Dual Ducted Tiltrotor Spindle Assembly for Fewer Stressed Joints
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Solution Overview
Problem
Ducted-rotor aircraft have a complex structure with multiple components, which can lead to increased weight and stress on joints during operation, making it desirable to minimize the number of separate components and reduce joint stress.
Innovation Solution
A conversion spindle is developed for dual ducted tiltrotors that can be coupled to ducted-rotor aircraft, allowing for the reduction of separate components and minimizing joint stress by facilitating the conversion between helicopter and airplane modes while maintaining aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple separate components are used in ducted-rotor aircraft structure, then adaptability and functionality are improved, but device complexity and weight increase
Solution Approach 1:
The patent merges multiple separate components (spindle body, mounting brackets, bearing housings, and duct attachments) into a single integrated conversion spindle assembly. This consolidation maintains the flight mode conversion functionality while reducing the number of separate parts, assembly joints, and overall structural complexity in the aircraft.
Solution Approach 2:
The conversion spindle is designed as a multi-functional component that simultaneously provides rotational support, structural mounting, bearing housing, and duct attachment capabilities. This universal design allows a single component to perform multiple functions that would traditionally require several separate parts, thereby reducing device complexity while maintaining adaptability.
2Adaptability or versatility
If multiple separate components and joints are used, then structural functionality is improved, but stress concentration and reliability issues worsen
Solution Approach 1:
By combining multiple separate joints into a single integrated spindle assembly with internal connections, the patent eliminates multiple external joints that would be subject to stress. The integrated structure distributes mechanical loads more evenly throughout the assembly, reducing stress concentration at joint interfaces and improving overall reliability during flight mode conversions.
3Adaptability or versatility
If multiple separate components are used, then functional capability is improved, but aircraft weight increases
Solution Approach 1:
The patent consolidates multiple separate structural components into a single integrated conversion spindle assembly, thereby reducing the total weight of the aircraft structure. This merging eliminates the weight of multiple separate parts, fasteners, and joining materials while maintaining the full flight mode conversion capability.
Solution Approach 2:
The multi-functional spindle design allows a single component to replace several separate parts, each with their own weight. By making the spindle universal in its capabilities (providing rotational support, structural mounting, bearing housing, and duct attachment), the patent achieves weight reduction without sacrificing functional capability.
Data Source
AI summary
A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.