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JCSAT-14 commsat

 

Customer: SKY Perfect JSAT, Japan

 

Satellite bus: SSL (Loral) 1300
Satellite mass: ???? (usually 3-4.5 tonnes)
Satellite status: delivered to KSC

 

Launch date: NET mid April, 2016
Launch window: TBD
Stage landing type: TBD

 

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JCSAT-14 will replace and expand on the capacity of JCSAT-2A at the 154° East longitude orbital slot. The satellite is designed to provide service for broadcast, data networks, and internet connectivity for maritime and aviation for 15 years or longer.

 

1300overview.jpg

 

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https://www.neowin.net/forum/topic/1291928-falcon-9-jcsat-14-mission-thread/
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BFR will be built near the launch site and/or a canal near an ocean so it can be barged to a coastal launch facility. The odds are this will be Brownsville, Texas, a major seaport, as Musk testified before the Texas Legislature that this was in the cards.

 

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Oh yeah. It's about as large as you can go without additional arrangements/costs, routing around overpasses etc.

 

Routing is easy within Texas as they have a state software tool that automatically rerouts big loads for the carriers.

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  • 4 weeks later...

I have been hunting around to find the payload mass...and strangely....no public info from anyone.

 

SSL, Sky Perfect JSAT, Via Satellite, Aerospace Technology, SpaceX, NSF non paywall, reddit, and multiple data banks, that I have checked, show no mass, yet has no issue showing mass for prior instances.

 

 Ford → Space Systems Loral (SSL): SSL-1300

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The 1300, a powerful, space-proven platform for a wide range of services, has been in constant evolutionary development to deliver increasingly greater power, communications capability, and longer useful life, keeping the company in the forefront of satellite technology.

 

Total satellite power ranges from 5 to 12 kW continuously throughout the life of the spacecraft. On-board transmitter power – exceeding 5,000 RF watts – can accommodate as many as 70 active transponders. Launch mass tops out at approximately 5,500 kg. Standard satellites in the 1300 line will fit into a 4 meter launch-vehicle fairing.

 

The size and capabilities of the 1300 can be expanded to generate and process more power, and accommodate larger, more powerful payloads. In total, these changes can provide up to 40 percent more capacity than available in the basic model, ideal for any of today's demanding multi-band and spot-beam payloads. The expanded models feature total satellite power that ranges from 12 to 18 kW throughout the life of the spacecraft, and on-board transmitter power – approaching 10,000 RF watts – that can accommodate as many as 90 active transponders. Launch mass of the largest version tops out at approximately 6,700 kg. This version was earlier called 1300S.

 

With all of their features and power, satellites in the 1300 line will fit into a 5-meter launch-vehicle fairing.

 

Loral does not use (anymore?) the sometimes reported designators for sub-versions like 1300E, 1300HL, 1300S, 1300X.

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and

 

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Following failures of SSL-1300 models have occured:

 

EchoStar 5: one momentum wheel failed, thruster problems - potential shorting of lifetime
EchoStar 6: 2001 - partial thruster failure - performance loss.
GOES 9: 1998 - momentum wheel failure - total loss
PAS 6: 2004 - power failure - total loss
PAS 7: 2001 - 25% power loss - no service loss
Telstar 6: 2001 - control processor failure - no service loss
Telstar 7 (Intelsat Americas 7): electrical-distribution system failed on 28. November 2004. Contact was regained a few days later, with 22 transponders returning to operation.
Telstar 14 / Estrela do Sul 1: 2004 - solar wing deployment of one wing only partial - performance loss
Telstar 14R / Estrela do Sul 2: 2011 - solar wing deployment of one wing only partial - performance loss
Tempo 2 (DirecTV 6) 1997 - solarflare damaged 3 transponders and one solar array, occasional power outage - no performance loss

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http://space.skyrocket.de/doc_sat/ssloral-1300.htm

 

from the prior launches of this platform, the mass ranges from 3700 kg to 4700 kg.

 

The contract to build this payload was issued before the F9 became the full thrust version.

 

The transponders are not maxed out, they have allotted 44 out of 70 and 10 kW EOL.

 

Launch is for a transfer orbit (GTO-?, no mention)

 

After launch conference (CRS-8), It was stated that the next 2 launches would be ASDS, "hot and fast"

 

So far, I have not heard of any special flight accommodations being made for this launch.....

 

// With the above data, unless I missed something, it would appear....ASDS landing, enough fuel for 1 or 3 engine landing depending on velocity and what SpaceX would like to test next.

 

I will "guess" a little bit of a "punch" for better sat placement ( not as much as the last SES) and a 3 engine "slam test"....any thought's ?

 

:)

I'm a bit leery about the "hot and fast" ASDS landings. We know what happened last time one of those was attempted ... damage to the ASDS will slow down the launch cadence for the rest of the Spring.

 

I'd really like to see three more ASDS's put into service (Pacific, Atlantic and Gulf) to have some redundant capability.

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  On 21/04/2016 at 02:17, DocM said:

Small slip

 

Launch date: May 3
Launch window: 0122-0322 EDT (0522-0722 GMT) 

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Bummer.  Wish they would have "slipped" the liftoff time to a bit later. :)

 

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