Spacecraft Dynamics
Assignment #5 Solutions
ASE 366K
Prof. Todd E. Humphreys
October 15, 2010
Problem 1. Given that the satellite is in an elliptical orbit(e = 1) about
the Earth ( = 1 DU 3 /T U 2 ) with a semi-major axis, a = 1.2 DU .
(a) Recall that the
Practice Problems: ASE366K Spacecraft Dynamics
Magruder
Spring 2011
Problem 6.24) Spacecraft B and C, which are in the same elliptical earth orbit 1,
are located at the true anomalies shown. At this instant, spacecraft B executes a
phasing maneuver so as
ASE 366K Problem Set #6
Posting Date: October 18, 2010
Due Date:
October 22, 2010
Turn in homework at the beginning of class. If you have any doubts about your ability to make
it to class on time, you may turn in your problem solutions by sliding them und
Equations
ASE 366K Spacecraft Dynamics
Spring 2011
Note the following constants:
e (Earth) = 398600.44 km3/sec2
s (Sun) = 1.3271x1011 km3/sec2
e = 360/rotation time of the Earth
re = radius of the Earth = 6378.14 km
G = 6.67x10-20 km3/(sec2-kg)
1 sidereal
Equations
ASE 366K Spacecraft Dynamics
Spring 2011
Note the following constants:
e (Earth) = 398600.44 km3/sec2
s (Sun) = 1.3271x1011 km3/sec2
e = 360/rotation time of the Earth
re = radius of the Earth = 6378.14 km
G = 6.67x10-20 km3/(sec2-kg)
1 sidereal
Equations
ASE 366K Spacecraft Dynamics
Spring 2011
Note the following constants:
e (Earth) = 398600.44 km3/sec2
s (Sun) = 1.3271x1011 km3/sec2
e = 360/rotation time of the Earth
re = radius of the Earth = 6378.14 km
G = 6.67x10-20 km3/(sec2-kg)
1 sidereal
ASE 367K
Quiz
#1
Closed Book
1. (30pts) Consider a rocket-powered aircraft accelerating at constant altitude.
a. (5) Draw a free-body diagram showing the coordinate systems,
the angles, and the forces for this particular problem.
b. (20) Starting from the
Spacecraft Dynamics
Preliminary Exam #2 Solutions
ASE 366K
Prof. Todd E. Humphreys
November 11, 2010
Problem 1. Given that = 1 DU 3 /T U 2 and that
0.0
0.8
r = 1.1 DU v = 0.0 DU/T U
0.0
1.0
(a) Determine the canonical orbital elements a, e, i, , , f . The
Spacecraft Dynamics
Preliminary Exam #1 Solutions
ASE 366K
Prof. Todd E. Humphreys
October 1, 2010
Problem 1. Given that the eccentricity of the asteroid (e = 1), G =
6.67 1020 km3 /kg s2 , and msun = 1.989 1030 kg .
(a) The value of for a two body system
Name
Problem _
_Solutions_
Page _
Problem 1. 20 points (4 points per part).
Short answer / short calculation questions. Write your answer and any calculations on a separate page.
(a) The
minimum
inclination a satellite can achieve is equal to the
latitude
Spacecraft Dynamics
Assignment #6 Solutions
ASE 366K
Prof. Todd E. Humphreys
October 22, 2010
Problem 1. Given that Alt = 0.5 DU , v = 2/3 DU/T U , = 30 ,
RE = 1 DU , and = 1 DU 3 /T U 2 the energy, semi-major axis, and eccentricity
of the object can be c
ASE 366K Problem Set #7
Posting Date: October 25, 2010
Due Date:
October 29, 2010
Turn in homework at the beginning of class. If you have any doubts about your ability to make
it to class on time, you may turn in your problem solutions by sliding them und
Spacecraft Dynamics
Assignment #7 Solutions
ASE 366K
Prof. Todd E. Humphreys
October 29, 2010
Problem 1. Given that = 3.986 105 km3 /s2 and that the initial conditions at ti = 2010 Oct 25 00:00:00 UTC are
R (ti ) = 250.296
723.071
V (ti ) = 2.184495
7.110
ASE 366K Problem Set #8
Posting Date: October 29, 2010
Due Date:
November 5, 2010
Turn in homework at the beginning of class. If you have any doubts about your ability to make
it to class on time, you may turn in your problem solutions by sliding them und
Spacecraft Dynamics
Assignment #8 Solutions
ASE 366K
Prof. Todd E. Humphreys
November 5, 2010
Problem 1. Given that = 1 DU 3 /T U 2 the total vtotal required to
transfer between two circular co-planar orbits of radii r1 = 2 DU and r2 = 5 DU
using a transf
ASE 366K Problem Set #9
Posting Date: November 15, 2010
Due Date:
November 19, 2010
Turn in homework at the beginning of class. If you have any doubts about your ability to make
it to class on time, you may turn in your problem solutions by sliding them u
Spacecraft Dynamics
Assignment #9 Solutions
ASE 366K
Prof. Todd E. Humphreys
November 19, 2010
Problem 1. Assuming zero drag, no gravitational eld, and that the initial
(ignition) velocity is zero.
(a) A single-stage rocket is designed to the following sp
ASE 366K Problem Set #10
Posting Date: November 22, 2010
Due Date:
December 3, 2010
Turn in homework at the beginning of class. If you have any doubts about your ability to make
it to class on time, you may turn in your problem solutions by sliding them u
Spacecraft Dynamics
Assignment #10 Solutions
ASE 366K
Prof. Todd E. Humphreys
December 3, 2010
Problem 1. To prove that CC T = I and C T C = I , recall that
X = CT x
x = CX
(1)
so premultiplying both of these equations by C T and C respectively
CT x = CT
Spacecraft Dynamics
Preliminary Exam #1 Solutions
ASE 366K
Prof. Todd E. Humphreys
October 1, 2010
Problem 1. Given that the eccentricity of the asteroid (e = 1), G =
6.67 1020 km3 /kg s2 , and msun = 1.989 1030 kg .
(a) The value of for a two body system
Performance Report
ASE-367K, Spring 2016, Homework 5&6
(Due date: April 5th , 2016)
From the documents available on the course website on canvas, choose an aircraft and
give a detailed report describing its performance. Organize your report around the fol