Computation of Azimuth and Elevation George H. Born

1 / 6

# Computation of Azimuth and Elevation George H. Born - PowerPoint PPT Presentation

Computation of Azimuth and Elevation George H. Born.

I am the owner, or an agent authorized to act on behalf of the owner, of the copyrighted work described.

## Computation of Azimuth and Elevation George H. Born

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.

- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -
Presentation Transcript
Computation of Azimuth and ElevationGeorge H. Born

These slides describe how to convert a spacecraft vector, , in ECEF or ECI coordinates to Azimuth and Elevation given geocentric latitude, east longitude, and height above the ellipsoid of a tracking station. ECEF coordinates are considered first.

is given

ECEF vector of spacecraft

Station location ( , , H)

ECEF frame

Geodetic latitude

East longitude

Height above ellipsoid

Computation of Azimuth and Elevation

1) Compute in the ECEF ( , , ) frame

and are the equatorial radius and flattening respectively of the reference ellipsoid

Computationof Azimuth and Elevation

2) Compute in ECEF coordinates

3) Now convert to coordinates

To get replace with the coordinates of .

Computation of Azimuth and Elevation

4) Compute Azimuth, , and Elevation, .

Computation of Azimuth and Elevation
• If the spacecraft vector is given in J2000 ECI coordinates (X, Y, Z) it is necessary to transform it into the ECEF frame. To be accurate this involves a series of five rotations to account for equatorial precession, nutation, Earth rotation, and polar motion. However, a close approximation can be obtained by only accounting for Earth rotation. This can be accomplished by computing the Greenwich sidereal time, , given by
• where is the rotation rate of the Earth, 0.72921158553 x 10-4 rad/sec, is the angle between the ECI X-axis and the prime meridian measured in the equatorial plane, and is the value of at the reference time, . The spacecraft vector in the ECEF frame is given by

Now proceed with step 1.

Then

Computation of Azimuth and Elevation

The value of at any UTC can be obtained by inserting a satellite into a scenario in STK. Set the orbit epoch and start time to the desired UTC, set the longitude of the ascending node to 0.0° and click the apply button. Then choose right ascention of the ascending node (RAAN). This will be the value of for the chosen time. Of course, one can also compute the Azimuth and Elevation in STK.

For example, at universal time coordinated, UTC, JAN 1, 2008, 0 h, 0 m, 0 sec, .

• References:
• Bate, Muller, and White, Fundamental of Astrodynamics, Dover, 1971,
• Chapter 2.
• Curtis, H. D., Orbital Mechanics for Engineering Students, Elsevier, 2005,
• Chapter 5.5.