Spacecraft Propulsion |
Contents
IV | 1 |
V | 4 |
VI | 7 |
VIII | 9 |
X | 12 |
XI | 23 |
XII | 25 |
XIII | 27 |
XXXVI | 133 |
XXXVII | 135 |
XXXIX | 141 |
XL | 145 |
XLI | 150 |
XLII | 152 |
XLIV | 160 |
XLV | 165 |
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Common terms and phrases
AIAA apoapsis area ratio attitude attitude-control bipropellant systems blowdown system burning rate calculated catalyst bed chamber pressure density diameter diaphragm engine performance Equation exit external torque fuel geosynchronous orbit grain Heater helium hydrazine ignition injector Input Menu Intelsat km/s launch vehicle lb-s lb/s limit cycle liquid Magellan Main Menu maneuver mass maximum mission mixture ratio Molecular weight monomethylhydrazine monopropellant monopropellant system nitrogen tetroxide nozzle one-sided limit orbit insertion oxidizer parameters periapsis press Enter propellant Propellant Flow Rate propellant load propellant tank propellant weight propulsion system psia pulse width radius Ratio of specific reaction wheel rocket engine Select shown in Fig solid motor solid rocket motor spacecraft spacecraft propulsion specific heats specific impulse spherical steady-state System File Table Tank Design tank pressure thrust chamber valves thrust level thrust vector thrusters Titan IV titanium total impulse UDMH ullage usable propellant velocity change Viking Orbiter