AES 4607 MSUD Satellite Tool Kit & Basic Orbital Mechanics Worksheet

User Generated

obljbaqrere

Science

AES 4607

Metropolitan State University of Denver

AES

Description

The attached document has 3 Two Line Element Sets(TLE) questions and I have no idea how to complete it.

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Satellite Tool Kit (STK) and Basic Orbital Mechanics Class AES 4607 Homework 3 Name ___________________ Date _____________________ Two Line Element (TLE) Set Google or use class presentations for Two Line element set and print the instructions. Use the two cards as shown below. Create them as if they were to be fed to a computer in terms of entering the numbers (i.e. – place the period in the correct place; enter zeros properly; no extraneous characters; and blank entry as shown in TLE instructions). If not given, do not enter. Label ALL entries. Use them to create TLE’s for the following orbits (NOTE: DO NOT enter N-DOT, n-DOUBLE DOT, or B-STAR): 1. Satellite Number - 6609A International Designator - 86017A Epoch = 29 Sep 2010 18:00:00.000 UTC Inclination = 45 deg Right Ascension of Node = 60deg Eccentricity = 0.105567 Argument of Perigee = 25 deg Mean Anomaly = 0deg Mean Motion = 13.1601 revs/day Period = 6565.31 sec Page 1 Satellite Tool Kit (STK) and Basic Orbital Mechanics Class AES 4607 2. Satellite Number – 7701B International Designator – 98017B Epoch = 29 Sep 2010 18:32:00.000 UTC Inclination = 1 deg Right Ascension of Node = 26 deg Eccentricity =0.00149477 Argument of Perigee = 40 deg Mean Anomaly = 0 deg Mean Motion = 1.42227 revs/day Period = 60747.8 sec 3. Satellite Number – 9701B rp= Page 2 Satellite Tool Kit (STK) and Basic Orbital Mechanics Class AES 4607 3. Satellite Number – 9701B International Designator – 95500 B Epoch = 29 Sep 2010 18:45:00.000 UTC Inclination = 16 deg Right Ascension of Node = 216 deg Eccentricity = 0.219999 Argument of Perigee = 20 deg Mean Anomaly = 0 deg Mean Motion = 3.67835 revs/day Period = 23488.8 sec Page 3 Satellite Tool Kit (STK) and Basic Orbital Mechanics Class AES 4607 4. Satellite Number – 9701B International Designator – 95500 B Epoch = 29 Sep 2010 19:00:00.000 UTC Inclination = 70 deg Right Ascension of Node = 58 deg Eccentricity = 0.149999 Argument of Perigee = 28 deg Mean Anomaly = 0 deg Mean Motion = 3.67835 revs/day Period = 200000 sec Page 4
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Explanation & Answer

Hi buddy! Thank you for waiting. Here is the document for your homework. I added an excel file should you need to make some changes on the table. As for the content, I made sure to follow the initial directions. It says there to label the essential components of the TLE but if the value is not given, it is advised not to enter anything, and so I did. Anyway, take a look at the file and let me know if any changes are needed to be made. I'd be obliged. Thank you so much! 😍

Satellite Tool Kit (STK) and Basic Orbital Mechanics Class AES 4607
Homework 3 Name ___________________ Date _____________________
Two Line Element (TLE) Set
Google or use class presentations for Two Line element set and print the instructions. Use the
two cards as shown below. Create them as if they were to be fed to a computer in terms of
entering the...


Anonymous
Awesome! Perfect study aid.

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