SpaceX Draco

  (Redirected from Draco (rocket engine family))

The SpaceX Draco is a family of hypergolic liquid rocket engines designed and built by SpaceX for use in their space capsules. Two engine types have been built to date: Draco and SuperDraco.

SpaceX Draco
Draco In-space Firing.png
A SpaceX Dragon spacecraft approaching the International Space Station fires one of its 18 Draco thrusters.
Country of originUnited States
ApplicationReaction control system
Liquid-fuel engine
PropellantNTO / MMH[1]
Thrust (vac.)400 N (90 lbf)[1]
Isp (vac.)300 s (2.9 km/s)
Used in
SpaceX Dragon

The original Draco thruster is a small rocket engine for use on the Dragon spacecraft.[2][3][4]

SuperDraco is derived from Draco, and utilizes the same storable (non-cryogenic) propellant as the small Draco thrusters, but is much larger and delivers over 100 times the thrust. SuperDraco engines have been used on the Crew Dragon spacecraft to provide launch-escape capability to low Earth orbit.

Draco and SuperDraco combine the functions of a reaction control system and main propulsive engine.


Draco thrusters generate 400 newtons (90 pounds-force) of thrust using a storable propellant mixture of monomethyl hydrazine fuel and nitrogen tetroxide oxidizer. The Draco thrust is comparable to the Marquardt R-4D engine developed for the Apollo Service and Lunar Modules in 1960s and used for apogee/perigee maneuvers, orbit adjustment, and attitude control.

Eighteen Draco thrusters are used on the Dragon spacecraft for attitude control and maneuvering.[1]


SuperDraco firing at full thrust
Country of originUnited States
ApplicationLAS (Launch Abort System), powered landing[5]
Liquid-fuel engine
PropellantNTO / MMH[6]
Thrust (SL)73 kN (16,400 lbf)[7]
Isp (SL)235 s (2.30 km/s) [7]
Burn time25 seconds [7]
Propellant capacity1,388 kg (3,060 lbs)[6]
Used in
Crew Dragon, DragonFly test vehicle

On February 1, 2012 SpaceX announced that it has completed the development of a new, more powerful version of a storable-propellant rocket engine, this one called SuperDraco. This high-thrust hypergolic engine—about 200 times larger than the Draco RCS thruster hypergolic engine—offers deep throttling ability and just like the Draco thruster, has multiple restart capability and uses the same shared hypergolic propellants. Its primary purpose is for SpaceX's LAS (launch abort system) on the Dragon spacecraft. According to the NASA press release, the engine has a transient from ignition to full thrust of 100 ms.[8] During launch abort, eight SuperDracos are expected to fire for 5 seconds at full thrust. The development of the engine is partially funded by NASA's CCDev 2 program.

SuperDracos will be used on both the Crew Dragon[9] and on the DragonFly (rocket), a prototype low-altitude reusable rocket that will be used for flight testing various aspects of the propulsive-landing technology. While the engine is capable of 73,000 newtons (16,400 lbf) of thrust, during use for DragonFly testing, the engines will be throttled to 68,170 newtons (15,325 lbf) to maintain vehicle stability.[7] First firing of all 8 Super Draco engines took place on 6 May 2015 at 9am EST at the SpaceX Crew Dragon Pad Abort Test.[10][11]

SuperDraco engines are capable of being restarted many times, and have the capability to deeply reduce their thrust providing precise control during propulsive landing of the Dragon capsule.[12] SpaceX have since announced they will not be using propulsive landing on the Dragon 2. [13]

As of 2015, SuperDraco is the third most powerful engine developed by SpaceX, approximately 200 times[8] more powerful than the Draco thruster engines, and only outmatched by the Raptor and Merlin. By comparison, it is more than twice as powerful as the Kestrel engine that was used in SpaceX's Falcon 1 launch vehicle second stage, and about 1/9 the thrust of a Merlin 1D engine.

In addition to the use of the SuperDraco thrusters for powered-landings on Earth, NASA's Ames Research Center is studying the feasibility of a Dragon-derived Mars lander for scientific investigation.[5] Preliminary analysis indicates that the final deceleration will be within the retro-propulsion SuperDraco thruster capabilities.[5][14][needs update]

See alsoEdit


  1. ^ a b c "SpaceX Updates — December 10, 2007". SpaceX. 2007-12-10. Archived from the original on 2011-01-04. Retrieved 2010-02-03.
  2. ^ "SpaceX Draco Thruster Performs Long-Duration Firing and Restart" (Press release). SpaceX. December 9, 2008. Retrieved July 17, 2014.
  3. ^ "Falcon 9 Launch Vehicle Payload User's Guide, 2009" (PDF). SpaceX. 2009. Archived from the original (PDF) on April 29, 2011. Retrieved 2010-02-03.
  4. ^ "Falcon 9 Users Guide Rev 2" (PDF). SpaceX. 21 October 2015. Archived from the original (PDF) on 14 March 2017. Retrieved 14 January 2016.
  5. ^ a b c NASA; SpaceX (October 31, 2011). "Red Dragon" (PDF). Retrieved 2012-05-14.
  6. ^ a b "Finding of No Significant Impact (FONSI) and Record of Decision (ROD)" (PDF). Federal Aviation Administration. March 5, 2014. Retrieved July 17, 2014.
  7. ^ a b c d James, Michael; Salton, Alexandria; Downing, Micah (November 12, 2013), Draft Environmental Assessment for Issuing an Experimental Permit to SpaceX for Operation of the Dragon Fly Vehicle at the McGregor Test Site, Texas, May 2014 – Appendices (PDF), Blue Ridge Research and Consulting, LCC, p. 12
  8. ^ a b "SpaceX Test Fires Engine Prototype for Astronaut Escape System". NASA. 2012-02-01. Retrieved 2012-02-01.
  9. ^ "Dragon". SpaceX. Retrieved 3 September 2015.
  10. ^ SpaceX Pad Abort Test. YouTube. 8 May 2015. Retrieved 3 September 2015.
  11. ^ "Crew Dragon Completes Pad Abort Test". SpaceX. Retrieved 3 September 2015.
  12. ^ "SuperDraco Thruster Powers Revolutionary Launch Escape System (Rocket Thruster Test)". Satnews Daily. 2014-05-27. Retrieved 2014-05-28.
  13. ^ "SpaceX drops plans for powered Dragon landings -". 2017-07-19. Retrieved 2018-06-04.
  14. ^ NASA Ames Research Center (1 November 2011). "NASA ADVISORY COUNCIL (NAC) - Science Committee Report" (PDF). Archived from the original (PDF) on 2013-01-20. Retrieved 2012-05-01.

External linksEdit