HIGH-PRESSURE TUBE ( VARIANTS ) Russian patent published in 2000 - IPC

FIELD: determination of flight parameters of aircraft. SUBSTANCE: high-pressure tube includes axially-symmetric body anchored on support which nose part has hole to determine total pressure. It also houses electric heating elements of anti-icing system. Support has two holes designed to determine angle of attack, electric heating elements are placed inside support. High- pressure tube incorporates plate with holes to measure static pressure linked to flange attaching support to fuselage. Technical objective of given high-pressure tube lies in simplified design, reduced aerodynamic pressure and mass of tube. According to second variant high-pressure tube includes body with inlet holes arranged over periphery of section which are connected with the aid of pneumatic lines to pipe unions. Electric heating elements of anti-icing system located inside body are also connected to inlet holes. Cross-sections of body have shape of specialized aerodynamic profile. Technical objective of this variant consists in decrease of required power of heating anti-icing system. In correspondence with third variant high- pressure tube has three groups of holes to determine total pressure and angle of attack, axially symmetric body and support with base for attachment of pneumatic lines and electric heating elements of anti-icing system arranged inside them. Inlet holes measuring angel of attack are positioned on support above axially symmetric body with reference to base of support. Technical objective of third variant consists in diminished effect of angle of sideslip of aircraft on measurement of local angle of attack. EFFECT: expanded functional capabilities of proposed high-pressure tube. 13 cl, 25 dwg