Determination of the Internal Ballistic Properties of Solid Heterogeneous Rocket Propellants

• Autorzy: Florczak B. , Białek M. , Cholewiak A.
• Języki publikacji: EN

Abstrakty

EN

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.

Słowa kluczowe

EN

solid heterogeneous rocket propellant (SHRP); internal ballistic properties; laboratory rocket motor (LRM)

• Wydawca: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
• Czasopismo: Central European Journal of Energetic Materials
• Rocznik: 2014
• Tom: Vol. 11, no. 4
• Strony: 589--601
• Opis fizyczny: Bibliogr. 8 poz., rys., tab.

Twórcy

autor

Florczak B.

• Institute of Industrial Organic Chemistry, 6 Annopol St., 03-236 Warsaw, Poland

autor

Białek M.

• ZPS „GAMRAT” Sp. z o. o., Jasło, Poland

autor

Cholewiak A.

• ZPS „GAMRAT” Sp. z o. o., Jasło, Poland

Bibliografia

• [1] Kubota N., Propellants and Explosives. Thermochemical Aspects of Combustion, Wiley-VCH GmbH, Weinheim, 2007, pp.17, 412.
• [2] Maggi K, DeLuca L.T., Bandera A., Burn-rate Measurement on Small-scale Rocket Motors, Def. Sci. J., 2006, 56, 353-367.
• [3] Strecker R., Ch. 3, Comparison of Burning Rate Measurements Technologies/ Devices, NATO-RTO Technical Report No. RTO-TR-043, 2002, 38.
• [4] Fry R.S., Gadiot G.M.H.J.L., Ch. 4, Burning Rate Measurement Analysis Method, NATO-RTO Technical Report No. RTO-TR-043, 2002, (Table 4.6), 62.
• [5] Florczak B., Biatek M., Szczepanik M, Dzik A., Studies on Elaborating Non-homogeneous Solid Rocket Propellant for Propellant Cartridges Bonded to Motor Chamber Well, Chemik, 2013, (57(1), 25-32.
• [6] Florczak B., Bialek M., Szczepanik M., Dzik A., Matlok A., Study on Double-base Propellant with Laboratory Rocket Motor (in Polish), Przem. Chem., 2013, 92(6), 1042-1045.
• [7] Florczak B., Investigation of an Aluminized Binder/AP Composite Propellant Containing FOX-7, Cent. Eur. J. Energ. Mater., 2008, 5(3-4), 65-75.
• [8] Florczak B., Kwilosz S., Cholewiak A., Biatek M., Miszczak M., Laboratory Rocket Motor (in Polish), PL Patent 217675, 2014.