Reducing the weight of the spars while maintaining sufficient structural integrity is important because the spar is the heaviest load bearing component in the main. SMALL UNMANNED FIXED-WING AIRCRAFT DESIGN.
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Design manufacturing and testing of a HALE-UAV structural demonstrator.
. The Boeing X-45A has a wingspan of 103m a chord length of 8m an air weight of 3640kg and a payload capacity of 680kg. The project describes the major features of High Altitude Long Endurance unmanned aerial vehicle HALE UAV designed with morphed wing that has performance requirements for surveillance missions. Indeed the low on-board power of the latter involve a high level of aero-dynamic and structural performance.
Module can design the wing structure for the given aerodynamic load. Classical proce-duresusually refer toaero-structural systemswhere theundeformedstate is takenas the reference point. The wing was modeled as a beam structure.
The wing structure is broken down into non-spar elements and spars. High-altitude long endurance unmanned aerial vehicles HALE-UAV flying in the stratosphere can provide a. Finite element software.
The wing was made of a carbonepoxy laminate with orthotropic arrangement 0045. Phenomena as are concerned a new type of innovative aircraft namely solar powered High Altitude Long Endurance HALE Unmanned Aerial Vehicles UAV. Design manufacturing and testing of a HALE-UAV structural demonstrator.
The analysis is conducted with load factor of 38 and -152 which represent maximum and minimum load factor. Flight test gave the result of broken wings due to extreme side-wind that causes large bending to its high aspect ratio wing. The fuselage consists of a high-speed cutting aluminum alloy keel beam and frame covered with a composite skin.
Optimization procedure to design composite wing box of solar powered HALE UAV. This paper is a continuation of the first paper and presents buckling and flutters analysis. This is not the case with slender wing configuration where due to the high structural flex-ibility a proper beam model capable of describing the structural flight deflections should be adopted.
Structural tests on the UAV were successfully completed in January 2018. Moelyadi Analysis and Design of Composite Wing Structure of HALE Aircraft in ICIUS 2015. The strength and stiffness requirements of the wing structure were evaluated during the tests.
Composite Structural Analysis of a High Altitude. The latest Lim et al 9 optimized wing design of Solar-HALE aircraft by considering interaction between aerodynamics and structures. A good way to meet this objective is to design an aircraft with a high aspect ratio.
ULTRA LIGHT WING STRUCTURE FOR HIGH ALTITUDE LONG ENDURANCE UAV 4763 However because these numerical results were not validated by testing a representative structure so they have to be treated as approximated values with a prescribed degree of uncertainties. In general the main wing of a HALE UAV is composed of composite spars ribs leading edge trailing edge and thin plastic covering film to reduce structural weight 3 4 5. BAE Systems and Prismatic entered a new collaboration agreement for the joint development of the PHASA-35 UAV in May 2018.
Previously the 1st generation of HALE UAV ITB used balsa wood for most of its structure. High Altitude Long Endurance HALE UAV is a type of aircraft that is able to fly in high operational altitude 65000 ft and longer duration 36 hours. The composite material accounts for 45 of the weight of the X-45A structure.
They achieved 253 of weight reduction. The weight of non-spar. The first paper deals only with the static strength analysis.
Close Log In. For composite materials the ply stacking sequence is defined by firstly predicting the. Structural Analysis of Composite Wing using Finite Element Method Journal of Physics.
PHASA-35 design and features. Composite Structural Analysis of a High Altitude. Based on the results the wing composite structure of the maritime surveillance UAV is safe because it has factor of safety of 166 for load factor 38 and 335 for load factor -152 based on Tsai-Wu failure criterion.
Research on a High Altitude Long Endurance HALE Unmanned Aerial Vehicle UAV is currently being conducted at Bandung Institute of Technology ITB. Wing structure an initial design. Design of High Altitude Long Endurance UAV.
The wing structure of HALE UAV ITB consists of various materials on each part. This is the second part on the design of a high aspect ratio HALE-UAV wing using composite materials. Flight test gave the result of broken wings due to extreme side-wind that causes large bending to its high aspect ratio.
This paper conducted a study on designing the 2 nd generation of HALE UAV ITB which used composite materials in order to substitute balsa wood at some critical parts of the wings structure. The spar also used a sandwich structure. Fig1213 give bending and torsional stiffness for main wing versus spanwise station.
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