Rotor Blade Retention Device Centrifugal Force Management
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Solution Overview
Problem
Ducted-rotor aircraft require a reduction in the number of separate components to minimize weight, complexity, and cost while maintaining control over direction, thrust, and lift, particularly in transitioning between helicopter and airplane modes.
Innovation Solution
The implementation of a rotor blade retention device that integrates with the ducted rotor system, utilizing tension-torsion straps and a retention device with a radial array of cavities to securely fasten blades, reducing the need for additional components and allowing for pitch adjustment and centrifugal force management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple separate components are used for rotor blade retention and control, then reliability and control precision are improved, but weight and device complexity increase
Solution Approach 1:
The patent combines multiple separate components (retention device, pitch control mechanism, and centrifugal force management system) into a single integrated rotor blade assembly. The retention device includes cavities that receive pitch straps, which are tensioned during blade installation to simultaneously secure the blade and establish pitch control geometry. This integration reduces the number of separate components while maintaining reliability through the unified structure.
2Measurement precision
If multiple separate components are used for rotor blade retention and control, then control precision is improved, but weight increases
Solution Approach 1:
The integration of pitch control geometry directly into the retention device cavities eliminates separate pitch control components. The cavities are specifically shaped to guide pitch straps and establish precise pitch angles during blade installation, achieving control precision without the weight penalty of additional dedicated pitch control mechanisms.
3Reliability
If complex retention mechanisms are used, then blade retention reliability is improved, but ease of manufacture decreases
Solution Approach 1:
The retention device cavities are pre-configured with specific geometries during manufacturing to automatically guide pitch strap tensioning and blade positioning. This preliminary configuration of the cavities ensures that when blades are installed, the correct retention and pitch control geometry is established without requiring complex assembly procedures or additional adjustment mechanisms, thereby improving ease of manufacture while maintaining reliability.
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
This configuration minimizes weight and complexity while enabling efficient control and operation in various flight modes by reducing the number of separate components, enhancing the aircraft's versatility and performance.
Implementation Method 1
rotating the rotor blades about a rotor axis, wherein the rotor blades generate a centrifugal force that is directed outward from the rotor axis
Data Source
AI summary
A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.