Aircraft Piston Engine Actuator Automation via Helical Guide
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Solution Overview
Problem
There is a need for a system that can automate the throttle, mixture, and propeller controls in existing piston engine powered aircraft, as no commercially available product currently exists to retrofit and achieve this automation.
Innovation Solution
An actuation control system comprising a controller and actuators with a motor, helical guide, actuation tube, inner rod, and inner rod actuator, which translates and moves the inner rod between positions to control the aircraft's engine parameters via motor control signals, allowing for automated control of throttle, mixture, and propeller settings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Extent of automation
If manual control cables are used to control throttle, mixture, and propeller, then the system is simple and reliable, but the pilot workload is high and automation is not achieved
Solution Approach 1:
The control system is divided into separate modular actuators for throttle, mixture, and propeller controls. Each actuator is an independent unit with its own motor, helical guide, and actuation tube, allowing individual replacement and simplifying the overall system architecture while achieving automation of all three controls.
Solution Approach 2:
A single actuator design is developed that can perform multiple functions by controlling different engine parameters (throttle, mixture, propeller). The universal actuator design with standardized components like the helical guide and actuation tube can be applied across all three control functions, reducing overall system complexity despite achieving comprehensive automation.
2Productivity
If automated actuators are installed to reduce pilot workload, then operational efficiency is enhanced, but the device complexity and installation requirements increase
Solution Approach 1:
The actuator incorporates a helical guide mechanism that converts rotational motor motion into linear actuation tube movement dynamically. This dynamic mechanism allows the actuator to adapt to different control positions and provides smooth, controlled movement of the control cables, enhancing operational efficiency while maintaining a compact design suitable for retrofit installation.
Solution Approach 2:
The actuation tube serves as an intermediary component that translates the motor's rotational output through the helical guide into linear motion that can pull or push the control cables. This intermediary mechanism enables precise control of the throttle, mixture, and propeller cables while isolating the motor from direct mechanical connection to the control linkages, simplifying installation.
3Measurement precision
If the actuation tube translates continuously to provide fine control, then control precision is improved, but the inner rod position control becomes more complex
Solution Approach 1:
The inner rod actuator incorporates a feedback mechanism that monitors the position of the inner rod and provides signals to the control system. This feedback allows the controller to precisely control the actuation tube's translation by adjusting the motor rotation, achieving fine control precision while managing the complexity through automated position monitoring and adjustment.
Solution Approach 2:
The system replaces complex mechanical linkages with an electric motor and helical guide mechanism. The motor provides precise rotational control, and the helical guide converts this to controlled linear motion of the actuation tube, eliminating the need for complex mechanical positioners while achieving continuous, precise control of the inner rod position.
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
Enables the automation of throttle, mixture, and propeller controls in existing piston engine powered aircraft, enhancing operational efficiency and reducing pilot workload by integrating with existing avionics systems to implement automatic control laws.
Implementation Method 1
The motor is responsive to the motor control signals to rotate and supply a drive torque
Implementation Method 2
The helical guide is coupled to receive the drive torque from the motor and is configured, in response to the drive torque, to rotate in either a first rotational direction or a second rotational direction
Implementation Method 3
The actuation tube is at least partially surrounded by the helical guide and is configured, in response to rotation of the helical guide in the first rotational direction or the second rotational direction, to selectively translate in either a first axial direction or a second axial direction
Implementation Method 4
The inner rod actuator is coupled to the inner rod and is configured to move the inner rod between the first position and the second position
Data Source
AI summary
An actuation system for an aircraft piston engine includes a controller and an actuator. The controller selectively supplies motor control signals to a motor. The actuator includes a housing, a motor, a main rod, a control handle, and an inner rod. The main rod receives a drive torque from the motor and translates in either a first axial direction or a second axial direction. The main rod is responsive to an axial drive force to translate in either the first axial direction or the second axial direction. The inner rod is disposed within the main rod and is movable between a first position, in which main rod rotation causes the main rod to translate, and a second position, in which main rod rotation does not cause the main rod to translate, but application of the axial force to the control handle causes the main rod to translate.