By ORBITEC M. Chiaverini, Pennsylvania State University and K. Kuo
"Fundamentals of Hybrid Rocket Combustion and Propulsion" is the 1st textual content to supply a entire therapy of hybrid rockets. during this booklet, editors have pooled jointly one of the most revered minds within the box, every one delivering their very exact perception and services to the textual content. The content material is for that reason as updated because it is wide. each one bankruptcy bargains a professional account of each point of hybrid rocket propulsion, together with primary elements of hybrid combustion, numerical and theoretical ways, and numerous functions. All chapters are more desirable with greater than 25 to 35 graphical parts - together with tables, figures and images. Making for a simple and informative learn, this ebook is a must have source for a person presently operating in or learning rocket propulsion.
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Additional info for Fundamentals of Hybrid Rocket Combustion and Propulsion
However, it does experience a low-frequency chugging-type behavior that can be aggravated by inadequate vaporization of a liquid oxidizer in the precombustion chamber. This is not a fundamental objection because all rocket and airbreathing engines have experienced instability at some time in their development, but it does need more research for acceptable resolution. In contrast to the solid and liquid rocket development programs, the hybrid has received only a fraction of the investment made with the other engines.
320. Ewing, E. G. Journal of the Pacific Rocket Society, 1947. Moore, G. , and Berman, K. “A Solid Liquid Rocket Propellant System,” Jet Propulsion, Vol. 26, No. 11, 1956. S. Patent No. 3,136,119, 9 June 1964. La Force, P. , and Wolff, H. “Demonstration of an Upper Stage High Energy Hybrid Rocket,” 12th Annual Liquid Propulsion Meeting, 24 Aug. 1970. Salmon, M. “An ONERA Hybrid Rocket for Scientific Probes,” World Aerospace Systems, May 1968, p. 5. Aviation Week and Space Technology, 12 May 1997.
Except for the component failure, the motor performance was as predicted for the initial period and was the largest hybrid vehicle flown, despite its short duration. The company was subsequently reorganized in 1985 and renamed AMROC under a new sponsor. The company was founded on the belief that a nonexplosive, throttleable and low-cost manufacturing system could translate to a profitable, competitive commercial launch vehicle. With private funding, AMROC proceeded to build a series of motors at vacuum thrust levels between 5000 lb and 260,000 lb based on LOX/HTPB propellants.