GOES I-M - Revision history

Ben at 19:44, 10 November 2009

2009-11-10T19:44:41Z

Ben: /* Reference */

2009-06-30T15:13:15Z

‎Reference

Ben at 15:11, 30 June 2009

2009-06-30T15:11:30Z

Ben at 20:32, 8 May 2009

2009-05-08T20:32:15Z

Ben: New page: The Geostationary Operational Environmental Satellite (GOES) I-M series use solar torque to help their attitude control systems. [[wikipedia:Reaction wheel|Momentum whee...

2009-05-08T20:31:58Z

New page: The Geostationary Operational Environmental Satellite (GOES) I-M series use solar torque to help their attitude control systems. [[wikipedia:Reaction wheel|Momentum whee...

New page

The [[wikipedia:GOES|Geostationary Operational Environmental Satellite (GOES)]] I-M series use solar torque to help their attitude control systems. [[wikipedia:Reaction wheel|Momentum wheels]] point the spacecraft, but can build up speed over time until they reach the limit of their bearings. One solar array sticks out one side of the GOES I-M satellites, which is balanced by a small conical "solar sail" on the end of a long boom on the other side. A trim tab on the end of the solar array controls the solar torque, which can slow down the wheels by torquing in opposite directions. This saves propellant that would otherwise be required to slow down the wheels.

===See also===
* The [[wikipedia:INSAT|Indian National Satellite System]] uses a similar system

===Reference===
* [http://goes.gsfc.nasa.gov/text/databook GOES I/M Databook]
** [http://goes.gsfc.nasa.gov/text/databook/section02.pdf Chapter 2: The GOES Spacecraft Configuration]

← Older revision		Revision as of 19:44, 10 November 2009
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	[[Category:Attitude Control]]		[[Category:Attitude Control]]
		+	[[Category:Missions]]

← Older revision		Revision as of 20:32, 8 May 2009
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	* [http://goes.gsfc.nasa.gov/text/databook GOES I/M Databook]		* [http://goes.gsfc.nasa.gov/text/databook GOES I/M Databook]
	** [http://goes.gsfc.nasa.gov/text/databook/section02.pdf Chapter 2: The GOES Spacecraft Configuration]		** [http://goes.gsfc.nasa.gov/text/databook/section02.pdf Chapter 2: The GOES Spacecraft Configuration]
		+
		+	[[Category:Attitude Control]]

@@ Line 5: / Line 5: @@
 ==Reference==
-* [http://goes.gsfc.nasa.gov/text/databook GOES I/M Databook]
+* [http://goes.gsfc.nasa.gov/text/goes.databook.html GOES I/M Databook]
 ** [http://goes.gsfc.nasa.gov/text/databook/section02.pdf Chapter 2: The GOES Spacecraft Configuration]
 [[Category:Attitude Control]]

@@ Line 1: / Line 1: @@
 The [[wikipedia:GOES|Geostationary Operational Environmental Satellite (GOES)]] I-M series use solar torque to help their attitude control systems. [[wikipedia:Reaction wheel|Momentum wheels]] point the spacecraft, but can build up speed over time until they reach the limit of their bearings. One solar array sticks out one side of the GOES I-M satellites, which is balanced by a small conical "solar sail" on the end of a long boom on the other side. A trim tab on the end of the solar array controls the solar torque, which can slow down the wheels by torquing in opposite directions. This saves propellant that would otherwise be required to slow down the wheels.
-===See also===
+==See also==
 * The [[wikipedia:INSAT|Indian National Satellite System]] uses a similar system
-===Reference===
+==Reference==
 * [http://goes.gsfc.nasa.gov/text/databook GOES I/M Databook]
 ** [http://goes.gsfc.nasa.gov/text/databook/section02.pdf Chapter 2: The GOES Spacecraft Configuration]
 [[Category:Attitude Control]]