Tiltrotor Pylon Actuation Mechanism for Load Management
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Solution Overview
Problem
Tiltrotor aircraft face unique challenges in articulating between helicopter and airplane modes, experiencing excessive structural loads and vibrations due to aerodynamic and operational forces, which can impact structural integrity and performance.
Innovation Solution
A system comprising a rotor system, a pylon, a spindle, an actuator arm, and an actuator that rotates the pylon and rotor system, with the actuator arm positioned between the wing and the fuselage to manage loads and facilitate mode conversion, using a down stop mechanism to mitigate vertical and lateral forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the tiltrotor assemblies are articulated to rotate between helicopter mode and airplane mode, then the aircraft's versatility and flight capabilities are improved, but excessive structural loads and vibrations are generated that can compromise structural integrity
Solution Approach 1:
The system segments the load management function by introducing separate structural components (actuator arm, down stop mechanism, horizontal support) that handle specific load types independently. The actuator arm manages rotation, while the down stop mechanism specifically handles vertical and lateral forces, preventing these loads from being transmitted to the wing structure.
Solution Approach 2:
The down stop mechanism acts as an intermediary between the tiltrotor assembly and the wing structure. It mediates the force transmission by absorbing and redirecting vertical and lateral loads away from the wing, allowing the articulation function to proceed without compromising structural integrity.
2Ease of operation
If the actuator arm is positioned close to the wing to facilitate mode conversion, then the ease of operation is improved, but the structural loads on the wing increase
Solution Approach 1:
The down stop mechanism serves as an intermediary that decouples the actuator arm's proximity to the wing from direct force transmission. It allows the actuator arm to be positioned close to the wing for efficient operation while preventing the transmission of excessive forces to the wing structure.
Solution Approach 2:
The down stop mechanism extracts and isolates the vertical and lateral force components from the articulation system. By taking out these specific force vectors and handling them separately through the down stop striker and block interface, the system can operate efficiently without overloading the wing.
3Strength
If the down stop mechanism is added to manage vertical and lateral forces, then the structural integrity is improved, but the device complexity increases
Solution Approach 1:
The down stop mechanism merges multiple functions into a compact assembly: the down stop block is integrated into the actuator arm, and the striker is attached to the wing. This combining of elements manages vertical and lateral forces without adding significant complexity to the overall system.
Solution Approach 2:
The down stop mechanism provides dynamic load management that adapts to different flight modes. During articulation, the mechanism engages and disengages as needed, providing structural support when required without permanently complicating the system architecture.
Data Source
AI summary
A tiltrotor aircraft is described and includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.