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US 12,724,036 B2Granted
Aerodynamic measurement probe
AssigneeThales
InventorsFrançois Perez, Eric Loil, Serge Petit
Life of this patent
Estimating the term…
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AssigneeThales
InventorsFrançois Perez, Eric Loil, Serge Petit
Estimating the term…
An aerodynamic measurement probe intended to measure a local angle of attack of an airflow circulating along the fuselage of an aircraft, the support comprising a circular cover with a central opening which is passed through by the mobile shaft, the outer surface of the cover comprising a frustoconical face exhibiting symmetry of revolution about the longitudinal axis, the cover comprising polyether ether ketone reinforced with glass or carbon fibers, with a thermal conductivity of less than 3 W·m−1·K−1 and being provided with metallic inserts at its fastenings, at least one metallic electrical continuity insert being configured to establish an electrical connection between the inner part of the probe and an interface of the metallic insert disposed under the lower periphery of that part of the metallic insert which is furthest away from the shaft.
An aerodynamic measurement probe to measure a local angle of attack of an airflow circulating along an aircraft fuselage, comprising a support, a heated body and a shaft that is able to rotate about a longitudinal axis with respect to the support and the body, the support, the body on one hand and the shaft on the other hand being configured to form a gap, to maintain functional play to allow one end of the shaft to pivot freely in the support, and communicating with a circuit for discharging impurities, the shaft comprising a part internal to the support, a vane part external to the support and a base plate of the vane part connecting the internal part and the external part, the support comprising a circular cover with a central opening which is passed through by the shaft, an outer surface of the circular cover comprising a frustoconical face exhibiting symmetry of revolution about the longitudinal axis, the circular cover being made of polyether ether ketone reinforced with glass or carbon fibers, and being provided with fastening metallic inserts for fastening of said circular cover on the aircraft fuselage or on the support, and with at least one metallic electrical continuity insert that establishes an electrical connection between an inner part of the probe and an interface of one of said fastening metallic inserts, said interface being disposed away from the shaft compared to said inner part of the probe.
Dependencies are inferred from the claim text.