MR Actuator Backup for Single-Hydraulic Rotorcraft Flight Controls
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft, particularly rotorcraft, face challenges with dual hydraulic systems that increase weight, cost, and space requirements due to dual parallel power systems for boosting pilot flight control inputs, necessitating a more efficient and compact solution.
Innovation Solution
Implementing a single hydraulic system with a magnetorheological (MR) actuator that provides both autopilot/trim functions and force assistance in case of hydraulic failure, using MR fluid to modulate force feedback and actively drive pilot input devices.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a dual hydraulic system is used to provide force assistance and autopilot functions, then reliability is improved, but weight increases
Solution Approach 1:
The patent combines force assistance and autopilot functions into a single hydraulic system with a unified actuator that performs both roles. The flight control computer manages both functions through one hydraulic circuit, eliminating the need for separate dual hydraulic systems while maintaining operational reliability through electronic control and backup capabilities.
Solution Approach 2:
The single hydraulic actuator is designed to perform multiple functions: providing force assistance during normal operation and serving as the autopilot actuator when needed. The system can switch between these functions based on operational requirements, reducing overall system weight while maintaining the reliability of both functions through a multi-functional design.
2Reliability
If a dual hydraulic system is used to provide force assistance and autopilot functions, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent merges force assistance and autopilot systems into a single hydraulic circuit with one actuator, reducing the number of components and interconnections. This simplification lowers device complexity while the flight control computer maintains reliable control through electronic management of the unified system.
Solution Approach 2:
The single actuator is designed as a universal component that can perform both force assistance and autopilot functions. This multi-functionality reduces the number of specialized components needed, thereby simplifying the overall system architecture while maintaining the reliability of both functions through a streamlined design.
3Reliability
If a dual hydraulic system is used to provide force assistance and autopilot functions, then reliability is improved, but volume increases
Solution Approach 1:
The patent combines the hydraulic reservoirs, actuators, and control circuits for both force assistance and autopilot into a single integrated system. This consolidation significantly reduces the total volume occupied by hydraulic components while maintaining the reliability of both functions through shared infrastructure and unified control.
Solution Approach 2:
The single hydraulic actuator serves as a universal component for both force assistance and autopilot operations, eliminating the need for separate actuators and their associated mounting spaces. This multi-functional approach reduces the overall system volume while preserving the functional capabilities and reliability of both systems.
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 MR actuator reduces weight and space requirements while ensuring safe flight operations by providing reliable force assistance during hydraulic failures, meeting certification standards without additional pilot effort.
Implementation Method 1
a magnetorheological (MR) actuator that provides both autopilot/trim functions and force assistance in case of hydraulic failure, using MR fluid to modulate force feedback
Data Source
AI summary
One embodiment is an aircraft comprising a fuselage; a rotor system connected to the fuselage and comprising at least one rotor blade; a pilot input device; a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.