摘要:

AbstractThis study introduces a new type of gs generator on the basis of triaminoguanidine nitrate with polymeric binders in the form of polyurethane polymers, cellulose acetate and the azidopolymer GAP with nitroplasticizer. TAGN propellants demonstrate low burning temperatures, high yields of gaseous products adn adjustable medium to high burning velocities. Together with high chemical and thermal stabilities, good mechanical properties to high and low temperatures, no exhaust of corrosive gases and very low sensitivity, the gas‐generator propellants exhibit outstanding propertie

ISSN:0721-3115    

DOI:10.1002/prep.19920170402

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractGas generators with high boron content of interest for ducted rockets were prepared and characterized. The parameters tested were:–combustion residue–pressure exponent–flow and temperature of the ejected boron particles–mechanical properties.The results of the experments (optical bomb, high speed camera, two‐color pyrometer, thermal analysis, tensile test) are presented and

ISSN:0721-3115    

DOI:10.1002/prep.19920170403

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractFirst results will be presented in the field of LOVA gun propellants with polyglycidylazide‐binder system. Theoretical calculations and experimental investigations were carried out to get informations about the ballistic behavior of this type of gun propellant. Chemical stability and mechanical properties were also determined. In addition, the bullet impact test was performed. All these dta were compared with those of nitramine‐gun propellants based on H

ISSN:0721-3115    

DOI:10.1002/prep.19920170404

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractFour double‐base rocket propellants and a single‐base gun propellant were tested to find out stabilizer consumption molar mass degradation, and heat generation between 50 °C and 90 °C and between 40 °C and 110 °C, respectively. Stabilizer depletion was measured by high performance liquid chromatography (HPLC), molar mass degradation by gel permeation chromatography (GPC), and heat generation by microcalorimetry. The conditioning times at different temperatures were determined with one of the rocket propellants, and the influence of the long‐term storage on heat generation at 60 °C for 2191 dys was investigated. A correlated experiment between stabilizer consumption and heat generation showed that heat production does not increase substantially until the stabilizer has been consumed almost completely. The experimental data of molar mass degradation are described by a kinetic model based on statistical chain scission, and the stabilizer decrease by a first order reaction. For the gun propellant the Arrhenius plots of the reaction rate constants show two temperatures of teh stabilizer consumption, molar mass degradation and heat generation were

ISSN:0721-3115    

DOI:10.1002/prep.19920170405

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractRDX products obtained at high heating rates are discussed. RDX was decomposed by combustion in pressurized bomb and by short laser pulse irradiation.

ISSN:0721-3115    

DOI:10.1002/prep.19920170406

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractThis paper describes the synthesis of linear azidopolyesters which appear suitable as high‐energy binders in explosive systems. Preparation is carried out via a nucleophilic substitution reaction from the corresponding halogenic polyesters with sodium azide. In the polycondensation of the halogen derivates, the authors examined the influence of the intial compound ratio of dicarbonic acid and diol on the distribution of end groups and molecular weight. In this work it was found that the azido group could be introduced into the polyester backbone relatively easily. Some properties of polyesters are fundamentally changed through the introduction of the azido group. The changes as regards viscosity, thermal stability and glass transition temperature were documented and the friction and impact sensitivities recorde

ISSN:0721-3115    

DOI:10.1002/prep.19920170407

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractMain topics of developing and optimizing liquid gun propellants are the suppression of oscillations, and increase in performance and an improvement of electrical conductivity. Additives for the liquid system nitromethane/methanol will be described, that will change the evaporation and reaction kinetics by varying the physical and chemical properties. This will lead to an improved escillation behavior.Energetic additives, based on organic azido‐compounds, will cause a significant enhancement in performance. The electrical conductivity is improved by special compounds on the base of transition metal nitrates.The investigations show a small effect of the physical modifiers. A significant suppression of oscillations is reached by mechnistical additives. Using these additives, the interaction of the specific energy with an accompanying increase in intensity of oscillation ‐ will be minimized. As a consequence, the possibility of an additional enhancement in performance is given, due to the developed energetic additi

ISSN:0721-3115    

DOI:10.1002/prep.19920170408

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractThe phases of HMX and their transitions were investigated by thermal analysis using X‐ray diffraction. Series of diffraction pattern were measured, while the samples were heated and cooled. The thermal expansion coefficients and the colume changes at the transitions were extracted from the diffraction series. A contraction of β‐HMX was found before changing into δ‐HMX resulting in a high volume difference during the transition. On cooling, the reconversion of the high temperature phase requires days. It is further slowed down by decomposition products, which are formed at temperatures beyond 490 K. The final reconversion results in mixtures of α‐and βHMX.The mechanical sensitivities and the buring rates of the HMX phase were determined. The high sensitivity of δ‐HMX against impact together with its slow reconversion creates handling risks when the HMX is exposed to temperatur

ISSN:0721-3115    

DOI:10.1002/prep.19920170409

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractA process for determining the aging characteristics of solid rocket propellants by measuring their dynamic mechanical properties is described. Samples of rocket propellant are tested using a mechanical spectrometer at low strain levels and low frequencies. The change in the dynamic storage modulus of the propellant with aging time and temperature is used to determine the aging rate anf the likely mechanisms occuring during aging. The technique is advantageous is several respects:(1)because the tests are non‐destructive and use small test specimens, and entire aging program can be conducted using much less propellant than is required ihn traditional aging programs (propellant requirements are reduced by more than an order of magnitude)(2)the technique can be applied to samples with unusual or unique geometries which cannot be tested using traditional methods;(3)test specimens can be obtained directly from live, operational solid rocket motors, and service life and mechanical property degradation can be determine

ISSN:0721-3115    

DOI:10.1002/prep.19920170410

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY

摘要:

AbstractTwo methods are described to determine the temperature in a solid propellant flame by analysis of emission spectra. First, experimental spectra of NH and CN radicals were compared with calculated spectra using a least squares fit routine with the parameters temperature T and halfwidth of the line profile Δλ. Second, in flames where no or only small band intensities were observed, the occurring continuous spectra were fitted to a Planck radiation. The emission coefficient ϵ was there by suggested as a function of wavelength λ and temperature T. The first technique was applied to the nitrmine propellant HMX, the second to a composite propellant consisting of 15% AI, 15% GAP and 70% ammonium perchlorate. TO detect the emission, propellant strands were burnt in an optical bomb under nitrogen atmosphere at various pressures (octogen at 0.1 MPa, composite at 2 MPa). To calibrate the intensities of the continous spectra tungsten strip lamp was used. The maximum time resolution of the used spectrometer system is about 10 ms. The determined temperature range was from 2300 K to 3000 K, which is about 20% below the corresponding adiabatic temperature (nitramine propellant: 2900 K, composite propellant: 3500

ISSN:0721-3115    

DOI:10.1002/prep.19920170411

出版商:WILEY‐VCH Verlag GmbH    

年代:1992

数据来源: WILEY