Helicopter Autopilot Actuator with Vibration Isolator
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Solution Overview
Problem
Helicopter pilots face instability and fatigue due to the need for constant cyclic control, which is exacerbated by the high cost of traditional autopilots, making them uncommon in light helicopters.
Innovation Solution
A redundant actuator system with dual motors and a gear arrangement that allows for automatic control of the cyclic control, including a cyclic vibration isolator and force-limited link for mechanical isolation and pilot override, integrated with an autopilot display unit and electronics section for automated flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a traditional autopilot system is installed to provide automatic control, then pilot workload is reduced and hands-free tasks are enabled, but the cost becomes prohibitive compared to the helicopter itself
Solution Approach 1:
The autopilot system is segmented into modular components: a control unit with processor and memory, separate actuator assemblies for each flight control surface, and individual sensor units. This modular architecture reduces overall system cost while maintaining functionality, making autopilots affordable for light helicopters.
Solution Approach 2:
The control unit serves multiple functions: processing sensor data, generating control commands, managing actuator operations, and implementing failure detection. This multi-functional design consolidates what would traditionally require multiple separate systems, reducing cost and complexity.
2Ease of operation
If automatic control is implemented to reduce pilot fatigue, then hands-free activities are enabled, but system reliability must be maintained against motor failures
Solution Approach 1:
Each actuator assembly has dedicated redundant motors and individual failure detection mechanisms tailored to its specific control surface requirements. This localized redundancy approach provides reliable failure protection without the excessive cost of full system redundancy, balancing reliability with affordability.
Solution Approach 2:
The system continuously monitors motor performance, actuator position, and control surface response through sensors and feedback loops. This real-time feedback enables the control unit to detect failures, adjust control commands, and maintain stable operation even when individual components fail.
Data Source
AI summary
An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.