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In 1912, Robert Esnault-Pelterie published a lecture [71] on rocket theory and interplanetary travel. He independently derived Tsiolkovsky's rocket equation, did basic calculations about the energy required to make round trips to the Moon and planets, and he proposed the use of atomic power (i.e. radium) to power a jet drive. Robert Goddard
The propellant used in a rocket engine plays an important role in both engine design and in design of the launch vehicle and related ground equipment to service the vehicle. Weight, energy density , cost, toxicity, risk of explosions, and other problems make it important for engineers to design rockets with appropriate propellants.
For rocket-like propulsion systems, this is a function of mass fraction and exhaust velocity; mass fraction for rocket-like systems is usually limited by propulsion system weight and tankage weight. [ citation needed ] For a system to achieve this limit, the payload may need to be a negligible percentage of the vehicle, and so the practical ...
A space vehicle's flight is determined by application of Newton's second law of motion: =, where F is the vector sum of all forces exerted on the vehicle, m is its current mass, and a is the acceleration vector, the instantaneous rate of change of velocity (v), which in turn is the instantaneous rate of change of displacement.
A liquid apogee engine (LAE), or apogee engine, refers to a type of chemical rocket engine typically used as the main engine in a spacecraft. The name apogee engine derives from the type of manoeuvre for which the engine is typically used, i.e. an in-space delta-v change made at the apogee of an elliptical orbit in order to circularise it.
They are used for commercial electricity, marine propulsion, weapons production and research. When a fissile nucleus , usually uranium-235 or plutonium-239 , absorbs a neutron , it splits into lighter nuclei, releasing energy, gamma radiation , and free neutrons, which can induce further fission in a self-sustaining chain reaction .
In 1946, work began on a pair of new British-built rocket motors, the de Havilland Sprite with a maximum thrust of 22 kN (5,000 lbf) and the Armstrong Siddeley Snarler with 8.9 kN (2,000 lbf) of thrust; these rocket motors made use of different propellants, the Sprite used a high-test peroxide (HTP) monopropellant while the Snarler harnessed a ...
Rocket Propulsion Elements 7th ed, 2001, Wiley-Interscience. Sutton and Biblarz This book provides a thorough introduction to many facets of rocket engineering and a summary of the various altitude compensating nozzles (pp. 75–84). Aerospaceweb.org This site discusses various types of nozzle including the expansion-deflection design.