SOLID-PROPELLANT CHARGE FOR AIRCRAFT MISSILE ROCKET ENGINE AND DEVICE FOR ITS MOULDING Russian patent published in 2015 - IPC F02K9/18 F02K9/24 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant channelled charge to provide boost thrust at start mode, further decay and progressive thrust increase at cruising mode. Charge is composed of mixed solid propellant rigidly secured to rocket engine. Charge channel perimeter is provided with trapezoidal shape splines this mean width being defined by the ratio protected by this invention. Depth of splines makes 1.0-2.5 of mean width while spline profile rounding radii make 1-2 mm at top and 1.5-4 mm at bottom. Another invention of the set relates to the device for group forming of solid-propellant charges of rocket engines. Said set comprises cartridge with vertically filled moulds and cutoff plates, bulk duct with propellant composition feed distributor, mechanism to pres the mould bottom cover to said distributor and to control said cutoff plates secured with cartridge moving crossbar. Moulds are shaped to rocket engine housings with top and bottom covers. Bottom covers of said housings contact with cartridge plate thrust surface and, via elastic bushes fitted in bottom cover necks, with common thrust surface of distributor plate. Distributor plate has propellant feed holes aligned with said covers. Air release device in every top cover is composed of resilient collar overlapping the air release channels.

EFFECT: decreased effects of rocket engine effluxes of rockets launched from under aircraft fuselage, higher reliability of moulding.

2 cl, 6 dwg