Falcon Heavy
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 Drawing of the Falcon Heavy reusable (left) and expendable (right) configurations | |
| Function | Orbital launch vehicle and potential Lunar launch vehicle[1] |
|---|---|
| Manufacturer | SpaceX |
| Country of origin | United States |
| Cost per launch (2014) | $85M for up to 6,400 kg to GTO |
| Size | |
| Height | 68.4 m (224 ft) |
| Diameter | 3.66 m (12.0 ft) |
| Mass | 1,462,836 kg (3,225,001 lb) |
| Stages | 2+ |
| Capacity | |
| Payload to LEO | 53,000 kg (117,000 lb) |
| Payload to GTO | 21,200 kg (46,700 lb) |
| Launch history | |
| Status | In Development |
| Launch sites | KSC LC-39A Vandenberg SLC-4E[2] |
| Total launches | 0 |
| Successes | 0 |
| Failures | 0 |
| First flight | 2015 (projected) |
| Boosters (Stage 0) | |
| No. boosters | 2 |
| Engines | 9 Merlin 1D |
| Thrust | 5,880 kN (1,323,000 lbf)(sl) |
| Total thrust | 17,615 kN (3,960,000 lbf) (total sea-level thrust of boosters plus core)[3] |
| Specific impulse | Sea level: 282 sec Vacuum: 311 sec |
| Burn time | Unknown |
| Fuel | LOX/RP-1 |
| First stage | |
| Engines | 9 Merlin 1D |
| Thrust | 5,880 kN (1,323,000 lbf)(sl) |
| Specific impulse | Sea level: 282 sec Vacuum: 311 sec |
| Burn time | |
| Fuel | LOX/RP-1 |
| Second stage | |
| Engines | 1 Merlin 1D Vacuum |
| Thrust | 801 kN (180,000 lbf) |
| Specific impulse | Vacuum: 342 sec [4] |
| Burn time | 375 seconds[5] |
| Fuel | LOX/RP-1 |
Falcon Heavy (FH), previously known as the Falcon 9 Heavy, is a spaceflight launch system being designed and manufactured by SpaceX. The Falcon Heavy is a variant of the Falcon 9 v1.1 launch vehicle and will consist of a standard Falcon 9 rocket core, with two additional Falcon 9 first stages as strap-on boosters[6] – this will increase the low Earth orbit (LEO) payload to about 53 tonnes, compared to about 13 tonnes for a Falcon 9. The first launch is expected in 2015.[7]
Design
The Falcon Heavy configuration consists of a standard Falcon 9 with two additional Falcon 9 first stages acting as liquid strap-on boosters,[6] which is conceptually similar to EELV Delta IV Heavy launcher and proposals for the Atlas V HLV and Russian Angara. Falcon Heavy will be more capable than any other operational rocket, with a payload to low earth orbit of 53,000 kilograms (117,000 lb).[10] The rocket was designed to meet or exceed all current requirements of human rating. The structural safety margins are 40% above flight loads, higher than the 25% margins of other rockets.[20]
The Falcon Heavy's designed payload capacity, capabilities, and total thrust are equivalent to the Saturn C-3 launch vehicle concept (1960) for the Earth Orbit Rendezvous approach to an American lunar landing.[21]
First stage
The first stage is powered by three Falcon 9 derived cores, each equipped with 9 Merlin 1D engines. The Merlin 1D is an updated version of the previous Merlin 1C engine and provides a sea level thrust of 620 kN (140,000 lbf) at a specific impulse of 282 seconds,[22] a vacuum thrust of 690 kN (155,000 lbf) at 311 seconds,[22] and is throttleable from 100% to 70%.[23]The Falcon Heavy has a total sea-level thrust at liftoff of 17,615 kN (3,960,000 lbf), from the 27 Merlin 1D engines, while thrust rises to 20,000 kilonewtons (4,500,000 lbf) as the craft climbs out of the atmosphere.[5] Falcon Heavy has been designed with a unique propellant crossfeed capability, where some of the center core engines are supplied with fuel and oxidizer from the two side cores, up until the side cores are near empty and ready for the first separation event.[24] This allows engines from all three cores to ignite at launch and operate at full thrust until booster depletion, while still leaving the central core with most of its propellant at booster separation.[25]
After the side cores are released, the center engine in each side core will continue to burn for a few seconds in order to control the trajectory of the side booster.[26][27]
All three cores of the Falcon Heavy arrange the engines in a structural form SpaceX calls Octaweb, aimed at streamlining the manufacturing process,[28] and each core will include four extensible landing legs,[27] which are intended to be used for vertical-landing once the post-mission technology development effort is completed.[29]
Second stage
The upper stage is powered by a single Merlin 1D engine modified for vacuum operation, with an expansion ratio of 117:1 and a nominal burn time of 345 seconds. For added reliability of restart, the engine has dual redundant pyrophoric igniters (TEA-TEB).[6]The interstage, which connects the upper and lower stage for Falcon 9, is a carbon fiber aluminum core composite structure. Stage separation occurs via reusable separation collets and a pneumatic pusher system. The Falcon 9 tank walls and domes are made from aluminum lithium alloy. SpaceX uses an all-friction stir welded tank. The second stage tank of Falcon 9 is simply a shorter version of the first stage tank and uses most of the same tooling, material and manufacturing techniques. This approach reduces manufacturing costs during vehicle production.[6]
Reusable technology development
Although not a part of the initial Falcon Heavy design, SpaceX is doing parallel development on a reusable rocket launching system that is intended to be extensible to the Falcon Heavy, first to the booster stage and ultimately to the second stage as well.Early on, SpaceX had expressed hopes that both rocket stages would eventually be reusable.[30] More recently, in 2011, SpaceX announced a funded development program to build and fly a reusable launch system that will ultimately bring a first stage back to the launch site in minutes — and a second stage back to the launch pad, following orbital realignment with the launch site and atmospheric reentry, in up to 24 hours — with both stages designed to be available for reuse within "single-digit hours" after return.[31] As of February 2012[update], design is complete on the system for "bringing the rocket back to launchpad using only thrusters."[31]
The reusable launch system technology is under consideration for both the Falcon 9 and the Falcon Heavy. It is particularly well suited to the Falcon Heavy where the two outer cores separate from the rocket much earlier in the flight profile, and are therefore both moving at a slower velocity at the initial separation event.[31]
As of March 2013[update], the publicly announced aspects of the SpaceX reusable rocket technology development effort include an active test campaign of the low-altitude, low-speed Grasshopper vertical takeoff, vertical landing (VTVL) technology demonstrator rocket,[32][33] and a high-altitude, high-speed Falcon 9 post-mission booster-return test campaign where—beginning in late-2013, with the sixth overall flight of Falcon 9—every Falcon 9 first stage which was instrumented and equipped as a controlled descent test vehicle to accomplish propulsive-return over-water tests.[29]
SpaceX has indicated that the Falcon Heavy payload performance to Geosynchronous transfer orbit (GTO) will be reduced by addition of the reusable technology, but would fly at much lower launch price. With full reusability on all three booster cores, GTO payload will be 7,000 kg (15,000 lb). If only the two outside cores fly as reusable cores while the center core is expendable, GTO payload would be approximately 14,000 kg (31,000 lb).[34] "Falcon 9 will do satellites up to roughly 3.5 tonnes, with full reusability of the boost stage, and Falcon Heavy will do satellites up to 7 tonnes with full reusability of the all three boost stages," [Musk] said, referring to the three Falcon 9 booster cores that will comprise the Falcon Heavy's first stage. He also said Falcon Heavy could double its payload performance to GTO "if, for example, we went expendable on the center core."
Pricing and development funding
At an appearance in May 2004 before the U.S. Senate Committee on Commerce, Science and Transportation, Elon Musk testified, "Long term plans call for development of a heavy lift product and even a super-heavy, if there is customer demand. We expect that each size increase would result in a meaningful decrease in cost per pound to orbit. ... Ultimately, I believe $500 per pound or less is very achievable."[35] This $500 per pound goal stated by Musk in 2011 is 35 percent of the cost of the lowest-cost-per-pound LEO-capable launch system in a circa-2000 study, referenced by spaceref.com in 2001, the Zenit, a medium-lift launch vehicle that can carry 14,000 kilograms (30,000 lb) into LEO.[36]As of March 2013[update], Falcon Heavy launch prices are below $1,000 per pound ($2,200/kg) to low-Earth orbit when the launch vehicle is transporting its maximum delivered cargo weight.[37] The published prices for Falcon Heavy launches have moved some from year to year, with announced prices for the various versions of Falcon Heavy priced at US$80-125 million in 2011,[13] US$83-128 million in 2012,[14] US$77.1-135 million in 2013,[38] and US$85 million for up to 6,400 kg to GTO (with no published price for heavier GTO or any LEO payload) in 2014.[39] Launch contracts typically reflect launch prices at the time the contract is signed.
SpaceX has claimed the cost of reaching low Earth orbit can be as low as US$1,000/lb if an annual rate of four launches can be sustained, and as of 2011 planned to eventually launch 10 Falcon Heavy and 10 Falcon 9 annually.[9] A third launch site, intended exclusively for SpaceX private use, is planned, with locations in Texas, Florida, and Georgia under consideration.[40] A site near Brownsville, Texas was the front runner as of April 2013[update]. SpaceX expects to start construction on the third Falcon Heavy launch facility, after final site selection, no earlier than 2014, with the first launches from the facility no earlier than 2016.[40] In late 2013, SpaceX had projected Falcon Heavy's inaugural flight to be sometime in 2014,[5] but as of March 2014[update] expects the first launch to be in 2015[41] due to limited manufacturing capacity and the need to deliver on the Falcon 9 launch manifest.[7]
The Falcon Heavy is being developed with private capital. No government financing is being provided for its development.[42]
SpaceX current prices for space launch are already the lowest in the industry.[43] If SpaceX is able to successfully complete development on its SpaceX reusable rocket technology and return booster stages to the launch pad for reuse, a new economically-driven Space Age could result.[42][44]
Testing
A new, partially underground test stand is being built at the SpaceX Rocket Development and Test Facility in McGregor, Texas specifically to test the triple cores and twenty seven rocket engines of the Falcon Heavy.[45]Launches and potential payloads
| Flight Number | Date & Time (GMT) | Payload | Customer | Outcome | Remarks |
|---|---|---|---|---|---|
| 1 | 2015[46][47] | Falcon Heavy Demo Flight 1 | SpaceX | Scheduled | Hardware is expected to arrive at the Vandenberg AFB in 2014[46] |
| 2 | 2015[46] | Falcon Heavy Demo Flight 2 called: STP-2[48] Payload: GPIM[49][50][51] | DoD | Scheduled | The mission will support the U.S. Air Force EELV certification process for the Falcon Heavy.[47] |
| 3 | 2017[47] | Communications satellite[52] | Intelsat[53] | Scheduled | First Commercial mission for Falcon Heavy.[53] First launch to a Geostationary transfer orbit for Falcon Heavy.[52] |
'Red Dragon' Mars Mission[edit]
Main article: Red Dragon (spacecraft)
In 2011, NASA Ames Research Center developed a proposal for a low-cost Mars mission that would use Falcon Heavy as the launch vehicle and trans-Martian injection vehicle, and the Dragon capsule to enter the Martian atmosphere. The science objectives of the mission would be to look for evidence of life — detecting "molecules that are proof of life, like DNA or perchlorate reductase ... proof of life through biomolecules. ... Red Dragon would drill 3.3 feet (1.0 m) or so underground, in an effort to sample reservoirs of water ice known to lurk under the red dirt." The mission cost as of 2011 was projected to be less than US$425,000,000, not including the launch cost.[54] The concept was to be formally proposed in 2012/2013 as a NASA Discovery mission but has not been selected for funding.[55]
