Experimental investigation of a bi-planar micro air vehicle

• Main Author: Chang, Collin Wei Teck.
• Other Authors: Go Tiauw Hiong
• Format: Final Year Project
• Language: English
• Published: 2011
• Subjects: DRNTU::Engineering::Aeronautical engineering::Aircraft
• Online Access: http://hdl.handle.net/10356/45984
• Institution: Nanyang Technological University

The focus of final year project is on the experimental investigation of bi-planar micro air vehicle (MAV). One of the problems found on mono-planar MAVs is the difficulty in capturing high quality visual data during missions. Mono-planar MAVs are required to travel at a higher relative speed, in order to produce significant lift force from its limited wing area. These compromises the quality of data captured and reduces its effectiveness during missions. Bi-planar configuration serves to increase the aerodynamic performance of the MAVs by contributing higher lift force while reducing the speed needed to produce similar lift force. The main purpose of this research project is to investigate the effects of various geometrical parameters – Gap, Stagger and Decalage Angle at low Reynolds number in low speed wind-tunnel. Flexible wings are used to evaluate the effect of gap, while the rigid wings are used to evaluate all three identified geometric parameters. Moreover, the report incorporates the identification of the corresponding optimized rigid wing bi-planar MAV configuration for flight performance comparison with its monoplane. In addition, empirical formulas relating the aerodynamic properties of monoplane and biplane are derived using least square regression methods based on the experimental data. The Main Aircraft Laboratory low speed, low turbulence closed loop wind tunnel was used to test the full scale bi-planar prototype at various geometric configurations. Results show that the bi-planar configuration results in higher lift and drag than monoplane. Bi-planar MAVs are able to accommodate more payloads onboard due to higher lift produced, but the corresponding increment in drag reduces its aerodynamic performance. Although the effect of decalage angle affects most significantly in both lift and drag produced, the aerodynamic performance will only be enhanced through the proper combination of gap and stagger effects. Flight performance evaluations are done to show that the performance is highly dependent on its structural design and aerodynamic configurations.