Performance Augmentation of Boron–HTPB-Based Solid Fuels by Energetic Additives for Hybrid Gas Generator in Ducted Rocket Applications
Experimental investigations were conducted using an opposed flow burner system (OFBS) to examine the combustion characteristics of boron–HTPB-based solid fuels with nano-energetic metal additives such as magnesium and titanium. The study has been mainly on regression rate characteristics and effects of additives on combustion behavior of B–HTPB-based solid fuels for hybrid gas generator in solid fuel ducted rocket (SFDR) applications. In the OFBS, gaseous oxygen (GOX) has been impinged on the solid fuel surface at mass flux range (Gox) of 20–57 kg/m2 s for various concentrations of solid fuel samples. Magnesium addition to the boron–HTPB mixture has been found to help in increasing the regression rate by 12.5% compared to only boron-loaded case at 57 Gox. However, similar result has not been noticed for titanium case. A high-speed camera is used to visualize the burning surface and the ejected burning agglomerates of the solid fuels. Standard material characterization techniques such as FE-SEM, XRD, EDS, and TGA are used for characterizing feed particles as well as condensed combustion products (CCP) of various samples studied in this investigation.
KeywordsBoron nanoparticles (nB) HTPB Metal additives (nMg/nTi) OFBS Hybrid gas generator SFDR
The authors are grateful to the Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, for providing support for establishing the experimental setup. Some of the equipment used in this study were supported by the Institute’s seed grant given to the author ‘SK’ (Grant number: IIT/SRIC/ISIRD/2013-2014, Dt. 21-02-2014).
- 2.Leingang, J.L., Petters, D.P.: Ducted rockets. In: Jensen, G.E., Netzer, D.W. (eds.) Progress in Astronautic and Aeronautic, Tactical Missile Propulsion, vol. 170, pp. 447–468 (1996)Google Scholar
- 3.Miyayama, T., Oshima, H., Toshiyuki, S., Odawara, T., Tanabe, M., Kuwahara, T.: Improving combustion of boron particles in secondary combustor of ducted rockets. In: 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, California, USA (2006)Google Scholar
- 7.Fink, L.E.: Chronological History of SFRJ Flight Tests. Engineering Technology Boeing Aerospace Company (1981)Google Scholar
- 11.Kuo, K.K., Risha, G.A., Evans, B.J., Boyer, E.: Potential usage of energetic nano-sized powders for combustion and rocket propulsion. In: Proceeding of Materials Research Society, vol. 800 (2003)Google Scholar
- 13.Korchagin, M.A., Grigor’eva, T.F., Bokhonov. B.B., Sharafutdinov, M.R., Barinova, A.P., Lyakhov, N.Z.: Solid-state combustion in mechanically activated SHS systems. I: Effect of activation time on process parameters and combustion product composition. Combust. Explos. Shock Waves 39(1), 43–50 (2003)Google Scholar
- 15.Hashim, S.A., Lahariya, M., Karmakar, S., Roy, A.: Calculation of theoretical performance of boron-based composite solid propellant for the future applications. In: 2nd Innovative Design and Development Practices in Aerospace and Automotive Engineering Conference (International), Springer, New Delhi, pp. 327–335 (2016)Google Scholar
- 22.Hashim, S.A., Kangle, S., Karmakar, S., Roy, A.: Combustion characteristics of boron-HTPB based solid fuels for hybrid rocket applications. In: 7th Theoretical, Applied, Computational and Experimental Mechanics Conference (International), Chennai, India (2017)Google Scholar
- 31.Chaturvedi, S., Dave, P.N.: Solid propellants: AP/HTPB composite propellants. Arab. J. Chem., 1–8 (2015)Google Scholar
- 32.Beckstead, M.W.: A summary of aluminum combustion. Paper Presented at the RTO/VKI Special Course on Internal Aerodynamics in Solid Rocket Propulsion, vol. 32, no. 6, pp. 2107–2114 (2002)Google Scholar