Authors :
Mihir Zambare; Apurva Pardeshi; Aniket Pingle; Rifa Ansari
Volume/Issue :
Volume 9 - 2024, Issue 10 - October
Google Scholar :
https://tinyurl.com/54ttdfmp
Scribd :
https://tinyurl.com/938zh6uh
DOI :
https://doi.org/10.38124/ijisrt/IJISRT24OCT747
Note : A published paper may take 4-5 working days from the publication date to appear in PlumX Metrics, Semantic Scholar, and ResearchGate.
Abstract :
This study focuses on designing and developing
a fixed-wing unmanned aerial vehicle (UAV) to meet strict
operational requirements while maximizing cargo
capacity. The design must adhere to specific constraints,
including a maximum wingspan of 80 inches and a
structural weight limit of 5 kilograms. Achieving these
goals involves a delicate balance between maintaining the
UAV's structural integrity and ensuring its
maneuverability, effectiveness, and ease of
transportation. The challenge lies in maximizing the
structural strength within these limits to ensure the
UAV’s long-term reliability in field operations. The
ultimate goal is to create a proficient and efficient UAV,
utilizing resources and methods to optimize performance.
Keywords :
Unmanned Aerial Vehicle; Fixed Wing; Design; Analysis; High Lifting UAV, Sizing.
References :
- Sadraey, M. H. (2013). Aircraft design: a system engineering approach. Wiley.
- Anderson Jr., J. (1999), Aircraft Performance and Design. McGraw-Hill.
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- Nicolai, Leland M. (2009). Estimating r/c model aerodynamics and performance.
- Simons, M. (1994). Model aircraft aerodynamics. Argus Books.
- (1980). MIL-F-8785C Military specification flying qualities of piloted airplanes.
- Wood handbook: wood as an engineering material. (1974). Madison: The Laboratory. ort.pdf
- Old Dominion University. (2015). 2015 SAE Aero Design East Technology Report.
- Raymer, D.P. (2004). Aircraft design: A conceptual approach. Retrieved from http://soaneemrana.org/onewebmedia/AIRCRAFT%20DESIGN%20%3B%20A%20 Concept ual%20Approach%20BY%20DANIEL%20P%20RAYMER.pdf
- Miranda L.E. (2013), Fundamentos Da Engenharia Aeronáutica.PD
This study focuses on designing and developing
a fixed-wing unmanned aerial vehicle (UAV) to meet strict
operational requirements while maximizing cargo
capacity. The design must adhere to specific constraints,
including a maximum wingspan of 80 inches and a
structural weight limit of 5 kilograms. Achieving these
goals involves a delicate balance between maintaining the
UAV's structural integrity and ensuring its
maneuverability, effectiveness, and ease of
transportation. The challenge lies in maximizing the
structural strength within these limits to ensure the
UAV’s long-term reliability in field operations. The
ultimate goal is to create a proficient and efficient UAV,
utilizing resources and methods to optimize performance.
Keywords :
Unmanned Aerial Vehicle; Fixed Wing; Design; Analysis; High Lifting UAV, Sizing.
