AI summary
A flight control system of an aircraft and a flight control method of the aircraft are provided in which the overrunning an operation limitation on a flight condition can be prevented even when a pilot operates a flight control device fast. The flight control system of the aircraft includes a flight control device; a sensor configured to detect a first parameter changed based on a flight condition of the aircraft; a limitation flight control position calculating section configured to calculate a limitation flight control position of the flight control device when the first parameter reaches a limitation value, based on the first parameter; a reaction force generating actuator configured to change a reaction force which the pilot receives when carrying out a flight control input to the flight control device, in response to a reaction force generating command generated based on the flight control position of the flight control device and the limitation flight control position; an inner loop command calculating section configured to generate an inner loop command based on the flight control position; and a control surface actuator configured to drive a control surface of the aircraft based on the flight control position and the inner loop command.