Mathematical Modelling and Analysis of Nonlinear Aeroservoelastic framework for Light Aircraft / (Record no. 607346)
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| 000 -LEADER | |
|---|---|
| fixed length control field | 01716nam a22001697a 4500 |
| 003 - CONTROL NUMBER IDENTIFIER | |
| control field | NUST |
| 082 ## - DEWEY DECIMAL CLASSIFICATION NUMBER | |
| Classification number | 621 |
| 100 ## - MAIN ENTRY--PERSONAL NAME | |
| Personal name | NASEER, MARIYAM |
| 245 ## - TITLE STATEMENT | |
| Title | Mathematical Modelling and Analysis of Nonlinear Aeroservoelastic framework for Light Aircraft / |
| Statement of responsibility, etc. | MARIYAM NASEER |
| 264 ## - PRODUCTION, PUBLICATION, DISTRIBUTION, MANUFACTURE, AND COPYRIGHT NOTICE | |
| Place of production, publication, distribution, manufacture | Islamabad : |
| Name of producer, publisher, distributor, manufacturer | SMME- NUST; |
| Date of production, publication, distribution, manufacture, or copyright notice | 2023. |
| 300 ## - PHYSICAL DESCRIPTION | |
| Extent | 116p. ; |
| Other physical details | Soft Copy |
| Dimensions | 30cm. |
| 520 ## - SUMMARY, ETC. | |
| Summary, etc. | In this research, an aeroelastic model of light aircraft is developed with the help of structural mesh<br/>from PATRAN and aero model in ZAERO. Flutter analysis of this aeoelastic model is performed in<br/>ZAERO and lowest flutter speed is identified along with critical mode shapes. The effect of freeplay<br/>motion of different control surfaces of aircraft are modeled and isintegrated with the flight control<br/>algorithm in MATLAB to obtain the aeroservoelastic model. The model thus developed is solved for<br/>numerous flight conditions and different freeplay angles of the control surfaces. Analysis for aileron,<br/>rudder and elevator are conducted independently and simultaneous analysis for aileron and elevator<br/>freeplay is also studied. It is observed that the aeroservoelastic response of light aircraft is most<br/>senstive to elevator while rudder has negligible effect on aeroservoelastic response of light aircraft.<br/>Moreover the simultaneous motion of two control surfaces reduce the lowest flutter speed of aircraft.<br/>Hence the effect of simultaneous motion of control surfaces need to be addressed during design of<br/>light aircraft. |
| 650 ## - SUBJECT ADDED ENTRY--TOPICAL TERM | |
| Topical term or geographic name entry element | MS Mechanical Engineering |
| 700 ## - ADDED ENTRY--PERSONAL NAME | |
| Personal name | Supervisor : Dr Muhammad Safdar |
| 856 ## - ELECTRONIC LOCATION AND ACCESS | |
| Uniform Resource Identifier | <a href="http://10.250.8.41:8080/xmlui/handle/123456789/34353">http://10.250.8.41:8080/xmlui/handle/123456789/34353</a> |
| 942 ## - ADDED ENTRY ELEMENTS (KOHA) | |
| Source of classification or shelving scheme | |
| Koha item type | Thesis |
| Withdrawn status | Permanent Location | Current Location | Shelving location | Date acquired | Full call number | Barcode | Koha item type |
|---|---|---|---|---|---|---|---|
| School of Mechanical & Manufacturing Engineering (SMME) | School of Mechanical & Manufacturing Engineering (SMME) | E-Books | 12/13/2023 | 621 | SMME-TH-865 | Thesis |