2010-026A
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.
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| 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 |
