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- Title
Neutral Burning Grain Geometry of Composite Propellant for Solid Rockets of Multi Barrel Rocket Launcher.
- Authors
Bose, P.; Pandey, K. M.
- Abstract
Ballistic requirement of the solid rocket motors of multi barrel rocket launcher (MBRL) is constant thrust generated by the propellant gas during the entire course of flight. This thrust is developed by constant pressure burning of propellant in the rocket casing. For constant pressure burning the propellant grain geometry is designed to have the constant burning surface area during thermal decomposition of the propellant. Grain geometry can be designed in several ways to provide neutral burning of propellant. Presently cord, tube, funnel port and star propellant are available which when suitably inhibited provide neutral burning. In this paper a reference composite propellant grain has been considered for various neutral burning surfaces. Major dimensions like outer and inner radii and length have been kept constant to suit common MBRL application. Burning surface areas have been calculated in each case and compared. Burning surface area of particular grain geometry found to be different when the inhibited surface(s) are changed. The surface which provides maximum area and at the same time follows neutral burning is taken into account for comparison. Cord is found to be the simplest neutral burning surface while permitted one end burning but having the minimum burning surface area. Star shape cross section is found to be the most complicated neutral burning surface while permitted internal burning keeping the ends and outer surface inhibited. However, it provides maximum burning surface area. Hence star shape is found to be the shape which would best suit for MBRL application.
- Subjects
COMPOSITE materials; PROPELLANTS; ROCKETS (Aeronautics); ROCKET launching; SURFACE area
- Publication
International Review of Aerospace Engineering, 2012, Vol 5, Issue 6, p268
- ISSN
1973-7459
- Publication type
Article