Optimization of transition maneuvers through aerodynamic vectoring
This paper discusses the optimization of transition maneuvers between hover and cruise for small aircraft using a novel aerodynamic vectoring feature, which is achieved by allowing the wing to have variable incidence angle with respect to the fuselage. Compared to the fixed-wing aircraft case, the a...
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| Main Authors: | , |
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| Other Authors: | |
| Format: | Article |
| Language: | English |
| Published: |
2013
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| Online Access: | https://hdl.handle.net/10356/85444 http://hdl.handle.net/10220/12360 |
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| Institution: | Nanyang Technological University |
| Language: | English |
| Summary: | This paper discusses the optimization of transition maneuvers between hover and cruise for small aircraft using a novel aerodynamic vectoring feature, which is achieved by allowing the wing to have variable incidence angle with respect to the fuselage. Compared to the fixed-wing aircraft case, the angle of incidence of the wing provides an additional independent control variable in the optimization problem formulation. The objective of the study is to achieve a transition scheme with minimal variation in altitude and reasonable thrust-to-weight ratio under specified transition time. The aerodynamics of the aircraft in pre- and post-stall regimes are obtained through wind-tunnel tests. The unsteady aerodynamic effects are incorporated in aerodynamic model to cater for rapid changes in the aircraft motion, which is modeled as three degree of freedom longitudinal dynamics. A nonlinear constrained optimization scheme based on Sequential Quadratic Programming (SQP) is used to generate the optimal maneuver motions. The results are discussed in light of their comparison with the fixed-wing case. |
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