| 摘要 |
FIELD: rocket manufacturing, applicable for enhancement of the engine specific impulse that is mean for the trajectory. ^ SUBSTANCE: the flight vehicle engine installation has two or several combustion chambers arranged in one or two rows and provided with round Laval nozzles consolidated by a common flat probe, each thrust wall of the probe is the continuation of the contours of the supersonic sections of the round nozzles, its two side walls are positioned perpendicularly to the probe thrust walls, each row of the combustion chambers with round Laval nozzles is hinge-joined for turning relative to the probe rigidly fastened to the body of the engine installation. ^ EFFECT: provided convenient arrangement of the engine installation consisting of two or more engines on the flight vehicle, enhanced payload or flying range of the flight vehicle due to the increment of the engine installation thrust. ^ 3 cl, 2 dwg |
