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  2. Comparison of orbital rocket engines - Wikipedia

    en.wikipedia.org/wiki/Comparison_of_orbital...

    This page is an incomplete list of orbital rocket engine data and specifications. Current, upcoming, and in-development rocket engines ... [29] 4,860,000: 58: 160,200 ...

  3. Dawn (spacecraft) - Wikipedia

    en.wikipedia.org/wiki/Dawn_(spacecraft)

    Engineers determined that this hybrid mode would conserve fuel. On November 13, 2013, during the transit, in a test preparation, Dawn engineers completed a 27-hour-long series of exercises of said hybrid mode. [116] On September 11, 2014, Dawn 's ion thruster unexpectedly ceased firing and the probe began operating in a triggered safe mode. To ...

  4. Rocketdyne F-1 - Wikipedia

    en.wikipedia.org/wiki/Rocketdyne_F-1

    While outwardly very similar to the F-1, the F-1A produced about 20% greater thrust, 1,800,000 lbf (8 MN) in tests, and would have been used on future Saturn V vehicles in the post-Apollo era. However, the Saturn V production line was closed prior to the end of Project Apollo and no F-1A engines ever flew. [10]

  5. Comparison of orbital launch systems - Wikipedia

    en.wikipedia.org/wiki/Comparison_of_orbital...

    Falcon 9 Block 5, the most prolific active orbital launch system in the world.. This comparison of orbital launch systems lists the attributes of all current and future individual rocket configurations designed to reach orbit.

  6. Cold gas thruster - Wikipedia

    en.wikipedia.org/wiki/Cold_gas_thruster

    A cold gas thruster (or a cold gas propulsion system) is a type of rocket engine which uses the expansion of a (typically inert) pressurized gas to generate thrust.As opposed to traditional rocket engines, a cold gas thruster does not house any combustion and therefore has lower thrust and efficiency compared to conventional monopropellant and bipropellant rocket engines.

  7. Apollo command and service module - Wikipedia

    en.wikipedia.org/wiki/Apollo_command_and_service...

    The sixteen-thruster arrangement provided rotation and translation control in all three spacecraft axes. Each R-4D thruster measured 12 inches (30 cm) long by 6 inches (15 cm) diameter, generated 100 pounds-force (440 N) of thrust, and used helium-fed monomethylhydrazine (MMH) as fuel and nitrogen tetroxide (NTO) as oxidizer. [25]

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