Fixed Rotorcraft Landing Gear Structure for Lower Interface Loads
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Solution Overview
Problem
Existing retractable wheel-type landing gears for rotorcrafts increase design complexity, weight, and require significant storage volume, while non-retractable gears lack efficient load distribution and accessibility for maintenance.
Innovation Solution
A non-retractable wheel-type landing gear design with a shock absorber, mounting arm, and link fixations that provide rigid attachment, minimizing housing volume and facilitating easy maintenance, with improved load distribution and reduced interface loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a retractable wheel-type landing gear is used, then aerodynamic drag is reduced and flight speed is increased, but design complexity and weight increase
Solution Approach 1:
The patent extracts the retraction mechanism from the landing gear system, converting it to a fixed non-retractable design. This eliminates the complex actuation systems, hinges, and storage compartments while maintaining adequate aerodynamic performance through optimized fairing integration.
Solution Approach 2:
Instead of making the landing gear retractable to reduce drag, the patent inverts the approach by making it fixed and integrating it aerodynamically into the fuselage structure. The fixed design is fairinged to match the fuselage contour, achieving acceptable drag without retraction complexity.
2Loss of energy
If a retractable wheel-type landing gear is used, then aerodynamic drag is reduced, but storage volume and weight increase
Solution Approach 1:
The retraction storage function is completely removed from the design. The landing gear remains permanently extended but is aerodynamically integrated into the fuselage through fairings, eliminating the need for internal storage compartments and associated volume penalties.
Solution Approach 2:
The landing gear structure is merged with the fuselage fairing structure. The fairing serves dual purposes: aerodynamic streamlining and structural support for the fixed landing gear, eliminating separate storage volume requirements.
3Weight of moving object
If a non-retractable wheel-type landing gear is used, then weight is reduced and maintenance is simplified, but load distribution and accessibility are insufficient
Solution Approach 1:
The landing gear is designed as a modular assembly with separable components including the wheel assembly, shock absorber, and mounting structure. This segmentation enables easy removal and maintenance of individual components while keeping overall weight low.
Solution Approach 2:
The fairing structure incorporates localized access panels and openings positioned to provide direct access to critical landing gear components. This allows maintenance personnel to reach specific areas without removing entire fairing sections, balancing aerodynamic integrity with maintenance accessibility.
4Device complexity
If a non-retractable wheel-type landing gear is used, then structure is simplified, but interface loads increase
Solution Approach 1:
The mounting structure employs asymmetric bracing and load path routing that directs interface loads along optimized structural paths. The fairing integration uses asymmetric attachment points that better distribute reaction forces, reducing peak interface loads compared to symmetric conventional designs.
Solution Approach 2:
The landing gear mounting structure is nested within the fuselage framework, utilizing existing structural members for load bearing. This nesting approach distributes interface loads across multiple fuselage structural elements rather than concentrating them at single attachment points.
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 achieves weight efficiency, reduced installation volume, and simplified maintenance with enhanced load distribution, maintaining structural integrity and accessibility.
Implementation Method 1
a shock absorber (8b) connected to the at least one wheel (8a), the shock absorber (8b) comprising a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c)
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
A non-retractable wheel-type landing gear (8) for a rotorcraft, comprising: at least one wheel (8a); a shock absorber (8b) with a circumferential direction (8o), which is connected to the at least one wheel (8a) and comprises a shock absorber tube (8c) and a shock absorber rod (8d) telescopically mounted to the shock absorber tube (8c); a mounting arm (8e) extending laterally from the shock absorber tube (8c), the mounting arm (8e) being integrally formed with the shock absorber tube (8c) and adapted for attachment to a first fitting (14) of a rotorcraft; and a link fixation (8i) extending laterally from the shock absorber tube (8c), the link fixation (8i) being arranged in the circumferential direction (8o) of the shock absorber (8b) at an angle in a range from 45° to 120° with respect to the mounting arm (8e) and adapted for connection to a second fitting (15) of the rotorcraft.