Aircraft Fuselage Front Structure Landing Gear Force Transfer
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Solution Overview
Problem
Current aircraft front structures with landing gear systems face inefficiencies in force transmission and structural reinforcement, leading to increased weight and complexity, particularly due to the need for extensive side walls and complex connections that interfere with cockpit windows and pressure zones.
Innovation Solution
A front structure design featuring a main shaft and stay shaft connected to reinforcing frames, with a device for mechanical connection and force transfer that directs forces through the simplest path, using a rod assembly with connecting rods and clevises, and optionally parallelogram bars, to minimize weight and interference with cockpit windows, while enhancing pressure resistance and reducing the need for extensive side wall reinforcement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the landing gear forces are transmitted through the landing-gear housing side walls to the front structure, then the housing must have extensive side walls and complex connections, but this increases structural weight and complexity
Solution Approach 1:
The invention extracts the force transmission function from the landing-gear housing side walls and transfers it directly to the aircraft frames through dedicated connection points. The main shaft and stay shaft are connected directly to the frames, eliminating the need for complex side wall structures while maintaining reliable force transmission path.
Solution Approach 2:
The force transmission system is segmented into distinct functional components: the landing gear leg, main shaft, stay shaft, and direct frame connections. This segmentation allows each component to be optimized for its specific function, with the housing focusing on aerodynamic containment rather than structural load bearing.
2Reliability
If extensive side walls are used in the landing-gear housing to transmit forces, then force transmission is achieved, but this interferes with cockpit windows and pressure zones
Solution Approach 1:
The force transmission function is extracted from the housing side walls and assigned to dedicated structural elements (main shaft and stay shaft connected to frames). This allows the housing side walls to be minimized or eliminated, removing interference with cockpit windows and pressure zones while maintaining force transmission capability.
Solution Approach 2:
The force transmission path is redirected from the lateral dimension (through side walls) to the longitudinal dimension (through main and stay shafts connected to frames). This dimensional change allows the housing to have minimal side walls, freeing up space for cockpit windows and maintaining pressure zone integrity.
3Ease of operation
If the main shaft and stay shaft are connected to the housing walls, then the gear can pivot and retract, but the housing must be reinforced increasing weight
Solution Approach 1:
The pivot support function is extracted from the housing walls and assigned to dedicated frame structures. The main shaft and stay shaft connect directly to the frames, which are inherently stronger and do not require additional reinforcement. This allows the housing to be lighter while maintaining full landing gear retraction capability.
Solution Approach 2:
The aircraft frames serve multiple functions: they provide structural support for the fuselage and serve as the mounting points for the landing gear shafts. This multi-functionality eliminates the need for separate reinforcement structures in the housing, reducing overall weight while maintaining operational capability.
Data Source
AI summary
A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.