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METHOD OF DETERMINATION OF PARAMETERS OF INCOMING FLOW OF FLYING VEHICLE IN FLIGHT IN GLIDING MODE AT HYPERSONIC AND SUBSONIC SPEEDS
METHOD OF DETERMINATION OF PARAMETERS OF INCOMING FLOW OF FLYING VEHICLE IN FLIGHT IN GLIDING MODE AT HYPERSONIC AND SUBSONIC SPEEDS
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机译：超音速和亚音速滑行飞行中飞行器入流参数的确定方法
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摘要
FIELD: aerospace engineering. SUBSTANCE: dependence of aerodynamic efficiency in longitudinal and side planes of flying vehicle and lifting force coefficient depending on angle of attack and slip angle are determined in wind tunnel on flying vehicle model at various parameters of flying vehicle configuration. During flight, g-loads are measured by axes of body-axis coordinate system and magnitudes of aerodynamic efficiency are calculated for longitudinal and side planes. Relationships obtained in wind tunnel are used for determination of magnitudes of in-flight angles of attack and slip angles for present in-flight configuration of flying vehicle. Then magnitude of lifting force coefficient is found from respective wind tunnel dependence. And finally, magnitude of dynamic head of incompressible gas flow is calculated by this coefficient and magnitude of measured normal g-load. EFFECT: enhanced reliability of flying vehicle and accuracy of determination of its flight parameters required for forming permissible trajectory of descent of manned flying vehicle. 2 cl, 7 dwg
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