Stationary Actuator Rotor Control Apparatus for Rotary Wing Aircraft
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Solution Overview
Problem
Conventional swashplate mechanisms for controlling rotor pitch, roll, and yaw in rotary aircraft are complex and heavy, requiring dynamic components that rotate at the same RPM as the rotor, leading to increased weight and complexity.
Innovation Solution
A rotor control apparatus with a stationary frame and a pivotable rotary propulsion shaft, featuring a first and second shaft portion coupled at a joint, where the second shaft portion is pivotable in two degrees of freedom, and actuated by non-rotatable actuators to control pitch, roll, and yaw without the need for a swashplate, reducing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional swashplate mechanism is used to control rotor pitch, roll, and yaw, then the rotor control function is achieved, but the system weight and complexity increase due to dynamic components rotating at rotor RPM
Solution Approach 1:
The patent inverts the conventional approach by making the control system stationary rather than rotating. Instead of having the swashplate and control components rotate with the rotor, the invention uses a stationary actuator system that controls a pivotable shaft portion, thereby eliminating the need for heavy dynamic balancing and reducing overall system weight while maintaining full rotor control capability
Solution Approach 2:
The patent extracts the rotating control components from the rotor assembly and places them on the stationary airframe. The control function is separated from the rotating mass, with only the lightweight second shaft portion needing to pivot rather than fully rotate, significantly reducing the weight of moving control components
2Reliability
If a conventional swashplate mechanism is used to control rotor pitch, roll, and yaw, then the rotor control function is achieved, but the device complexity increases due to multiple dynamic components
Solution Approach 1:
The patent simplifies the control system by inverting the rotation relationship - the actuator remains stationary while controlling the shaft portion to pivot. This eliminates the need for complex rotating linkages, bearings, and balancing mechanisms required in conventional swashplate systems, reducing the number of moving parts and overall system complexity
Solution Approach 2:
The shaft is divided into a first shaft portion that remains stationary relative to the airframe and a second shaft portion that pivots to control the rotor. This segmentation allows the complex control function to be isolated to a single pivotable component rather than requiring a complex assembly of rotating parts
Data Source
AI summary
An apparatus for controlling a rotor of a rotary wing aircraft, including a stationary frame, a rotary propulsion shaft extending through the frame, the propulsion shaft having a first shaft portion and a second shaft portion coupled to the first shaft portion at a joint, the first shaft portion being configured to be coupled to a drive unit and the second shaft portion being pivotable relative to a centerline of the first shaft portion in two degrees of freedom about the joint, and at least one actuator coupled to the stationary frame at one end and connected to the second shaft portion at the other end so that the second shaft portion rotates relative to the at least one actuator, the at least one actuator being configured to pivot the second shaft portion in the two degrees of freedom.