This is a tale of a satellite-rocket pair re-union not seen in over 25 years, or more accurately between the children of both. For the duty of transporting new satellites for our beloved Global Positioning System (GPS) has always fell to the rockets named Delta (Delta II between 1989 and 2009, then the different Delta IV since 2010) since the experimental Block I satellites were launched in the 1980s on refurbished Atlas missiles (using a completely different orbit, plus launched out of California). Tomorrow, however, will finally see this rule being broken as an Atlas V is getting the job of lifting the newest satellite for the system - something that the Centaur has never done before.
The new GPS satellite, numbered SVN66 (SVN = Space Vehicle Number), will head for plane C, slot 2 to replace GPS IIA-25 (SVN33, launched March 1996), which in turn will become a reserve satellite.
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Launch coverage: (starts 5:18 pm EDT / 21:18 UTC)
Payload:
Launch Vehicle:
Launch Timeline & Ground Track:
Event|Time rel lift-off|Time UTC|Comment
RD-180 Engine Ignition|-0:00:02.7|21:37:58.3|
T=0 (Engine Ready)|0:00:00.0|21:38:00|
Liftoff (Thrust to Weight > 1)|0:00:01.1|21:38:01.1|
Begin Pitch/Yaw/Roll Maneuver|0:00:17.7|21:38:17.7|
Maximum Dynamic Pressure|0:01:18.4|21:39:18.4|
Atlas Booster Engine Cutoff (BECO)|0:04:04.4|21:42:04.4|
Atlas Booster/Centaur Separation|0:04:10.4|21:42:10.4|
Centaur First Main Engine Start (MES-1)|0:04:20.4|21:42:20.4|
Payload Fairing Jettison|0:04:28.4|21:42:28.4|
Centaur First Main Engine Cutoff (MECO-1)|0:17:07.1|21:55:07.1|1st Burn's Duration 00:12:46.7
Centaur Second Main Engine Start (MES-2)|3:17:37.8|00:55:37.8|
Centaur Second Main Engine Cutoff (MECO-2)|3:19:07.1|00:57:07.1|2nd Burn's Duration 00:01:29.3
GPS IIF-4 Separation|3:23:52.8|01:01:52.8|
Links:
The new GPS satellite, numbered SVN66 (SVN = Space Vehicle Number), will head for plane C, slot 2 to replace GPS IIA-25 (SVN33, launched March 1996), which in turn will become a reserve satellite.
Launch date:
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May 15, 2013
Window open:
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21:38 UTC / 5:38 p.m. EDT
Window close:
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21:56 UTC / 5:56 p.m. EDT
Launch site:
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SLC-41, CCAFS, Florida
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[highlight]L[eventtimer]2013-5-15 21:38;%c%%ddd%/%hh%:%mm%:%ss%[/eventtimer][/highlight]
Mission Insignia
Launch coverage: (starts 5:18 pm EDT / 21:18 UTC)
- ULA webcast: http://www.ulalaunch.com/site/pages/Multimedia_Webcast.shtml
- ULA webcast 2: http://mfile.akamai.com/29730/live/reflector:51679.asx?bkup=50982
- Spaceflight Now: http://www.spaceflightnow.com/atlas/av037/status.html
Payload:
GPS-2F (Global Positioning System) or Navstar-2F (Navigation System using Timing And Ranging) satellites are the fourth evolution stage of the second generation of the GPS satellites. Improvements included an extended design life of 12 years, faster processors with more memory, and a new civil signal on a third frequency.
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Operator:|
Contractors:|
Equipment:|
Configuration:|
Dimensions:|
Propulsion:|
Power:|
Launch Weight:|
On-orbit Weight:|
Orbit:|
Specifications
Type / Application:
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- Navigation
Operator:|
- USAF
Contractors:|
- Boeing
Equipment:|
- 2 Rubidium clocks
- 1 Cesium clock
Configuration:|
- ?
Dimensions:|
- 8.17 ft x 6.67 ft x 7.33 ft (stowed)
Propulsion:|
- ?
Power:|
- 2 deployable solar arrays
- batteries
- 1900 watts (end of life)
Launch Weight:|
- 1630 kg (3590 lb) - max wet weight at launch
On-orbit Weight:|
- 1466 kg (3230 lb) - initial on-orbit estimated wet weight
Orbit:|
- 20200 * 20200 km, 55° inc.)
The Atlas 5 was developed by Lockheed Martin Commercial Launch Services as part of the US Air Force Evolved Expendable Launch Vehicle (EELV) program. Each Atlas 5 rocket uses a Russian-built RD-180 engine burning kerosene and liquid oxygen to power its first stage and an American-built RL10 engine burning liquid hydrogen and liquid oxygen to power its Centaur upper stage.
The Atlas 5 launcher will fly in the so-called 401 configuration, denoting a 4-meter payload fairing, no strap-on solid rocket boosters and a single-engine Centaur upper stage.
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The Atlas 5 launcher will fly in the so-called 401 configuration, denoting a 4-meter payload fairing, no strap-on solid rocket boosters and a single-engine Centaur upper stage.
Specifications
Gross mass:
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- 338640 kg (746570 lb)
Payload:
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- 7095 kg (15641 lb) SSO
- 4950 kg (10910 lb) GTO
Height:
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- 58.30 m (191.20 ft)
Diameter:
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- 3.81 m (12.49 ft)
Span:
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- 3.81 m (12.49 ft)
Thrust:
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- 3827.00 kN (860343 lbf)
Launch Timeline & Ground Track:
RD-180 Engine Ignition|-0:00:02.7|21:37:58.3|
T=0 (Engine Ready)|0:00:00.0|21:38:00|
Liftoff (Thrust to Weight > 1)|0:00:01.1|21:38:01.1|
Begin Pitch/Yaw/Roll Maneuver|0:00:17.7|21:38:17.7|
Maximum Dynamic Pressure|0:01:18.4|21:39:18.4|
Atlas Booster Engine Cutoff (BECO)|0:04:04.4|21:42:04.4|
Atlas Booster/Centaur Separation|0:04:10.4|21:42:10.4|
Centaur First Main Engine Start (MES-1)|0:04:20.4|21:42:20.4|
Payload Fairing Jettison|0:04:28.4|21:42:28.4|
Centaur First Main Engine Cutoff (MECO-1)|0:17:07.1|21:55:07.1|1st Burn's Duration 00:12:46.7
Centaur Second Main Engine Start (MES-2)|3:17:37.8|00:55:37.8|
Centaur Second Main Engine Cutoff (MECO-2)|3:19:07.1|00:57:07.1|2nd Burn's Duration 00:01:29.3
GPS IIF-4 Separation|3:23:52.8|01:01:52.8|
Links:
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