Aircraft Buoyancy System Triangular Float Configuration
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Solution Overview
Problem
Existing buoyancy systems for aircraft, particularly rotary-wing aircraft, face instability in extreme sea conditions, where floats can sink, leading to capsizing due to misalignment of the aircraft's center of gravity with the float configuration, especially in rough seas or high-intensity waves.
Innovation Solution
The aircraft is equipped with a buoyancy system featuring outer floats arranged on either side and an inner float positioned inside the cell, with the inner float located above a transverse plane intersecting the outer floats, forming a triangular configuration that maintains the aircraft afloat even if one outer float is submerged, and an inflatable system controlled by sensors to inflate floats based on roll angle and immersion detection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If floats are connected to the cell by rigid means, then the floats maintain fixed positions for stable buoyancy, but the aircraft may capsize in extreme rough seas when the center of gravity misaligns with the float configuration
Solution Approach 1:
The patent applies elasticity to the float connection means, transforming the rigid fixed-position system into a dynamic adaptable system. The elastic connection allows floats to move relative to the cell when the aircraft rolls in rough seas, maintaining alignment between the center of gravity and float configuration, thereby preventing capsizing while preserving buoyancy stability.
2Reliability
If multiple outer floats are arranged on either side of the cell, then buoyancy is improved, but the complexity of the buoyancy system increases
Solution Approach 1:
The patent divides the buoyancy system into functionally independent outer floats and inner floats. The outer floats provide primary buoyancy and stability, while the inner floats serve as a backup system. This segmentation allows each float type to be optimized for its specific function, improving overall buoyancy capacity while managing system complexity through modular design.
3Reliability
If the inner float is positioned in the upper part of the cell above the transverse plane, then it can compensate for outer float failures, but the inner float is exposed to impact damage during water landing
Solution Approach 1:
The patent positions the inner float in the upper part of the cell above the transverse plane, creating a strategic backup buoyancy system. While this positioning exposes the inner float to potential impact damage, it ensures that if outer floats fail, the inner float can compensate and prevent capsizing. The elastic connection means further cushion the inner float against impact forces.
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 enhances stability and prevents capsizing by ensuring at least one float remains above water, even in severe conditions, while protecting the inner float from impact damage and allowing it to compensate for outer float failures, facilitating safe evacuation and maintaining aircraft buoyancy.
Implementation Method 1
a buoyancy system, the buoyancy system being provided with at least two so-called 'outer floats' floats arranged outside the cell
Implementation Method 2
an inflatable system controlled by sensors to inflate floats based on roll angle and immersion detection
Data Source
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AI summary
The present invention relates to an aircraft (1) equipped with a fuselage (2) which delimits at least one internal space (11) extending upwards from a floor (16) to a ceiling (17), said aircraft comprising a buoyancy system (20), the buoyancy system (20) being provided with at least two external floats (30) arranged transversely on either side of an anteroposterior plane (100) outside (EXT) the fuselage (2). The buoyancy system (20) has at least one internal float (35) arranged in an internal space (11), each internal float (35) being arranged above a plane (200) which is perpendicular to the anteroposterior plane (100) and which passes through two external floats (30) arranged on either side of the fuselage (2).