Falcon 9 v1.1
Second version of the SpaceX medium-lift launch vehicle / From Wikipedia, the free encyclopedia
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Falcon 9 v1.1 was the second version of SpaceX's Falcon 9 orbital launch vehicle. The rocket was developed in 2011–2013, made its maiden launch in September 2013,[7] and its final flight in January 2016.[8] The Falcon 9 rocket was fully designed, manufactured, and operated by SpaceX. Following the second Commercial Resupply Services (CRS) launch, the initial version Falcon 9 v1.0 was retired from use and replaced by the v1.1 version.
Function | Medium-lift launch vehicle |
---|---|
Manufacturer | SpaceX |
Country of origin | United States |
Cost per launch | $56.5M (2013) – 61.2M (2015)[1] |
Size | |
Height | 68.4 m (224 ft)[2] |
Diameter | 3.7 m (12 ft)[2] |
Mass | 505,846 kg (1,115,200 lb)[2] |
Stages | 2 |
Capacity | |
Payload to LEO (28.5°) | |
Mass | 13,150 kg (28,990 lb)[2] 10,886 kg (24,000 lb) (PAF structural limitation)[3] |
Payload to GTO (27°) | |
Mass | 4,850 kg (10,690 lb)[2] |
Associated rockets | |
Family | Falcon 9 |
Based on | Falcon 9 v1.0 |
Derivative work | Falcon 9 Full Thrust |
Comparable | |
Launch history | |
Status | Retired |
Launch sites | |
Total launches | 15 |
Success(es) | 14 |
Failure(s) | 1 |
Landings | 0 / 3 attempts |
First flight | 29 September 2013[4] |
Last flight | 17 January 2016 |
Type of passengers/cargo | Dragon, DSCOVR |
First stage | |
Powered by | 9x Merlin 1D |
Maximum thrust | Sea level: 5,885 kN (1,323,000 lbf)[2] Vacuum: 6,672 kN (1,500,000 lbf)[2] |
Specific impulse | Sea level: 282 seconds[5] Vacuum: 311 seconds[5] |
Burn time | 180 seconds[2] |
Propellant | LOX / RP-1 |
Second stage | |
Powered by | 1x Merlin 1D Vacuum |
Maximum thrust | 716 kN (161,000 lbf)[6] |
Specific impulse | 340 seconds[2] |
Burn time | 375 seconds[2] |
Propellant | LOX / RP-1 |
Falcon 9 v1.1 was a significant evolution from Falcon 9 v1.0, with 60 percent more thrust and weight. Its maiden flight carried out a demonstration mission with the CASSIOPE satellite on 29 September 2013, the sixth overall launch of any Falcon 9.[9]
Both stages of the two-stage-to-orbit vehicle used liquid oxygen (LOX) and rocket-grade kerosene (RP-1) propellants.[10] The Falcon 9 v1.1 could lift payloads of 13,150 kilograms (28,990 lb) to low Earth orbit, and 4,850 kilograms (10,690 lb) to geostationary transfer orbit,[1] which places the Falcon 9 design in the medium-lift range of launch systems.[11]
Beginning in April 2014, the Dragon capsules were propelled by Falcon 9 v1.1 to deliver cargo to the International Space Station under the Commercial Resupply Services contract with NASA.[12] This version was also intended to ferry astronauts to the ISS under a NASA Commercial Crew Development contract signed in September 2014[13] but those missions are now scheduled to use the upgraded Falcon 9 Full Thrust version, first flown in December 2015.
Falcon 9 v1.1 was notable for pioneering the development of reusable rockets, whereby SpaceX gradually refined technologies for first-stage boostback, atmospheric re-entry, controlled descent and eventual propulsive landing. This last goal was achieved on the first flight of the successor variant Falcon 9 Full Thrust, after several near-successes with Falcon 9 v1.1.