Rocket launching conditions with relation to loading of solid rocket propellants are simulated by using a modified Rotter apparatus and a Zwick impact testing device. Samples of N-4 propellant have been loaded in compression or tension tests to evaluate the testing apparatus and to determine stress-strain relationships. The impact experiments of N-4 propellant at 20 C confirm that no mechanical failure of this solid propellant will occur during the fast pressure-rise after ignition. (Author)
Reliability Analysis of Solid Rocket Propellants and Engines. Part 11: Determination of Mechanical Properties of Homogeneous Solid Rocket Propellants for Fast Deformation Betrouwbaarheidsonderzoek van Raketkruit en Raketmotoren. Elfde Deelverslag. Bepaling van Mechanische Eigenschappen van Homogeen Raketkruit Bij Snelle Deformatie
1975
73 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Rocket Propellants , Double base rocket propellants , Sidewinder missiles , Solid propellant rocket engines , Deformation , Mechanical properties , Reliability analysis , Computer programming , Cracking (Fracturing) , Impact tests , Propellant grains , Rocket launching , Strain rate , Stress-strain diagrams , Viscoelasticity , Netherlands
NTIS | 1967
|Online Contents | 1996
|NTIS | 1969
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