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The first Mini Sugar Shot rocket, a single-stage dual-pulse design motor prototype of the Extreme Sugar Shot rocket, reached an altitude of 4 kilometres (2.5 mi) before a catastrophic motor malfunction occurred; contact with the second Mini Sugar Shot rocket was lost at an altitude of nearly 6 kilometres (3.7 mi) going in excess of Mach 1. In ...
The J-2, commonly known as Rocketdyne J-2, was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the United States by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH 2) and liquid oxygen (LOX) propellants, with each engine producing 1,033.1 kN (232,250 lb f) of thrust in vacuum.
The primary usage of 0-6-2 types in the United States were Tank locomotives. Many were found in the state of Hawaii on sugar cane railroads across the state. Most notable were the 0-6-2T's of the Mcbryde Sugar Company of Kauai, 3 of which survive and are currently the only original steam engines operating in Hawaii.
A tank locomotive is a steam locomotive which carries its water in one or more on-board water tanks, instead of a more traditional tender. Most tank engines also have bunkers (or fuel tanks ) to hold fuel; in a tender-tank locomotive a tender holds some or all of the fuel, and may hold some water also.
The weight associated with a cooling system could be eliminated, but that would be balanced by a need for a water tank in addition to the normal fuel tank. The Crower six-stroke engine was an experimental design that attracted media attention in 2006 because of an interview given by the 75-year-old American inventor, who has applied for a ...
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 ...
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1.7 to 2.9 km/s (3800 to 6500 mi/h) for liquid monopropellants; 2.9 to 4.5 km/s (6500 to 10100 mi/h) for liquid bipropellants; 2.1 to 3.2 km/s (4700 to 7200 mi/h) for solid propellants; As a note of interest, v e is sometimes referred to as the ideal exhaust gas velocity because it based on the assumption that the exhaust gas behaves as an ...