Please use this identifier to cite or link to this item: http://hdl.handle.net/10603/182336
Title: Development of GPS and obstacle avoidance Based low altitude navigation system for a Powered parachute aerial vehicle
Researcher: Devalla, Vindhya
Guide(s): Om Prakash
Keywords: Aerospace engineering
Parafoil UAV
Unmanned Aerial Vehicle
University: University of Petroleum and Energy Studies (UPES)
Completed Date: 2017
Abstract: Unmanned Aerial Vehicle is an aircraft with no on board pilot. UAVs can be controlled with remote or autonomously. They are used for number of different missions depending upon the application. There are different types of UAVs available like fixed wing, multi copter and Parafoil UAV. Certain characteristics like low speed, high payload carrying capability, etc. makes Parafoil UAV a versatile platform for various applications. Parafoil is entirely made of fabric and is a non- rigid wing. A Parafoil get inflated just like a parachute when dropped from a height. The wing has a low aspect ratio with an elliptical or a rectangular plan form when inflated. To act as an airfoil, the upper membrane and the lower membrane are sewn together with a gap between both. The leading edge is kept open so as to allow the air inside the cells creating air pressure, which maintains the shape of the Parafoil as a wing. The vents in the ribs allow the air pass from one cell to another which helps in maintaining uniform air pressure in the wing. To avoid the air loss the fabric is made of nonporous material. The suspension lines are used to connect the Parafoil to the newlinepayload. Addition of a Propulsion unit on the payload makes the Paraglider a Parafoil UAV. This Vehicle has a Fly-bar to which the Parafoil is connected and a motor on the Payload. Directional control is achieved by pulling the fly-bar either side, which changes the direction of the lift making the aircraft turn. The Powered Parafoil has a tendency to fly at constant airspeed. These systems have pendulum stability and oscillations, because of the mass of the airframe suspended significantly below the canopy, which allows the system to have a yaw motion rather than roll motion. Lateral control is obtained by the propulsion system which is attached to the payload. The thrust of the propulsion system is controlled to maintain the altitude, take-off or landing. Modeling of Parafoil UAV has been studied in detail in this work.
Pagination: 176p.
URI: http://hdl.handle.net/10603/182336
Appears in Departments:Department of Aerospace Engineering

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01_title.pdfAttached File256.55 kBAdobe PDFView/Open
02_completion_certificate.pdf164.89 kBAdobe PDFView/Open
03_preliminary pages.pdf591.09 kBAdobe PDFView/Open
08_nomenclature.pdf172.91 kBAdobe PDFView/Open
09_list_of_figures.pdf240.7 kBAdobe PDFView/Open
10_list_of_tables.pdf233.54 kBAdobe PDFView/Open
11_chapter1.pdf881.76 kBAdobe PDFView/Open
12_chapter2.pdf482.84 kBAdobe PDFView/Open
13_chapter3.pdf662.9 kBAdobe PDFView/Open
14_chapter4.pdf2.99 MBAdobe PDFView/Open
15_chapter5.pdf1.53 MBAdobe PDFView/Open
16_chapter6.pdf314.83 kBAdobe PDFView/Open
17_publications.pdf344.7 kBAdobe PDFView/Open
18_references.pdf257.92 kBAdobe PDFView/Open
19_appendix.pdf600.31 kBAdobe PDFView/Open


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