Dragon Qualification Unit

 2010-026A

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First Falcon 9. Two stage rocket 6000 kg to LEO.

Stage 1 has 9 Merlin 1C total thrust 4400 kN. 3.6m dia. 33m long. guess: 248t f 12.4t dry

Stage 2 has 1 Merlin 1C, Isp 304 s 513 kN 345s burn time. 3.6m dia 6.0? m long guess: 65t f 3.9t dry

Launch from CC SLC40

Planned orbit 250 x 250 x 34.5.

F9-1
Date	Time	Event	Orbit
2010 Jun 4	1845:00	Launch by Falcon 9	CC LC40
		T+2:35 Stage 1 engines 1, 2 shutdown
		T+3:00 Stage 1 MECO engines 3-9 off
		T+3:05 St 1 sep
		T+3:09 St 2 ignition 1
	1848:19?	T+3:19 Fairing sep
	1848:55	140 km, Vi =3.50 km/s
	1849:50	189 km, 4.0 km/s
	1851:26	239 km, 5.0 km/s
	1853:20	256 km, 7.0 km/s
	1853:37	T+8:37 SECO-1
	1939	Predicted SES-2 1:08
	1940	Predicted SECO-2
	2004		89.63 235 x 276 x 34.50
	2025?	SES-2 "Test burp" 5.4m/s 0.1s? 14 kg?
	2025?	SECO-2	243 x 273 x 34.50

F9 Second stage:
   Estimate 4.2m high 3.6m dia
   Mass in orbit after S/C sep and depletion: UNKNOWN Guess at 2500 kg (3000 kg Ed Kyle 44000f?)
   Propulsion: 1 x Merlin Vac
   Targeted Orbital parameters: (first flight)
     Perigee x Apogee  250 x 250 km (needs confirmation) Inclination 51.6 deg

Dragon has 6000 kg cargo capacity and 1290 kg prop.

Capsule is 2.9m high 3.6m dia. Cone is 2.4m dia 1.8?m high.
Standard Trunk section is 2.3m high 3.6m dia.

F9/Dragon overall:
   Size 55.0m high 3.6m dia
   Mass 14000 kg empty?  325000 kg full

F9 First stage:
   Estimate 36.0m high 3.6m dia
   Includes 3.6m dia 8.0m high interstage
   Mass: UNKNOWN Guess at 11500 kg dry  (14730 kg Ed Kyle  276000 f)
   Apogee parameters: Guess 150 km, velocity unknown
   Propulsion: 9 x Merlin 1C

F9 Second stage:
   Estimate 4.2m high 3.6m dia
   Mass in orbit after S/C sep and depletion: UNKNOWN Guess at 2500 kg (3000 kg Ed Kyle 44000f?)
   Propulsion: 1 x Merlin Vac
   Targeted Orbital parameters: (first flight)
     Perigee x Apogee  250 x 250 km (needs confirmation) Inclination 51.6 deg

Dragon Spacecraft, total:
   Mass: UNKNOWN but F9 reported mass to 200 km, 51.6 deg is 9800 kg.
   Reported capacity of 6000 kg cargo and 1290 kg prop leaves 2500 kg
   for spacecraft (Capsule + Trunk) dry mass

Dragon Nose Cone:
   Cone is rounded cap about 2.4m dia 1.8m? high
   Mass: UNKNOWN
   Separation time: UNKNOWN seconds after launch

Dragon Capsule:
   Capsule is 2.9m high 3.6m dia truncated cone.
   Mass: UNKNOWN
   Propulsion: 12 to 18 x  Draco 400N NTO/MMH thrusters (dummy on Qual)
   Propellant:  1290 kg NTO/MMH (not on Qual)
   Separation: Not clear if Capsule and Trunk will sep on Qual S/C

Dragon Trunk:
   Extended Trunk is 4.3m high 3.6m dia, this seems to be the version being used
   Mass: UNKNOWN
   Separation: Trunk and Falcon Stage 2 will separate on Qual S/C  (confirm?)
   Sep time:  UNKNOWN time after stage 2 engine cutoff.

F9 Typical GTO
Date	Time	Event	Orbit
		Launch from CC
		T+2:35 Stage 1 engines 1, 2 shutdown
		T+2:54 Stage 1 MECO engines 3-9 off
		T+2:56 St 1 sep
		T+2:59 St 2 ignition 1
		T+3:19 Fairing sep
		T+7:55 SECO-1
		T+24:48 St 2 ignition 2
		T+25:44 SECO-2
		T+5:31:53 RCS-1
		T+5:49:28 RCS cutoff
		T+5:49:38 Stage 2 sep from payload