Experimental Approaches to Develop a High Thrust Ratio in a Single Chamber Dual Thrust Motor Using a Composite Propellant Formulation Based on HTPB/AP/Al

• Autorzy: Kurva R. , Ukey S. , Modgi M. , Mehilal

Identyfikatory

DOI

10.22211/cejem/76704

• Języki publikacji: EN

Abstrakty

EN

A high thrust ratio in a single chamber dual thrust motor is required to reach a peak velocity very quickly. To achieve a high thrust ratio in a single chamber dual thrust motor, a composite propellant grain, which acts both as booster and sustainer, based on HTPB/AP/Al (84% solid loading) with low aluminum content and having a burning rate of 25±0.5 mm/s at 7 MPa, was successfully developed. This was studied for viscosity build-up, mechanical and ballistic properties, followed by casting and curing as a single type propellant grain. The high burning surface area was created by making grooves of 3 mm width and 60 mm depth over the surface of the nozzle side of the grain while casting and a prototype, thus obtained, was static tested. The data revealed that a grain with one groove demonstrated a thrust ratio of 8, while two grooves, realized a thrust ratio of 30. The experimental thrust ratio values achieved are also in agreement with the predicted values of the thrust ratio of the same composition.

Słowa kluczowe

EN

dual thrust ratio; single chamber; composite propellant; high burning rate; burning surface area

• Wydawca: Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
• Czasopismo: Central European Journal of Energetic Materials
• Rocznik: 2017
• Tom: Vol. 14, no. 4
• Strony: 917--932
• Opis fizyczny: Bibliogr. 20 poz., rys., tab.

Twórcy

autor

Kurva R.

• High Energy Materials Research Laboratory, Pune-411021, India

autor

Ukey S.

• High Energy Materials Research Laboratory, Pune-411021, India

autor

Modgi M.

• High Energy Materials Research Laboratory, Pune-411021, India

autor

Mehilal

• High Energy Materials Research Laboratory, Pune-411021, India

Bibliografia

• [1] Ricciardi, A. Generalized Geometric Analysis of Right Circular Cylindrical Star Perforated and Taper Grains. Journal of Propulsion 1992, 8: 51-58.
• [2] Shekhar, H. Modelling of Burning Surface Regression of Taper Convex Star Propellant Grain. Def. Sci. J. 2000, 50: 207-11.
• [3] Shekhar, H. Parametric Studies on Star Port Propellant Grain for Ballistic Evaluations. Def. Sci. J. 2005, 55: 459-469.
• [4] Kuo, K. K.; Kokal, R. A.; Paulauskas, M.; Alaksin, P.; Lee, L. S. Flame Spreading Phenomena in Fin Slots of Solid Rocket Propellants. J. Propul. Power 2001, 17:1005-1011.
• [5] Shekhar, H. Close-form Solution for Burning Surface Evolution and Performance Prediction of Finocyl Shaped Propellant Grain. Int. Autumn Seminar on Propellant, Explosives and Pyrotechnics, Xi’an, China, 23-26 October 2007, 907-911.
• [6] Nissar, K.; Guozhu, L. Design and Optimization of Three-dimensional Finocyl Grain for Solid Rocket Motor. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibits, Hartford, CT, 21-23 July 2008, Paper No. AIAA-2008-4696.
• [7] Hartfield, R. J.; Burkhalter, J. E.; Jerkins, R. M.; Witt, J. Analytical Development of a Slotted Grain Solid Rocket Motor. J. Propul. Power 2004, 20: 690-694.
• [8] Umbel, M. R. An Exact Geometric Analysis of the Generalized Anchor Grain Configuration. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibits, Hartford, CT, 21-23 July 2008, Paper No. AIAA 2008-4697.
• [9] Thomson, B. L. Demonstration of a Single-Chamber Dual Thrust Motor (U). Report No. S93, Rohm & Haas Company Redstone Arsenal Research Division, Huntsville, Alabama, USA 1996.
• [10] Penny, P. D. Rocket Missile with Two Different Charges. Patent EP 0142 246A1, 1985.
• [11] Kubota, N. Propellants and Explosives, Thermochemical Aspects of Combustion. 3rd ed. Wiley-VCH, Weinheim, Germany 2015; ISBN 978-3-527-33178-9.
• [12] Hu, K. X.; Zhang, Y. C.; Cai, X. F.; Ma, Z. D.; Zhang, P. Study of High Thrust Ratio Approaches for Single-chamber Dual Thrust Solid Rocket Motors. 30th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Indianapolis, IN, June 27-29, 1994.
• [13] Barrere, M.; Jaumotte, A.; Fraeijs de Veubeke, B.; Vandenkerchove, J. Rocket Propulsion. Elsevier, London, New York, Princeton 1960.
• [14] Carrier, J. L. C. Solid Rocket Motor with Interrupted Thrust. Patent US 4972673, 1990.
• [15] Carter, J. M. M. Single Chamber Dual Thrust Rocket Motor. Patent US 3011309 A, 1961.
• [16] Bornstein, L. J. Method of Making Dual Thrust Rocket Motor. Patent US 4137286 A, 1970.
• [17] Iwama, A.; Aoyagi, S.; Sofue, T.; Yamazaki, K. Characteristics of Dual-layer Propellants for End-burning Type Rockets and Their Application to a Dual Thrust Motor. 6thProc. Int. Symp. Space Technol. Sci. 1966, 57-67.
• [18] Gupta, G.; Jawale, L.; Mehilal; Bhattacharya, B. Various Methods for the Determination of the Burning Rates of Solid Propellants: an Overview. Cent. Eur. J. Energ. Mater. 2015, 12: 593-620.
• [19] Propellants, Solid Sampling, Examination and Testing, Method, 403.1.3. MIL-STD-286C, 1991.
• [20] Kurva, R.; Gupta, G.; Jawalkar, S. N.; Vipin, L.; Kulkarni, P. S.; Mehilal Studies on Comparative Performance of RDX, HMX and CL-20 in Hydroxyl Terminated Polybutadiene Based Composite Propellant Formulations. Adv. Sci., Eng. Med. 2016, 8: 543-551.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).