Problem 1. (50 points)
Determine the classic (Keplerian) orbit elements for a satellite with the
following Earth-centered inertial position and velocity:
rECI
624.5
= 7138.6 km,
0
v ECI
7.3905
= 0.3267 km/s
0
Determine all quantities to 4 signicant digits
Spacecraft Dynamics
Final Exam
ASE 366K
Prof. G. Lightsey
14 May 2009
Name:
This test is closed book. No notes or materials may be used during this
test except the 5 provided reference sheets (double sided) that have been
handed out separately. A pocket c
Talk about the evolution of the system and the center of mass. Mention details you see.
n -o) you should notice that decreasing the tolerance of the numerical integration will reduce the accuracy of the
model (i.e. Changes in the angular momentum and in t
Talk about the evolution of the system and the center of mass. Mention details you see.
n -o) you should notice that decreasing the tolerance of the numerical integration will reduce the accuracy of the
model (i.e. Changes in the angular momentum and in t
l)
Talk about the evolution of the system and the center of mass. Mention details you see.
n -o) you should notice that decreasing the tolerance of the numerical integration will reduce the accuracy of the
model (i.e. Changes in the angular momentum and i
n X-axla - moan n x-cm (m1 - Lunu)
-2
.4
6
1.5
l
n V-axla - mun n mm (m1 1mm) 5
0
X m." Angular Morn. - Mean Angular Mom. In X-axla vs Tlrna
O 0.5 I 1.5 2 2.5 3
The (T0)
0-10 Angular Morn. - Mean Angulu Mom. In Y-axla vs Tlma
-O.5
-I
o 05 1 :5 2 25 3
Tlr
ASE 366K - EXAM 1
OCTOBER 9, 2013
Version B
NAME:
Instructions: Do not open the exam until prompted. You are given two hours to complete
this exam. A single 3x5 sized Sheet of paper may be used for equations and supplementary
material. You are allowed to
Rocket Equation Problem
ASE 366K. Spacecraft Dynamics
Assigned: Tuesday October 20, 2015
Will be discussed in class: Wednesday October 21 or Monrday October26, 2015
Work the problem on your own and the solution will be covered in class
This problem consis
c.(r-U)(Lu"uww)
mw 'Munu) 11wz ' MUITU)
.737 . .737
8 a a: a: a:
a: a: a: a: a:
Klnetlc Enemy vs 11me
Potential Energy vs Tlme
0 05 I 15 Z 25 3
m. (TU)
c = Klneuc - Potential vs 11me
O
05 I 15 2 25 3
MOUU)
Comment for part(g):
% The center of mass for the 6 bodies moves linearly on all three axes, which
satisfies the law of conservation of linear momentum.
Comment for part(h and i):
% In the three graphs for the calculation of the angular momentum, we can s
Appendix 1
Astronomical Constants
The Sun
Mass = 1.989 ‘ I0 3” kg
Radius 2 6.9599 - 10 5 km
Usun = Gmsun : 1327 . ]011 ka-Ilegg
The Earth
Mass 2 5.9?4-101’4 kg
Radius = 6.37812 - 10 3 km
“earth 2 earl I1 = 86 ' 10 5 kl'l’lg’a‘IS"I
Mean distance from sun 2
ASE 366K Spacecraft Dynamics, Fall 2014
Reference Page of Equations that may be useful in this exam.
Newtons Second Law.
F =
d(mv)
dt
Newtons Law of Gravitation.
F g2 =
Gm1 m2
r
r3
r = r2 r1
,
with appropriate assumptions,
r
Gm1
r = 3r
r3
r
Denition of C
Spacecraft Dynamics
Assignment #8
ASE 366K
Prof. G. Lightsey
23 October 2014
Due: 30 October 2014, turn in at beginning of class.
Reading: Wiesel, Spaceight Dynamics, Chapter 7 (available on the
course web site).
Note: Midterm Exam 2 is scheduled for Tues
Spacecraft Dynamics
Assignment #7
ASE 366K
Prof. G. Lightsey
16 October 2014
Due: 23 October 2014, turn in at beginning of class.
Reading: BMW Chapter 3 (pages 151-173).
1
Problem 1.
On launch, the Space Shuttle did not directly inject into the nal missio
Spacecraft Dynamics
Assignment #6
ASE 366K
Prof. G. Lightsey
9 October 2014
Due: 16 October 2014, turn in at beginning of class.
Reading: BMW Chapter 2.15 (pages 140-143), 3-3.2 (pages 151-161).
Problem 1.
For this assignment, you will write a Matlab func
Spacecraft Dynamics
Assignment #5
ASE 366K
Prof. G. Lightsey
2 October 2014
Due: 9 October 2014, turn in at beginning of class
Reading: BMW Chapter 2.1 - 2.6 (pages 51-83).
Problem 1
BMW, Problem 2.2.
Problem 2.
Determine the classical orbital elements (a
Talk about the evolution of the system and the center of mass. Mention details you see.
n -o) you should notice that decreasing the tolerance of the numerical integration will reduce the accuracy of the
model (i.e. Changes in the angular momentum and in t
u w) hv-axls(ulu"Lu1'rU) hX-axls(lU"LU/TU)
L I
0| 0|
bl in
Angular Momentum In Xaxla va 11me
0 0.5 I 1.5 2 2.5 3
Tim (TU)
Angular Momentum In Y-axls vs Tlma
o 05 7 l 15 2 25 a
11m. (TU)
Angular Momentum In Z-axla vs Tine
o 05 1 15 2 25 7
Th. (TU) n X-ax
