Vernier thruster (English Wikipedia)

Analysis of information sources in references of the Wikipedia article "Vernier thruster" in English language version.

Last modified:

Ref.Un. Ref.Website
Global rank English rank
1st place
1st place
12th place
73rd place
low place
low place
2,029th place
1,519th place

heroicrelics.org (Global: low place; English: low place)

nasa.gov (Global: 12th place; English: 73rd place)

microgravity.grc.nasa.gov

science.ksc.nasa.gov

  • "Reaction Control Systems". NASA Kennedy Spaceflight Center. Archived from the original on 2009-05-24. Retrieved 2011-10-03. The flight crew can select primary or vernier RCS thrusters for attitude control in orbit. Normally, the vernier thrusters are selected for on-orbit attitude hold. ... The forward RCS had 14 primaries and two vernier engines. The aft RCS had 12 primary and two vernier engines in each pod. The primary RCS engines provided 870 pounds of vacuum thrust each, and the verniers provided 24 pounds of vacuum thrust each. The oxidizer-to-fuel ratio for each engine is 1.6-to-1. The nominal chamber pressure of the primary thrusters was 152 psia. For each vernier, it was 110 psi.

nasaspaceflight.com (Global: 2,029th place; English: 1,519th place)

web.archive.org (Global: 1st place; English: 1st place)

  • "Rocket Control: Examples of Controls". NASA's Glenn Research Center. Archived from the original on March 7, 2011. Retrieved December 30, 2011.
  • "Reaction Control Systems". NASA Kennedy Spaceflight Center. Archived from the original on 2009-05-24. Retrieved 2011-10-03. The flight crew can select primary or vernier RCS thrusters for attitude control in orbit. Normally, the vernier thrusters are selected for on-orbit attitude hold. ... The forward RCS had 14 primaries and two vernier engines. The aft RCS had 12 primary and two vernier engines in each pod. The primary RCS engines provided 870 pounds of vacuum thrust each, and the verniers provided 24 pounds of vacuum thrust each. The oxidizer-to-fuel ratio for each engine is 1.6-to-1. The nominal chamber pressure of the primary thrusters was 152 psia. For each vernier, it was 110 psi.