Precision Aiming - Revision history

Smaldonado: Changed image align to right

2015-12-05T11:03:00Z

Changed image align to right

← Older revision		Revision as of 11:03, 5 December 2015
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			[[File:PrecisionAiming.png\|frame\|right]]

	If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's [[OpComms]] team.		If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's [[OpComms]] team.

	~~[[File:PrecisionAiming.png\|frame\|center]]~~

	Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.		Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

Smaldonado: Added image

2015-12-05T11:01:42Z

Added image

← Older revision		Revision as of 11:01, 5 December 2015
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	If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's [[OpComms]] team.		If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's [[OpComms]] team.

			[[File:PrecisionAiming.png\|frame\|center]]

	Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.		Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

Smaldonado: Added to Optical Communications category

2015-08-11T06:11:21Z

Added to Optical Communications category

← Older revision		Revision as of 06:11, 11 August 2015
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	It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].		It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].

			[[Category:Optical Communications]]

Ehillstrom at 05:54, 30 July 2015

2015-07-30T05:54:52Z

← Older revision		Revision as of 05:54, 30 July 2015
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	If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's OpComms team.		If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's [[OpComms]] team.

	Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.		Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

	It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].		It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].

Ehillstrom at 04:40, 30 July 2015

2015-07-30T04:40:39Z

← Older revision		Revision as of 04:40, 30 July 2015
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	If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's OpComms team.		If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's OpComms team.

	Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.		Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians [https://directory.eoportal.org/web/eoportal/satellite-missions/s/spot-4] and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

	It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].		It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].

Ehillstrom at 04:38, 30 July 2015

2015-07-30T04:38:25Z

← Older revision		Revision as of 04:38, 30 July 2015
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	Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.		Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

	It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability .		It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability [http://bluecanyontech.com/wp-content/uploads/2015/05/XB1-Data-Sheet_1.0.pdf].

Ehillstrom: Created page with "If the beam divergence of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam..."

2015-07-30T04:36:21Z

Created page with "If the beam divergence of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam..."

New page

If the [[beam divergence]] of a transmitter is small, i.e. it forms a tighter cone, then more power actually reaches the receiver. However, low divergence means that the beam must be very well aligned for the spot to actually coincide with the receiver aperture. By contrast, if the transmit beam is wider, the spot becomes larger and it is easier to hit the receiver, but less power will be transmitted into the receiver system. This tradeoff is an ongoing high-level design question for SSI's OpComms team.

Precision pointing is arguably the greatest challenge in satellite optical communications. Given the extremely long distances involved, extremely accurate pointing is required to achieve a link of sufficient power. For example, the ESA [[ARTEMIS and SPOT-4]] inter-satellite link required a pointing error of less than 10 microradians and NASA’s [[LLCD]] was designed to have a pointing stability of just 4 microradians . Achieving this kind of precision with a mechanism that must withstand the shock and vibrations levels of launch and payload deployment is even more difficult.

It is likely not technically feasible to achieve this level of pointing precision in a CubeSat in the near future, however there is a lot of promising work in this field. One CubeSat components manufacturer, for example, is offering a CubeSat bus that claims +/- 0.002 degree (34.9 microradian) pointing accuracy with 1 arc second stability .