| 000 | 03124cam a2200349 a 4500 | ||
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| 003 | EG-GiCUC | ||
| 005 | 20250223032411.0 | ||
| 008 | 191003s2019 ua o f m 000 0 eng d | ||
| 040 |
_aEG-GiCUC _beng _cEG-GiCUC |
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| 041 | 0 | _aeng | |
| 049 | _aDeposite | ||
| 097 | _aPh.D | ||
| 099 | _aCai01.13.01.Ph.D.2019.Mo.D | ||
| 100 | 0 | _aMohannad Ahmed Mohamed Draz | |
| 245 | 1 | 0 |
_aDesign and implementation of rate table framework for autopilot testing / _cMohannad Ahmed Mohamed Draz ; Supervised Gamal Mahmoud Elbayoumi , Ayman Hamdy Kassem , Mohamed Sayed Bayoumi |
| 246 | 1 | 5 | _aتصميم و تنفيذ منظومة عمل لمنصة معدل زاوى متغير لاختبار الطيار الآلى |
| 260 |
_aCairo : _bMohannad Ahmed Mohamed Draz , _c2019 |
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| 300 |
_a128 P. : _bphotographs ; _c30cm |
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| 502 | _aThesis (Ph.D.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering | ||
| 520 | _aThe rate gyro is an essential sensor for aircraft autopilot systems, as it is used to measure the angles rate of aircraft attitudes and feed them back to the autopilot algorithm. The accuracy and testing of such sensors is a must in order to guarantee the operation of the autopilot. Therefore a three degree of freedom rate table has been designed and manufactured to perform the testing of rate gyro sensors. The rate table is controlled using three stepper motors with high precision stepper driver supported with an FPGA controller to guarantee highly accurate and precise rate motion. The aircraft under test is the mantis mini UAV which is designed and manufactured in the Aerospace department in 2008. In order to design the autopilot for such UAV, the aerodynamic derivatives are needed to be measured. A wind tunnel testing and measurements for a quarter scale model for the Mantis has been done to measure the aerodynamic derivatives using a six degree of freedom force/torque sensor as well as manual tilting table to perform different angles of attack and angles of the side slip to the model. The results from the testing have been validated with a numerical results using ANSYS software. Then, the aerodynamic derivatives will be used in the aircraft nonlinear simulation program which demonstrates the aircraft motion and also testing the autopilot and guidance algorithms on the aircraft. This simulation program is integrated with both the 3 DOF rate table as a simulator for the aircraft attitudes, and with the rate gyro sensor as a feedback signal to the autopilot algorithm. Thus, hardware in the loop platform was suitable for testing the components of the autopilot system; such as the sensor of rate gyro and the implemented algorithm of the designed autopilot | ||
| 530 | _aIssued also as CD | ||
| 653 | 4 | _aDesign | |
| 653 | 4 | _aImplementation | |
| 653 | 4 | _aRate Table | |
| 700 | 0 |
_aAyman Hamdy Kassem , _eSupervisor |
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| 700 | 0 |
_aGamal Mahmoud Elbayoumi , _eSupervisor |
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| 700 | 0 |
_aMohamed Sayed Bayoumi , _eSupervisor |
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| 856 | _uhttp://172.23.153.220/th.pdf | ||
| 905 |
_aNazla _eRevisor |
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| 905 |
_aSamia _eCataloger |
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| 942 |
_2ddc _cTH |
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| 999 |
_c74285 _d74285 |
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