S-Shaped Leaf Spring Landing Gear for High-Impact Shock Absorption
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Solution Overview
Problem
The elastic body type landing gear is vulnerable to high impact loads during high-speed landings, leading to bounce and potential accidents, due to limited strain absorption and smaller dissipated energy compared to other types of landing gears.
Innovation Solution
A leaf spring type landing gear is designed with a frame configuration that includes a first frame bent in an arc shape, a second frame with 2-1st and 2-2nd frames bent in an S shape, and a third frame partially bent with a circle center below, along with a damper connected to the second frame to enhance shock absorption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If elastic body type landing gear is used, then ease of manufacture and light weight are improved, but shock absorption capability deteriorates under high impact loads
Solution Approach 1:
The landing gear employs curved frame structures with specific circle centers positioned below the landing gear. The first frame is bent to have a circle center below, and the third frame is at least partially bent to have a circle center below. This curvature design allows the structure to better absorb and distribute impact loads during landing, improving shock absorption capability while maintaining the lightweight elastic body construction.
2Device complexity
If elastic body type landing gear is used, then device complexity is reduced, but energy dissipation capability deteriorates
Solution Approach 1:
The curved geometry of the frames with circle centers below creates a mechanical advantage that increases energy dissipation through structural deformation during impact. The S-shaped second frame with circle centers in opposite directions further enhances this effect by distributing stress more effectively throughout the structure, allowing greater energy absorption without increasing device complexity.
3Ease of manufacture
If traditional frame shapes are used, then manufacturing simplicity is maintained, but shock mitigation performance deteriorates
Solution Approach 1:
The patent applies specific curved shapes to the frames where the first frame is bent to have a circle center below and the third frame is at least partially bent to have a circle center below. This curvature configuration optimizes the structural response to impact loads, improving shock mitigation performance while maintaining manufacturing simplicity through consistent bending geometry.
Solution Approach 2:
The second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape. This asymmetric design with opposite curvature directions creates a more effective shock absorption mechanism that handles multi-directional impact forces, improving overall shock mitigation performance.
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 leaf spring type landing gear effectively mitigates and absorbs shocks during high-speed landings, reducing bounce and enhancing safety and comfort, while also improving weight efficiency and reducing moment energy transfer to the fuselage.
Implementation Method 1
a first frame (110) connected to the fuselage (11) and bent to have a circle center below; a second frame (120) connected to the first frame (110); and a third frame (130) connected to the second frame (120) and at least partially bent to have a circle center below
Implementation Method 2
The leaf spring type landing gear may further include a damper having both ends connected to the 2-1st frame and the 2-2nd frame, respectively
Data Source
AI summary
The present disclosure relates to a leaf spring type landing gear mounted on a lower portion of a fuselage of an aircraft, and more particularly, to a leaf spring type landing gear having improved performance for mitigation and absorption of shocks, including: a first frame connected to the fuselage and bent to have a circle center below; a second frame connected to the first frame; and a third frame connected to the second frame and at least partially bent to have a circle center below, wherein the second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape.