Abstract:The carrier-based plane is a special aircraft, which is the main component of the aircraft carrier formation. Its design has the more difficulty than land-based aircraft. In addition to outside land-based aircraft must have proper design requirements, It’s also need to consider the special way of landing and the use of the environment, unique structural / mechanism design features, etc. Analyze and summarize the Restrict to General Design of Carrier-based Aircraft on the cockpit design, adaptation, power plant and structure. This paper can provide design reference for Design of Carrier-based Aircraft.

Abstract:The ultrathin-ply carbon fiber laminated composites is a new study trend in current years. The study of this kind of composite started relatively late and the research direction is a little single in our country. Comprehensived summarize is helpful to the future research value and make a clear research direction. And numbers of experiments data compared ultrathin-ply laminated composites and normal laminated composites which including unnotched tension, open hole tension, compressed, mechanical connection, compact, fatigue and environmental influence experiments are included. According to it, the laminated composites made from ultrathin-ply prepregs have a great advantages of damage resistance which means it can defer the happen of fracture and resist the expanding of fracture. That character influent many performance of laminates and indicate a good application prospect.

Abstract:This paper is based on an aircraft with four wheels. The relationship of angle between two nose landing gear tires is calculated based on the geometrical principle of Ackerman steering during taxiing procedure. The influence on turning radius of the four wheels aircraft is investigated when using respective nose wheels as driving wheels. Four wheels aircraft virtual prototype is built, which consists of airframe model, shock absorber model and tire dynamics model. Four wheels aircraft ground taxiing simulation has been conducted as well. Result shows that four wheels aircraft turning radius is smaller than conventional three wheels aircraft under the same taxiing circumstances when nose wheel steering is applied. Four wheels aircraft turning radius is slightly more than three wheels aircraft when main wheel is differential braking. When both nose wheels steering are applied, the four wheels aircraft has minimum turning radius.

Abstract:Pivot torque and tire contact point load calculation under pivot load case had important significance for landing gear structure design. Twin wheels and twin tandem landing gears were taken as research objects. Contact patch between tire and ground was assumed to be elliptic impression. Double integral under polar coordinates was applied. Calculation expressions of pivot load and contact point ground load were deduced. Combined with calculation cases some useful results were gained: Pivot torque was increasing as tire deflection increased; Pivot torque calculated by reference method was small; Contact point torque was much less than pivot torque, and contact point had great longitudinal as well as lateral force with regard to twin wheels and twin tandem landing gear.

Abstract:The present work is aimed to analyze the influence of the mixing between slat wake and main element boundary layer on aerodynamic force of the main element of multi-element airfoils. In order to alter the mixing condition of slat wake and main element boundary layer, slat wake varies with different momentum coefficients jet which applied at the trailing edge of slat. Numerical computation is used for solving two dimensional unsteady flow of multi-element airfoils model 30P30N at different jet momentum coefficients, the numerical results indicate that: the onset location of mixing between slat wake and main element boundary layer move downstream along main element chordwise direction, the suction peak of main element upper surface is improved, and the main element lift is enhanced with the jet momentum coefficients increased; onset location of mixing has effect on suction peak and lift of main element; the mixing of slat wake and main element boundary layer is restrained by angle of attack increasement.

Abstract:In order to estimate power of light aircraft quickly and accurately and to decide engine model at the beginning of the concept design phase, design target and airworthiness need to be satisfied. According to performance parameter and engine information statistics of multiple light aircrafts, empirical formula and functional relationship between parameters are concluded, we can calculate the internal values of power . The result show that consideration of design target and airworthiness elicit the final intersection of value, which is useful for applicant engine selection

Abstract:The aerodynamic performance of Flapping-wing Micro Air Vehicle (FMAV) is dependent on the motion of flapping wings completely. The kinematics of flapping-wing can mainly be divided into plunging, pitching and swing, representatively. The swing effects on the aerodynamic performance of flapping-wing in “0”-figure and “8”-figure wingtip path are studied quantitatively in this paper by solving the RANS equations. According to the numerical results, the pitching motion can increase the lift and the thrust forces simultaneously. The swing can mainly increase the lift force, also increase the drag force a little. The “8”-figure swing motion increase the lift and the drag forces more than the “0”-figure swing motion. The result of this paper suggested that the pitching is a good manner to increase the thrust and the swing is a good manner to increase the lift, especially the “8”-figure swing can increase the lift notably.

Abstract:In order to study the ditching of aircraft and the influence of rear fuselage suction force on pitch attitude , the ditching of aircraft is numerically studied in detailed by using dynamic mesh method, user-defined function, six degrees of freedom model, volume of fluid model based on FLUENT software. On the beginning, the slamming coefficient, pressure distribution and free water surface of water entry of 2D circular cylinder are studied; Then, the vertical water entry of 3D elliptic paraboloid and the planing of 3D flat plate are simulated to validate the reliability of 3D numerical simulation method by comparing with the test results; Finally, the ditching of NACA TN 2929 aircraft model is also simulated, the results of which show that the rear fuselage suction force plays an important role in the change of pitch attitude and this method can be properly used to simulate the rear fuselage suction force and pitch attitude in ditching.

Abstract:It introduces the trailing-edge flap of High Lift System architecture and failure type of some civil airplanes, describe the failure type of the asymmetry fault and the skew fault of the trailing-edge flap. As for how to monitor and protect the asymmetry fault and the skew fault question, it research and analysis the monitor and protection method as well as working logic of the both type faults, during making sure the threshold parameter of the working logic roundly considering the process to check and ensure the fault, and the brake process of Flap Power Drive Unit as well as the system mechanical error, and so on. Lastly it builds the Simulink model of the fault protection work logic, and simulinks several different failure conditions, the result indicates the fault protection method can monitor system and prevent fault spreading. using for reference to design of civil airplane High Lift system.

Abstract:Abstract: FMECA is the basis of reliability analysis, maintainability analysis and so on. In the criticality matrix, the horizontal axis is severity level, the vertical axis is criticality value of the failure mode or product. However, the failure modes can not be accurately identified while they have the same severity level. And then, that will lead to criticality with deviation and non-optimal improvement decisions. In addition, the efficiency of graphic method is low. A new calculation method of quantitative analysis method of criticality matrix based on the current method is described in this paper, which can be used for improving the precision and efficiency of FMECA. A sample is demonstrated that quantitative value of failure mode or product criticality can be obtained easily, which is the basis for supporting improvement decisions.

Abstract:In order to reduce the landing gear aerodynamic noise, a new method based on edge jet is proposed, which is used to analyze the active control technology of landing gear, and the validity of the method is verified by numerical calculation. Taking a certain type of aircraft landing gear as the research object, the flow field around the structure of the model is calculated by using Detached Eddy Simulation, and the sound source distribution is obtained. The far field noise characteristic is obtained by using FW-H integral. The results show that the edge jet can effectively suppress the interference and pillar noise, and the middle band noise of the landing gear can be reduced, and the broadband noise intensity is weakened. Through the analysis of the flow field and sound field, the mechanism of the noise reduction is explained: the flow of the jet is changed to reduce or even eliminate the impact of vortex shedding on the pillars.

Abstract:The authors have collected airfoils used in training aircraft wings and provided a method of airfoil sellecting for wing design using rough set theory. Weight reflecting improtance of each factor is vital in evaluating or decision-making. The method of weight determining combined the attribute imporance with conditional information entropy, which was conformed in this paper by conducting a project of trainer wing design, is suitabale for airfoil selection in wing design. The number of breaking point in discretization of parameter of airfoil was studied. The authors advised that two breaking point method is preferable than one and three ones in limited number of airfoils in data base available. The method used in this paper is believed to be useful for trainer aircraft wing’s design.

Abstract:The nature and characteristics of attack unmanned combat aerial vehicle (UCAV) are analyzed. The principles of selecting takeoff thrust-weight ratio and takeoff weight of attack UCAV are presented by analyzing the statistical data of weights for various main combat aircraft. The UCAV airborne weapons are analyzed, followed by the preliminary estimation of the payload weight. Various typical engines are analyzed and one of them is selected. Then the takeoff weight of the UCAV is determined. Based on some basic parameters and assumptions, the qualitative decomposition calculation for takeoff weight is completed. The key factors for obtaining longer endurance of aircraft with small aspect ratio configuration are found to be high lift-drag ratio and internal space. On the basis of the conclusions mentioned above, a highly blended flying-wing plus lifting body concept is proposed. According to this concept, the UCAV configuration is designed and optimized. Finally, the UCAV configuration with small aspect ratio, high lift-drag ratio, and high stealth characteristic is obtained.

Abstract:The fatigue performance of Al-Li-S4 aluminum-lithium alloys with two riveted joints is investigated. The detail fatigue rating (DFR) values are measured and calculated based on the fatigue tests. The fatigue crack initiation and propagation behavior are observed by scanning electron microscopy. The results indicate that DFR value of Al-Li-S4 alloy with riveted lap joins is 102.24MPa, and the DFR value of rivet-filled countersink hole structure is 169.41MPa. Fatigue fractography shows that Al-Li-S4 alloy has superior fatigue properties. The study can be used to select suitable materials from the fatigue strength design and fatigue life evaluation of the civil aircraft.

Abstract:The function of water and waste system (WWS) of civil aircraft is to provide the potable water, washing water and toilet flashing water for the flight members and passengers in the flight, to disposal the waste water at the same time. The location of the WWS Components and lines cross the the FWD EE bin to the AFT WWS compartment along the airframe. Temperature distribution is complex among different zones. The system will lose function due to icing without icing protection when in low temperature. The heaters location is an emphasis and difficult to confirm. This document analyzes the temperature of different zones using the module analysis method to confirm the icing protection areas, the electrical heater location confirming rule. To make the icing protection efficiency maximum, the document gives the approciate icing protection method for different components. At the same time, this document also provides the heater electrical power calculation for hose, line and tank. The icing preotection method in this document can provide the reference for civil aircraft WWS design without the aircraft temperature distrbution.

Abstract:Touch screen has been widely used in various areas of life, which make its application of display&control device possible in the civil cockpit. Meanwhile there must be some subsequent issues about ergonomic when the touch screen is applied in cockpit, thus several analyses and research related should be done. The characteristics of the touch screen are demonstrated in this paper, based on which the possibility and the ergonomics of the application in civil cockpit are analyzed. The conclusion reveals that the suitable equipment for touch screen control in cockpit would be the main instrument panel, pedestal and multifunction display control module (MCDU), etc.; while there also are ergonomic problems needed for further research when the touch screen is used, such as activation and wrong operation, the concurrent influences of display / control tasks of interface design, the missing feedback of screen, ensuring the time of response and the installation location, the environmental effect. Finally, comparative analysis of performance is made with other control methods. This paper is expected to provide a theoretic support and technology reference for application of touch screen in the civil cockpit.

Abstract:Low-altitude wind shear is one of especial phenomena, which has bad effects on civil aircraft flight. So one of counter-measures to the effects of low-altitude wind shear is to escape such phenomena. Airborne wind shear system is an effective system which could provide wind shear warning and escape guidance commands based upon sensing the airplane’s encounter of such phenomena. This paper recommends the concept and damage of low-altitude wind shear briefly. At the same time, this paper also introduces the type of civil aircraft airborne wind shear system. In order to meet the CCAR25 and CCAR121 regulations requirements well, requirements of airworthiness terms of airborne wind shear system are deeply studied, the means of compliance are put forward. It can be a reference for domestic civil aircraft to meet regulations requirements well.

Abstract:Aimed at the complicated aerodynamic constraints and geometry constraints of the aircraft design engineering,the high-fidelity unstructured-grid RANS equation solver, the FFD geometry parameterization method, the spring dynamic mesh method, the RBF function surrogate model and the PSO optimizer are integrated to build an aerodynamic shape multi-point optimization and design tool. It is employed for the advanced low-speed laminar-flow airfoil shape design and the high subsonic supercritical wing shape design via the single-point and multi-point cases, with/without the aerodynamic and the geometry constraints. The results show that the tool works, and the constraints and the intelligence optimizer automatically and effectively guide the airfoil and wing shape to change with improved aerodynamic performances.