Over the course of the history of today's rockets, liquid rocket engines have been used as primary propulsion for most space launch vehicles and early ballistic missiles. The basic idea of modern liquid rocket propulsion was first published in 1903. In the early 1900s, various design concepts were introduced, built and tested to explore the feasibility of liquid propulsion technology. The first successful flight with a liquid-propellant sounding rocket was made in 1926. A large engine development effort started in the 1930s as part of the world's first ballistic missile program with its first deployment in 1944. Subsequently, several major engine efforts were undertaken for longer range ballistic missiles, enabling intercontinental ballistic missile (ICBM) capability in 1957. Space launch vehicles evolved immediately from ICBMs and opened the door to space in 1957 and finally to the moon in 1969. Since then, various classes of operational liquid rocket engines have been designed, developed and flown with a continued increase in confidence. In general, liquid rocket engines enable a wide range of space lift capabilities from small to large payloads. Many satellites, spacecrafts and upper stages also use smaller liquid rocket engines, typically called thrusters, for orbit maneuvering or reaction control. Today, continued improvements in performance, reliability, operability and cost are sought through various research and development efforts.
Liquid Propulsion: Historical Overview, Fundamentals and Classifications of Liquid Rocket Engines
2009
32 pages
Report
No indication
English
Rocket Engines & Motors , Liquid propellant rocket engines , Intercontinental ballistic missiles , Reprints , Maneuverability , Deployment , Payload , Costs , Propulsion systems , Reliability , Range(Extremes) , Liquid rocket fuels , Space flight , Thrusters , Launch vehicles , Rockets , Rocket propulsion , Sounding rockets , Reaction control systems , Guided missiles , Orbits
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