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Sunday, August 9, 2020 | History

3 edition of Flight investigation of various control inputs intended for parameter estimation found in the catalog.

Flight investigation of various control inputs intended for parameter estimation

Flight investigation of various control inputs intended for parameter estimation

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  • 14 Currently reading

Published by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility in Edwards, Calif .
Written in English

    Subjects:
  • Flight control.,
  • Airplanes -- Control systems.

  • Edition Notes

    StatementMary F. Shafer.
    SeriesNASA technical memorandum -- 85901.
    ContributionsDryden Flight Research Facility.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17666593M

    in parts of the flight envelope, it is augmented with a closed-loop flight control system. At the flight conditions used for parameter estimation in this paper, the aircraft was statically stable so no changes were made to the parameter estimation algorithms used. Figure 1. . The work presented in this paper addresses the longitudinal parameter estimation of an unmanned configuration using wind tunnel testing and flight data. For this purpose, an unmanned aerial vehicle has been designed with a cropped delta planform and rectangular cross-section.

    The present article details a method suitable for fault detection of hydraulic flight control system actuators. A model based method is discussed, which use the linear parameter-varying (LPV) framework, which leads to a minimum number of tuning Cited by: 9. B.C. de Oliveira Maciel et al. / Flight path reconstruction and parameter estimation using output-error method Fig. 1. The body-fixed, vehicle carried and the.

    tool to identify from flight data aerodynamic characteristics valid over the entire operational flight envelope. This paper briefly presents aircraft parameter estimation methods for both stable and unstable aircraft, highlighting the developmental work at the DLR Institute of Flight Mechanics. Various aspects of. A lot of flight control boards with very mature function capability can be selected implemented and into UAVs, such as AutoPilot, ArduPilot and Micropilot. No matter how autopilot performs, the flight control board requires some basic for data control parameter settings. These parameters will change its control effort.


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Flight investigation of various control inputs intended for parameter estimation Download PDF EPUB FB2

FLIGHT INVESTIGATION OF VARIOUS CONTROL INPUTS INTENDED FOR PARAMETER ESTIMATION Mary F. Shafer* NASA Ames Research Center Dryden Flight Research Facility Edwards, California Abstract An experiment assessing the stability and con-trol derivatives resulting from various control inputs was undertaken using the F-8 digital fly-by-wire aircraft.

Get this from a library. Flight investigation of various control inputs intended for parameter estimation. [Mary F Shafer; Dryden Flight Research Facility.]. Title: Flight Investigation of Various Control Inputs Intended for Parameter Es timation Author: Mary F.

Shafer Subject: H Keywords: Parameter estimation; Maximum likelihood estimation; Control inputs; Fli ght test; Stability and control derivatives; Dynamic flight data analysi s. and does contain definitive works related to most aircraft parameter estimation approaches.

Theoretical studies as well as practical applications are included. Many of these publications are pertinent to subjects peripherally related to parameter estimation, such as aircraft maneuver design or instrumenta- tion by: 8.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA   A note on state and parameter estimation in a Van der Pol oscillator.

Automatica, 46(10 M. Flight investigation of various control inputs intended for parameter estimation. Google Scholar. Sinha, N. & Kuszta, B. () Auxiliary Signal Design and Liénard-type Models for Identifying Pipeline Parameters.

In: Verde C Cited by: 2. Aerodynamic Parameter Estimation from Flight Data Applying Extended and Unscented Kalman Filter Girish Chowdhary* and Ravindra Jategaonkar† DLR Institute for Flight Systems, Braunschweig, Germany.

Aerodynamic parameter estimation is an integral part of aerospace system design and life cycle process. The problem of aircraft identification and parameter estimation demands for accurate mathematical model of the aerodynamics and adequate. This paper presents a consequence of the systematic approach to identify the aerodynamic parameters of an unmanned aerial vehicle (UAV) equipped with the automatic flight control system.

A excitation is applied for the longitudinal mode while a multi-step input is applied for lateral/directional excitation. Optimal time step for excitation is sought to provide Cited by: Title: Aircraft Parameter Estimation - AIAA Dryden Lecture in Research for Author: Kenneth W. Iliff Subject: H Keywords: Aircraft flight testing; Aircraft stability and control; Maximum likelih ood; Parameter estimation.

Flight Investigation of Prescribed Simultaneous Independent Surface Excitations for Real-Time Parameter The stability and control derivative estimation process is known as parameter identification (PID) or control-surface inputs run by the aircraft flight control computer in which each control surface.

Murray-Smith, David J. () Methods of system identification, parameter estimation and optimisation applied to problems of modelling and control in engineering and physiology. DSc thesis, University of Glasgow.

Full text available as. MathWorks engineers will introduce new capabilities for online parameter estimation and will explain and demonstrate how these capabilities can be used for fault detection and adaptive control.

The webinar will begin with an overview of recently developed online parameter estimation algorithms. Parameter estimation can also be done in the Frequency Domain.

Need to convert time-domain data into the frequency domain, using the Fourier Transform. Can be:. More robust. Faster, due to reduced data points in converting to frequency. File Size: 1MB. The parameter values of interest for system identification are the elements of matrix A d (stability derivatives), matrix B d (control derivatives), and the delays associated with the aircraft response (2).

Furthermore, the parameters include the estimation of an unknown bias vector, xbias. This vector is introduced in the mathematical model Author: Ivana Y. Sumida, F Haroldo, Campos Velho, Eduardo F. Luz, Ronaldo V. Cruz, Luiz Carlos, S. Góes. Practica.l input optimiza­tion for aircraft parameter estimation experi­ments.

Technical report CR Morelli, E.A. Flight test of optimal in­puts and comparison with conventional in­puts.

Journal of Aircraft. Morelli, E.A. and V. Klein (). Optimal in­put design for aircraft parameter estimation using dynamic programming Cited by: 3. Lateral Parameter Estimation Using NGN Method ISSN: P a g e | 85 The data compatibility check was carried out on both flight data sets pertaining to lateral-directional case using observation equations and the ML method.

Figs. () present the measured and computed response of motion variables suchFile Size: KB. Flight test maneuvers are specified for the F High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for longitudinal and lateral linear model parameter estimation at 5,20,30,45, and 60 degrees angle of attack, using the Actuated Nose Strakes for Enhanced Rolling (ANSER.

aerodynamic parameter estimation using flight test data a thesis submitted to the graduate school of natural and applied sciences of middle east technical university.

Fast parameter estimation is a non-trivial task, and it is critical when the system parameters evolve with time, as demanded in real-time control applications.

In this study, a new computational approach for parameter identification is proposed based on. testing, the parameter estimation using flight data help to enhance the confidence in the estimates significantly.

Designing optimal controls and autopilots, expansion of flight envelopes, updating simulators and verification of overall aircraft performance are .Analytic works for similar problems [8] demonstrate that inputs similar to square waves were superior to sinusoidal inputs for parameter estimation [2].

The initial step uses dynamic programming, which gives a first result but re- quires a restrictive admissible input set.The flight tests analyzed in the present research took place during theC-S23/FAR 23 certification campaign of the PT. Although some flight maneuvers presented here are not strictly required for certificationthe in these categories, they are necessary for the purpose of aircraft parameter estimation.

reported The PT flight qualitiesFile Size: 1MB.