Rotary-Wing Seat Beam Linkage for Tolerance-Insensitive Installation
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Solution Overview
Problem
Existing seat beam systems for rotary-wing aircraft face issues with tolerance sensitivity, installation complexity, and interference with the airframe's elastic and dynamic behavior, leading to mechanical instability and the need for frequent adjustments.
Innovation Solution
A seat beam design featuring a link and hinge mechanism with rotatable fixations that decouple from the airframe, allowing easy installation and interchangeability without re-adjustment, while maintaining structural integrity and load-bearing capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a rigid attachment principle with simple pin lugs is used for the transverse beam, then the installation is simple, but production tolerances strongly affect installation capability and require complicated adjustments
Solution Approach 1:
The patent changes the attachment principle from rigid to elastic, allowing the transverse beam to deform elastically during installation and operation. This elastic deformation accommodates production tolerances in the airframe fittings and beam length, eliminating the need for complicated adjustments while maintaining installation simplicity
Solution Approach 2:
The patent introduces dynamic behavior by allowing the transverse beam to deform elastically rather than maintaining a fixed rigid position. This dynamic adaptation enables the beam to adjust to tolerance variations automatically, resolving the contradiction between simple installation and precise installation capability
2Stability of the object's composition
If a rigid transverse beam is attached to airframe fittings, then the structural stability is improved, but the beam negatively affects the airframe's elastic and dynamic behavior in crash scenarios
Solution Approach 1:
The patent changes the beam's mechanical properties from rigid to elastic, allowing it to deform under load. This elastic behavior reduces antagonistic axial loads and membrane effects during crash scenarios, eliminating the harmful interference with airframe dynamics while maintaining structural stability through controlled deformation
Solution Approach 2:
The patent converts the previously harmful rigid constraint into a beneficial elastic element. The elastic deformation of the beam during crash scenarios absorbs energy and reduces harmful axial loads on the airframe, turning what was a source of harm into a protective mechanism
3Manufacturing precision
If transverse beams are made adjustable in length with screwed end-fittings, then the tolerance sensitivity is reduced, but the cost-efficiency is penalized and specific tooling is required for installation
Solution Approach 1:
Instead of making the beam length adjustable through complex screwed fittings, the patent changes the attachment principle to elastic deformation. This allows the beam to accommodate tolerance variations naturally through elastic strain, achieving tolerance insensitivity without increasing device complexity or requiring special tooling
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
The design ensures tolerance-insensitive installation, reduces mechanical interference with the airframe, and enhances operational robustness by decoupling the beam's behavior from the airframe's dynamics, allowing for efficient and tool-free installation across different aircraft models.
Implementation Method 1
The link-beam fixation is attached to the seat beam body and rotatable around a first link rotational axis that is perpendicular to the seat beam extension axis. The first seat beam fixation is connected to the link-beam fixation and adapted for being attached to the first airframe attachment point such that the first seat beam fixation is rotatable around a second link rotational axis that is parallel to the first link rotational axis.
Implementation Method 2
the beam affects the overall elastic and dynamic behavior of the rotary-wing aircraft. In turn, the beam can negatively affect the airframe's behavior e.g. in a crash scenario with unpredicted interactions.
Data Source
AI summary
A seat beam for a rotary-wing aircraft adapted for receiving seat posts of a seat bench device, including a first seat beam end; a second seat beam end; and a seat beam body connecting both. A link with a link working line is arranged at the first seat beam end and includes: a link-beam fixation that is attached to the seat beam body and rotatable around a first link rotational axis that is perpendicular to the seat beam extension axis, and a first seat beam fixation that is connected to the link-beam fixation and adapted for being attached to the airframe attachment point such that the first seat beam fixation is rotatable around a second link rotational axis that is parallel to the first link rotational axis.