Model rocket motors

First find the two wires in the rocket tail section which disappear through a plastic plug into the rocket motor. (In the current model of the 3.5, these are the two wires covered with clear plastic.)... 

Sirignano L. Crocco, "A Shock Wave Model of Unstable Rocket Combustors , AIAA 2, 1285(1964) I) B.T. Zinn, "A Theoretical Study of Nonlinear Transverse Combustion Instability in Liquid Propellant Rocket Motors (PhD Thesis)> Princeton Univ, May 1966 J) C.E. Mitchell, "Axial Mode Shock Wave Combustion Instability in Liquid Propellant Rocket Engines (PhD Thesis), Princeton Univ, NASA CR 72229(1967) K) E.L. 

Rocket Launcher and Rocket Motor Model 10 (p 172) was designed to propel the 60-kg aircraft bomb out of an inclined trough. The launcher was constructed of wood and metal with legs made of iron pikes. The launcher channel was a right angle wooden trough, ca 20 ft long with a motor and bomb positioner... 

Rocket Motors (Roketto Hasshaki) are devices designed to provide propulsive power (propel or launch) to a Bomb or Rocket Projectile of an inclined trough or barrel called Launchers One of such Rocket Motors is described and illustrated in the book of Tantum Hoffschmidt (Ref 7, p 172) under the title Rocket Launcher and Rocket Motor Model 10 . It is briefly described here under Rocket Launchers. They are also described in Ref 2, pp 120-1 Another Rocket Mortar (Type 4 Mk 1) is described here under ROCKET BOMBS as a device used to propel Baka Piloted Rocket Bomb (Ref 2, p 118)... 

There was also Special Mk 1 Rocket Motor Model 21 which consisted of a cylinder 80.3 inches long 11.8 inches in diam with rounded nose and a venturi tube attached at the rear. 

NFPA 1125 Pyrotechnic Articles Code for the Manufacture of Model Rocket and High Power Rocket Motors... 

SIMPLIFIED MODEL OF COMBUSTION IN A LIQUID-PROPELLANT ROCKET MOTOR... 

Simplified Model of Combustion in a Liquid-Propellant Rocket Motor... 

It is of interest to consider a bipropellant rocket motor (M = 2) in which liquid fuel FJ = 1) and liquid oxidizer (OJ = 2) undergo the overall reaction v F + v O products. Since the present model prevents us from considering gaseous reactions, the fuel and oxidizer must evaporate in stoichiometric proportions—that is, by the same kind of reasoning that was used in Section 11.2.3. 

Although analyses in which some of these assumptions are removed, for example, by accounting for finite gas-phase reaction rates [53], for non-uniform particle-size distributions [54], [55], [56] and for droplet breakup [57], [58], are more realistic in that correlations with observed rocket-motor performance sometimes can be obtained, they involve numerical integrations which may tend to obscure the essential ideas. Simple analytical results have, however, been 5eveloped for a model that accounts in an approximate way for nonuniform size distributions [59]. Comprehensive reviews of related studies may be found in [58] and [60]. The major drawback to all of these analyses is the one-dimensional flow approximation, which excludes from consideration the three-dimensional flows generally observed in real engines. 

The phenomenon of unstable combustion results from a self-amplifying interaction between combustion processes and the. acoustic oscillations of the gas within the rocket motor. The unexpected appearance of combustion instability in any rocket generally terminates its mission thru motor case rupture from overpressure, disruption of guidance systems by severe vibration, or thrust malalignment. Both axial mode and transverse mode instabilities are observed (Ref 45). In the case of the transverse mode the characteristic wave time is usually that required to travel radially around the proplnt cavity whereas the characteristic time for the axial mode is the time for the wave to travel from end to end in the combustion chamber. Double-base proplnts predominantly are prone to transverse wave instabilities and infrequently to those in the axial mode, while composite proplnts appear to go unstable mostly in the axial mode. In the case of transverse instability chamber pressures have been known o double whereas in axial mode instabilities artificially induced by pulsing the chamber pressure at lOOOpsi, the pressure excursion may reach 300—400psi. A review of recent theoretical combustion modeling for combustion instability has been made by Price (Ref 47)... 

In model rocketry and fireworks, most rocket motors use Black Powder or compositions similar to Black Powder. Generally fireworks rockets produce a trail of sparks, which result from the addition of large charcoal or metal particles. 

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