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A method for determining an aerodynamic parameters and process for the recognition of a failure of a probe, which is used for the determination of an aerodynamic parameters

机译:一种用于确定空气动力学参数的方法和用于识别探针故障的方法,该方法用于确定空气动力学参数

摘要

The invention concerns a method for determining aerodynamic parameters of an air stream surrounding an aircraft. The method, based on at least two probes located on the skin of the aircraft, each probe comprising means for measuring the local incidence (αloc i αloc j), consists in determining the incidence (α) and/or the side slip (β) of the aircraft, based on the local incidence of each probe et on the aerodynamic field of the aircraft. The invention also concerns a method for detecting failure in a probe used for determining the aerodynamic parameters of the air stream surrounding an aircraft. Said failure detection method consists in: determining for the set of the two probe blocks: the incidence and/or side slip on the basis of the local incidences and on the aircraft aerodynamic field; different pressure coefficient values of each probe based on the local incidence of each probe and on the aircraft aerodynamic field; the upstream infinite static pressure based on the pressure coefficient and the local static pressure of one and the same probe and based on a total pressure measurement; in comparing between them the upstream infinite static pressure, the incidence values and/or the side slip values.
机译:本发明涉及一种用于确定飞行器周围的空气流的空气动力学参数的方法。该方法基于位于飞机皮肤上的至少两个探针,每个探针包括用于测量局部入射角(αlociαlocj)的装置,该方法在于确定入射角(α)和/或侧滑(β)。根据每个探头的局部入射角以及飞机的空气动力场来确定飞机的位置。本发明还涉及一种用于检测用于确定飞行器周围的空气流的空气动力学参数的探针中的故障的方法。所述故障检测方法包括:对于两个探针块的集合,确定:基于局部入射和飞机空气动力场的入射和/或侧滑;根据每个探头的局部入射角和飞机的空气动力场,每个探头的压力系数值会有所不同;基于一个同一个探头的压力系数和局部静压力,并基于总压力测量值,确定上游无限静压力;在它们之间比较上游无限静压力,入射值和/或侧滑值。

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