S1_4 The microwave-thermal rocket engine
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This paper describes a new design of electrically powered rocket engine. A microwave thermal rocket uses microwave energy to heat a propellant, which expands in the rocket chamber and out of the rocket’s nozzle, the reaction of which pushes the rocket forwards. It is shown that by varying the mass flow rate, the exhaust velocity and thrust can be altered arbitrarily, making the rocket theoretically suitable for both atmospheric and orbital propulsion. A performance comparison is done with existing forms of space propulsion and ideas for further development are given.Keywords:
Rocket (weapon)
Rocket engine nozzle
Rocket engine
Rocket propellant
Liquid-propellant rocket
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Solid-fuel rocket
Specific impulse
Cone (formal languages)
Rocket (weapon)
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Solid-fuel rocket
Rocket engine
Rocket (weapon)
Space launch
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The analytical procedures described in NASA CR-150162 were extended for the purpose of analyzing the data from the first static test of the Solid Rocket Booster for the Space Shuttle. The component of thrust associated with the rapid changes in the internal flow field was calculated. This dynamic thrust component was shown to be prominent during flame spreading. An approach was implemented to account for the close coupling between the igniter and head end segment of the booster. The tips of the star points were ignited first, followed by radial and longitudinal flame spreading.
Booster (rocketry)
Solid-fuel rocket
Rocket (weapon)
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Rocket engine
Rocket (weapon)
Solid-fuel rocket
Solid fuel
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Solid-fuel rocket
Rocket (weapon)
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A short-duration rocket testing technique which exactly duplicates the combustion flows of multi-engine rocket boosters at high altitudes is described. The application of this technique to the investigation of the reverse flow characteristics of a 4-engine rocket cluster model is discussed. The use of a comparatively new diagnostic tool, the electron beam density probe, in mapping the recirculating flow field of a rocket cluster is described and experimental density results presented. Finally, the use of a reflection plane for the examination of reverse flow phenomena, whereby a plane of symmetry is replaced by a solid surface on which measurements may be made,is evaluated and experimental data presented.
Rocket (weapon)
Rocket engine
Rocket engine nozzle
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Abstract : An analysis of solid rocket motors was made in order to find the chamber pressure and thrust during the transient periods of buildup and decay. The results are differential equations and solutions of closed form.
Solid-fuel rocket
Transient (computer programming)
Chamber pressure
Rocket (weapon)
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