摘要:

AbstractRecent developments in extrudable composite propellant technology enable higher energy/density formulations and novel charges to be successfully manufactured, which cannot be produced by castable composite technology processes. These also offer substantial capital, labour and time savings in certain production applications.New heavy duty processing machines have been developed recently, which have been used successfully for the safe and efficient manufacture of new high energy/fast burning rate composite propellants, using batch and continuous processes. These include injection flow forming techniques and die extrusion processes for filling rocket motors. A range of non‐energetic binder systems based on non‐curing plastic, curing HTPB and TPE binder systems have been successfully manufactu

ISSN:0721-3115    

DOI:10.1002/prep.19900150602

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractA large variation in surface roughness of the procclain plates, in use on the BAM friction tester (Julius Peters), was observed and confirmed by surface texture measurement. The relationship between the friction sensitivity of primary explosives and the rubbing surface roughness was investigated by using different emery‐paper grades.The replacement of porcelain friction plates by an emery‐paper test‐piece is suggested. Apart from improved reliability of results, this modification to the existing technique greatly reduces the associated safety risk, costs and lesting

ISSN:0721-3115    

DOI:10.1002/prep.19900150603

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

Abstract2,6‐Diphenylmcthylene‐thiazolo‐pyrimidine‐trione, the o‐, m‐, and p‐nitrophenyl‐derivatives were prepared and incorporated as stabilizers in a double base smokeless powder. The prepared powders were subjected to some standard qualitative and quantitative stability tests. It was found that the 2,6 diphenyl trione (Ia) has a good stabilizing effect for double

ISSN:0721-3115    

DOI:10.1002/prep.19900150604

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractTemperature sensitivity of burning rate of magnesium‐sodium nitrate propellants has been determined at different mixture ratios in the temperature range between – 40°C and + 50°C. The results indicate that the temperature sensitivity is minimum at high magnesium loadings and increases as the proportion of magnesium in the mixture decreases. Thermal decomposition data indicate that the oxidation of magnesium with sodium nitrate in a propellant is governed by the condenscd phase heat release. This heat which is maximum at high fuel concentration is seen as causing prcssure independent, high burning rate with low temperature sensitivity. The reduction of magnesium content in the mixture increases the metal agglomeration on the surface of the propellant and causes for the decrease of condenscd phasc heat release and the reaction zone temperature. This causes for pressure dependent, low buring rate with high temperature sensitivity. The burning surface temperature data indicate that the change in the initial temperature of the propellant at low fuel concentration might be causing for the change in the degree of mctal agglomcration which lead to the increase of temperature sensitivity of burning rate. The photographs of the sliver surface obtained after static test at different initial temperature of the propellant support the suggested mech

ISSN:0721-3115    

DOI:10.1002/prep.19900150605

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractThe description of the fragmcnt mass distribution according to Held is in cxcellent agreement with the experimental data. This is true in particular when the total mass, Mo. used in describing the distribution, is slightly modified in that some of the hcavicst fragments are neglected. Because in the case of a shell they do not necessarily follow the distribution law.

ISSN:0721-3115    

DOI:10.1002/prep.19900150606

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractPorous ammonium perchlorate (PAP) was prepared by a successfully developed fluidization process at 230°C. The geometric structure of manufactured PAP was characterized by means of a scanning electron microscope (SEM). The physical and mechanical properties of composite propellans containing PAP were also determined. Owing to the diffusion of binder into pores of PAP, the elongation of propellants decreased

ISSN:0721-3115    

DOI:10.1002/prep.19900150607

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractThe effect of a non‐uniform temperature distribution on the thrust‐time performance of an end‐burning solid propellant rocket motor charge is examined. It is shown that non‐planar surfaces develop. For some classes of temperature distribution, the effect of these non‐planar surfaces os always between the limits of the thrust predicted at the maximum and minimum temperatures. The class of temperature distributions that meet this criterion is determined and a simple inequality is derived to test any actual distribution. An expression for the departure from specification is given for distributions outside this class. These results partially justify the proof of ballistic design by testing motors of uniform temperature at upper and lower limits, when service motors may be exposed to uneven heating. The validity of such testing in actual cases can be d

ISSN:0721-3115    

DOI:10.1002/prep.19900150608

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

摘要:

AbstractVarious methods of preparation of the different polymorphs of HMX have been evaluated. Infrared and Raman spectra have been used to differentiate the polymorphs and understand their conformational behaviour. Possible conformation of the γ form has been suggested

ISSN:0721-3115    

DOI:10.1002/prep.19900150609

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

ISSN:0721-3115    

DOI:10.1002/prep.19900150610

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY

ISSN:0721-3115    

DOI:10.1002/prep.19900150611

出版商:WILEY‐VCH Verlag GmbH    

年代:1990

数据来源: WILEY