FIELD: volley fire systems; rocket shells. SUBSTANCE: proposed charge has housing, protection-and- fastening layer, end face cups, head semicharge with star-like channel and tail semicharge with cylindrical channel. Charge is made with rounding off radii in places where cylindrical sections of star-like channel arms change into arm surface, being equal to 0.08-0.15 of thickness of head semicharge burning arch. Length of cantilever section of tail semicharge pointed to nozzle is equal to 0.6-1.5 of thickness of tail semicharge burning arch at beginning of cantilever section. Axisymmetrical recess converging in direction towards nozzle end face is made in area of front end face of tail semicharge. This recess includes the following conical sections arranged one after the other: maximum diameter section (Dmax) on front end face of tail semicharge equal to 1.2 - 1/5 of outer diameter of arms of head semicharge with taper angle of 25 - 35o and length of (0.015 - 0.03)L; section with taper angle of 3-8o and length of (0.02- 0.04)L; section with taper angle of 10-20o and length of (0.015-0.03)L, where L is length of tail semicharge. EFFECT: provision of solid propellant charge with 8-10% increase in volumetric fill factor at decrease in spread of output characteristics and reliability criteria in preset range of application. 3 dwg
Title | Year | Author | Number |
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SOLID PROPELLANT CHARGE | 1999 |
|
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SOLID-PROPELLANT ROCKET ENGINE | 1998 |
|
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ROCKET SOLID FUEL CHARGE | 2008 |
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CHARGE OF SOLID PROPELLANT FOR ROCKETS | 2003 |
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Authors
Dates
2000-02-20—Published
1999-05-25—Filed