INTRODUCTION
TO
STABILITY
AND
CONTROL
F-8 PIO Tests
F-22 PIO
1
F-4 PIO
F-16 Stores Vibration
Lesson 35 Overview
Axis System
Aircraft Controls
Traditional
Alternate Control Methods
Aircraft Motions
S
ANICS
umber at point
ontours of the
the properties
:ra. With the
airspeed. The
denoted by a
ity, the Mach
estrearn Mach
the oweld,
where in the
onic ow, the
try, transomc
teen approxj_
nena become
inc
Propulsion
Drag Polar Whole Aircraft
CD
Total
CD = CD0 + k CL2
Induced Drag (Drag due to Lift)
Parasite Drag (Zero Lift Drag)
CL
Thrust Required (TR )
TR = D = CD q S
= [CD0 + k CL2] q S
C
( CL = L /
T
I
C
G
Airspeed Measurements
ICeT
E
Airspeed Fun (part 1)
In his book, Sled Driver, SR-71 Blackbird pilot
Brian Shul writes: "I'll always remember a certain
radio exchange that occurred one day as Wa
Wing Design Methods
Aerodynamic Coefficients
Airplane Convention
L,n
V
D,l
Y ,m
Aerodynamic Coefficients
CL = L
qS
CY = Y
qS
CD = D
qS
Cn = n
qSb
Cm = m
qSc
Cl = l
qSb
2
2
q = 1 V = p M
2
2
1
Wing Ge
How Airplanes Fly
Bob Kelley-Wickemeyer
Chief Engineer - Aerodynamics
& Enabling Technology
Boeing Commercial Airplanes
Agenda
Basic Physics of Flight
Whats happening during a flight
Rule of Thumb air
NACA Airfoils
6-Feb-08
AE 315 Lesson 10: Airfoil nomenclature and properties
1
Definitions: Airfoil Geometry
z
Mean camber line
x
Chord line
Chord
x=0
Leading edge
x=c
Trailing edge
NACA Nomenclature
STABILITY CRITERIA
AND
CHANGING STABILITY
Pilot Induced Oscillations
(PIO) Videos
F-4B Sageburner PIO (May 18, 1961):
Pilot J. L. Felson attempted high-speed, low-altitude record run
Pitch damper fa
University of Colorado, Colorado Springs
Mechanical & Aerospace Engineering Department
MAE 4415/5415
Assn. #1
1) Using experimental data, find the lift and pitching moment (moment
taken about the quar
LLE
b = wing span, horizontal distance between wing tips
cr =
wing root chord length
ct =
wing tip chord length
x = x-distance to front of component, measured from nose tip, (+) back
z = z-distance to
University of Colorado, Colorado Springs
Mechanical & Aerospace Engineering Department
MAE 4415/5415 Flight Dynamics
2007-2008 Catalog Data:
MAE 4415. Flight Dynamics. (3) Advanced treatment of the
fl
University of Colorado, Colorado Springs
Mechanical & Aerospace Engineering Department
MAE 4415/5415
Assn. #2
1) Read Ch. 2.1 to 2.5
2) Do Problems 2.1, 2.2, 2.3, and 2.5
University of Colorado, Colorado Springs
Mechanical & Aerospace Engineering Department
MAE 4415/5415
Standard Atmosphere Project
Write a Matlab subroutine called "ATMOS" that calculates the standard d
University of Colorado, Colorado Springs
Mechanical & Aerospace Engineering Department
MAE 4415/5415
Project #1
Glider Design
Due: March 11, 2008
MATERIALS
Each student glider must be able to be made
Complex Plane / Time Response
Overview
Review
Second Order Differential Equations
Complex Plane / Time Response
Plot the Roots (Poles on a Complex Plane:
Poles)
P1,2 = N iD = a ib
P1
Im (b)
X
r = N
Equations of Motion:
Moment Equations II
Overview
Review
Equations of Motion: Moment Equations I
Equations of Motion: Moment Equations II
6 Degrees of Freedom (DOF)
Force Eqs
y
Axis
x
Translational
Mass-Spring-Damper
First Order Differential Equations
Overview
Mass-Spring-Damper
First Order Differential Equations
1
Summing the Forces
F=ma
F
x
= m
d2x
dt 2
Fd + Fs = CV K x
f(V)
V =
dx
dt
f(x)
Second Order Differential Equations
Overview
Review
First Order Differential Equations
Second Order Differential Equations
Second Order Differential Equations
&
m& + Cx + Kx = 0
x
(H)
= Ky
(NH)
Sta
Equations of Motion:
Moment Equations I
Overview
Review
Equations of Motion: Force Equations
Equations of Motion: Moment Equations I
6 Degrees of Freedom (DOF)
Force Eqs
y
Axis
x
Translational
Velo
Equations of Motion:
Force Equations
Overview
Review
Coordinate Transformations
Equations of Motion: Force Equations
Body Axis System Summary
Axis
x
y
z
Translational
Velocity
Angular Velocity
U
V
Aircraft Dynamic Stability
Glider Construction Tips
Lesson Overview
Review
Dynamic Stability
Longitudinal Modes
Short Period
Phugoid
Lateral-Directional Modes
Spiral
Dutch Roll
Roll
Stability
Coordinate Axis Systems
Three Axis Systems
Earth (E)
Body (B)
Stability (Wind) (S)
- Right Hand Systems
- Origin at aircraft c.g.
Earth Axis System
x
y
E1
E2
North
East
z
E3
Down (into the earth)
1