AE 202
Problem Set 1
(due Sep 7)
Fall 2016
1. A space shuttle is in an orbit about the Earth with a semimajor axis of 7000 km and an
eccentricity of 0.05. What are the perigee and apogee altitudes of the shuttle?
(Earth radius = 6378 km)
2. What is the pe
Aerospace Flight Mechanics
Interplanetary Mission Analysis
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 9 of Orbital Mechanics by Prussing and Conway.
Interplanetary Mission Analys
AE 202
Problem Set 3
(due Oct 5)
Fall 2016
1. Suppose astronauts go to Mars via a Hohmann transfer (ignore the eccentricity of the
Martian orbit).
Mars semimajor axis = 1.5237 AU
a) After arrival, how many days must they spend on Mars before it is possibl
Aerospace Flight Mechanics
The Orbit in Space
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 3 of Orbital Mechanics by Prussing and Conway.
The Orbit in Space
A coordinate system is
Aerospace Flight Mechanics
Rocket Dynamics
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 6 of Orbital Mechanics by Prussing and Conway.
Rocket Dynamics
The force provided by a rocke
AE 202
Problem Set 2
(due Sep 21)
Fall 2016
1. A satellite is in an elliptic orbit with e = 0.5. Using a starting value of E0 = M, determine
the value of E to an accuracy of 10-4 rad at the time the satellite is one-quarter period past
periapse passage. L
Aerospace Flight Mechanics
The n-Body Problem
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 1 of Orbital Mechanics by Prussing and Conway.
Orbital Mechanics
Astrodynamics: Study of
Aerospace Flight Mechanics
Position in Orbit as a Function of Time
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 2 of Orbital Mechanics by Prussing and Conway.
Position in Elliptica
Aerospace Flight Mechanics
Impulsive Orbit Transfer
Dr. Christian M. Chilan
Department of Aerospace Engineering
University of Illinois at Urbana-Champaign
Based on Chapter 7 of Orbital Mechanics by Prussing and Conway.
Impulsive Orbit Transfer
General cla
AE 202
Outline for AE 202
Astrodynamics
Keplers Laws of Planetary Motion
Process of their discovery
Orbit geometry
Newtons Laws of Motion and Gravitation
Potential function
Conservation of mechanical energy
Conservation of angular momentum
Derivation of v
AE202
Midterm Exam
(55 minutes, open book)
aEarth = 1AU,
aVenus = 0.723AU,
Spring 2011
1AU = 1.496108km , sun = 1.3271011km3.s-2
Earth to Venus sample return mission.
a)
Find the total v required for the Earth-Venus leg of the mission. Assume that both or
AE202
Problem Set 6:
DUE: 27 April 2011
Spring 2011
Read Anderson Secs. 5.1-5.5, 5.11 (just for fun, we wont discuss supersonic flight in class), 5.13-5.15.
1. Find the temperature, pressure and density for the standard atmosphere at altitudes of 2000m,
7
AE202
Problem Set 5:
DUE: 20 April 2011
Spring 2011
1. Three astronauts are about to leave Mars, departing in their Martian lander vehicle.
a) They need to leave the surface (v=0) for low Martian orbit, i.e. orbit at a constant altitude of
200km.
What vel
AE202
Problem Set 4
DUE: 18 March 2011
Spring 2011
Include a printout of your MATLAB code with your homework
solutions.
Email electronic copies of your MATLAB functions to
[email protected] In a single zip (or rar) file named
LastName_FirstName_AE202
AE202
Problem Set 3: MATLAB
DUE: 9 March 2011
Spring 2011
1. Anderson Problems:
a. 8.3
b. 8.4
c. 8.5
d. 8.9
e. 8.10
f. 8.11
2.
aMars=1.524 AU
1AU = 1.496 108km
eMars=0.0934
Sun = GMSun = 1.3271011km3.s-2
a. What is the speed of Mars at aphelion and at per
AE202
Problem Set 2: MATLAB
DUE: 23 February 2011
Instructions for
submitting
MATLAB code:
Spring 2011
Include a printout of your MATLAB code with your homework
solutions.
Email electronic copies of your MATLAB functions to
[email protected] In a sin
AE202
Problem Set 2: MATLAB
DUE: 23 February 2011
Spring 2011
Include a printout of your MATLAB code with your homework
solutions.
Email electronic copies of your MATLAB functions to
[email protected] In a single zip (or rar) file named
LastName_Firs
AE202
Instructions for
submitting
MATLAB code:
Problem Set 1: MATLAB
DUE: 9 February 2011
Spring 2011
Include a printout of your MATLAB code with your homework
solutions.
Email electronic copies of your MATLAB functions to
[email protected] In a sing
AE202
Instructions for
submitting
MATLAB code:
Problem Set 1: MATLAB
DUE: 9 February 2011
Spring 2011
Include a printout of your MATLAB code with your homework
solutions.
Email electronic copies of your MATLAB functions to
[email protected] In a sing
Numerical Integration in MATLAB
Aditya Paranjape
February 16, 2011
Dierential Equations
A dierential equation describes the variation of a variable, called the state
variable (x ), as a function of an independent variable (t ).
x (t ) =
dx
= f (x (t ), t
AE202
Aerospace Flight
Mechanics
Lecture 6: Symbolic Computation
Symbolic Computation
MATLAB symbolic toolbox
lets you perform symbolic (algebraic) manipulations
uses MuPAD as its computer algebra systems (CAS)
Allows you to perform:
Linear algebraic
AE202
Aerospace Flight
Mechanics
Lecture 4: Linear Systems and
Matrix Operations
Linear systems
Linear systems of equations have many applications in engineering
Structural analysis
Finite Element analysis
Electrical networks
Control engineering
Solv
AE202
Aerospace Flight
Mechanics
Lecture 3: Data Visulaization
Data Visualization
Graphs are a useful and powerful way to presenting information
MATLAB has many inbuilt functions to creates graphs and manipulate
them
2D
3D
Standard line graphs
Histogr
AE202
Aerospace Flight
Mechanics
Lecture 2: Programming in
MATLAB
Repetition
May want to repeat certain operations multiple times
Use loops
In general want to avoid loops in MATLAB, using vectorization is much
faster.
Two basic kinds of loops
for
Lo