CONSTRUCTION OF INSTRUMENT TRANSDUCER FOR MEASURING FLOW PARAMETERS AND POSITION ON STREAMLINED BODY

摘要

FIELD: instrumentation for flying vehicles. ^ SUBSTANCE: proposed instrument transducer (sensor) includes structural member which is aircraft member directed to air flow. Structural member is just front part of nose fuselage, for example front part of antenna fairing; it is made in form of cone with at least two measuring openings to which channels for transmitting pressure to pressure conversion system are connected. External envelope of cone has two sections located in way of flow; heat conductivity of first section exceeds that of second section. Located within first section in structural member are heating elements connected with temperature control circuit on surface of first section. Length of first and second sections and their materials are so selected that temperature drops at preset mode from first section to second one. Sensor withstands high thermal loads. ^ EFFECT: enhanced reliability of aircraft; enhanced accuracy of determination of actual mode of flight as compared with external sensors. ^ 14 cl, 3 dwg