Rotorcraft Load Attachment Beam with Oblique Profiles
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Solution Overview
Problem
Conventional rotorcraft attachment systems for external loads lack structural support under the fuselage, leading to potential fuselage perforation during crashes due to non-deformable support beams, especially when fuel tanks are present.
Innovation Solution
A support beam with oblique side profiles and a central support member, where each side profile has an obtuse angle with the horizontal web, allowing for deformation and crushing upon impact to reduce aggression on the fuselage, and optionally includes a spring member to tilt the attachment means away from the ground during crashes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a conventional support beam with vertical side sections is used, then the beam provides sufficient structural support during flight, but the beam becomes aggressive and risks penetrating the fuselage during a crash
Solution Approach 1:
The side sections are changed from vertical to oblique orientation with obtuse angles at the lower ends. This geometric parameter change allows the beam to deform in a controlled manner during impact, with the lower ends moving apart to absorb energy and reduce penetration risk, while maintaining flight structural integrity
Solution Approach 2:
The support beam is designed with asymmetric oblique side sections that enable dynamic deformation during crash. The oblique geometry allows the structure to transition from a rigid flight configuration to a deformable impact configuration, where the side sections can move apart to reduce aggression toward the fuselage
2Object-affected harmful factors
If the side profiles are made oblique with obtuse angles, then the beam can deform during crash to reduce fuselage damage, but the bending stiffness during flight may be reduced
Solution Approach 1:
The support beam exhibits different structural characteristics in different regions: the upper portions maintain sufficient stiffness for flight, while the lower oblique sections are designed to deform during impact. This local differentiation allows the beam to provide both flight structural support and crash energy absorption
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 oblique side profiles provide sufficient bending stiffness for flight while deforming to minimize fuselage damage during crashes, reducing the risk of perforation and damage to fuel tanks.
Implementation Method 1
the side sections can come into contact with the ground. Therefore, the inclination of the side profiles increases. The side profiles are crushed by moving away from each other.
Data Source
Figure 1~6
Figure 7~11
AI summary
The present invention relates to a fastening system (10) equipped with an attachment means (15) for attaching an external load to a rotorcraft. The fastening system (10) has a support beam (20) for attaching the attachment means (15) to the rotorcraft. The support beam (20) has a horizontal web (25) and two lateral profiles (30) extending upwards from the horizontal web (25). The fastening system (10) has a support member (50) in a central space (100) separating the lateral profiles (30) for carrying an attachment means (15). The support member (50) is connected to each lateral profile (30). Each lateral profile (30) includes a horizontal wall (31) connected to the horizontal web (25). Each wall (31) has an obtuse angle. (α) with said horizontal core (25) in said central space (100),each lateral profile (30) being an oblique profile capable of approaching said horizontal web (25) under the effect of vertical forces.