Non-Coupled Landing Gear Layout for Lower Rotation Torque
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Solution Overview
Problem
Aircraft landing gear designs face constraints on weight and space, particularly in new jetliner aircraft types, which require additional components that increase space and weight, complicating rotation and de-rotation during takeoff and landing.
Innovation Solution
A non-coupled landing gear system with a nose gear positioned forward of the neutral point and a main gear positioned aft, allowing independent operation and reduced torque requirements for pitch rotation, facilitated by a controller that manages mechanical power sources and actuators for each gear.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If additional components are added to meet design requirements for new jetliner aircraft types, then the landing gear can support new aircraft configurations, but the weight and space requirements increase
Solution Approach 1:
The landing gear system is divided into independent nose gear and main gear units, each capable of independent operation. This segmentation allows the system to meet the adaptability requirements for new aircraft types while minimizing weight by eliminating the need for additional coupling mechanisms and unified control systems.
2Adaptability or versatility
If additional components are added to meet design requirements for new jetliner aircraft types, then the landing gear can support new aircraft configurations, but the space occupied increases
Solution Approach 1:
By segmenting the landing gear into independent nose and main gear units, the system achieves adaptability for new aircraft configurations without requiring additional space for integrated control mechanisms, thereby minimizing the overall volume occupied by the landing gear system.
3Device complexity
If coupled landing gear is used, then the structure is simplified, but the torque requirements for rotation and de-rotation increase
Solution Approach 1:
The landing gear is segmented into independent nose and main gear units, each with its own actuation system. This segmentation reduces the torque requirements for rotation and de-rotation by eliminating the need to move entire coupled assemblies, while the overall structure remains simplified through modular design.
Solution Approach 2:
The independent gear units enable dynamic, independent control of each gear during rotation and de-rotation operations. This dynamic capability allows the system to optimize torque distribution and reduce peak torque requirements compared to coupled systems where all gears must move simultaneously.
4Force
If independent gear operation is implemented, then the torque requirements are reduced, but the control system complexity increases
Solution Approach 1:
The control system is designed with multi-functional capabilities that can manage independent gear operation while maintaining simplicity. The same control architecture can handle various operating conditions and gear configurations, reducing the need for separate control mechanisms and thereby minimizing overall system complexity despite the independent operation capability.
Data Source
AI summary
A non-coupled landing gear for an aircraft includes at least a nose gear and at least a main gear. The at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and the at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are uncoupled from each other.