| 摘要 |
FIELD: rocketry. SUBSTANCE: profile of fuel-flow rocket nozzle corresponds to parabola in longitudinal section in which starting from point corresponding to expansion coefficient equal to 50%, parabolic contour of nozzle in direction from its critical section (neck) is transformed either into strictly conical profile with apex angle between 15o and 25o, or into curvilinear profile with slight convexity outwards, i.e. into profile characterized by positive second derivative of radius, or into curvilinear profile with slight concavity inwards, i. e. into profile characterized by negative second derivative of radius, but lying outside parabolic contour. According to last third version, third derivative r is equal to zero. EFFECT: provision of control of flow division and reduction of side load. 2 cl, 1 tbl, 4 dwg
|
