Falcon Heavy

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Falcon Heavy
Function Orbital launch vehicle and potential Lunar launch vehicle[1]
Manufacturer SpaceX
Country of origin United States
Cost per launch (2013) $80–125M
Size
Height 69.2 m (227 ft)
Diameter 3.66 m (12.0 ft)
Mass 1,400,000 kg (3,100,000 lb)
Stages 2+
Capacity
Payload to LEO 53,000 kg (120,000 lb)
Payload to
GTO		 12,000 kg (26,000 lb)
Launch history
Status In Development
Launch sites Vandenberg SLC-4E
Cape Canaveral LC-39A[2]
Total launches 0
Successes 0
Failures 0
First flight 2013
Boosters (Stage 0)
No. boosters 2
Engines 9 Merlin 1D
Thrust 5,600 kN (1,260,000 lbf) (sea-level)
Total thrust 11,200 kN (2,520,000 lbf) (sea-level)[citation needed]
Specific impulse Sea level: 275 sec (2.6 kN/kg)[citation needed]
Vacuum: 304 sec (3.0 kN/kg)[citation needed]
Burn time Unknown
Fuel LOX/RP-1
First stage
Engines 9 Merlin 1D
Thrust 5,600 kN (1,260,000 lbf)(sl)[citation needed]
Specific impulse Sea level: 275 sec (2.6 kN/kg)[citation needed]
Vacuum: 304 sec (3.0 kN/kg)[citation needed]
Burn time
Fuel LOX/RP-1
Second stage
Engines 1 Merlin Vacuum
Thrust 445 kN (100,000 lbf)
Specific impulse Vacuum: 342 sec (3.45 kN/kg)[3]
Burn time 345 seconds[citation needed]
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. Both stages of the two-stage-to-orbit vehicle use liquid oxygen (LOX) and rocket-grade kerosene (RP-1) propellants, on a SpaceX-designed rocket engine, the Merlin 1D. Multiple variants are planned with payloads of 53,000 kilograms (120,000 lb) to low Earth orbit (LEO),[4] and 12,000 kilograms (26,000 lb) to geostationary transfer orbit (GTO).[5]

The payload to LEO falls into the category that a classification system used by a NASA review panel for plans for human spaceflight calls the super heavy lift range of launch systems.[6]

Contents

Design [edit]

From left to right, Falcon 1, Falcon 9 v1.0, Falcon 9 v1.1 and Falcon Heavy

The Falcon Heavy configuration consists of a standard Falcon 9 with two additional Falcon 9 first stages acting as liquid strap-on boosters,[7] 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 (120,000 lb).[8] 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.[9]

The Falcon Heavy's designed payload capacity, capabilities, and total thrust (17,000 kilonewtons (3,800,000 lbf)) are equivalent to the Saturn C-3 launch vehicle concept (1960) for the Earth Orbit Rendezvous approach to an American lunar landing.[10]

First stage [edit]

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 engine that provides a sea level thrust of 620 kN (140,000 lbf),[11] and a vacuum thrust of 690 kN (155,000 lbf), and is throttleable from 100% to 70%.[12]

Engines from all three cores ignite at launch, but until fuel runs out in the booster cores, the main core uses little or none of its own propellant. Falcon Heavy is being designed with a unique propellant crossfeed capability, where fuel and oxidizer are fed to power most of the engines on the center core from the two side cores, up until the side cores are near empty and ready for the first separation event.[13] There are three separation events: the simultaneous separation of the two booster cores followed later by the separation of the main booster core from the second stage. This is akin to a three stage rocket and thus enables greater performance.[14] Compared to what is thought of as a two and a half stage rocket, like the Delta IV Heavy, the Falcon Heavy central core can operate at full thrust and still be left with a full fuel load after booster separation, as opposed to a partial load.

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.[15]

Second stage [edit]

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).[7]

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.[7]

Related development [edit]

Main article: SpaceX reusable rocket launching system

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.

Early on, SpaceX had expressed hopes that both rocket stages would eventually be reusable.[16] More recently, in 2011, SpaceX announced a funded development program to build and fly a reusable launch system that will 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.[17] As of February 2012, design is complete on the system for "bringing the rocket back to launchpad using only thrusters."[17]

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.[17]

As of March 2013, the publically 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,.[18][19] and a high-altitude, high-speed Falcon 9 post-mission booster-return test campaign where—beginning in mid-2013, with the sixth overall flight of Falcon 9—every Falcon 9 first stage will be instrumented and equipped as a controlled descent test vehicle to accomplish propulsive-return over-water tests.[20]

Launcher versions [edit]

The initial version of the Falcon Heavy will use Falcon 9 v1.1 extended-length stages with Merlin 1D engines.

Version Falcon Heavy
Stage 0 2 boosters with 9 × Merlin 1D engines each[4][21]
Stage 1 9 × Merlin 1D[4]
Stage 2 1 × Merlin 1D
Height
(max; m)		 69.2[4]
Diameter
(m)		 11.6 m (38 ft), composed of three 3.6 m (12 ft) falcon9 core aligned side by side[5]
Initial thrust
(kN)		 17,000[4]
Takeoff weight
(tonnes)		 1,400[4]
Fairing diameter
(outer; m)		 5.2[5]
Payload
(LEO; kg)		 53,000[4][13] (if crossfeed not used : 45,360)[22]
Payload
(GTO; kg)		 12,000[5]
Price
(Mil. USD)		 83-128 in 2012,[5] 80-125 in 2011[4]
minimal Price/kg (Price/lb)
(LEO; USD)		 2,200 (1,000)[23]
minimal Price/kg
(GTO; USD)		 12,970 up to 6,400 kg[5][dated info]
Success ratio
(successful/total)

History [edit]

SpaceX breaking ground at Vandenberg AFB SLC-4E for the Falcon Heavy launch pad

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. "[24] This $500 per pound goal is approximately half the cost that is currently achievable by the next closest competitor: the Zenit launch vehicle.[25]

At a press conference at the National Press Club in Washington, DC. on 5 April 2011, Elon Musk stated, “Falcon Heavy will carry more payload to orbit or escape velocity than any vehicle in history, apart from the Saturn V moon rocket, which was decommissioned after the Apollo program. This opens a new world of capability for both government and commercial space missions.”[26] As of March 2013, Falcon Heavy launch costs are below $1,000 per pound ($2,200/kg) to low-Earth orbit when the launch vehicle is transporting its maximum delivered cargo weight.[23]

As of April 2011, SpaceX anticipated that the Falcon Heavy demonstration rocket would arrive at SpaceX's west-coast launch location, Vandenberg AFB, California, before the end of 2012,[27] with a launch planned for 2013.[8] After early launches from Vandenberg, the first launch from the Cape Canaveral east coast launch complex was planned for late 2013 or 2014.”[26] By late 2012, the company had modified the planned dates to say that the launch vehicle hardware would arrive in Vandenberg in 2013,[28] with first launch from the east-coast Cape Canaveral launch complex still planned for 2013 or 2014. 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. SpaceX plans to launch 10 Falcon Heavy and 10 Falcon 9 annually.[27] A third launch site, intended exclusively for SpaceX private use, is planned, with locations in Texas, Florida, and Georgia under consideration.[29] A site near Brownsville, Texas is the front runner as of April, 2013, however 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.[29]

While the official specifications of the new launcher limits LEO payloads to 53,000 kilograms (120,000 lb)[4] and GTO payloads to 12,000 kilograms (26,000 lb),[5] reports in 2011 had suggested higher payloads beyond low Earth orbit, including 19,000 kilograms (42,000 lb) to geostationary transfer orbit,[30] 16,000 kilograms (35,000 lb) to translunar trajectory, and 14,000 kilograms (31,000 lb) on a trans-Martian orbit to Mars.[27][31]

'Red Dragon' Mars Mission [edit]

Main article: Red Dragon (spacecraft)

As of July 2011, NASA Ames Research Center is developing a concept 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 concept would be proposed in 2012/2013 as a NASA Discovery mission for launch in 2018 and arrival at Mars several months later. 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 is projected to be less than US$425,000,000, not including the launch cost.[32]

First commercial contract: Intelsat [edit]

In May 2012, SpaceX announced that Intelsat had signed the first commercial contract for a Falcon Heavy flight. It was not confirmed when the first Intelsat launch would occur, but the agreement will have SpaceX delivering satellites to geosynchronous transfer orbit.[33][34]

First DoD contract: USAF [edit]

In December 2012, SpaceX announced its first Falcon Heavy launch contract with the United States Department of Defense (DoD). "The United States Air Force Space and Missile Systems Center awarded SpaceX two Evolved Expendable Launch Vehicle (EELV)-class missions" including the Space Test Program 2 (STP-2) mission for Falcon Heavy, initially scheduled to be launched in 2015.[35][36]

Testing [edit]

A new, partially underground test stand has been built specifically to test the triple cores and twenty seven rocket engines of the Falcon Heavy.[37]

Launches and scheduled launches [edit]

Flight Number Date & Time (GMT) Payload Customer Outcome Remarks
1 2013[38] Falcon Heavy Demo Flight 1 SpaceX Scheduled Hardware is expected to arrive at the Vandenberg AFB in 2013[28]
Late 2013 or 2014[26] Not yet announced Scheduled First FH flight from Cape Canaveral[26]
Late 2015[35] STP-2[35] DoD Scheduled The mission will support the EELV certification process for the Falcon Heavy.[citation needed]
TBA Communications satellite[33] Intelsat[34] Scheduled First Commercial mission for Falcon Heavy.[34] First launch to a Geostationary transfer orbit for Falcon Heavy.[33]

See also [edit]

References [edit]

  1. ^ Tybor,FrankSpaceX: Access to Space in the Commercial Era,February 12th 2013,Speech.
  2. ^ Clark, Stephen (11 March 2012). "SpaceX eyes shuttle launch pad for heavy-lift rocket". Spaceflight Now. Retrieved 12 March 2012. 
  3. ^ "SpaceX Falcon 9 Upper Stage Engine Successfully Completes Full Mission Duration Firing" (Press release). SpaceX. March 10, 2009. 
  4. ^ a b c d e f g h i Clark, Stephen (April 5, 2011). "SpaceX enters the realm of heavy-lift rocketry". Spaceflight Now. Retrieved 2012-06-04. 
  5. ^ a b c d e f g "Space Exploration Technologies Corporation - Falcon Heavy". SpaceX. 2011-12-03. Retrieved 2011-12-03. 
  6. ^ HSF Final Report: Seeking a Human Spaceflight Program Worthy of a Great Nation, October 2009, Review of U.S. Human Spaceflight Plans Committee, p. 64-66: "5.2.1 The Need for Heavy Lift ... require a “super heavy-lift” launch vehicle ... range of 25 to 40 mt, setting a notional lower limit on the size of the super heavy-lift launch vehicle if refueling is available ... this strongly favors a minimum heavy-lift capacity of roughly 50 mt ..."
  7. ^ a b c "Falcon 9 Overview". SpaceX. 8 May 2010. 
  8. ^ a b "US co. SpaceX to build heavy-lift, low-cost rocket". Reuters. 5 April 2011. Archived from the original on 5 April 2011. Retrieved 5 April 2011. 
  9. ^ "SpaceX Announces Launch Date for the World's Most Powerful Rocket". Spaceref.com. Retrieved 10 April 2011. 
  10. ^ "Saturn C-3". Encyclopedia Astronautica. Retrieved 8 June 2012. 
  11. ^ Harwood, William (2011-04-05). "World's biggest private space rocket planned". CBS. Retrieved 2011-04-05. 
  12. ^ "SpaceX Unveils Plans To Be World’s Top Rocket Maker". Aviation Week and Space Technology. 2011-08-11. Retrieved 2011-08-07 (print edition is out prior to publication date). "Revealing several new details of the 1D, Tom Mueller, propulsion engineering vice president, says the engine is designed to produce 155,000 lb. vacuum thrust and have a chamber pressure at “the sweet spot” of roughly 1,410 psia. “We’ve also increased the nozzle expansion ratio to 16 [compared with 14.5 on the Merlin 1C],” says Mueller, who adds that the initial engine “is doing better than we hoped.” The engine is designed for an Isp (specific impulse) of 310 sec. and has a thrust-to-weight ratio of 160:1. “We took structure off the engine to make it lighter. The engine we shipped [for test] to Texas was a development engine and hopefully the production engines will be even better.”" 
  13. ^ a b (this technique is nick-named 'Asparagus staging') Strickland, John K., Jr. (September 2011). "The SpaceX Falcon Heavy Booster". National Space Society. Retrieved 2012-11-24. 
  14. ^ "SpaceX Announces Launch Date for the World's Most Powerful Rocket". SpaceX. 2011-04-05. Retrieved 2011-04-05. 
  15. ^ Nield, George C. (April 2014). Draft Environmental Impact Statement: SpaceX Texas Launch Site (Report). 1. Federal Aviation Administration, Office of Commercial Space Transportation ". p. 2-3. http://1.usa.gov/YtxBzo. "The center core engines are throttled down after liftoff and up to two engines may be shut down as the vehicle approaches maximum acceleration. After the side boosters drop off, the center core engines throttle back up to full thrust. The center engine in each side core continues to burn for a few seconds after separation to control the descent trajectorie of the side boosters."
  16. ^ Musk ambition: SpaceX aim for fully reusable Falcon 9, NASAspaceflight.com, 2009-01-12, accessed 2010-06-03
  17. ^ a b c Simberg, Rand (2012-02-08). "Elon Musk on SpaceX’s Reusable Rocket Plans". Popular Mechanics. Retrieved 2012-02-07. 
  18. ^ Klotz, Irene (2011-09-27). "A rocket that lifts off — and lands — on launch pad". MSNBC. Retrieved 2011-11-23. 
  19. ^ Mohney, Doug (2011-09-26). "SpaceX Plans to Test Reusable Suborbital VTVL Rocket in Texas". Satellite Spotlight. Retrieved 2011-11-23. 
  20. ^ Lindsey, Clark (2013-03-28). "SpaceX moving quickly towards fly-back first stage". NewSpace Watch. Retrieved 2013-03-29. 
  21. ^ Clark, Stephen (May 29, 2012). "SpaceX signs first commercial customer for Falcon Heavy". Spaceflight Now. Retrieved 2012-06-04. 
  22. ^ "SPACEX ANNOUNCES LAUNCH DATE FOR THE WORLD'S MOST POWERFUL ROCKET". spacex. April 5, 2011. 
  23. ^ a b Upgraded Spacex Falcon 9.1.1 will launch 25% more than old Falcon 9 and bring price down to $4109 per kilogram to LEO, NextBigFuture, 22 Mar 2013.
  24. ^ Testimony of Elon Musk (May 5, 2004). "Space Shuttle and the Future of Space Launch Vehicles". U.S. Senate. 
  25. ^ http://www.spaceref.com/news/viewnews.html?id=301
  26. ^ a b c d "SpaceX announces launch date for FH". 2011-04=05. Retrieved 2011-08-25. "First launch from our Cape Canaveral launch complex is planned for late 2013 or 2014." 
  27. ^ a b c "SpaceX Press Conference". SpaceX. Retrieved 16 April 2011. 
  28. ^ a b "Launch Manifest". SpaceX. Retrieved 12 Dec 2012. 
  29. ^ a b Foust, Jeff (2013-04-01). "The great state space race". The Space Review. Retrieved 2013-04-03. 
  30. ^ "SpaceX Brochure". Retrieved 14 June 2011. 
  31. ^ "Red Dragon" (PDF), Feasibility of a Dragon-derived Mars lander for scientific and human-precursor investigations, 8m.net, October 31, 2011, retrieved 2012-05-14 
  32. ^ Wall, Mike (2011-07-31). "'Red Dragon' Mission Mulled as Cheap Search for Mars Life". SPACE.com. Retrieved 2011-07-31. "This so-called "Red Dragon" mission, which could be ready to launch by 2018, would carry a cost of about $400 million or less. ... developing the Red Dragon concept as a potential NASA Discovery mission, a category that stresses exploration on the relative cheap. ... NASA will make another call for Discovery proposals in 18 months or so... If Red Dragon is selected in that round, it could launch toward Mars in 2018. ... Assuming that $425 million cap [for NASA Discovery missions] is still in place, Red Dragon could come in significantly under the bar. We'd have money left over to do some science." 
  33. ^ a b c "SpaceX Announces First Commercial Contract For Launch In 2013". Red Orbit. 2012-05-30. Retrieved 2012-12-15. 
  34. ^ a b c "Intelsat Signs First Commercial Falcon Heavy Launch Agreement With SpaceX" (Press release). SpaceX. 2012-05-29. Retrieved 2012-12-16. 
  35. ^ a b c Lindsay, Clark (2012-12-05). "SpaceX awarded 2 EELV-Class missions from the USAF". NewSpace Watch. Retrieved 2012-12-15. 
  36. ^ Clark, Stephen (2012-12-06). "SpaceX books first two launches with U.S. military". NewSpace Watch. Retrieved 2012-12-31. 
  37. ^ "Falcon Heavy Test Stand". Retrieved 6 May 2013. 
  38. ^ "F9/Dragon: Preparing for the ISS". SpaceX. 2011-08-15. Retrieved 3 September 2011. "We are targeting late 2012 to bring Falcon Heavy to Vandenberg for vehicle to pad integration tests and 2013 for liftoff." 

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