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The pintle injector is a type of propellant injector for a bipropellant rocket engine. Like any other injector, its purpose is to ensure appropriate flow rate and intermixing of the propellants as they are forcibly injected under high pressure into the combustion chamber, so that an efficient and controlled combustion process can happen. [1]
The TR-106 or low-cost pintle engine (LCPE) was a developmental rocket engine designed by TRW under the Space Launch Initiative to reduce the cost of launch services and space flight. Operating on LOX / LH2 the engine had a thrust of 2892 kN, or 650,000 pounds, making it one of the most powerful engines ever constructed.
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).
Executor is a rocket engine developed by ARCA [1] for use on its Haas rocket series and on IAR 111 Excelsior supersonic airplane. Executor uses kerosene [2] and liquid oxygen as propellants in a gas-generator power cycle. The injector of Executor is of the pintle type that was first used in the Apollo Program for the lunar module landing engine.
The rocket is designed to send up to 100 kg into low-Earth orbit, at a price of US$1 million per launch. [9] They later announced that their Executor Aerospike engine would produce 50,500 pounds-force (225 kN) of thrust at sea level and 73,800 pounds-force (328 kN) of thrust in a vacuum.
The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N 2 O 4 oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion ...
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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 .