Papers by Keyword: Wing

Abstract: The Scramjet performance of air-breathing hypersonic vehicle is highly correlated with flight height, Mach and angle of attack (AOA). The violent disturbance of the AOA can cause the engine power off. Consequently the maneuverability of hypersonic vehicle is strictly limited in the phase of cruise. A composite Control system for an air-breathing hypersonic vehicle is presented. The hypersonic vehicle has a configuration with tail control rudders and a set of deflectable wings installed nearby the center of gravity. During the phase of cruise, the precision of AOA is achieved by deflecting tail rudders, and the maneuverable acceleration command is tracked by deflecting wings. A linear quadratic (LQ) track control algorithm with integrator is used to design the composite control system. Simulation results demonstrate that the composite control system has good performance in tracking AOA and acceleration command by respective deflection in cruise.

Abstract: Experimental details of the flow field and wake over airfoils and 2-D wings are time and cost consumption. In this study, the flow visualization technique was adopted to investigate the flow field surrounding NACA4412 airfoil. The investigations were carried out in smoke tunnel, operating at low Reynolds number in a range of 10⁵. The airfoil was tested in two operational cases: first as clean wing and the second as under-loaded wing by attached missile model. The experiments were conducted at various angles of attack as 0⁰, 5⁰,10⁰, 15⁰ and 20⁰. It was found that the under-load of external body under the wing is influencing the flow structure over the wing. Also, the wake after the external body is swirling, leading to very complicated wake interaction. The results from the work can support the numerical simulation and the prediction of the laminar to turbulent transition and the separation and wake interaction of high lift airfoil flow fields.

Abstract: The flight mechanism of flapping-wing was studied by using the translation-rotation model. We established the flapping-coordinate of the wing, gave the equation of the motion, and simplified the flapping-wing model. The aerodynamic and vortices were simulated by the CFD software of Fluent. The leading-edge vortex generated in the translation phase, and delayed stall mechanism had an important effect on the high lift. In the rotation phase, lift peaks appear due to the wing rapidly rotating and rotational circulation mechanism. The aerodynamics were obtained in different amplitudes, frequencies, angles of attack, the locations of rotating axis and timings of rotation. The influence of these parameters on average lift coefficient is obvious, while it can be ignored to average drag coefficient. Keywords: wing, aerodynamics, vortices, numerical simulation.

Abstract: Any aircraft wing is the major component which will play vital role in the generation of lift and at different maneuvering moments throughout the flight. So to maintain this good maneuverability the aircraft wing has to undergo deferent deflections called angle of attack such that the high lift and low drag or vice versa can be settled in the flight. Taking this as the motivation the analysis was carried out on the standard wing airfoil comparing with new designed airfoil. Analyze the numerical simulation values like coefficient of lift, coefficient of Drag, Lift, Drag, and Energy parameters with wind tunnel data to predict accuracy for both the airfoils. Through the selected public literature standard airfoil data and designed airfoil data has been chosen, the geometry was created in the GAMBIT and also the meshing by selecting the suitable c-grid and rectangular grid for the better flow analysis in the FLUENT. The mesh file was imported into the FLUENT software there suitable boundary conditions and operating conditions are given for successful flow convergence. Finally analyzing these results are expecting to be best suitable for good aeromechanical features.

Abstract: Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at different angles of attack (AoA) from 0 to 5 degrees. For this the fighter aircraft wing performance for various flow conditions and sweep angles are obtained based on the empirical, semi-empirical and CFD simulation results. Hence by studying these computational results would help in the optimizing geometry for better performance, an finest wing design for the air launched air to surface body with conservative wing can be obtained.

Abstract: This research was mainly on morphology observation of syrphid common species including Episyrphus balteatus, Eristalis latréillè, Eupeodes osten, and Melanostoma schiner. Observations of four species of syrphid morphological characteristics in Shenyang were of the first radial cell area (R1), the third radial cell area (R3), the fifth radial cell area (R5), the second median cell area (M2), the first anal cell area (1A), spurious vein and wing length. The results showed that the first radial cells area, the third radial cells area, the fifth radial cell area, the second median cells area, the first cell area and wing length of M. schiner were the minimum, and spurious vein length was the maximum. The first radial cell area of E. latréillè was larger than that in other three species. The first radial cell area of E. latréillè was larger than that in other three species. The third radial cell area, the fifth radial cell area and the second median cell area of E. balteatus were larger than that in other three species. The wing length of E. osten was longer than that in other three species. Significance test showed that syrphid wings of the same individual from the four species had no significant differences.

Abstract: The article describes process of implementation of optical Fiber Bragg Grating (FBG) sensors into the composite wing structure and their behavior during the strength test. The wing is of all-composite construction. The upper and lower skins are made of glass/epoxy composite. The spar caps are made of carbon/epoxy unidirectional composite. Optical fibers were integrated directly into the spar caps and into the adhesive joints. They were oriented in parallel with the main spar axis. The first optical fiber with chain of multiple FBG sensors was integrated into the structure of upper spar cap. Another FBG chain of FBG sensors was located in the adhesive joint of lower spar cap and shear web. The wing was instrumented with strain gages as well. Strain gages were glued to the sides of the spar caps. Static load was produced by a hydraulic actuator. Experimental results from strain gages and FBG sensors were compared with the results of the analytical analysis of the wing.

Abstract: Insect-like flapping-wing aircraft is a research focus in the study of Micro Aerial Vehicle. In the paper, a cicada is chosen as the object, and based on the analysis of its wing, its kinematics and three-dimensional model are researched. In the study of kinematics, two softwares (Movias-pro and Photoshop) are applied, and the laws of flap and torsion movements are obtained. In the study of three-dimensional mode, the wing is scanned by the use of flat plane scanning method, and the resulting picture is vectorized. Based on the wing datum, the three-dimensional model of wing is created by the use of Pro/E. The result from the paper lays foundation for the development of cicada-like flapping-wing aircraft.

Abstract: For an unmanned aerial vehicle, in order to study the aerodynamic characteristics of the large aspect ratio wing during the deployment process with variable sweep angles, the scaled model was tested in the wind tunnel at different angles of attack with various sweep angles of wing. Experimental results indicate that the aerodynamic configuration satisfies the cruise design requirements, providing favorable longitudinal and lateral-directional stability. Fuselage of multi-plane combination brings beneficial effect for lift. Analysis have been made on the cases including wing flow separation which lead to the step of lift curve, and the existence of longitudinal unstable range during wing unfolding, which make the foundation for next optimum of configuration. The work described in this paper can be applied in the design of unmanned aerial vehicles, missiles and other research areas.

Abstract: 3D digital assembly process design technology is the combination of the three dimensions and information with the new software technology in traditional process design. This article is based on an aviation manufacturing enterprises priority to the realization of the whole assembly process design, simulation and verification business process, which mainly with Dassault Companys DELMIA and 3DVIA Composer platform. In this paper, some process design thinking and methods are introduced to the aircraft product process about the separation technology division, BOM reconstruction, process simulation, 3d assembly instruction compiling, and the like. It also introduces some application methods of system integration.