Aircraft Flight Controls with Personalized Dynamic Force Feedback
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Solution Overview
Problem
Existing aircraft flight control systems, particularly fly-by-wire systems, lack the ability to provide personalized and dynamic feedback to pilots, failing to replicate the feel of mechanical connections and not adapting to individual pilot preferences or physical characteristics.
Innovation Solution
An aircraft flight control apparatus with a control input device and feeling feedback apparatus, controlled by a processing unit that generates aircraft control signals and applies forces based on user-specific control input profiles, allowing customization of feedback forces and control signals to match pilot preferences and physical characteristics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If fly-by-wire control systems are used to improve aircraft control precision and efficiency, then control precision is improved, but the system loses direct mechanical connection and inherent feedback feel
Solution Approach 1:
The patent implements an active feedback system using electric actuators that apply forces to the flight control inputs based on real-time aircraft state data. This creates a closed-loop system where the computer monitors aircraft parameters (altitude, speed, attitude) and dynamically adjusts the feedback force on the control inputs, restoring the sense of connection and feedback feel that was lost in traditional fly-by-wire systems.
Solution Approach 2:
The patent replaces the passive mechanical feedback system (springs, dampers, friction elements) with an active electro-mechanical system. Electric actuators powered by the aircraft's electrical system substitute for mechanical springs and dampers, allowing computer-controlled force application that can dynamically adapt to flight conditions rather than providing fixed mechanical resistance.
2Ease of operation
If passive mechanical components (springs, dampers, friction elements) are added to FBW controls to recreate feel, then feedback feel is improved, but no dynamic feedback on actual aircraft behaviour is provided
Solution Approach 1:
The system continuously monitors aircraft state parameters (altitude, airspeed, attitude, acceleration) and uses this information to dynamically adjust the feedback forces applied to control inputs. This creates an information-rich feedback loop where the pilot receives real-time information about aircraft behavior through tactile feedback, enabling better situational awareness and control.
Solution Approach 2:
The feedback system transitions from static mechanical properties to dynamic, computer-controlled forces that can change in real-time. The electric actuators can vary the magnitude, direction, and timing of feedback forces based on current flight conditions, allowing the system to adapt to different phases of flight and provide context-appropriate feedback.
3Ease of manufacture
If standardized flight controls are used to simplify manufacturing and operation, then ease of manufacture and operation are improved, but adaptability to individual pilot preferences and characteristics is reduced
Solution Approach 1:
The system allows dynamic adjustment of feedback force parameters (spring rate, damping coefficient, friction level) through software configuration rather than physical modification. Pilots can customize these parameters to match their preferences and physical characteristics, and the system can adapt parameters based on detected pilot size or requested profiles, all while maintaining the same standardized hardware platform.
Solution Approach 2:
The standardized electric actuator and control system serves multiple functions: it provides the primary fly-by-wire control, generates customizable feedback forces, adapts to different pilot preferences, and can simulate different aircraft configurations. This multi-functionality allows a single standardized system to replace what would traditionally require multiple specialized control systems.
Data Source
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AI summary
An aircraft flight control apparatus (200) is provided which comprises a control input device (202) comprising a moveable control input component (210) and a feeling feedback apparatus (212). A processing apparatus (204) is arranged to use user information to determine a control input profile (300) and generate at least one aircraft control signal and/or control the feeling feedback apparatus to apply force to the control input component. The processing apparatus is arranged to generate the at least one aircraft control signal and/or control the feeling feedback apparatus based at least partially on the control input profile.