New Fuel Gauging Technique for LCA: Modeling with ANSA Data

Shantha Kumar, N and Rao , P Narayana and Girija, G New Fuel Gauging Technique for LCA: Modeling with ANSA Data. Project Report. CSIR-NAL.

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    An algorithm based on least squares technique was developed by NAL using available LCA flight data to improve the in-flight estimation of fuel mass in the internal tanks. In order to generate more accurate model coefficients, ADA has carried out fuel tank solid model simulation for all the internal tanks and generated truth tables relating probe measurements to the fuel mass in the tank at various aircraft attitudes using analytical software tool ANSA (Automatic Net generation Tool for Structural Analysis by β BETA CAE SYSTEM SA). This report presents details of a global nonlinear 3rd order multivariate orthogonal polynomial model fit to the truth table data to arrive at a global model valid across a range of aircraft attitude for each of the probes in the F1A and wing tanks. The estimated model fit error was found to be less than 20 kg for all the probes. The estimated global model was used to predict the fuel mass from few flight data sets of PV3. The predicted fuel mass was compared with fuel estimates from least square models and lookuptable estimates which is currently being used in LCA. While the trends appear similar, the global model predicts higher fuel content (50 to 100 kgs) as compared to the earlier estimates. This could be attributed to the fact that ANSA model generated fuel mass is higher than the mass that was used in generating the lookuptables which were based on fill and drain tests. This issue has to be resolved before the model can be used for getting accurate predictions. Inorder to improve the model further, a few recommendations are also made for ANSA truth table generation.

    Item Type: Proj.Doc/Technical Report (Project Report)
    Subjects: AERONAUTICS > Aircraft Propulsion and Power
    Division/Department: Flight Mechanics and Control Division, Flight Mechanics and Control Division, Flight Mechanics and Control Division
    Depositing User: Mr. Shantha Kumar N
    Date Deposited: 30 May 2011 15:37
    Last Modified: 30 May 2011 15:37

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