Fly-By-Wire Pedal System Double Gradient Linkage
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Solution Overview
Problem
Conventional anti-torque tail rotor systems in helicopters require significant pilot workload due to large displacement pedal systems, which are inefficient and uncomfortable when autopilot is engaged, limiting the benefits of Fly-By-Wire (FBW) flight control systems.
Innovation Solution
A double gradient linkage assembly with a spring system and damper system in the pedal system provides a compact, minimal displacement input mechanism that reduces pilot workload by offering a double gradient force feeling, allowing for reduced pedal travel and eliminating mechanical interconnections, thus integrating effectively with full authority FBW flight control systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a large displacement pedal system is used, then the control provides sufficient force feedback and stability, but the pilot workload increases significantly and the system complexity increases
Solution Approach 1:
The patent replaces the conventional mechanical pedal linkage system with a Fly-By-Wire (FBW) electronic control system. The pedal assembly includes position sensors that convert pedal displacement into electrical signals, which are then processed by a flight control computer to generate control commands for the tail rotor actuators. This substitution eliminates the need for complex mechanical linkages and trim modules, reducing pilot workload while maintaining control stability through electronic feedback control.
Solution Approach 2:
The patent changes the control parameter from large mechanical displacement to small electronic signal variation. The FBW system allows for minimal pedal travel (reduced displacement parameter) while maintaining effective control authority through electronic signal amplification and processing. The flight control computer interprets small pedal position changes and generates appropriate control commands, enabling compact pedal design without sacrificing control effectiveness.
2Ease of manufacture
If a conventional large displacement pedal system is used, then the mechanical interconnections provide direct control, but the system complexity and parts count increase
Solution Approach 1:
The patent extracts and eliminates the mechanical interconnection components from the pedal system. By removing the mechanical linkages, trim modules, and synchronization mechanisms between pilot stations, the design simplifies the mechanical structure. The FBW system uses electronic sensors and digital signals to replace these mechanical components, reducing parts count and simplifying manufacturing while maintaining control functionality.
Solution Approach 2:
The patent replaces the mechanical control linkage system with an electronic FBW system. Pedal position sensors convert mechanical pedal displacement into electrical signals that are processed by the flight control computer. This substitution eliminates complex mechanical interconnections, trim modules, and synchronization mechanisms, reducing system complexity and parts count while improving reliability through electronic control.
3Ease of operation
If minimal pedal travel is implemented, then the pilot workload is reduced, but the force feedback and control feeling must be precisely optimized
Solution Approach 1:
The patent replaces mechanical force feedback mechanisms with electronic control and software-based force simulation. The FBW flight control computer processes pedal position signals and generates control commands with virtual force feedback characteristics programmed into the control logic. This allows for optimized force feedback perception through electronic damping and spring rate simulation without complex mechanical feedback linkages, enabling minimal pedal travel with appropriate control feeling.
Solution Approach 2:
The patent optimizes the pedal system by changing physical parameters including reduced pedal travel distance, adjusted spring rates in the pedal assembly, and tuned damper characteristics. These parameter optimizations create appropriate force feedback perception with minimal displacement. The electronic FBW system complements these physical parameter changes by providing digital signal processing that enhances the control feeling without requiring large mechanical movements.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution significantly reduces pilot workload by minimizing the frequency and magnitude of control inputs, enhances aircraft stability, and simplifies the mechanical design, increasing reliability and reducing complexity in the flight control system.
Implementation Method 1
The double gradient linkage assembly includes a spring system and a damper system to provide a double gradient force feeling to the pedal dynamics of the pedals
Implementation Method 2
The double gradient linkage assembly includes a spring system and a damper system to provide a double gradient force feeling to the pedal dynamics of the pedals
Data Source
AI summary
A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.