Spacecraft Dynamics and Control
(Lecture 15 Angular Momentum & Kinetic Energy)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buf
Spacecraft Dynamics and Control
(Lecture 16 Attitude Matrix)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~johnc
Un
Spacecraft Dynamics and Control
(Lecture 13 Transport Theorem)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~johnc
Spacecraft Dynamics and Control
(Lecture 12 Earth-Satellite Operations)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.ed
Spacecraft Dynamics and Control
(Lecture 11 Orbit Determination)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~john
Spacecraft Dynamics and Control
(Lecture 8 Orbital Coordinate Systems)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu
Spacecraft Dynamics and Control
(Lecture 10 Spacecraft Formation Flying)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.e
Spacecraft Dynamics and Control
(Lecture 9 Lagrange/Gibbs F and G Solution)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffal
Spacecraft Dynamics and Control
(Lecture 14 Newtonian Mechanics)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~john
Spacecraft Dynamics and Control
(Lecture 22 Energy/Momentum Integrals
and Attitude Control)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
SpacecraftDynamicsandControl
(Lecture21EulersRotationalEquations)
Dr.JohnL.Crassidis
UniversityatBuffaloStateUniversityofNewYork
DepartmentofMechanical&AerospaceEngineering
Amherst,NY142604400
[email protected]
http:/www.buffalo.edu/~johnc
University at B
A
Matrix Properties
T
HIS appendix provides a reasonably comprehensive account of matrix properties, which are used in the linear algebra of estimation and control theory. Several theorems are shown, but are not proven here; those proofs given are constru
Spacecraft Dynamics and Control
(Lecture 18 Attitude Kinematics)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~john
Spacecraft Dynamics and Control
(Lecture 19 Rotational Dynamics)
Dr. John L. Crassidis
University at Buffalo State University of New York
Department of Mechanical & Aerospace Engineering
Amherst, NY 14260-4400
[email protected]
http:/www.buffalo.edu/~john
MAE 425: Homework 3
Name
An object is detected passing by the earth. At the instant we decide to call t = 0, we measure the altitude to be
9000km from the Earths center, and the translational velocity to be 8 km/s perpendicular to the line between the
dir
MAE 425: Homework 8
Name
Looking down. In this HW we make some approximate calculations that are important for Earth-observing
satellites (EOS).
Use the following data:
G = 6.674 1011 m3 /(kgs2 ) ,
mE = 5.972 1024 kg ,
rE = 6.371 106 m
Assume that all orb
MAE 425: Homework 9
Name
Orbit Transfers
Use the following data:
G = 6.674 1011 m3 /(kgs2 ) ,
mE = 5.972 1024 kg ,
rE = 6.371 106 m
The spacecraft has a mass of 100 kg, and the ISP is 300 seconds.
1. Find the V for a due East launch from Kennedy Space Cen
MAE 425: Homework 2
Name
For a geo-stationary satellite weighing 400 kg,
1. Calculate the radius of the orbit (measured from the center of the Earth)
2. Calculate the scalar speed of the satellite in its orbit path relative to the center of the Earth
3. A
MAE 425: Project 2
Name
Venus: We investigate sending spacecraft on various trajectories to Venus!
Use the following data:
G = 6.674 1011 m3 /(kgs2 ) ,
mE = 5.972 1024 kg ,
rE = 6.371 106 m , dSE = 149, 600, 000 km
Assume that Venus is spherical, with a c
MAE 425: Homework 7
Name
Estimating orbits from data - 2 In a separate file HW7data, you are provided with a set of observations made
of an object from another object, both of which are believed to be in elliptical orbits around the same massive body.
The
MAE 425: Homework 3 Solution
Name
An object is detected passing by the earth. At the instant we decide to call t = 0, we measure the altitude to be
9000km from the Earths center, and the translational velocity to be 8 km/s perpendicular to the line betwee
MAE 425: Homework 4
Solution
Two-body problems?!?
Use the following data:
G = 6.674 1011 m3 /(kgs2 )
mE = 5.972 1024 kg
,
mS = 1.989 1030 kg
dSE = 92.96 106 mi
,
mM = 7.346 1022 kg
,
dEM = 378, 000 km
Also, assume that both the Earths orbit about the Sun,
MAE 425: Homework 8
Solution
Looking down. In this HW we make some approximate calculations that are important for Earth-observing
satellites (EOS).
Use the following data:
G = 6.674 1011 m3 /(kgs2 ) ,
mE = 5.972 1024 kg ,
rE = 6.371 106 m
Assume that all
MAE 425: Homework 1 Solution
Name
The sphere we live on
Lets become more familiar with spaceship Earth. For simplicity, assume the following values, and answer the
questions below:
The Sun is an inertial reference point
(The Sun orbits the center of the
MAE 425: Homework 6
Solution
Energy
Use the following data:
G = 6.674 1011 m3 /(kgs2 )
mE = 5.972 1024 kg
rE = 6.371 106 m
,
mM = 7.346 1022 kg
rM = 1.7375 106 m
,
1. Calculate the work done by Earths gravity for a 100 kg satellite launched from sea level