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  2. Light-gas gun - Wikipedia

    en.wikipedia.org/wiki/Light-gas_gun

    The target tank is generally configured for planar and inclined impact experiments. Soft catch systems are often used to recover materials for post-shot analysis. [2] Diagram of a light-gas gun 1 — Breech block 2 — Chamber 3 — Propellant charge (gunpowder) 4 — Piston 5 — Pump tube 6 — Light gas (helium or hydrogen) 7 — Rupture disk

  3. SM-65C Atlas - Wikipedia

    en.wikipedia.org/wiki/SM-65C_Atlas

    On the Atlas B missiles, the vernier helium tank was mounted in a higher location resulting in a different fuel tank attachment point above the baffles. Helium pressure gas from the vernier propellant tanks leaked into the sustainer RP-1 turbopump, leading to cavitation which caused propellant unloading, pump overspeed, and rupture of low ...

  4. SM-65D Atlas - Wikipedia

    en.wikipedia.org/wiki/SM-65D_Atlas

    Missile 60D launched July 2. The vernier start tanks were inadvertently vented and refilled several times during the flight. This resulted in depletion of control helium and decay in propulsion system performance, and so the Mark III Mod 1B reentry vehicle landed some 40 miles (64 km) short of its intended target point.

  5. SM-65B Atlas - Wikipedia

    en.wikipedia.org/wiki/SM-65B_Atlas

    The Convair SM-65B Atlas, or Atlas B, also designated X-12 [1] was a prototype of the Atlas missile. First flown on 19 July 1958, the Atlas B was the first version of the Atlas rocket to use the stage and a half design with an operational sustainer engine and jettisonable booster engine section.

  6. Pressure-fed engine - Wikipedia

    en.wikipedia.org/wiki/Pressure-fed_engine

    Pressure-fed rocket cycle. Propellant tanks are pressurized to directly supply fuel and oxidizer to the engine, eliminating the need for turbopumps. The pressure-fed engine is a class of rocket engine designs. A separate gas supply, usually helium, pressurizes the propellant tanks to force fuel and oxidizer to the combustion chamber. To ...

  7. Space Launch System core stage - Wikipedia

    en.wikipedia.org/wiki/Space_Launch_System_core_stage

    The core stage comprises five major sections: the engine section, the liquid hydrogen (LH 2) tank, the intertank, the liquid oxygen (LO x) tank, and the forward skirt.These elements can be further divided into ten barrel sections, four domes, and seven rings, together forming the structure of the rocket stage.