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Ammonium perchlorate composite propellant (APCP) is a solid rocket propellant. It differs from many traditional solid rocket propellants such as black powder or zinc-sulfur , not only in chemical composition and overall performance but also by being cast into shape, as opposed to powder pressing as with black powder.
A solid rocket booster (SRB) is a solid propellant motor used to provide thrust in spacecraft launches from initial launch through the first ascent. Many launch vehicles, including the Atlas V , [ 1 ] SLS and Space Shuttle , have used SRBs to give launch vehicles much of the thrust required to place the vehicle into orbit.
The P160C is a solid-fuel rocket engine designed for use as the first stage of the Vega-E and as the boosters of the Ariane 6 Block 2 launch vehicles. The solid rocket motors were developed by Europropulsion, a joint venture of Avio and ArianeGroup, for the European Space Agency. The "C" in the name signifies its "Common" use across these ...
The Graphite-Epoxy Motor (GEM) is a family of solid rocket boosters developed in the late 1980s and used since 1990. GEM motors are manufactured with carbon-fibre-reinforced polymer casings and a fuel consisting of HTPB-bound ammonium perchlorate composite propellant. GEM is produced by Northrop Grumman Space Systems. [1]
Polybutadiene acrylonitrile (PBAN) [1] copolymer, also noted as polybutadiene—acrylic acid—acrylonitrile terpolymer [2] is a copolymer compound used most frequently as a rocket propellant fuel mixed with ammonium perchlorate oxidizer. [3] It was the binder formulation widely used on the 1960s–1970s big boosters (e.g., Titan III and Space ...
The Space Shuttle Solid Rocket Booster (SRB) was the first solid-propellant rocket to be used for primary propulsion on a vehicle used for human spaceflight. [1] A pair of them provided 85% of the Space Shuttle 's thrust at liftoff and for the first two minutes of ascent.
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The rocket is launched using liquid hydrogen and liquid oxygen cryogenic propellants. Rocket propellant is used as reaction mass ejected from a rocket engine to produce thrust . The energy required can either come from the propellants themselves, as with a chemical rocket , or from an external source, as with ion engines .