Research on manufacturing of charge for target missile cruise motor based on RST propellant
101 viewsDOI:
https://doi.org/10.54939/1859-1043.j.mst.IPE.2024.60-67Keywords:
Missile; MTB01; Propellant RST; Rocket motor.Abstract
This article presents the results of research on manufacturing and testing a target missile cruise engine using RST solid propellant. In particular, we have researched and calculated the design of a test engine, and built a flow chart to calculate the system of internal discharge equations of the engine. Research on the design and manufacture of propellant doses for cruise engines, including presenting the technology for manufacturing fireproof coatings for solid propellant ingots and perfecting the complete propellant dose. Test combustion of the cruise engine on a static stand has been conducted. The results of the tested engines are stable, the main parameters obtained are as follows: Pressure Pmax = 61,9 bar; Burning time 31,75 seconds; Average engine thrust: 670,7 N, Total thrust impulse: 21247,9 N.s, Engine housing temperature during the engine working period is equivalent to the ambient temperature after the engine stops thermal operation Engine cover temperature increased to 86 oC. This is the largest solid propellant cruise engine researched and manufactured by domestic units, on that basis creating a new type of MTB01 flying target with a maximum speed of 248 m/s, flight time of not less than 60 seconds.
References
[1]. А.П. Денисюк, “Горение пороха и ТРТ”, ст 42, (1988).
[2]. А.С.Ковальчук, “Основания устройства и конструкция орудий и боеприпасов наземной артиллерии.Учб”. МО СССР, стр 8, (1976).
[3]. NASA Goddard Space Flight Center, NASA Sounding rockets user handbook, Sounding rockets program office, Sub-orbital and special orbital projects directorate, (2015).
[4]. Vu Thanh Hai, Project The approach of launching technics of low altitude booster rockets by physical models based on the sample of testing rocket TV-01, VAST, (2016).
[5]. Banzula J. B., Bogatkin G. S. Patent RU 2426000 Device to produce channel charge from rocket mix rocket solid propellant, (2009).
[6]. Krasilnikov F. S., Filimonova E. J. Patent RU 2465257 Thermoplastic armour compound for charge of solid rocket propellant of ballistite type, (2011).
