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008 100603t2009 my dao f m 000 0 eng d
020 _aTHE0007774(Local)
039 9 _a201905241518
_bfawwaz
_c201107132213
_dVLOAD
_c201006041121
_dFida
_y201006031630
_zFida
040 _aUMP
090 _aUG1242 .D7 Z35 2009 rs Bc.
100 0 _aMohamed Zaid Mohamed Zakaria
245 1 0 _aWeight distribution, stability and structural analysis for reconnaissance UAV /
_cMohamed Zaid Bin Mohamed Zakaria
246 3 _aWeight distribution, stability and structural analysis for reconnaissance UAV
_h[electronic resource]
260 _aKuantan, Pahang :
_bUMP ,
_c2009
300 _axv , 63 p. :
_bill. (some col.) ;
_c30 cm. +
_e1 computer disc
502 _aProject paper (Bachelor of Mechanical Engineering) -- Universiti Malaysia Pahang - 2009
504 _aBibliography : p. 53
520 3 _aUAV is a new pattern of surveillances system that has being used in for many purposes this day. However, smaller UAVs are needed for friendlier handling. This is a Mini UAV which capable to compete with other Mini UAV in the market now days. In this project, the focus is to analyze and design the airframe of the Mini UAV. The UAV is 2m in span and 1.2m in length and takeoff weight of 3.8 kg. it is light weight, so the stability on the highest altitude has to be considered as very important. The estimation of location of wing on the fuselage and its relevancy of the wingspan has to converge with the wing area. The weight plays an important specification for the UAV. The entire component including the power plant has to light. The placements of weight in the fuselage can change the position of center of gravity. The function of the UAV would affect the placement of component in the fuselage. The more stable the UAV the more reliable it'll be. The method of iteration is going to be used for calculation and analysis for. The CAD model will be designed using SolidWork.
650 0 _aDrone aircraft
650 0 _aStability of airplanes
999 _aVIRTUA40
_c1329
_d1335
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