GUIDED MISSILE Russian patent published in 1999 - IPC

Abstract RU 2135944 C1

FIELD: rocketry. SUBSTANCE: missile has a rocket engine with oblique - seat nozzles, located in the middle part of the missile. A protrusion of erosion material is made in the supersonic sections of the nozzles. The cross-section area of the nozzle supersonic section over its entire length exceeds the nozzle throat area. The axes of the nozzle supersonic sections are shifted in the radial direction relative to the axes of the throat section from the axis of the missile. EFFECT: reduced effect of combustion products on missile body at a minimum loss of the engine total impulse. 2 dwg

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RU 2 135 944 C1

Authors

Andreev V.A.

Korneichev V.V.

Krejer K.V.

Palajchev A.A.

Dates

1999-08-27—Published

1998-08-10—Filed