Homework #4
Due: 5pm, Oct. 24, 2015
Problem 1. (40pt) An observer positioned at 30 degrees North latitude on the surface of the earth
tracks a satellite.
You may assume that the inertial frame of reference for the problem is attached to the center of the
Homework #5
Due: 5pm, Oct. 31, 2015
Problem 1. If the orientation of two aircraft A and B relative to an inertial frame be given
through the asymmetric (3-2-1) Euler angles Ea=[30,-45,60]T and Eb=[10,25,-15]Tdegrees, what
are the relative orientation of a
Homework #1
Due: 5pm, Sep. 19, 2016
1. (5points) This is a survey question:
a. What are your reasons to register for this course? What you hope to gain?
2. (15points) List
a. All you know about the physical characteristic of the glider.
b. All you know ab
Aircraft Flight Dynamics
Lecture 19
XIAOLI BAI
NOV 30, 2016
FOR EDUCATION PURPOSE ONLY
Note
Two lectures left: Nov. 28 and Nov. 30
Presentation due: 11:59pm Dec. 4.
Your 3 min talk: the part you are mostly proud of your project.
Label your presentatio
Homework 10 Solutions
Problem 1
Solution:
For this problem we must first develop the equation of motion
=
From Figure P5.3 we can easily see that the model spins down from
10.5 rad/s to zero roll rate when the motor drive is disengaged. This
implies tha
Aircraft Flight Dynamics
Lecture 16
XIAOLI BAI
NOV 16, 2016
FOR EDUCATION PURPOSE ONLY
NOTE
We will have a 30min lecture, and then you will take a 30min quiz.
If we have time, I will briefly talk about the derivations of the rotational kinematics, and t
Aircraft Flight Dynamics
Lecture 15
XIAOLI BAI
NOV 14, 2016
FOR EDUCATION PURPOSE ONLY
Note
A short quiz on Wed. Nov. 16. After 30min of lecture.
Focus on:
State space
Solutions of ODEs we have talked in the class
Perturbation concept
Difficult leve
Let the vectcr w dene the instantaneous rctatinnal velcrcitjvr cf the 5 frame
relative tn the N frame. Te avcid having tn integrate the directinn cnsine matrix
directlv given an a: time histnrjv, the Euler angle kinematic differential equatinns
are needed
Homework 6 Solutions
Problem 1
Solution:
a)
Reason#1
Inertia matrix will be time invariant since the mass distribution is not changing in
time relative to the body-fixed reference, also the controls and the measurements
are often defined in this frame.
Re
Quiz 4 Solutions
Problem 1
Solution:
a) Choose and
as our state variables and let 1 = and 2 =
1
S = [ ]
2
2
1 = =
; 2 = 2 = 3
2 + 4 = 32 21 + 4
-10points
Thus, the state space form can be written as:
S = +
1
0
[ ] = [
2
2
1 1
0
] [ ] + [ ] 1
3 2
4
0
1
Homework #6
Due: 5pm, Nov. 7, 2016
Problem 1:
(a) Provide two reasons of why equations of motion in airplane flight dynamics are always
expressed in a body-fixed reference and not in an inertial reference.
(5 points) Reason #1:
(5 points) Reason #2:
(b) (
ATTITUDE REPRESENTATION
Attitude cannot be represented by vector in 3-dimensional space, like
position or angular velocity, even though attitude is a 3-dimensional
quantity.
Attitude is always specified as a rotation relative to a base, or reference
frame
Homework 2 Solutions
Problem 1
Solution:
1) Determine the trim lift coefficient
= @
+ = @
=0
+
=0
pitch moment at zero lift is equal to 0.08 @
the slope of the Cm versus CL curve is 0.15
airplane is flying at the trim point = 0
=0
= 0.15
therefore 0
Homework #2
Due: 5pm, Sep. 26, 2015
1. Problems 2.1 (10pints)
2. Problems 2.3(15pints)
3. Consider a wing-body model with Cmac,wb 0.022 , h 0.33 , hac,wb 0.22 ,
awb 0.08 . The area and chord of the wing are 0.1 m 2 and 0.1 m, respectively. Now
assume that
Quiz #5
Due 7am Dec. 14 ( a box outside of B222)
Name_
(Print Your Name)
I certify that I have neither given help to, nor received help from, any individual in
matters relating to this examination.
_
Signature
NOTE:
1) Include your code in the submission
Aircraft Flight Dynamics
Lecture 5
XIAOLI BAI
SEP.21, 2015
Xiaoli Bai
Notice
Please leave ASAP after the lecture. We have a few students
take a quiz. Thanks for your corporation!
Differences between the slides and the book: some are from
the recommended
Quiz #3
Due in class 5pm Nov. 9 (submit paper)
Name_
(Print Your Name)
I certify that I have neither given help to, nor received help from, any individual in
matters relating to this examination.
_
Signature
NOTE:
1) Please write down your steps clearly.
Quiz #4
Due 7am Dec. 14 ( a box outside of B222)
Name_
(Print Your Name)
I certify that I have neither given help to, nor received help from, any individual in
matters relating to this examination.
_
Signature
NOTE:
1) Include your code in the submission
5.2 GRAM-SCHMIDT PROCESS AND QR
FACTORIZATION
How can we construct an orthonormal basis?
Say, from any basis v1, v2, . . . , vm of a subspace
V?
If V is a line with basis v1:
1
w1 =
v1
v1
When V is a plane with basis v1, v2, we rst
get w1 as above.
Next n
Aircraft Flight Dynamics
Lecture 19
XIAOLI BAI
NOV 16, 2015
FOR EDUCATION PURPOSE ONLY
Notes
HW 9: posted
Final Proposal:
start
Estimation: will guide you next class
Return those either disqualified or I have concerns
Others, feel free to discuss if y
Particle Kinematics: x-y Coordinates
Current unit: Particle Kinematics
Last class: Curvilinear, Circular, Projectile Motion
Today:
(a) Math Preliminaries: Dot notation, chain rule
(b) Path Known x-y Problem
(c) Parametric Equations x-y Problem
Math Prelim