Solid rocket booster

A solid rocket booster (SRB) is a large solid propellant motor used to provide thrust in spacecraft launches from initial launch through the first ascent. Many launch vehicles, including the Ariane 5, Atlas V,[1] and Space Shuttle, have used SRBs to give launch vehicles much of the thrust required to place the vehicle into orbit. The Space Shuttle used two Space Shuttle SRBs, which were the largest solid propellant motors ever built and the first designed for recovery and reuse.[2] The propellant for each solid rocket motor on the Space Shuttle weighed approximately 500,000 kilograms.[3]

NASA Image of a solid rocket booster (right) being mated to a Delta II rocket (green). Two boosters (white) can be seen already attached.

Advantages

Compared to liquid propellant rockets, the solid-propellant SRBs have been capable of providing large amounts of thrust with a relatively simple design.[4] They provide greater thrust without significant refrigeration and insulation requirements. Adding detachable SRBs to a vehicle also powered by liquid-propelled rockets known as staging reduces the amount of liquid propellant needed and lowers the launch vehicle mass. Solid boosters are cheaper to design, test, and produce in the long run compared to the equivalent liquid propellant boosters. Reusability of components across multiple flights, as in the Shuttle assembly, also has decreased hardware costs.[5]

One example of increased performance provided by SRBs is the Ariane 4 rocket. The basic 40 model with no additional boosters was capable of lifting a 4,795 lb. (2,175 kg.) payload to Geostationary transfer orbit.[6] The 44P model with 4 solid boosters has a payload of 7,639 lb. (3,465 kg) to the same orbit.[7]

Disadvantages

Solid propellant boosters are not controllable and must generally burn until exhaustion after ignition, unlike liquid propellant or cold-gas propulsion systems. However, launch abort systems and range safety destruct systems can attempt to cut off propellant flow by using shaped charges.[8] As of 1986 estimates for SRB failure rates have ranged from 1 in 1,000 to 1 in 100,000.[9] SRB assemblies have failed suddenly and catastrophically. Nozzle blocking or deformation can lead to overpressure or a reduction in thrust, while defects in the booster's casing or stage couplings can cause the assembly to break apart by increasing aerodynamic stresses. Additional failure modes include bore choking and combustion instability.[10] Failure of an O-ring seal on the Space Shuttle Challenger's right solid rocket booster led to its disintegration shortly after liftoff.

Solid rocket motors can present a handling risk on the ground, as a fully fueled booster carries a risk of accidental ignition. Such an accident occurred in the August 2003 Brazilian rocket explosion at the Brazilian Centro de Lançamento de Alcântara VLS rocket launch pad, killing 21 technicians.[11] Liquid rocket boosters generally cannot be moved after preparation is completed.

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See also

References

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

  1. "Data", Assets (PDF), Lockheed Martin, archived from the original (PDF) on December 17, 2011
  2. "HSF - The Shuttle". spaceflight.nasa.gov. Retrieved 2016-02-08.
  3. "Solid rocket boosters". USA: NASA. 2009-08-09..
  4. "What are the types of rocket propulsion?". www.qrg.northwestern.edu. Retrieved 2016-02-08.
  5. Hoover, Kurt. "Doomed from the Beginning:The Solid Rocket Boosters for the Space Shuttle". Texas Space Grant Consortium. University of Texas.
  6. Ariane 4, Astronautix, archived from the original on 2012-07-16.
  7. Ariane 44P, Astronautix, archived from the original on 2011-05-13.
  8. Tasker, Douglas G. (1986-08-01). "Shock Initiation Studies of the NASA Solid Rocket Booster Abort System,". Cite journal requires |journal= (help)
  9. WINES, MICHAEL (1986-03-05). "NASA Estimate of Rocket Risk Disputed". Los Angeles Times. ISSN 0458-3035. Retrieved 2016-02-08.
  10. "Solid Rocket Motor Failure Prediction - Introduction". ti.arc.nasa.gov. Archived from the original on 2016-08-14. Retrieved 2016-02-08.
  11. VLS Archived 2005-08-12 at the Wayback Machine
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