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Wyszukujesz frazę "rocket, A." wg kryterium: Wszystkie pola

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    Wyświetlanie 1-10 z 10
    Tytuł:
    Measurement of Energy Emitted by Pyrogenic Tablets Used for Ignition of Solid Rocket Propellants
    Autorzy:
    Wolszakiewicz, T.
    Walenta, Z. A.
    Powiązania:
    https://bibliotekanauki.pl/articles/358492.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    pyrogenic tablets
    measurement of absorbed heat
    ignition of rocket propellant
    Opis:
    In order to ignite a solid rocket propellant special igniting devices – pyrogenic tablets – must be used. The reported research was aimed at finding the best material for such pyrogenic tablets, which would successfully replace the still frequently used black powder. The measurement of heat, absorbed by the rocket propellant from various kinds of pyrogenic tablets against time, as well as tests of the ignition of the rocket propellant in a stationary engine, were performed. It was concluded, that of all of the mixtures considered, the best material for pyrogenic tablets was a mixture of 25% Zr and 75% KNO3.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 2; 359-375
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Studies of the Influence of Nano Iron(III) Oxide on Selected Properties of Solid Heterogeneous Propellants Based on HTPB
    Autorzy:
    Bogusz, R.
    Magnuszewska, P.
    Florczak, B.
    Maranda, A.
    Drożdżewska, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/358189.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    combustion rate modifier
    nano iron(III) oxide
    solid heterogeneous rocket propellant
    HTPB
    LRM
    Opis:
    This paper presents the results of investigations into the use of 56 nm nano iron(III) oxide as a combustion rate modifier in a solid heterogeneous rocket propellant (SHRP). A series of solid heterogeneous rocket propellants based on HTPB and ammonium perchlorate with different nano iron(III) oxide contents in the propellant composition were prepared and investigated. The ballistic parameters of the examined propellants were determined by combustion in a laboratory rocket motor (LRM). The ballistic properties were evaluated in the pressure range 5-10 MPa. It was found that the linear burning rate at 7 MPa was increased by 15% for 1% nano iron(III) oxide content in comparison to 0.2% content. Determination of the sensitivity to friction and impact, the calorific value, hardness and decomposition temperature of the derived propellants were also investigated.
    Źródło:
    Central European Journal of Energetic Materials; 2016, 13, 4; 1051-1063
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Ballistic Analysis of Missile Propulsion in a Perforated Barrel Launcher
    Autorzy:
    Surma, Zbigniew
    Leciejewski, Zbigniew
    Powiązania:
    https://bibliotekanauki.pl/articles/1062726.pdf
    Data publikacji:
    2020
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    mechanics
    internal ballistics
    rocket propulsion system
    perforated barrel
    Opis:
    This study presents a ballistic analysis of the propulsion of a smart counter-projectile in an active protection system. In order to reduce the pressure of the propellant gases inside the semi-closed barrel of the launcher and to mitigate the effects of the recoil of the launcher, a perforated barrel was chosen. For the system considered, a physical model and a mathematical model of the propulsion of a rocket projectile in a perforated barrel, as well as a computer program, were developed. The gas pressures inside the combustion chamber of the rocket engine and the barrel, as well as the velocity and travel of the missile are the main results from the solution of the presented mathematical model. Based on the resulting calculations, the influence of the holes in the perforated barrel on the operating conditions of the rocket engine, as well as the pressure of propellant gases and the missile velocity inside the barrel were analysed. The use of a perforated barrel caused a significant reduction in the total impulse of the propellant pressure inside the barrel. Based on experimental tests of the barrel launcher-missile assembly, a decrease (about 50%) in the muzzle velocity of the missile was observed. The mathematical model of the interior ballistics presented here allows the missile propulsion, both in a monolithic- as well as a perforated barrel-launcher, to be investigated.
    Źródło:
    Central European Journal of Energetic Materials; 2020, 17, 4; 475-491
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Determination of the Internal Ballistic Properties of Solid Heterogeneous Rocket Propellants
    Autorzy:
    Florczak, B.
    Białek, M.
    Cholewiak, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/358111.pdf
    Data publikacji:
    2014
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    solid heterogeneous rocket propellant (SHRP)
    internal ballistic properties
    laboratory rocket motor (LRM)
    Opis:
    This paper describes the determination of the internal ballistic properties of tubular, solid heterogeneous rocket propellant (SHRP) charges based on hydroxyl terminated polybutadiene (HTPB) binder. The SHRP charges were screened (inhibited) on their external cylindrical surfaces and inserted into a laboratory rocket motor (LRM). These determinations originated from theoretical considerations and were developed using experimental measurements from static firings of SHRP charges in an LRM. Due to the design of the SHRP charge, its burning process began from the inner cylindrical surface and from both ends of the ring surfaces. The initial temperatures (Tp) of the SHRP charges tested were 233, 288 or 323 K in single static firing runs. On the basis of the pressure (p) of the combustion products of the SHRP vs. time (t) of the LRM operation, the dependence of the burning rates (rb) of the SHRP charges on (p) and on (Tp), and also the (rb) sensitivity to changes in (p) and (Tp), were determined by means of the indirect method.
    Źródło:
    Central European Journal of Energetic Materials; 2014, 11, 4; 589-601
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Ageing Behaviour of HTPB Based Rocket Propellant Formulations
    Autorzy:
    Cerri, S.
    Bohn, M. A.
    Menke, K.
    Galfetti, L.
    Powiązania:
    https://bibliotekanauki.pl/articles/358902.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    solid rocket propellant
    HTPB
    nanoAl
    ageing
    mechanical properties
    Opis:
    The ageing of HTPB propellant formulations containing nanoAl is investigated. During natural ageing the material undergoes a series of slow physico-chemical degradation reactions. By using accelerated ageing conditions it is possible to simulate the material behaviour at different time-temperature conditions especially focused on the in-service conditions. The mechanical and ageing behaviour of aluminised solid rocket propellants were investigated in terms of uniaxial tensile strength, DMA measurements, impact and friction sensitivity tests, SEM analyses.
    Źródło:
    Central European Journal of Energetic Materials; 2009, 6, 2; 149-165
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Study of Mechanical Properties of Naturally Aged Double Base Rocket Propellants
    Autorzy:
    Sućeska, M.
    Matečić Mušanić, S.
    Fiamengo, I.
    Bakija, S.
    Bakić, A.
    Kodvanj, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/357946.pdf
    Data publikacji:
    2010
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    mechanical properties
    rocket propellant
    natural ageing
    dynamic mechanical analysis
    tensile test
    Opis:
    Various chemical reactions and physical processes (such as stabilizer consumption, migration and evaporation of nitroglycerine, decomposition of nitroglycerine and nitrocellulose, etc.) take place in double based rocket propellants grains over the time, even under ambient storage conditions. The overall effect of these reactions and processes are changes of physical, chemical, thermal, ballistic and mechanical properties of rocket propellants with storage time, i.e. the reduction of the propellants performances and safe service life. The aim of this work was to evaluate the mechanical changes of rocket propellants – sustainers, built in in-service antitank guided missiles systems, induced by natural ageing at ambient conditions during up to 35 years of storage. The mechanical and viscoelastic properties were tested using a dynamic mechanical analyser, an uniaxial tensile and compression tester, and a notch toughness tester. The results have shown that the changes of the studied mechanical and viscoelastic properties are evident, although the results of the tests are rather scattered (as a consequence of measuring uncertainty, different ageing histories of propellants, etc.) or changes of some properties are not too pronounced. For example, after 15 years of storage at ambient conditions the glass transition temperature increases for about 5 C, the tan δ in the glass transition region decreases for about 5%, the storage and loss modulus at 25 °C increase for about 15%, Young modulus at 23 C increases up to 30%, the notch toughness at -30 C decreases up to 15%, etc. Along with these tests, the stabilizer content determination and proving ground ballistic tests were also done.
    Źródło:
    Central European Journal of Energetic Materials; 2010, 7, 1; 47-60
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The Effect of Different Copper Salts on the Mechanical and Ballistic Characteristics of Double Base Rocket Propellants
    Autorzy:
    Abdel-Ghani, N.
    Elbeih, A.
    Helal, F.
    Powiązania:
    https://bibliotekanauki.pl/articles/357974.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    double base rocket propellant
    burning rate modifiers
    ballistic performance
    mechanical properties
    Opis:
    This paper discusses the enhancement in the ballistic performance of double base rocket propellants (DBRPs) by the addition of different copper salts vs lead salts as burning rate modifiers through stable combustion and the formation of a plateau region in the low pressure region. Compositions based on DBRPs containing different percentages of lead stearate and different types of copper salts were prepared and studied. For comparison, a conventional DBRP was studied. The ignition temperature and heat of combustion were determined experimentally, and the mechanical properties were measured and evaluated. The performance in terms of ballistic characteristics (burning rate, operating pressure) were measured at different throat diameters (8, 8.5, 9, 9.5 mm) and at different temperatures (−20 and 50 °C). Specific impulses were calculated using the ICT thermodynamic code. The experimental data from the proportional study indicate that the compositions containing the studied burning rate modifiers are superior to the original DBRP in respect of ballistic performance and mechanical properties.
    Źródło:
    Central European Journal of Energetic Materials; 2016, 13, 2; 469-482
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Study of the Effect of Nitrated Hydroxyl-terminated Polybutadiene (NHTPB) on the Properties of Heterogeneous Rocket Propellants
    Autorzy:
    Florczak, B.
    Bogusz, R.
    Skupiński, W.
    Chmielarek, M.
    Dzik, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/358481.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    NHTPB
    HTPB
    heterogeneous solid rocket propellant
    linear burning rate
    Opis:
    This paper presents results from research concerning the effect of nitrated hydroxyl-terminated polybutadiene (NHTPB), content up to 3%, on the physicochemical, physico-mechanical and ballistic properties of heterogeneous rocket propellants based on hydroxyl-terminated polybutadiene (HTPB), ammonium perchlorate (AP) and aluminium powder. The results of research on the rheological and thermal properties of the tested solid rocket propellants are also presented. These studies have shown that 2% rubber NHTPB, contained within a composite solid propellant, increases the energy and ballistic parameters of the propellant.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 4; 841-854
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Influence of Polyglycidyl-type Bonding Agents on the Viscoelastic Properties of a Carboxyl-terminated Poly(butadiene-co-acrylonitrilе)-based Composite Rocket Propellant
    Autorzy:
    Brzić, S.
    Dimić, M.
    Jelisavac, L.
    Djonlagić, J.
    Ušćumlić, G.
    Bogdanov, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/358490.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    composite propellant
    carboxyl-terminated poly(butadiene-coacrylonitrilе)
    dynamic mechanical analysis
    viscoelastic properties
    Opis:
    In the present study, functionally substituted bonding agents (triglycidyl isocyanurate and diglycidyl dimethylhydantoin) were incorporated into a composite propellant formulation based on carboxyl-terminated poly(butadiene-co-acrylonitrilе) and ammonium perchlorate. Bonding agents are an important component of a composite propellant, making up to 0.5 wt.% of the formulation. They affect processing, mechanical properties, ballistics, ageing and the characteristics of insensitive munition (IM) propellants. All of the testing has been done using an unmetallized propellant formulation (80 wt.% bimodal ammonium perchlorate and 20 wt.% binder). The focus has been on the mechanical properties of the propellant, as influenced by the presence of these bonding agents. Mechanical uniaxial tensile tests were accompanied by a dynamic mechanical analysis (DMA) over a wide range of temperatures. The storage modulus, loss modulus, loss factor and glass transition temperature for each propellant sample have been evaluated. The network characteristics, such as sol-gel content and crosslink density have been calculated and successfully correlated with the mechanical properties. The dynamic mechanical studies showed that the content of the bonding agent did not influence the glass transition temperature; however, the loss factor was shown to be a function of the crosslink density.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 2; 307-321
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Synthesis and Characterization of a High Energy Combustion Agent (BHN) and Its Effects on the Combustion Properties of Fuel Rich Solid Rocket Propellants
    Autorzy:
    Pang, W.-Q.
    Zhao, F.-Q.
    Xue, Y.-N.
    Xu, H.-X.
    Fan, X.-Z.
    Xie, W.-X.
    Zhang, W.
    Lv, J.
    Deluca, L. T.
    Powiązania:
    https://bibliotekanauki.pl/articles/358474.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    fuel rich solid propellant
    BHN
    DSC
    TG-DTG
    burning rate
    combustion properties
    Opis:
    A high energy combustion agent (tetraethylammonium decahydrodecaborate, BHN) was prepared by means of an ion exchange reaction (IER), and the prepared samples were characterized by the advanced diagnostic techniques of Scanning Electron Microscopy (SEM), X-ray diffraction (XRD), Thermogravimetric Analysis (TGA), and Differential Scanning Calorimetry (DSC) etc. The effects of BHN particles on the hazard and combustion properties of fuel rich solid propellants were investigated. The results showed that the BHN samples and fuel rich propellants containing BHN particles can be prepared successfully and solidified safely. The peak temperature of thermal decomposition and the heat of decomposition of the BHN samples prepared were 305.8 °C and 210.9 J•g-1 at a heating rate of 10 K•min-1, respectively. The burning rate and pressure exponent of fuel rich solid propellants decreases with increases in the fraction of BHN particles in the propellant formulation. Compared with the reference formulation (sample BP-1), the burning rate of the propellant with 10% mass fraction of BHN particles (sample BP-4) had decreased 30% at 3.0 MPa, and the pressure exponent had dropped from 0.44 to 0.41.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 3; 537-552
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
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