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For rockets and space vehicles, propellants usually take up 2/3 or more of their total mass. Large upper-stage rocket engines generally use a cryogenic fuel like liquid hydrogen and liquid oxygen (LOX) as an oxidizer because of the large specific impulse possible, but must carefully consider a problem called "boil off," or the evaporation of the cryogenic propellant.
A Propulsive Fluid Accumulator is an artificial Earth satellite which collects and stores oxygen and other atmospheric gases for in-situ refuelling of high-thrust rockets. This eliminates the need to lift oxidizer to orbit and therefore brings significant cost benefits.
Liquid rocket engines have tankage and pipes to store and transfer propellant, an injector system and one or more combustion chambers with associated nozzles.. Typical liquid propellants have densities roughly similar to water, approximately 0.7 to 1.4 g/cm 3 (0.025 to 0.051 lb/cu in).
Oxygen is a moderate cryogen as air will not liquefy against a liquid oxygen tank, so it is possible to store LOX briefly in a rocket without excessive insulation. [ clarification needed ] In Germany, engineers and scientists began building and testing liquid propulsion rockets in the late 1920s. [ 5 ]
The 70-foot-long (21 m), 17-inch-diameter (430 mm) liquid oxygen feedline runs externally along the right side of the liquid hydrogen tank up and into the intertank. Two 5-inch (130 mm) diameter re-pressurization lines run beside it. One supplies hydrogen gas to the liquid hydrogen tank and the other supplies oxygen gas to the liquid oxygen tank.
The S-V stage was intended to be powered by two RL-10A-1 engines burning liquid hydrogen as fuel and liquid oxygen as oxidizer. The S-V stage was flown four times on missions SA-1 through SA-4 , all four of these missions had the S-V's tanks filled with water to be used a ballast during launch.
The target launch cost was $1 million. Aquarius was designed to be a single-stage vehicle 43 meters (141 ft) high and 4 meters (13.1 ft) in diameter and powered by a single pressure fed engine using liquid hydrogen and oxygen propellants stored in a composite pressure tank. [1]
During the ascent and boostback burns, the engines draw propellant from the main tanks, with the liquid oxygen being drawn from a dedicated header tank during the landing burn. [35] Like the thrust vector control system, the engine shielding, which isolates individual engines in the event of a failure, was upgraded after Starship's first flight ...