Active Landing Gear Damper for Dynamic Impact Adaptation
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Solution Overview
Problem
Current aircraft landing gear damping systems are passive and optimized for specific aircraft gross weights and crash velocities, failing to provide optimal energy absorption in varying crash conditions due to weight changes and different impact velocities and attitudes.
Innovation Solution
The implementation of a continuously adjustable damper system with a motor-controlled valve, a controller that calculates and adjusts damping coefficients based on real-time aircraft state data and terrain information to achieve target damping forces and velocities during impact.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If passive damping systems are used, then the system is simple and reliable, but it cannot adapt to varying aircraft weights and impact conditions
Solution Approach 1:
The patent applies dynamics by transitioning from a static passive damping system to a dynamic active damping system. The damping coefficient is continuously adjusted in real-time based on actual impact conditions through a controller that receives sensor data and modifies the damping force accordingly, enabling adaptation to varying aircraft weights and impact velocities while managing system complexity through controlled automation.
Solution Approach 2:
The patent implements parameter changes by dynamically modifying the damping coefficient parameter based on real-time impact parameters such as impact velocity, aircraft weight, and landing gear compression rate. This allows the damping system to optimize its performance for each specific crash scenario rather than being fixed for a single design condition.
2Reliability
If damping coefficient is fixed for optimal performance at specific weight and velocity, then energy absorption is optimized for that condition, but performance degrades when conditions vary
Solution Approach 1:
The patent employs feedback mechanisms where sensors continuously monitor impact parameters including impact velocity, aircraft weight, and landing gear compression rate. This real-time data feeds back to a controller that adjusts the damping coefficient to maintain optimal energy absorption performance across varying crash conditions, ensuring reliability regardless of the specific impact scenario.
Solution Approach 2:
The system performs preliminary action by pre-calculating optimal damping coefficients based on predicted impact parameters before the actual impact occurs. This allows the damping system to be properly configured in advance for the expected crash conditions, improving energy absorption reliability from the moment of impact.
3Adaptability or versatility
If active adjustment mechanisms are added, then adaptability to different crash conditions is improved, but system complexity and potential failure points increase
Solution Approach 1:
The active adjustment mechanism operates autonomously using onboard sensors and a controller that automatically adjust the damping coefficient based on detected impact parameters. This self-service capability eliminates the need for manual intervention while maintaining system reliability through automated real-time adaptation to crash conditions.
Solution Approach 2:
The patent replaces purely mechanical passive damping systems with an electro-mechanical active system that uses electronic sensors and controllers to adjust damping parameters. This substitution enables adaptability to varying crash conditions while maintaining reliability through electronic control systems that can process sensor data and make rapid adjustments during impact events.
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 solution allows for dynamic adjustment of damping forces to optimize energy absorption across varying aircraft weights and impact conditions, enhancing the landing gear's ability to manage kinetic energy during crashes.
Implementation Method 1
The damper can include a motor that adjusts the damper valve. The damper can also include a controller. The controller can receive a target damper force and an initial damper velocity for an impact of the vehicle with terrain.
Implementation Method 2
Specifically, each landing gear can include a damper that resists rapid compression of the landing gear. This resistance can decelerate the airframe during an impact.
Data Source
AI summary
An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.