Loading...
Loss of control prediction system for the longitudinal and lateral dynamics of an aircraft using Laplace methods
Rajaram, Kiran
Rajaram, Kiran
Files
Loading...
theses
Adobe PDF, 2.14 MB
Authors
Other Names
Location
Time Period
Advisors
Original Date
Digitization Date
Issue Date
2018-07
Type
Thesis
Genre
Keywords
Subjects (LCSH)
Electronic dissertation
Electronic dissertations
Electronic dissertations
Citation
Abstract
Loss-of-control events have contributed to many accidents worldwide to this date.
A signi cant amount of research has been done to provide safer
ight conditions and thus
prevent such events from occurring. One such area of research is the use of predictive systems
to warn pilots of impending entry into a Loss-of-control situation. This thesis explores the use
of Laplace-based methods as an analytic approach to predicting LOC events by calculating
the critical inputs needed for the pilot to reach prede ned limits.
To illustrate the proposed concept, a Mass Spring Damper system was used. The
position and velocity of the mass with respect to time were simulated using a state space
model. An LOC position limit was de ned and the Laplace equations were used to calculate
the force required to reach this limit within a speci ed time window. This process was
repeated for a step, ramp, parabolic and sinusoidal inputs. MATLAB/Simulink R
was used
as the main platform to run the simulations. This basic framework was applied to the
longitudinal and lateral dynamics of an aircraft.
For the longitudinal dynamics, the Short Period mode of the NASA Generic Transport
Model was used where the angle of attack was the limit while the critical elevator de
ection
was calculated. As for the lateral dynamics, the Roll mode and Dutch roll mode on a
business jet was used. The limits assigned for both modes were the bank angle and sideslip
angle while the critical inputs were the aileron de
ection and rudder de
ection respectively.
Through this method, the remaining amount of control authority available to the pilot is
found and the pilot can use this information to avert an LOC situation. A Fast Fourier
Transform was also utilized to simulate Pilot Induced Oscillations for the Short Period and
Dutch Roll mode. A 3-dimensional display was also developed for both these modes to show
the pilots current position in relation to the critical control de
ection, de
ection rate and
frequency boundary.
Table of Contents
Description
Thesis (M.S.)-- Wichita State University, College of Engineering, Dept. of Aerospace Engineering
Publisher
Wichita State University
Journal
Book Title
Series
Digital Collection
Finding Aid URL
Use and Reproduction
Copyright 2018 by Kiran Rajaram
All Rights Reserved