Box wing fundamentals an aircraft design perspective. Introduction to wing structural design aerotoolbox. Pdf this paper presents an introduction to box wing aircraft technology, and an overview of. Aero aircraft design and systems group, berliner tor 9, 20099hamburg. Preliminary structural design optimization of an aircraft. Development of an advanced composite aileron for the l101. The most common aircraft is the fixedwing aircraft. The comparison showed satisfactory convergence of coefficients for the clean configuration and some discrepancy for the takeoff. This structure increases strength while reducing weight. In order to calculate the induced drag coefficient of the box wing aircraft it is necessary to know its aspect ratio and its span efficiency factor. Richard hale for teaching me the mechanics and design of composite materials and making me aware of details that should be considered in. Box wing aircraft conceptual design has been studied by jemitola and fielding 2. Wing and fuselage structural optimization considering.
Box wing flight dynamics in the stage of conceptual. For example, when designing a wing it is necessary for this wing to have the maximum lifttodrag ratio, the minimum weight, the sufficient lifespan and enough internal volume to contain the large amount of fuel, to be easy to manufacture and etc. The design of an aircraft is a prolonged process that has mainly three phases. It is a wedgeshaped, onecell box, thinning slightly from root to tip. Box wing, layout design, oswald factor, novel aircraft design, conceptual design. Methods for improvements of the box wing aircraft concept and corresponding aircraft configuration cn201580051870. Conceptual design methodology of a box wing aircraft. This study investigates the aerodynamic tradeoffs of a boxwing aircraft configuration using highfidelity aerodynamic optimization.
Structural weight has always been important in aircraft manufacturing industry. The firstapproach techniques for analytical evaluation of the airfoil shape and calculation of the aerodynamic coefficients for a boxwing aircraft are suggested. The conceptual and preliminary design of a 300passenger boxwing aircraft configuration, designated the prandtlplane, is investigated. According the avls manual 12, the viscous drag is calculated from the. Box wing flight dynamics in the stage of conceptual aircraft design. Study of optimal design of spar beam for the wing of an. Analytical evaluation of box wing aircraft aerodynamic. The design is taken through the general steps in aircraft preliminary design. The design is taken through the general steps in aircraft preliminary.
The approach is to demonstrate how theoretical aspects, drawn from topics on airplane aerodynamics, aircraft structures, stability and control, propulsion, and compressible flows can be applied to produce a new conceptual aircraft. If that alignment is off, engineering comes down and designs us. Alternately, a fuelcarrying bladder or tank can be fitted inside a wing. Big cost drivers are involved in aircraft assembly and assemblyrelated. A rolls royce liberty works ultra fan engine uses advanced turbofan. Design of aircraft is intended as a text for a seniorlevel capstone aerospace or aeronautics engineering course dealing with the conceptual design of aircraft. Study of optimal design of spar beam for the wing of an aircraft 1ajith v s, 2dr. A box wing aircraft is based on a continuoussurface nonplanar wing formation with no wingtips.
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. Tail rotor assembly you need to be familiar with the terms used for aircraft construction to work in an aviation rating. Design optimization of a composite wing box for highaltitude longendurance aircraft institution. Keywords horizontal aircraft, wing box, skin, spar, stringer and ribs. This paper presents an introduction to box wing aircraft technology, and an overview of current re. A design optimization process is developed to define the wing box structure for highaltitude longendurance aircraft hale. Considering that a large number of candidate material and geometric shapes are available early in the design cycle, preliminary design optimization of skinstringer panels used to build an aircraft wing is required to obtain the best preliminary structure before the final design phase. The reliability of the calculation results was estimated using flz code the vortex lattice method.
A total of five optimization studies are conducted, where each study extends the previous one by progressively adding a combination of design variables and constraints. It also presents otherwise unpublished data and design methods that are suitable for aircraft conceptual, preliminary and detail design activities. A metal wing is a box structure with the skins comprising the top and bottom, with front. Aerodynamic analysis of box wing configuration for. Wing design the total wing area of the box wing aircraft is equal to that of the reference aircraft, and is split into the forward and aft wings in equal parts. Fixtures are large permanent structures that are costly to design, manufacture and install. Lockheed martin claims that an advantage of the boxwing concept is that it can carry multiple refueling booms, increasing the number of fighters that one aircraft can support. For improving the method and corresponding aircraft construction of boxlike wing aircraft. Professor, jawaharlal college of engineering and technology.
The box wing aircraft in this experiment is designed to act as a medium to large capacity, longrange aircraft. This approach can provide a better understanding of the relationship between various aeroelastic metrics and the distribution of material within a wing box, and therefore improve the understanding of the optimal topology when each of these metrics are eventually included in a unified. Lockheed martin janes joined wings and blended wingbody configurations are being considered for future airlift and tanker requirements. This artists concept shows a possible future subsonic aircraft using a boxed or joinedwing configuration to reduce drag and increase fuel efficiency.
Already in 1924 ludwig prandtl indicated that a wing system generating minimum induced drag consists of two wings whose tips are connected by vertical plates prandtl 1924. In the conceptual design of the box wing aircraft 2. Schiktanz and scholz perform a systematic and general investigation. The wingbox continues beyond the visible wing roots and interfaces with the fuselage in the centre wingbox, which forms the structural core of an aircraft. As the name implies, the wings on this type of flying machine are attached to the fuselage and are not intended to move independently in a fashion that results in the creation of lift. This paper presents a conceptual design process for a medium range box wing aircraft is pre sented. A conceptual design optimization methodology was developed for a.
Optimal topology of aircraft rib and spar structures under. The wingbox is so called since on many designs the combination of the forward and rear wing spars and the upper and lower wing skins together form a natural box shape running through the wing. Box wing aircraft will suffer from induced drag the same as any aircraft will, if they are heavierthanair vehicles and are using their wings to fly. Figure 18 shows a wing section with a box beam structural design such as one that might be found in a transport category aircraft. Conceptual design of a medium range box wing aircraft. Pdf this work studies the characteristics of the aerodynamics design of a box wing aircraft bwa with the potential gain of aerodynamics. Design optimization of a composite wing box for high.
Closed wing designs include the annular wing commonly known as the cylindrical or ring wing, the joined wing, the box wing and spiroid tip devices like many wingtip devices, the closed wing aims to reduce the wasteful effects associated with wingtip vortices. The top and bottom wings are each assigned 7 design variables. The design of a promising medium range box wing aircraft based on the airbus a320 taken as reference aircraft is performed. A closed wing is a wing that effectively has two main planes which merge at their ends so that there are no conventional wing tips. The fuel consumption of the final aircraft is 9 % lower than. A rotarywing aircraft consists of the following four major units.
The diamond box wing aircraft bwa was designed at hamburg university of applied sciences in the project airport 2030. It is shown that the designed wing could be a good candidate for similar general aviation airplane implementation. Examples of design variables include wing twist and sectional shape. Scholz hamburg university of applied sciences aero aircraft design and systems group berliner tor 9, 20099 hamburg, germany abstract a systematic and general investigation about box wing aircraft is conducted, including aerodynamic and performance characteristics. They bested all other competitors in the microclass due to high marks in their design report and presentation.
Box wing design by lockheed martin nasas big ideas for. Aerodynamic optimization trade study of a boxwing aircraft. This box wing design by lockheed martin is made possible by the use of advanced lightweight composite nonmetallic materials. Introduction a wing is a lifting surface, lift is produced due to pressure. Box wing aircraft conceptual design paul o jemitola.
Airframe wingbox preliminary design and weight prediction. Department of aerospace engineering, cranfield university email protected. The intent of this research is to mature hypersizers usability for final design and certification of traditional transport wing box structures. Task for a master thesis according to university regulations. A systematic and general investigation about box wing aircraft is conducted, including aerodynamic and performance characteristics. Identify the five basic stresses acting on an aircraft. Induced drag is a function of finite span loading, and moderated by various ways to improve design efficiency at a given span loading.
Load distribution on wing is also carried out in this paper. Pdf wing geometric parameter studies of a box wing aircraft. They found that a box wing design, due to its superior aerodynamics characteristics compared to a conventional aircraft, can help reduce the operating cost of a medium range aircraft. Volume 1 preliminary design approach of the wing box. The chosen airfoils are supercritical, and belong to the second. Joint fixity effect on structural design of a box wing. Conceptual design and optimization methodology for box wing.
When we reduce our weight per wingspan, or fight the result wake vortices using 3d geometries, such as winglets etc. Conceptual design of a mediumsized joinedwing aircraft 17 december 2009 proceedings of the institution of mechanical engineers, part g. Lift coefficient for maximum aerodynamics efficiency of box wing aircraft. In part 5 we looked at the role that the airfoil profile plays in determining the flying characteristics associated with its selection.
Currently there are still a number of technical issues which. Professor, jawaharlal college of engineering and technology, 2professor, arj college of engineering and technology, 3asst. For the corner fillets, the rotation planes are derived from a linear combination of xz and xy planes. Joint fixity effect on structural design of a box wing aircraft volume 116 issue 1178 p. Welcome to part 6 of a series on an introduction to aircraft design. A box wing aircraft can dramatically reduce the kind of drag caused by being heavier than air and having a finite wingspan. Wing geometric parameter studies of a box wing aircraft. Some values of c1 given in the aircraft mass prediction72 manual are. Design and stress analysis of a general aviation aircraft wing. Their design, manufacture and installation can be significant with long lead times. One, two, or three sets of wings have all been successfully utilized.