Back Falcon 9 v1.0 Czech Falcon 9 v1.0 Finnish Falcon 9 v1.0 Italian Falcon 9 v1.0 Latvian/Lettish Falcon 9 v1.0 Polish Falcon 9 v1.0 Portuguese Falcon 9 v1.0 Swedish Falcon 9 v1.0 Vietnamese
 A Falcon 9 v1.0 launches with an uncrewed Dragon spacecraft on a cargo resupply mission to the International Space Station in March 2013, the fifth and final flight of a version 1.0 Falcon 9. | |
| Function | Orbital medium-lift launch vehicle |
|---|---|
| Manufacturer | SpaceX |
| Country of origin | United States |
| Project cost | $ 300 million (including Dragon)[1][2] |
| Cost per launch | $54–59.5 million[3] |
| Cost per year | 2012 m |
| Size | |
| Height | 47.8 m (157 ft)[3] |
| Diameter | 3.66 m (12.0 ft) |
| Mass | 333,400 kg (735,000 lb)[3] |
| Stages | 2 |
| Capacity | |
| Payload to LEO | |
| Mass | 9,000 kg (20,000 lb)[4] |
| Payload to GTO | |
| Mass | 3,400 kg (7,500 lb)[4] |
| Associated rockets | |
| Family | Falcon 9 |
| Derivative work | Falcon 9 v1.1 |
| Launch history | |
| Status | Retired |
| Launch sites | Cape Canaveral SLC-40 |
| Total launches | 5 |
| Success(es) | 4 |
| Partial failure(s) | 1 (secondary payload only) |
| First flight | June 4, 2010[5] |
| Last flight | March 1, 2013 |
| Type of passengers/cargo | Dragon |
| First stage | |
| Powered by | 9x Merlin 1C[3] |
| Maximum thrust | 4,940 kN (1,110,000 lbf) |
| Specific impulse | |
| Burn time | 170 s |
| Propellant | LOX / RP-1 |
| Second stage | |
| Powered by | 1x Merlin 1C vacuum |
| Maximum thrust | 445 kN (100,000 lbf) |
| Specific impulse | 342 s (3.35 km/s) [6] |
| Burn time | 345 s |
| Propellant | LOX / RP-1 |
The Falcon 9 v1.0 was the first member of the Falcon 9 launch vehicle family, designed and manufactured by SpaceX in Hawthorne, California. Development of the medium-lift launcher began in 2005, and it first flew on June 4, 2010. The Falcon 9 v1.0 then launched four Dragon cargo spacecraft: one on an orbital test flight, then one demonstration and two operational resupply missions to the International Space Station under a Commercial Resupply Services contract with NASA.
The two stage vehicle was powered by SpaceX's Merlin engines, burning liquid oxygen (LOX) and rocket-grade kerosene (RP-1). Had the F9 V1.0 been used for launching payloads other than the Dragon to orbit, it would have launched 10,450 kg (23,040 lb) to low Earth orbit (LEO) and 4,540 kg (10,000 lb) to geostationary transfer orbit (GTO).
The vehicle was retired in 2013 and replaced by the upgraded Falcon 9 v1.1, which first flew in September 2013. Of its five launches from 2010 to 2013, all successfully delivered their primary payload, though an anomaly led to the loss of one secondary payload.
- ^ Elon Musk (May 4, 2011). "Why the US Can Beat China: The Facts About SpaceX Costs". SpaceRef. Retrieved 9 July 2017.[permanent dead link]
- ^ Cite error: The named reference
sx20110504was invoked but never defined (see the help page). - ^ a b c d "Falcon 9". SpaceX. 2012-11-16. Archived from the original on 23 March 2012. Retrieved 28 September 2013.
- ^ a b "SpaceX Falcon 9 Data Sheet". Space Launch Report. Archived from the original on September 10, 2012. Retrieved May 1, 2017.
{{cite web}}: CS1 maint: unfit URL (link) - ^ "Detailed Mission Data – Falcon-9 ELV First Flight Demonstration". Mission Set Database. NASA GSFC. Archived from the original on 2011-10-16. Retrieved 2010-05-26.
- ^ "SpaceX Falcon 9 Upper Stage Engine Successfully Completes Full Mission Duration Firing" (Press release). SpaceX. March 10, 2009. Archived from the original on March 6, 2012. Retrieved November 28, 2013.
© MMXXIII Rich X Search. We shall prevail. All rights reserved. Rich X Search