Anisotropic Vibration Isolation for UAV Fuselage Sections
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Solution Overview
Problem
Unmanned aircraft systems face significant imaging and operational issues due to vibrations from aircraft engines and components, which are difficult to isolate, leading to blurring and potential malfunction of sensitive surveillance equipment.
Innovation Solution
The implementation of passive vibration isolation devices that secure aircraft components together while minimizing vibration transfer, specifically configured to be 'stiff' along certain axes and 'soft' along others, using clips or attachment features and tension members to restrict movement in specific degrees of freedom and allow movement in others, thereby reducing vibration-induced issues.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If conventional rigid mounting arrangements are used to secure camera and gimbal system, then structural stability is improved, but vibration transmission increases causing imaging problems and equipment malfunction
Solution Approach 1:
The patent introduces vibration isolation elements as intermediary components between the aircraft structure and the camera/gimbal system. These elements act as mediators that decouple the rigid connection, allowing the mounting structure to remain stable while blocking vibration transmission paths to the sensitive equipment.
Solution Approach 2:
The patent changes the mechanical parameters of the mounting system by introducing elements with specific vibration isolation characteristics. These elements have controlled stiffness, damping, and natural frequencies that are optimized to reduce vibration transmission while maintaining structural stability, effectively changing the dynamic parameters of the mounting arrangement.
2Manufacturing precision
If vibration isolation elements are added to reduce vibrations, then imaging quality is improved, but device complexity increases
Solution Approach 1:
The patent segments the mounting structure into distinct functional components: rigid mounting elements for structural support and separate vibration isolation elements for vibration reduction. This segmentation allows each component to be optimized independently and simplifies the overall design by dividing the complex vibration isolation function into manageable, modular elements.
Solution Approach 2:
The patent employs flexible vibration isolation elements that can be made from elastomeric materials or thin film structures. These flexible components provide effective vibration isolation while maintaining a compact form factor, thereby improving imaging quality without significantly increasing the overall device complexity or size.
3Strength
If rigid housing structure is used at nose portion, then component protection is improved, but vibration-induced malfunctions increase
Solution Approach 1:
The patent introduces vibration isolation elements as intermediary components between the rigid housing structure and the sensitive surveillance equipment. These mediators allow the housing to maintain its protective strength while preventing vibration-induced malfunctions by decoupling the rigid structure from the sensitive components.
Solution Approach 2:
The patent modifies the dynamic parameters of the housing structure by incorporating vibration isolation elements with optimized stiffness and damping characteristics. This changes the natural frequencies and vibration transmission properties of the housing, allowing it to maintain structural strength while reducing vibration-induced malfunctions and improving equipment 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 solution effectively reduces vibrations by up to five orders of magnitude compared to conventional arrangements, preventing imaging problems and ensuring the operational integrity of sensitive surveillance components.
Implementation Method 1
a resilient member or structure positioned between the respective first and second aircraft components
Implementation Method 2
a tension member or link stretched between and operatively coupling the first and second members
Data Source
AI summary
Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.