Aircraft Landing Gear Structural Component Aerodynamic Stability
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Solution Overview
Problem
Non-retractable landing gears on electrically powered aircrafts increase air resistance, energy consumption, and reduce range due to their fixed position during flight, while traditional solutions for reducing drag and instability are separate from structural requirements and add weight.
Innovation Solution
Integration of a structural component with aerodynamic stability functions for the main landing gear, featuring an aerodynamically shaped outer surface and fairing components that reduce yaw instability and drag, eliminating the need for additional stabilizers and reducing overall weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a non-retractable (fixed) landing gear is used, then the device complexity and weight are reduced, but the air resistance and energy consumption increase significantly
Solution Approach 1:
The patent merges the structural support function and aerodynamic stability function into a single integrated structural component. The structural component includes both the load-bearing structure and aerodynamic surfaces (such as winglets or stabilizers) that work together to provide both mechanical support and flight stability, eliminating the need for separate aerodynamic stabilization devices.
Solution Approach 2:
The structural component is designed to perform multiple functions simultaneously: it serves as the load-bearing element for the landing gear while also providing aerodynamic stability during flight. This multi-functional design reduces the overall number of components needed and minimizes weight while addressing both structural and aerodynamic requirements.
2Object-affected harmful factors
If additional aerodynamic fairings are added to reduce drag, then the aerodynamic characteristics improve, but the weight increases
Solution Approach 1:
Instead of adding separate aerodynamic fairings to the landing gear structure, the patent integrates aerodynamic surfaces directly into the structural component itself. The structural component includes aerodynamic features such as winglets, stabilizers, or streamlined shapes that reduce drag without requiring additional external fairings, thereby avoiding the weight penalty of separate aerodynamic add-ons.
3Weight of moving object
If the structural component performs both structural and aerodynamic functions, then the weight is reduced, but the design complexity increases
Solution Approach 1:
The structural component is designed as a multi-functional element that simultaneously provides structural support and aerodynamic stability. By integrating these functions into a single component rather than using separate elements, the overall aircraft weight is reduced while the design complexity is managed through a unified structural approach rather than multiple separate systems.
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 dual-function design enhances aerodynamic stability and structural performance without increasing weight, leading to longer flight times and reduced energy consumption, providing a competitive advantage for electrically powered aircrafts.
Implementation Method 1
The wheels of each of the two main landing gears are mounted on a spring strut, which contains both components of various kinds necessary to absorb the rolling and landing shocks
Implementation Method 2
said structural component also has an aerodynamic stability function, in particular to reduce yaw instability during flight
Data Source
Figure 1~2
Figure 3
Figure 4~5
AI summary
The present invention pertains to the technical field of electrically powered aircraft. According to the present invention, such an electrically powered aircraft (1) is required to comprise at least one non-retractable main landing gear (2a, 2b), wherein said main landing gear (2a, 2b) comprises a wheel (3) and linkage kinematics (4) for attaching said wheel (3) to a structural component (5) of said aircraft (1), and wherein said structural component (5) supports and transmits the loads exerted by the main landing gear (2a, 2b) to a fuselage of the aircraft (1) as well as performs an aerodynamic stability function.