In-Situ Load System for Calibrating and Validating Aerodynamic Properties of Scaled Aircraft in Ground-Based Aerospace Testing Applications,申请号US201414191898-传众专利搜索

In-Situ Load System for Calibrating and Validating Aerodynamic Properties of Scaled Aircraft in Ground-Based Aerospace Testing Applications

申请公布号：US2016011068(A1)

申请号：US201414191898

申请日期：2014.02.27

申请公布日期：2016.01.14

申请人：

U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

发明人：Commo Sean A.;Lynn Keith C.;Landman Drew;Acheson Michael J.

分类号：G01L25/00

主分类号：G01L25/00

地址：Washington DC US

摘要：An In-Situ Load System for calibrating and validating aerodynamic properties of scaled aircraft in ground-based aerospace testing applications includes an assembly having upper and lower components that are pivotably interconnected. A test weight can be connected to the lower component to apply a known force to a force balance. The orientation of the force balance can be varied, and the measured forces from the force balance can be compared to applied loads at various orientations to thereby develop calibration factors.

主权项：1. An on-site method of calibrating a force balance in the presence of a gravitational field defining a gravity vector, the method comprising: providing a force balance defining a force balance coordinate system, wherein the force balance is configured to measure applied roll, pitch, and yaw moments and axial, side, and normal forces; connecting the force balance to a movable support that is capable of rotating the force balance in at least pitch and roll; utilizing an angle measurement system to measure an angular orientation of the force balance relative to the gravity vector; providing a pivotable connecting assembly having an upper mounting structure that is operably connected to the force balance such that forces applied to the upper mounting structure are transmitted to the force balance wherein the upper mounting structure is pivotably connected to a lower mounting structure by bearings that permit rotation of the lower mounting structure relative to the upper mounting structure in at least pitch and roll; operably connecting a test weight to the lower mounting structure to thereby apply a known test force to the force balance; comparing force measurements of the force balance to a test force applied to the force balance at a first angular orientation of the force balance relative to the gravity vector; rotating the force balance to a second angular orientation relative to the gravity vector; and comparing force measurements of the force balance to a test force applied to the force balance at the second angular position relative to the gravity vector.