This paper presents an analysis through simulation study of the structural design of a composite UAV wing. Structural Analysis of Composite Wing using Finite Element Method.
First Generation Of Hale Uav Itb Source Personal Documentation Download Scientific Diagram
The structural weight of HALE UAV is one of the most critical design requirements.
. Wing loading calculations were done based on the parameters. HALE High Altitude Long Endurance UAVs are aircraft systems for surveillance and reconnaissance for over 25 hours. Solar-Powered HALE UAV 21 History of development of HALE UAV in KARI KARI has developed the EAV-1 a wing span is 24m.
The latest Lim et al 9 optimized wing design of Solar-HALE aircraft by considering interaction between aerodynamics and structures. The wing was modeled as a beam structure. Design Optimization of a Composite Wing Box for High-Altitude Long-Endurance Aircraft Institution.
Structural Analysis of Composite Wing using Finite Element Method. Close Log In. The wing was made of a carbonepoxy laminate with orthotropic arrangement 0045.
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. Most of UAVs consist of fuselage and high aspect ratio wing because of long-endurance flight mission. A design optimization process is developed to define the wing box structure for High-Altitude Long-Endurance Aircraft HALE.
The spar also used a sandwich structure. The structural design of the UAV composite wing regarding buckling analysis is more effective when the laminates are stacked up with high percent of - 45 degrees plies and the -. The scaled boom-structure consists of a 598 m long tapered tubular member with a circular 235 mm diameter cross-section near the wing-box and a 150 mm diameter cross-section in correspondence to the vertical tail junctionThe 235 mm diameter cross-section is constant up to a distance of 255 m from the wing-boxThe two booms were made of a CFRP.
By continuing to use this site you agree to our use of cookies. In addition the structural stiffness for the high aspect ratio wing. Multi-Objective Optimization of the Composite Wing Box of Solar Powered Hale Uav.
IAI Israël Aircraft Industry has been in charge of the performance analysis and UNINA University of Naples - Italy has done both the structural analysis. 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. Optimization procedure to design composite wing box of solar powered HALE UAV.
HALE High Altitude Long Endurance UAVs are aircraft systems for surveillance and reconnaissance for over 25 hours. This site uses cookies. HALE UAV PLATFORM OPTIMISED FOR A SPECIALIZED 20-KM ALTITUDE PATROL MISSION Several others partners have been involved in this two cycle preliminary design process as mentioned in Fig.
HALE-UAVs are characterized by a high aspect ratio wing resulting in very flexible airframe. HALE High Altitude Long Endurance UAVs are aircraft systems for surveillance and reconnaissance for over 25 hours. SMALL UNMANNED FIXED-WING AIRCRAFT DESIGN.
Engineering Modeling Solar Cell. This is the second part on the design of a high aspect ratio HALE-UAV wing using composite materials. HALE Unmanned Aerial Vehicles UAV.
Indeed the low on-board power of the latter involve a high level of aero-dynamic and structural performance. UAV wing material characterization of the composites used in the UAV wing and prelimi-nary structural analysis of the UAV wing. Research on a High Altitude Long Endurance HALE Unmanned Aerial Vehicle UAV is currently being conducted at Bandung Institute of Technology ITB.
This paper is a continuation of the first paper and presents buckling and flutters analysis. Most of UAVs consist of fuselage and high aspect ratio wing because of long-endurance flight mission. Manufacturingisperformedatthe compositelaboratoryfounded in theDepartment ofAerospace Engineering and with hand lay-up and vacuum bagging method at room temperature the wing is produced.
The semi-monoque structure consists of one main mono-spar 4 major ribs carbon tubes and a flap. Design of EAV-2H2H EAV-3 is developed to verify a climb ability up to an altitude 20km and to demonstrate the developed systems stability and operational feasibility in the severe environment of the stratosphere. M E C H A N IC.
The fuselage consists of a high-speed cutting aluminum alloy keel beam and frame covered with a composite skin. Embry-Riddle Aeronautical University Degree. A good way to meet this objective is to design an aircraft with a high aspect ratio wing enhanced lift-to-drag ratio and a lightweight composite airframe low wing loading2 This kind of aircraft is.
In this research the wing structure of initial version of HALE UAV is designed using carbon composite material. The structural design of the UAV composite wing regarding buckling analysis is more effective when the laminates are stacked up with high percent of 45 plies and the 45 plies are located toward outside through the. The composite material accounts for 45 of the weight of the X-45A structure.
Design of High Altitude Long Endurance UAV. Flight test gave the result of broken wings due to extreme side-wind that causes large bending to its high aspect ratio. The very flexible wing need to be designed so it can satisfy the deformation and strength criteria.
Design manufacturing and testing of a HALE-UAV structural demonstrator. Fig1213 give bending and torsional stiffness for main wing versus spanwise station. To find out more see our Privacy and Cookies policy.
The real physical structure of aircraft. Master of Science in Mechanical Engineering Year. The wing structure is modeled and analyzed using finite element to assess its integrity.
The concept of load bearing types of the skin. Previously the 1st generation of HALE UAV ITB used balsa wood for most of its structure. The first paper deals only with the static strength analysis.
The structural weight of HALE UAV is one of the most critical design requirements. High-altitude long endurance unmanned aerial vehicles HALE-UAV flying in the stratosphere can provide a useful platform for sensors to support a range of military and civilian surveillance tasks. Design of High Altitude Long Endurance UAV.
They achieved 253 of weight reduction. In addition the structural stiffness for the high aspect ratio wing. The internal structures have been designed to promote better flight and structural performances.
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