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  • 1
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    Advances in Experiment Design for High Performance Aircraft (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: A general overview and summary of recent advances in experiment design for high performance aircraft is presented, along with results from flight tests. General theoretical background is included, with some discussion of various approaches to maneuver design. Flight test examples from the F-18 High Alpha Research Vehicle (HARV) are used to illustrate applications of the theory. Input forms are compared using Cramer-Rao bounds for the standard errors of estimated model parameters. Directions for future research in experiment design for high performance aircraft are identified.
    Keywords: Aircraft Design, Testing and Performance
    Type: System Identification for Integrated Aircraft Development and Flight Testing; 8-1 - 8-17; RTO-MP-11
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight test maneuvers for closed loop lateral-directional modeling of the F-18 High Alpha Research Vehicle (HARV) using forebody strakes (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight test maneuvers are specified for the F-18 High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for lateral linear model parameter estimation at 30, 45, and 60 degrees angle of attack, using the Actuated Nose Strakes for Enhanced Rolling (ANSER) control law in Strake (S) model and Strake/Thrust Vectoring (STV) mode. Each maneuver is to be realized by applying square wave inputs to specific pilot station controls using the On-Board Excitation System (OBES). Maneuver descriptions and complete specification of the time/amplitude points defining each input are included, along with plots of the input time histories.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-198270 , NAS 1.26:198270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    High Accuracy Evaluation of the Finite Fourier Transform Using Sampled Data (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Many system identification and signal processing procedures can be done advantageously in the frequency domain. A required preliminary step for this approach is the transformation of sampled time domain data into the frequency domain. The analytical tool used for this transformation is the finite Fourier transform. Inaccuracy in the transformation can degrade system identification and signal processing results. This work presents a method for evaluating the finite Fourier transform using cubic interpolation of sampled time domain data for high accuracy, and the chirp Zeta-transform for arbitrary frequency resolution. The accuracy of the technique is demonstrated in example cases where the transformation can be evaluated analytically. Arbitrary frequency resolution is shown to be important for capturing details of the data in the frequency domain. The technique is demonstrated using flight test data from a longitudinal maneuver of the F-18 High Alpha Research Vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-110340 , NAS 1.15:110340
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Piloted Parameter Identification Flight Test Maneuvers for Closed Loop Modeling of the F-18 High Alpha Research Vehicle (HARV) (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight test maneuvers are specified for the F-18 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 NASA 1A control law. Each maneuver is to be realized by the pilot applying square wave inputs to specific pilot station controls. Maneuver descriptions and complete specifications of the time/amplitude points defining each input are included, along with plots of the input time histories.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-198268 , NAS 1.26:198268
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Nonlinear Aerodynamic Modeling From Flight Data Using Advanced Piloted Maneuvers and Fuzzy Logic (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Results of the Aeronautics Research Mission Directorate Seedling Project Phase I research project entitled "Nonlinear Aerodynamics Modeling using Fuzzy Logic" are presented. Efficient and rapid flight test capabilities were developed for estimating highly nonlinear models of airplane aerodynamics over a large flight envelope. Results showed that the flight maneuvers developed, used in conjunction with the fuzzy-logic system identification algorithms, produced very good model fits of the data, with no model structure inputs required, for flight conditions ranging from cruise to departure and spin conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2012-217778 , L-20181 , NF1676L-15300
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Online Control Design for Learn-To-Fly (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Two methods were developed for online control design as part of a flight test e ort to examine the feasibility of the NASA Learn-to-Fly concept. The methods use an aerodynamic model of the aircraft that is being identified in real-time onboard the aircraft to adjust the control parameters. One method employs adaptive nonlinear dynamic inversion, whereas the other consists of a classical autopilot structure. E ects from the interaction between the realtime modeling and the developed control laws are discussed. The Learn-to-Fly concept has been deemed feasible based on successful flights of both a stable and unstable aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-28603 , AVIATION 2018 / Aviation Technology, Integration, and Operations Conference; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Real-Time Dynamic Modeling - Data Information Requirements and Flight Test Results (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Practical aspects of identifying dynamic models for aircraft in real time were studied. Topics include formulation of an equation-error method in the frequency domain to estimate non-dimensional stability and control derivatives in real time, data information content for accurate modeling results, and data information management techniques such as data forgetting, incorporating prior information, and optimized excitation. Real-time dynamic modeling was applied to simulation data and flight test data from a modified F-15B fighter aircraft, and to operational flight data from a subscale jet transport aircraft. Estimated parameter standard errors, prediction cases, and comparisons with results from a batch output-error method in the time domain were used to demonstrate the accuracy of the identified real-time models.
    Keywords: Aircraft Design, Testing and Performance
    Type: LF99-7582
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Parameter Identification Flight Test Maneuvers for Closed Loop Modeling of the F-18 High Alpha Research Vehicle (HARV) (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Flight test maneuvers are specified for the F-18 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) control law in Thrust Vectoring (TV) mode. Each maneuver is to be realized by applying square wave inputs to specific pilot station controls using the On-Board Excitation System (OBES). Maneuver descriptions and complete specifications of the time / amplitude points defining each input are included, along with plots of the input time histories.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-198269
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flight Test Validation of Optimal Input Design and Comparison to Conventional Inputs (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A technique for designing optimal inputs for aerodynamic parameter estimation was flight tested on the F-18 High Angle of Attack Research Vehicle (HARV). Model parameter accuracies calculated from flight test data were compared on an equal basis for optimal input designs and conventional inputs at the same flight condition. In spite of errors in the a priori input design models and distortions of the input form by the feedback control system, the optimal inputs increased estimated parameter accuracies compared to conventional 3-2-1-1 and doublet inputs. In addition, the tests using optimal input designs demonstrated enhanced design flexibility, allowing the optimal input design technique to use a larger input amplitude to achieve further increases in estimated parameter accuracy without departing from the desired flight test condition. This work validated the analysis used to develop the optimal input designs, and demonstrated the feasibility and practical utility of the optimal input design technique.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 97-3711
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Multiple Input Design for Real-Time Parameter Estimation in the Frequency Domain (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method for designing multiple inputs for real-time dynamic system identification in the frequency domain was developed and demonstrated. The designed inputs are mutually orthogonal in both the time and frequency domains, with reduced peak factors to provide good information content for relatively small amplitude excursions. The inputs are designed for selected frequency ranges, and therefore do not require a priori models. The experiment design approach was applied to identify linear dynamic models for the F-15 ACTIVE aircraft, which has multiple control effectors.
    Keywords: Aircraft Design, Testing and Performance
    Type: Paper REG-360 , 13th IFAC Conference on System Identification; Aug 27, 2003 - Aug 29, 2003; Rotterdam; Netherlands
    Format: application/pdf
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