Design and stress analysis of a general aviation aircraft wing. Crosssection of an aircraft wing with a longitudinal set of wing spars and several profiles types of. In the second step, the wing slides down while being rotated to the rear of the aircraft. Two of these booms were linked together by an alloy web, creating a. The aim of this project is to study about the various types of aircraft wing spar structure and to optimize an aircraft wing spar beam for a six seated aircraft. To locate the batteries in the apex as shown in figure 2, involvestwo criteriafor the design. Optimization of aircraft wing with composite material shabeer kp1, murtaza m a2 5. Welcome to part 6 of a series on an introduction to aircraft design.
The failure appears to be caused by high flight loads. Research and interviews were an important part of the process. The first project was to lay up a test wing spar panel to verify the design concept. Geometric model of spar beam of a passenger aircraft is done using solid edge st8 modeling tool. In order to maintain correct geometry throughout these processes, the strut.
Study of optimal design of spar beam for the wing of an. In addition to the main spars, some wings have a false spar to support the ailerons and flaps. Wing terminology leading edge is the portion of the wing front of the front spar trailing edge is the portion of the wing back of rear spar the chord is the distance between the leading edge and trailing edge wing box is portion of the wing between the front spar and rear spar ribs are the airfoil shaped members from leading edge to trailing edge. In addition, this report presents the planes wing and tail design, stability analysis and a mass breakdown. The response of the wing structure will be evaluated. The wing is then free to pivot about an axis running from the strutmain spar connection to the fuselagemain spar connection. The topology optimization is conducted within two inner spars and 20 ribs. Shear web spar widely adapted to design modern wing 2.
Pdf graphiteepoxy composite design for aircrcaft wing. Multispar and box beam wing designs were developed in response. Pdf complex wing spar design in carbon fiber reinforced. Design and finite element analysis of aircraft wing using. When other structural members of the wing are placed under load, most of the resulting stress is passed on to the wing spar.
The requirements for the aircraft wing are high stiffness, high strength, high toughness and low weight. Pdf since ancient times, human beings have been seeking to. Semitensioned type spars shear are much better than the truss type spars because of construction cost and efficiency. Panels with tshaped stringers and spars are made of composite materials.
A rotarywing aircraft consists of the following four major units. Structural analysis of the airplane wing is conducted to define the geometry of the wing spars and skin. Identify the five basic stresses acting on an aircraft. The spar mold was built up using sections of mdf board. Structural design of a uav wing using finite element method farrukh mazhar 3. Wing skin together with spar webs forms an efficient torsion member. Optimal design of composite wing spar subjected to fatigue loadings. Complex wing spar design in carbon fiber reinforced composite for a. Software packages are to be used to design an aircraft wing spar structure and. Pdf on aug 26, 2017, akindapo jacob olaitan and others published graphiteepoxy composite design for aircrcaft wing spar using computational techniques part i find, read and cite all the.
Wing design procedure wing design requirements performance, stability, producibility, operational requirements, cost, flight safety select wing vertical location select or design wing airfoil section determine other wing parameters ar, i. Upward bending loads resulting from the wing lift force that supports the fuselage in flight. In our final introductory post on the wing we look at a typical wing structure, the various loads that the wing is expected to carry during operation, and introduce the methodology behind. Once the geometry is created as per specification and it. As the aircraft design and manufacturing evolved, the development of lightweight metals and the demand for increased production moved the industry away from aircraft constructed entirely of wood. Design and optimization of a wing structure for a uas class i 145 kg. Varieze wing spar and wing attach structure a varieze wing centersection spar cap has failed. Software packages are to be used to design an aircraft wing spar structure and finite element method. Optimal topology of aircraft rib and spar structures under. Pdf structural analysis of a composite wing spar for a light. Complex wing spar design in carbon fiber reinforced composite for a light aerobatic aircraft article pdf available in mechanics and industry 176 january 2016 with 250 reads.
In principle, there are four options for the vertical location of the wing. For this we did a comparative study on particular 150 seater regional aircraft 123. The wing of airbus a350 is a two spar wing designed within the multi rib structural layout. Composite wing structures testing numerical simulations. The wing section is designed to have two spars, one at a quarter of the cord position and one at the. Composite wing spar web design composite webs, foam webs. Wing structure has axial members stringers, bending members spars, shear panels spar web, skin, ribs inplane transverse load. The wing design and optimization process, involved determining the loads acting. Impact of sweep angle on the critical mach number the greatest benefit of wing sweep is a reduction in the strength of and delay in the onset of shock formation. Juan reuben lazarin, and eltahry elghandour students at the cal poly department of mechanical and aerospace engineering were tasked with the challenge of ensuring that a wing structure is.
Abstract spar beam is an icross sectioned cantilever beam which is fixed to the fuselage for supporting of the wing. Method to assess the design using different analysis techniques. Design of wing using computational fluid dynamics cfd, we conducted an analysis of the wing as incorporated in our ultralight aircraft. Optimal topology of aircraft rib and spar structures. Semispan wing cover panel with complex contoured loft structure on advanced stitching machine semispan wing cover panel design base skin layup with spar caps stitched skin with integral spar caps stitching of stringer to skin stitching of rib clip to skin stitched wing cover panel preform stitched resin film infused semispan wing cover panel. In this thesis, the trainer aircraft wing structure with skin, spars and ribs is considered for the detailed analysis. Currently collier research is evaluating the performance of many panel concepts for highly loaded, transport wingbox structures. This compression cap totally failed just inboard of the right wing attach fitting.
Interdisciplinary wing design structural aspects dlr. The wing section is designed to have two spars, one at a quarter of the cord position and one at the three quarters of the cord. The efficient design will be achieved by the use of strength of material approach. The wing is swept forward to solve the cg issue that results from the engine and the two occupants sitting in front of the main spar. Using ansys simulation software, we designed the wing of our ultralight aircraft with a scale of 110. Front spar is located that the wing leading edge slats can be attached to it and rear spar is located such that control surfaces such as flaps, ailerons, spoilers, can be attached to it. Truss type the two primary conditions which determine efficiency of a spar are its construction cost and its efficiency as its load carrying member. A design aspect of the supermarine spitfire wing that contributed greatly to its success was an innovative spar boom design, made up of five square concentric tubes that fitted into each other. To prevent spar carrythrough frame structure failure, which, if not detected and corrected, could result in severe structural damage to the wing, accomplish the following.
It reduced the amount of guess work to arrive at a design that met all requirements. These forces are often offset by carrying fuel in the wings or employing wingtipmounted fuel tanks. Design and finite element analysis of aircraft wing 6. Conclusion the engineering design process was successfully implemented to find a viable solution for the air forces b52 wing spar. Wing design procedure wing design requirements performance, stability, producibility, operational requirements, cost, flight safety select wing vertical location select or design wing airfoil section determine other wing parameters ar, i w, t calculate lift, drag, and pitching moment optimization. They support all distributed loads as well as concentrated weights such as fuselage, landing gear and engines monospar wings incorporate only one main lateral member multispar wings incorporate more than one main lateral member. In part 5 we looked at the role that the airfoil profile plays in determining the flying characteristics associated with its selection. Structural safety with minimum weight is the major. Moreover, front and rear spar combined with wing skin panels form as closing member of. Some general aviation aircraft were produced with wood spars and wings, but today only a limited number of wood aircraft are produced. Design and structural analysis of the ribs and spars of swept back wing the aim of this paper work is to design and analyze the ribs and spars of a 150 seater regional aircraft for the stresses and displacements due to the applied loads.
In design and finite element analysis of aircraft wing using ribs and spars, an aircraft wing is designed and modeled in 3d modeling software proengineer. The wing structure consists of 15 ribs and two spars with skin. Varieze mandatory ground inspect for corrosion and limit. Airframe wingbox preliminary design and weight prediction.
The report nally ends with pictures of the current design. Structure determination and composite wing spar stressstrain state. Complex wing spar design in carbon fiber reinforced composite for a light. The wing ribs are constructed in the same manner as those in the horizontal stabilizer. Introduction to wing structural design aerotoolbox. Optimal design of composite wing spar subjected to fatigue. Regardless of type, the spar is the most important part of the wing. They are longitudinal members like spars but do not extend the entire spanwise length of the wing.
The structural design of the wing started from scratch with an empty aerodynamic shell, that had to be filled with all necessary structural members, like spars, ribs. Next we will tackle what could be the most exciting item in the aircraftthe wings main spar. Ribs extend from the leading edge to the trailing edge of the wing. Both wing and fuselage act like beams and torsion members. Oduntan, sovereignty and jurisdiction in airspace and outer. Aircraft is a complex mechanical structure with flying capability.
Structural analysis and optimization for spar beam of an. Design, analysis and testing of wing spar for optimum. Design and analysis of wing of an ultralight aircraft yuvaraj s r 1, subramanyam p 2 4. This involves the definition of the wing section and the planform.
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