How to Model Aircraft Landing Gear Vibrations?

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SUMMARY

This discussion focuses on modeling aircraft landing gear vibrations, specifically for a Boeing 747 and a Cessna 172. The proposed approach involves using a non-homogenous second order differential equation, with the Dirac Delta function as the forcing function. Key parameters to derive include damping ratio and equivalent spring constants, while considering the effects of Weight and Balance on system response. MATLAB will be utilized for quantitative analysis, generating data on maximum passenger acceleration and gear displacement over time.

PREREQUISITES
  • Understanding of non-homogenous second order differential equations
  • Familiarity with mechanical vibrations and dynamic systems
  • Knowledge of MATLAB for data analysis and simulation
  • Concepts of damping ratio and spring constants in mechanical systems
NEXT STEPS
  • Research the application of the Dirac Delta function in mechanical systems
  • Study methods for deriving damping ratios and spring constants
  • Learn about modeling multi-degree-of-freedom (MDOF) systems in MATLAB
  • Explore the effects of Weight and Balance on aircraft dynamics
USEFUL FOR

Aerospace engineers, mechanical engineers, and students in vibrations courses who are interested in modeling and analyzing aircraft landing gear dynamics.

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Homework Statement



Working on a project for a vibrations course, task is to quantitatively analyse a system in which mechanical vibrations occur. I chose to model aircraft landing gear, for a variety of different airplanes, namely one large transport (747), a simple tricycle gear GA plane with cantilever suspension (Cessna 172), and either a taildragger or else another trike with an oleo type shock absorber.


Homework Equations



I was planning on modelling the system as a non-homogenous second order differential equation, with the forcing function being some sort of impulse or sum of impulses (possibly using the Dirac Delta function or a convolution integral, but I still need to work that out). However, I was wondering if anyone would be able to help me to figure out or derive parameters such as damping ratio, equivalent spring constants, and also how factors like Weight and Balance, would affect the system response. I plan to do some quantitative analysis in MATLAB for this project, and what I would ultimately like to be able to do is to generate data and plots for maximum passenger acceleration and also gear displacement as a function of time.
 
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Just a few questions for you to think about.

1. Before touchdown, the aircraft in the air has 6 rigid body DOF, in addition to all the many vibratory DOF. This is true for all of your three air craft types. Even on the ground, moving, it still has 6 DOF if we allow for the fact that the tires and shocks offer significant vertical motion, and all other motions are almost as free as they were in the air. How then do you propose to reduce this to a single second order (1DOF) system?

2. Might it be a good idea to specify in advance what part of the aircraft motion you are going to attempt to model, say perhaps the heave and pitch following touch down? Or will you be more ambitious and try to model things like the yaw motion? or the possible flutter of the nose wheel? Just how far are you going to attempt to go in your model? It would seem wise to spell out your goals in advance, otherwise you will never know where you have met them or not.
 

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