Stability derivative extraction from flight test data for a general aviation aircraft /
(GA) aircraft. Due to a lack of technical information about
| Main Author: | |
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| Format: | Thesis eBook |
| Language: | English |
| Published: |
[Place of publication not identified] :
[publisher not identified] ;
1996.
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| Subjects: | |
| Online Access: | Link to OAKTrust copy |
| Summary: | (GA) aircraft. Due to a lack of technical information about accuracy and efficiency of the estimates with a reduced user and power approach configurations were obtained. average, MMLE predicted the stability derivatives with a being modeled on the Engineering Flight Simulator (EFS) for compared favorably with results obtained by other computationally expensive than the EKF and could provide derivatives that govern its motion were estimated from flight did not emulate the aircraft response since the models expected. Surprisingly though, the aircraft's directional extraction procedure is recommended for improving the Future efforts to improve the simulation should focus on information. Finally, development of an automated derivative is suggested as a possible means of extracting this Kalman filter (EKF), were utilized to extract these Modified Maximum Likelihood Estimator (MMLE) and the extended obtaining accurate estimates of the drag polars, producing of both models on the EFS also indicated that both were parameters. Models of the takeoff, initial climb, cruise, performance of the MMLE and EKF algorithms indicated that, on pilot was unable to distinguish between the two models. produced adverse rather than proverse yaw. In general, the proverse yaw, and improving the thrust model. Flight testing Rao bounds for both the EKF and MMLE derivative estimates rapid convergence to a fairly accurate model from poor Representative dynamic models were generated by both MMLE and representative of the Commander. Comparison of the researchers. The modeled time history responses generated by responded to changes in flight condition as theoretically slightly lower uncertainty than the EKF. MMLE was also less stability decreased with decreasing airspeed. Test flights stability derivatives and flying qualities of each model starting conditions. During simulated flight tests, the test data. However, the modeled response to an aileron input test data. Two system identification techniques, the testing of an integrated cockpit system for general aviation Texas A&M Flight Mechanics Laboratory (FML) is currently the Commander's dynamics, the stability and control the EKF for all of the above flight configurations. Cramer- The Gulfstream Commander 700 (N700AE) aircraft owned by the the measured flight test inputs compared well with the flight workload. |
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| Item Description: | "Major subject: Aerospace Engineering". Computer disk in pocket. Vita. |
| Physical Description: | xviii, 118 leaves : illustrations ; 28 cm. Also available online. Issued also on microfiche from Lange Micrographics. |
| Format: | System requirements for computer disk: IBM-PC. |
| Bibliography: | Includes bibliographical references: pages 97-100. |