Temat: composite solid propellant

Skocz do pozycji: 1.

Tytuł:: Thermal Hazards Studies for the Azidation Process in the Preparation of Tetra Functional Glycidylazide Polymer (t-GAP) Using a Thermal Screening Unit (TSU)
Autorzy:: Adak, Prasanta Kumar
Ghosh, Mrinal
Meena, Ashish Kumar
Jain, Mukesh
Banerjee, Shaibal
Tematy:: energetic binder
hazard
optimization
t-GAP
thermal screening
composite solid propellant; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/59115317.pdf Link otwiera się w nowym oknie
Opis:: Glycidylazide polymer (GAP) tetraol or tetra functional GAP (t-GAP) is a potential energetic binder, capable of exhibiting superior mechanical properties and better curing behaviour for application in high energy propellants. t-GAP is conventionally prepared through azidation of tetra functional poly-epichlorohydrin (t-PECH). Azidation reactions using a metal azide are known to be sensitive to temperature. The present study was aimed at a systematic evaluation of the safe temperature limit for the preparation of t-GAP and to derive optimized reaction conditions using a thermal screening unit (TSU), through both dynamic and isothermal heating experiments. The thermal hazard studies suggested that the azidation reaction is fairly stable at temperatures above 100 °C as it did not exhibit any abrupt rise in reaction temperature or pressure. The process was validated using laboratory scale batches and completion of the reaction was verified using FTIR spectroscopy.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Assessment of the Shelf Life of Composite Solid Propellants in Air and Nitrogen Atmospheres through Thermal Ageing
Autorzy:: Keshavarz, Mohammad Hossein
Hosseini, Seyyed Hesamodin
Mehran, Karimi
Tematy:: composite solid propellant
inert atmosphere
dynamic mechanical thermal analysis
DMTA
damping
ageing; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/27787850.pdf Link otwiera się w nowym oknie
Opis:: This work introduces dynamic mechanical thermal analysis (DMTA) as an efficient method for the assessment of the shelf life of solid composite solid propellants in air and nitrogen atmospheres. The samples were aged at three temperatures 323.15, 333.15, and 343.15 K for 60, 120, and 180 days. The two different methods of Arrhenius and Berthelot were used to compare the effects of air and nitrogen atmospheres on the ageing of composite solid propellants. Damping (Tan δ) of composite solid propellants was used to determine the shelf life of the samples based on the loss of half of the physical property Tan δ (50% drop in damping). For the air atmosphere, the calculated activation energy for the degradation reactions of the samples was 86.26 kJ·mol–1. Both models, Arrhenius and Berthelot, confirmed that the shelf lives of the samples under the nitrogen atmosphere are more than four times those in an air atmosphere.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Studies on the High Performance Characteristics of an Aluminized Ammonium Perchlorate Composite Solid Propellant Based on Nitrile Butadiene Rubber
Autorzy:: Sudhir, Singh
Sidharth, Raveendran
Dhirendra, Kshirsagar R.
Gupta, Manoj
Chetan, Bhongale
Tematy:: composite solid propellant
dibutyl phthalate
high density specific impulse
nitrile-butadiene rubber
pot life
spreadibility
yield stress; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/27787902.pdf Link otwiera się w nowym oknie
Opis:: n the present study, a high performance composite solid propellant formulation was prepared based on nitrile butadiene rubber (NBR) and dibutyl phthalate (DBP) plasticizer, which has a longer pot life and high density specific impulse. The developed cost effective novel binder system was prepared with readily available raw materials (NBR and DBP). The formulation of the composition was performed by varying the content of the NBR/DBP binder in the range of 14-20%. The rocket performance characteristics were determined theoretically using PROPEP and compared with those of an HTPB based propellant. The rheological, mechanical, physical, ballistic and thermal properties of the NBR/DBP propellant were studied and compared with literature data for similar compositions based on an HTPB/dioctyl adipate (DOA) binder. The yield stress was determined by spreadibilty measurements, and indicated the superiority of this binder based propellant over existing composite propellants. It was concluded that following decreasing the content of the NBR/DBP binder in the propellant from 20 to 14%: in the range 58.83-78.45 bar (5.883-7.845 MPa), the pressure index increased from 0.159 to 0.371, – at 68.64 bar (6.864 MPa), the burning rate increased from 4.10 to 6.54 mm/s, but the theoretical specific impulse value did not change significantly (258.0259.8 s), – the tensile strength and E-modulus increased from 6.03 to 9.88 (0.591-0.969) to and from 18.00 to 75.00 kgf/cm2 (1.765 to 7.355 MPa), respectively. Moreover, a DSC and TGA study indicated a lower decomposition temperature for the NBR/DBP propellant compared to the HTPB propellant. The NBR/DBP propellant exhibited a pot life more than double that of a conventional HTPB/ DOA based propellant.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Various Methods for the Determination of the Burning Rates of Solid Propellants : an Overview
Autorzy:: Gupta, G.
Jawale, L.
Mehilal, D.
Bhattacharya, B.
Tematy:: burning rate
composite solid rocket propellant
acoustic emission system
erosive burning; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/358413.pdf Link otwiera się w nowym oknie
Opis:: The burning rate of propellants plays a vital role among the parameters controlling the operation of solid rocket motors, therefore, it is crucial to precisely measure the burning rate in the successful design of a solid rocket motor. In the present review, a brief description of the methods for the determination of the burning rate of solid rocket propellants is presented. The effects of various parameters on the burning rate of solid propellants are discussed and reviewed. This review also assesses the merits and limitations of the existing different methods for the evaluation of the burning rate of solid rocket propellants.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Badania nad modyfikacją składu heterogenicznego paliwa dla dwuzakresowego silnika rakietowego
Studies on Modification of Formulations of Composite Solid Propellant for Dual Thrust Rocket Motor
Autorzy:: Florczak, B.
Cholewiak, A.
Tematy:: stałe heterogeniczne
paliwo rakietowe
dwuzakresowy silnik rakietowy
materiał wysokoenergetyczny
composite solid propellant
dual thrust rocket motor
high energetic material; Pokaż więcej
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Powiązania:: https://bibliotekanauki.pl/articles/403420.pdf Link otwiera się w nowym oknie
Opis:: W pracy przedstawiono wyniki z badań zmodyfikowanych ładunków napędowych dla dwuzakresowego silnika rakietowego. Modyfikacja polegała na optymalizacji składu heterogenicznego paliwa rakietowego na bazie nadchloranu amonu jako utleniacza i lepiszcza na bazie ciekłego kauczuku PBAN z dodatkiem Al. W rezultacie otrzymano paliwo z lepszymi parametrami energetycznymi w porównaniu do paliwa odniesienia.
This paper presents the results of investigations of modified composite solid propellant charges for the dual made rocket motor. The modification has been done by selection of composition of the heterogeneous solid propellant made on the base of ammonium perchlorate as an oxidizer and the binder on the base of liquid rubber PBAN. As a result of modifications it was obtained the composite solid rocket propellant of better energetic and ballistic properties in comparison with the reference composite propellant.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Energetic Performances of Solid Composite Propellants
Autorzy:: Lempert, D.
Nechiporenko, G.
Manelis, G.
Tematy:: solid composite propellant
specific impulse
density
combustion temperature
formation enthalpy; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/357962.pdf Link otwiera się w nowym oknie
Opis:: Different kinds of solid composite propellant (SCP) are described. All ways to increase energetic potential of SCP are considered as well as pro et contra of each of these ways. Different kinds of oxidizer (perchlorates of ammonium, hydroxylammonium, and hydrazinium; ammonium salt of dinitramine; other saltlike and molecular oxidizers) are under consideration. The main principles creation of SCP formulation with optimal characteristics in the context of their concrete purpose are discussed, e.g. for rockets with considerably low ratio propellant volume/empty construction mass (V/M lower than 1 Litr/kg or so) the ballistic effectiveness may be increased with the replacement of aluminum by high-dense zirconium or zirconium hydride. Possibilities for creation of special SCP formulations for application at the far space, e.g. for Mars exploration are discussed as well.
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

Tytuł:: Development of a Composite Propellant Formulation with a High Performance Index Using a Pressure Casting Technique
Autorzy:: Ramesh, K.
Jawalkar, S. N.
Sachdeva, S.
Bhattacharya, B.
Tematy:: composite propellant
high density
high performance index
pressure casting
solid loading; Pokaż więcej
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
Powiązania:: https://bibliotekanauki.pl/articles/358322.pdf Link otwiera się w nowym oknie
Opis:: There is a continuous demand for high performance composite propellant formulations to meet future requirements. The performance of composite propellant formulations can be enhanced by the addition of energetic oxidizers, like ADN/HNF as well as an energetic binder & a plasticizer. However, on incorporation of energetic ingredients, the composition becomes sensitive, and thus processing, handling and transportation pose a greater threat. Therefore, a moderately high burn rate composition having a burn rate ~ 13-14 mmźs -1 at 7000 kPa was tailored by increasing the solid loading of the propellant from 85.15% to 87.27% with the help of ammonium perchlorate and process aids without affecting the burn rate and mechanical properties. The tailored composition was studied for different properties such as end of mix viscosity, density, mechanical & ballistic properties. The evaluated data reveal that the end of mix viscosity of the tailored composition is higher than the base composition, i.e., 672 Paźs and 2340 Paźs at the same temperature; however, this viscosity was castable using a pressure casting technique. The properties of the cured propellant reveal that there is an enhancement of density from 1.74 gźcm -3 to 1.79 gźcm -3 with no other changes in mechanical properties. The performance index of the tailored composition has been increased from 416 to 437, well supported by results of ballistic evaluation motors of 2 kg.
Dostawca treści:: Biblioteka Nauki

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