MAE 180A – Spacecraft Guidance I

Winter 2008

Syllabus 

 

ANNOUNCEMENTS:

There will be no lecture on Tuesday March 4th.

One more question has been added to HW #3 (Problem 2.13 a)

Office Hours for Wednesday 2/13 and 2/20 have been cancelled due to room conflicts.  If there are any questions on the homework due Tuesday feel free to send me an email.

Midterm will be on Tuesday of Week 6  (2/12)

Office Hours for 1/23 will be from 3-4pm, EBU-II 305

 

Instructor: Professor M. Yousef Bahadori

Email: mbahadori@ucsd.edu

Office: EBU-II 562

Cell: (310) 480-2930

Office Hours: Tuesday 2:30-3:30pm, or by appointment

 

TA: Garrett Uyema

Email: guyema@ucsd.edu

Office Hours: Wednesday 2-3pm, EBU-II 305

 

Reader: Peng Liem

Email: peliem@ucsd.edu

 

Lectures: Tuesday and Thursday 3:30-4:50pm, U413-2

 

Textbook (required):

Fundamental of Astrodynamics” Bate, Mueller, and White, Dover Publications, Inc., 1971.

Recommended Text (not required):

Space Mission Analysis and Design, 3rd ed., J.R. Wertz & W.J. Larson (Eds.), Microcosm Press, Torrance, CA.  This is a collection of information on most of the basic topics of interest in planning a space mission and designing the spacecraft and its subsystems.  A very valuable book for anyone working in the field.  Website for order: www.astrobooks.com.

 

Grading:

Homework – 20%

Midterm – 35% (Tuesday, 2/12)        Solutions

Final – 45%  (Tuesday, March 18, 2008, 3:00-6:00pm)

ALL EXAMS ARE OPEN BOOK, BUT CLOSED NOTES/SOLUTIONS

 

Homework #1(due 1/24): 1.1, 1.2, 1.3, 1.5 (a,b,c,d), 1.8 (a,c,e), 1.9         Solutions

Homework #2 (due 2/7):  2.1, 2.2, 2.5 (c), 2.7, 2.8 (a)        Solutions

Homework #3 (due 2/19):  2.8(b), 2.10, 2.12, 2.13 (a) and 2.14       Solutions

For Problem 2.8(b), you will need the answer from Part (a) of the problem for the following vectors:

r = - 1.177 P - 0.208 Q   (DU);

v = 0.362 P - 0.344 Q         (DU/TU)

For Problem 2.13 (a), find e, p, unit vectors P, Q, and W, and velocity vector v2.

Homework #4 (due 2/28):         Solutions

3.1 (but use westward movement of the orbit at a rate of 5 degrees/day), 3.2, 3.6 (prove for each part whether the orbit is possible or impossible), 3.8

3.9 (for notation consistency, use r1 = 1 DU, r2 = 15 DU, and r3 = infinite);

 

Homework #5 (due 3/6):           Solutions

 

Problem 1:

 

The orbit of an Earth satellite has r(perigee) = 1.5 DU, and its parameter is p = 2.5 DU.  At point A on the

orbit, its true anomaly is 75 degrees. Calculate the time of flight to apogee (point B) after the satellite

passes three times through the perigee.  Provide the answer in "days-hours-minutes" for example: "5 days, 3 hours, 27 minutes."

 

Problem 2:

 

Using the data and results from Problem 1, show the following on a separate sheet (to-scale and detailed):

Earth (assumed spherical), satellite orbit, auxiliary circle, true anomaly for points A and B, perigee,

apogee, prime focus, vacant focus, and eccentric anomaly for points A and B.  Calculating the semi-minor

axis, b (in units of DU), helps in the drawing.  You can fit everything on a single 8.5"x11" sheet if you use

a scale of 2 cm = 1 DU for the drawing.

 

Problem 3:

 

A space probe is approaching the sun on a parabolic path (i.e., a one-time encounter), with perihelion

distance of 0.8 AU.  How many days is the probe closer than 1.1 AU to the sun?

 

Homework #6 (due 3/13):    8.10, 8.11, 8.12, 8.13, 8.14         Solutions