Aircraft Landing Gear Hydraulics for Angle and Stowage Control
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Solution Overview
Problem
Aircraft landing gear systems face challenges in weight and space constraints, particularly in new jetliner designs that require additional components, making it difficult to adjust the angle of attack during take-off and stowage during flight.
Innovation Solution
A system comprising a nose gear, main gear, hydraulic circuit, compliant elements, and actuators, controlled by a controller and sensors, allowing for adjustable displacement and folding of landing gear to optimize space and weight usage, enabling the use of blended wing body aircraft technology for commercial air travel.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If additional components are added to landing gear for new jetliner designs, then the adaptability and functionality are improved, but the weight and volume increase
Solution Approach 1:
The hydraulic circuit is designed to perform multiple functions: it provides compliant response for wheel displacement, enables angle of attack adjustment during take-off, and facilitates compact stowage during flight. By making the hydraulic system multi-functional, the patent avoids adding separate dedicated systems for each function, thereby improving adaptability without proportionally increasing weight
Solution Approach 2:
The landing gear system incorporates adjustable and variable features through the compliant element that can dynamically respond to different operational requirements. The system transitions between different states (extended for take-off/landing, folded for flight) and adjusts the angle of attack dynamically, allowing the landing gear to adapt to various flight phases without requiring heavy structural reinforcements
2Adaptability or versatility
If additional components are added to landing gear for new jetliner designs, then the adaptability and functionality are improved, but the space occupied increases
Solution Approach 1:
The landing gear is designed with folding capability that allows it to be nested or compacted into a smaller volume during flight. The main gear and nose gear can be folded back against the fuselage, significantly reducing the space occupied. This nesting principle enables the system to provide full functionality when extended while minimizing volume when retracted
Solution Approach 2:
The landing gear system transitions between extended and folded configurations dynamically based on flight phase. During take-off and landing, the gear is extended to provide necessary functionality. During cruise flight, the gear is folded to minimize space occupation. This dynamic reconfiguration allows the system to adapt its volume to operational requirements
3Reliability
If a compliant element is added to provide spring response, then the landing gear performance is improved, but the device complexity increases
Solution Approach 1:
The patent uses a hydraulic circuit with a compliant element to provide spring-like response in the landing gear. The hydraulic system absorbs shocks and provides smooth operation during gear extension and retraction. By using hydraulic principles, the patent achieves reliable performance with a single integrated system rather than combining multiple mechanical components, thereby managing complexity while improving reliability
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 system provides a spring response and adjustable displacement using a single landing gear component, saving space and weight, and allows for the use of blended wing body aircraft by locating landing gear away from the passenger compartment, facilitating efficient angle of attack adjustments and compact stowage.
Implementation Method 1
a hydraulic circuit in fluidic communication with each of the nose piston and the main piston
Implementation Method 2
a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response
Data Source
AI summary
Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.