International Journal of Aerospace Engineering http://www.hindawi.com The latest articles from Hindawi Publishing Corporation © 2016 , Hindawi Publishing Corporation . All rights reserved. Effects of Duct Cross Section Camber and Thickness on the Performance of Ducted Propulsion Systems for Aeronautical Applications Tue, 09 Feb 2016 14:20:19 +0000 http://www.hindawi.com/journals/ijae/2016/8913901/ The axisymmetric flow field around a ducted rotor is thoroughly analysed by means of a nonlinear and semi-analytical model which is able to deal with some crucial aspects of shrouded systems like the interaction between the rotor and the duct, and the slipstream contraction and rotation. Not disregarding the more advanced CFD based methods, the proposed procedure is characterised by a very low computational cost that makes it very appealing as analysis tool in the preliminary steps of a design procedure of hierarchical type. The work focuses on the analysis of the effects of the camber and thickness of the duct cross section onto the performance of the device. It has been found that an augmentation of both camber and thickness of the duct leads to an increase of the propulsive ideal efficiency. Rodolfo Bontempo and Marcello Manna Copyright © 2016 Rodolfo Bontempo and Marcello Manna. All rights reserved. Aero Engine Fault Diagnosis Using an Optimized Extreme Learning Machine Tue, 26 Jan 2016 13:20:06 +0000 http://www.hindawi.com/journals/ijae/2016/7892875/ A new extreme learning machine optimized by quantum-behaved particle swarm optimization (QPSO) is developed in this paper. It uses QPSO to select optimal network parameters including the number of hidden layer neurons according to both the root mean square error on validation data set and the norm of output weights. The proposed Q-ELM was applied to real-world classification applications and a gas turbine fan engine diagnostic problem and was compared with two other optimized ELM methods and original ELM, SVM, and BP method. Results show that the proposed Q-ELM is a more reliable and suitable method than conventional neural network and other ELM methods for the defect diagnosis of the gas turbine engine. Xinyi Yang, Shan Pang, Wei Shen, Xuesen Lin, Keyi Jiang, and Yonghua Wang Copyright © 2016 Xinyi Yang et al. All rights reserved. Triangle Interception Scenario: A Finite-Time Guidance Approach Sun, 24 Jan 2016 14:16:19 +0000 http://www.hindawi.com/journals/ijae/2016/2942686/ Considering an aircraft threatened by an interceptor, one of the effective penetration strategies is to release a Defender from the aircraft to confront the interceptor. In this case, the aircraft, the Defender, and the interceptor constitute the three-body guidance relationship, and the cooperation of the aircraft and its Defender to achieve the best tactical effects turns into a concerned problem. This paper studies the triangle interception guidance problem via the finite-time theory. The paper presents linear system Input-Output Finite-Time Stabilization (IO-FTS) method. The sufficient conditions of the linear system, being IO-FTS, under Finite-Time Boundedness (FTB) constraint are proposed, by which the state feedback controllers design method is obtained, via Linear Matrix Inequalities (LMIs). The triangle interception guidance problems are studied in three different cases, where the proposed methods are applied to the guidance design. The simulation results illustrate the effectiveness of the proposed methods. Yang Guo, Xiaoxiang Hu, Fenghua He, Hongjie Cheng, and Qinhe Gao Copyright © 2016 Yang Guo et al. All rights reserved. Projection-Based Adaptive Backstepping Control of a Transport Aircraft for Heavyweight Airdrop Thu, 31 Dec 2015 09:57:45 +0000 http://www.hindawi.com/journals/ijae/2015/538901/ An autopilot inner loop that combines backstepping control with adaptive function approximation is developed for airdrop operations. The complex nonlinear uncertainty of the aircraft-cargo model is factorized into a known matrix and an uncertainty function, and a projection-based adaptive approach is proposed to estimate this function. Using projection in the adaptation law bounds the estimated function and guarantees the robustness of the controller against time-varying external disturbances and uncertainties. The convergence properties and robustness of the control method are proved via Lyapunov theory. Simulations are conducted under the condition that one transport aircraft performs a maximum load airdrop task at a height of 82 ft, using single row single platform mode. The results show good performance and robust operation of the controller, and the airdrop mission performance indexes are satisfied, even in the presence of ±15% uncertainty in the aerodynamic coefficients, ±0.01 rad/s pitch rate disturbance, and 20% actuators faults. Ri Liu, Xiuxia Sun, Wenhan Dong, and Guangzhi Xu Copyright © 2015 Ri Liu et al. All rights reserved. Numerical Simulation of Oil Jet Lubrication for High Speed Gears Wed, 30 Dec 2015 11:46:07 +0000 http://www.hindawi.com/journals/ijae/2015/752457/ The Geared Turbofan technology is one of the most promising engine configurations to significantly reduce the specific fuel consumption. In this architecture, a power epicyclical gearbox is interposed between the fan and the low pressure spool. Thanks to the gearbox, fan and low pressure spool can turn at different speed, leading to higher engine bypass ratio. Therefore the gearbox efficiency becomes a key parameter for such technology. Further improvement of efficiency can be achieved developing a physical understanding of fluid dynamic losses within the transmission system. These losses are mainly related to viscous effects and they are directly connected to the lubrication method. In this work, the oil injection losses have been studied by means of CFD simulations. A numerical study of a single oil jet impinging on a single high speed gear has been carried out using the VOF method. The aim of this analysis is to evaluate the resistant torque due to the oil jet lubrication, correlating the torque data with the oil-gear interaction phases. URANS calculations have been performed using an adaptive meshing approach, as a way of significantly reducing the simulation costs. A global sensitivity analysis of adopted models has been carried out and a numerical setup has been defined. Tommaso Fondelli, Antonio Andreini, Riccardo Da Soghe, Bruno Facchini, and Lorenzo Cipolla Copyright © 2015 Tommaso Fondelli et al. All rights reserved. Optimization of Trajectory Correction Scheme for Guided Mortar Projectiles Tue, 29 Dec 2015 13:01:20 +0000 http://www.hindawi.com/journals/ijae/2015/618458/ Guidance with traditional trajectory correction scheme usually starts from the trajectory apex time to reduce drag penalties early in flight; however, this method cannot get the max trajectory correction capability of canards according to our analysis. This paper presents an optimized trajectory correction scheme by taking different control phases of canards in ballistic ascending segment and ballistic descending segment. Simulation indicates that the optimized trajectory correction can improve the trajectory correction capability greatly. The result of an example trajectory and Monte Carlo simulations with the predictive guidance law and the trajectory tracking guidance law testifies the effectiveness of the optimized trajectory correction scheme. Yongwei Zhang, Min Gao, Suochang Yang, and Dan Fang Copyright © 2015 Yongwei Zhang et al. All rights reserved. Effects of Asymmetries on the Dynamics of Motorized Momentum Exchange Tether and Payloads Injection Precision Tue, 29 Dec 2015 12:39:10 +0000 http://www.hindawi.com/journals/ijae/2015/468482/ This paper presents the error dynamic model of motorized momentum exchange tether (MMET) based on the momentum exchange principle of space tether. The error dynamics are caused by the structural bias of the differences in tethers’ length and the difference in payloads’ mass. After that, the coupling analysis between orbit and attitude is presented. It is shown that, with increasing the differences in tethers’ length and payloads’ mass, the COM deviation of the MMET increases linearly. The numerical simulations of the MMET by considering the structural asymmetries are presented; the results show that the asymmetries have tiny influences on the orbit of the chief satellite by decreasing the apogee, which will change the instantaneous velocity at the apogee and affect the payload injection precision. What is more, the structural asymmetries have effects on the attitude elements (including the pitch angle and yaw angle); however, the effects could be weakened by the external torque. The structural asymmetries and gravity gradient torque have composite effects on the angular velocity of the propulsion tether. Naiming Qi, Yong Yang, Jun Zhao, Qilong Sun, and Wenhui Zhang Copyright © 2015 Naiming Qi et al. All rights reserved. Prediction of Conducted Emissions in Satellite Power Buses Thu, 24 Dec 2015 15:13:56 +0000 http://www.hindawi.com/journals/ijae/2015/601426/ This work reports a modeling methodology for the prediction of conducted emissions (CE) in a wide frequency range (up to 100 MHz), which are generated by dc/dc converters and propagate along the power buses of satellites. In particular, the dc/dc converter seen as a source of CE is represented by a behavioral model, whose parameters can be identified by two unit-level experimental procedures performed in controlled test setups. A simplified multiconductor transmission-line (MTL) model is developed to account for the propagation of CE in shielded bundles of twisted-wire pairs used as power cables. The whole power system is represented by the interconnection of the circuit models of dc/dc converters, cables, and Power Conditioning and Distribution Unit (PCDU). By solving the obtained network, frequency spectra of CE can be predicted. Experimental results are reported to substantiate the accuracy of the proposed unit-level dc/dc converter model and the MTL model of cables. Finally, a system-level test setup composed of three dc/dc converters connected to a PCDU is considered, and predicted CE are compared versus experimental measurements. Giordano Spadacini, Flavia Grassi, Diego Bellan, Sergio A. Pignari, and Filippo Marliani Copyright © 2015 Giordano Spadacini et al. All rights reserved. Low-Thrust Transfer Design of Low-Observable Geostationary Earth Orbit Satellite Tue, 22 Dec 2015 06:42:01 +0000 http://www.hindawi.com/journals/ijae/2015/439815/ With radar and surface-to-air missiles posing an increasing threat to on-orbit spacecraft, low-observable satellites play an important role in low-thrust transfers. This paper presents the design for a low-thrust geostationary earth orbit (GEO) transfer control strategy which takes into consideration the low-observable constraint and discusses Earth shadow and perturbation. A control parameter optimization addresses the orbit transfer problem, and five thrust modes are used. Simulation results show that the method outlined in this paper is simple and feasible and results in reduced transfer time with a small amount of calculation. The method therefore offers a useful reference for low-thrust GEO transfer design. Bing Hua and Zhujun Shao Copyright © 2015 Bing Hua and Zhujun Shao. All rights reserved. Iterative Learning Control of a Nonlinear Aeroelastic System despite Gust Load Sun, 20 Dec 2015 09:56:17 +0000 http://www.hindawi.com/journals/ijae/2015/237804/ The development of a control strategy appropriate for the suppression of aeroelastic vibration of a two-dimensional nonlinear wing section based on iterative learning control (ILC) theory is described. Structural stiffness in pitch degree of freedom is represented by nonlinear polynomials. The uncontrolled aeroelastic model exhibits limit cycle oscillations beyond a critical value of the free-stream velocity. Using a single trailing-edge control surface as the control input, a ILC law under alignment condition is developed to ensure convergence of state tracking error. A novel Barrier Lyapunov Function (BLF) is incorporated in the proposed Barrier Composite Energy Function (BCEF) approach. Numerical simulation results clearly demonstrate the effectiveness of the control strategy toward suppressing aeroelastic vibration in the presence of parameter uncertainties and triangular, sinusoidal, and graded gust loads. Xing-zhi Xu, Ya-kui Gao, and Wei-guo Zhang Copyright © 2015 Xing-zhi Xu et al. All rights reserved. Drag Reduction of a Turbulent Boundary Layer over an Oscillating Wall and Its Variation with Reynolds Number Mon, 14 Dec 2015 09:33:27 +0000 http://www.hindawi.com/journals/ijae/2015/891037/ Spanwise oscillation applied on the wall under a spatially developing turbulent boundary layer flow is investigated using direct numerical simulation. The temporal wall forcing produces a considerable drag reduction over the region where oscillation occurs. Downstream development of drag reduction is investigated from Reynolds number dependency perspective. An alternative to the previously suggested power-law relation between Reynolds number and peak drag reduction values, which is valid for channel flow as well, is proposed. Considerable deviation in the variation of drag reduction with Reynolds number between different previous investigations of channel flow is found. The shift in velocity profile, which has been used in the past for explaining the diminishing drag reduction at higher Reynolds number for riblets, is investigated. A new predictive formula is derived, replacing the ones found in the literature. Furthermore, unlike for the case of riblets, the shift is varying downstream in the case of wall oscillations, which is a manifestation of the fact that the boundary layer has not reached a new equilibrium over the limited downstream distance in the simulations. Taking this into account, the predictive model agrees well with DNS data. On the other hand, the growth of the boundary layer does not influence the drag reduction prediction. Martin Skote, Maneesh Mishra, and Yanhua Wu Copyright © 2015 Martin Skote et al. All rights reserved. Solution of Turbine Blade Cascade Flow Using an Improved Panel Method Tue, 08 Dec 2015 13:20:56 +0000 http://www.hindawi.com/journals/ijae/2015/312430/ An improved panel method has been developed to calculate compressible inviscid flow through a turbine blade row. The method is a combination of the panel method for infinite cascade, a deviation angle model, and a compressibility correction. The resulting solution provides a fast flexible mesh-free calculation for cascade flow. A VKI turbine blade cascade is used to evaluate the method, and the comparison with experiment data is presented. Zong-qi Lei and Guo-zhu Liang Copyright © 2015 Zong-qi Lei and Guo-zhu Liang. All rights reserved. A Review of Wind Tunnel Based Virtual Flight Testing Techniques for Evaluation of Flight Control Systems Tue, 08 Dec 2015 12:11:10 +0000 http://www.hindawi.com/journals/ijae/2015/672423/ Wind tunnel based Virtual Flight Testing (VFT) is a dynamic wind tunnel test for evaluating flight control systems (FCS) proposed in recent decades. It integrates aerodynamics, flight dynamics, and FCS as a whole and is a more realistic and reliable method for FCS evaluation than traditional ground evaluation methods, such as Hardware-in-the-Loop Simulation (HILS). With FCS evaluated by VFT before flight test, the risk of flight test will be further reduced. In this paper, the background, progress, and prospects of VFT are systematically summarized. Specifically, the differences among VFT, traditional dynamic wind tunnel methods, and traditional FCS evaluation methods are introduced in order to address the advantages of evaluating FCS with VFT. Secondly, the progress of VFT is reviewed in detail. Then, the test system and key technologies of VFT for FCS evaluation are analyzed. Lastly, the prospects of VFT for evaluating FCS are described. Min Huang and Zhong-wei Wang Copyright © 2015 Min Huang and Zhong-wei Wang. All rights reserved. Perspectives for Sustainable Aviation Biofuels in Brazil Mon, 07 Dec 2015 14:17:29 +0000 http://www.hindawi.com/journals/ijae/2015/264898/ The aviation industry has set ambitious goals to reduce carbon emissions in coming decades. The strategy involves the use of sustainable biofuels, aiming to achieve benefits from environmental, social, and economic perspectives. In this context, Brazilian conditions are favorable, with a mature agroindustry that regularly produces automotive biofuel largely adopted by Brazilian road vehicles, while air transportation has been growing at an accelerating pace and a modern aircraft industry is in place. This paper presents the main conclusions and recommendations from a broad assessment of the technological, economic, and sustainability challenges and opportunities associated with the development of drop-in aviation biofuels in Brazil. It was written by a research team that prepared the initial reports and conducted eight workshops with the active participation of more than 30 stakeholders encompassing the private sector, government institutions, NGOs, and academia. The main outcome was a set of guidelines for establishing a new biofuels industry, including recommendations for (a) filling the identified research and development knowledge gaps in the production of sustainable feedstock; (b) overcoming the barriers in conversion technology, including scaling-up issues; (c) promoting greater involvement and interaction between private and government stakeholders; and (d) creating a national strategy to promote the development of aviation biofuels. Luís A. B. Cortez, Francisco E. B. Nigro, Luiz A. H. Nogueira, André M. Nassar, Heitor Cantarella, Márcia A. F. D. Moraes, Rodrigo L. V. Leal, Telma T. Franco, Ulf F. Schuchardt, and Ricardo Baldassin Junior Copyright © 2015 Luís A. B. Cortez et al. All rights reserved. Cone Algorithm of Spinning Vehicles under Dynamic Coning Environment Thu, 03 Dec 2015 11:02:24 +0000 http://www.hindawi.com/journals/ijae/2015/904913/ Due to the fact that attitude error of vehicles has an intense trend of divergence when vehicles undergo worsening coning environment, in this paper, the model of dynamic coning environment is derived firstly. Then, through investigation of the effect on Euler attitude algorithm for the equivalency of traditional attitude algorithm, it is found that attitude error is actually the roll angle error including drifting error and oscillating error, which is induced directly by dynamic coning environment and further affects the pitch angle and yaw angle through transferring. Based on definition of the cone frame and cone attitude, a cone algorithm is proposed by rotation relationship to calculate cone attitude, and the relationship between cone attitude and Euler attitude of spinning vehicle is established. Through numerical simulations with different conditions of dynamic coning environment, it is shown that the induced error of Euler attitude fluctuates by the variation of precession and nutation, especially by that of nutation, and the oscillating frequency of roll angle error is twice that of pitch angle error and yaw angle error. In addition, the rotation angle is more competent to describe the spinning process of vehicles under coning environment than Euler angle gamma, and the real pitch angle and yaw angle are calculated finally. Shuang-biao Zhang, Xing-cheng Li, and Zhong Su Copyright © 2015 Shuang-biao Zhang et al. All rights reserved. Modelling of Solar Radiation Pressure Effects: Parameter Analysis for the MICROSCOPE Mission Mon, 30 Nov 2015 06:14:02 +0000 http://www.hindawi.com/journals/ijae/2015/928206/ Modern scientific space missions pose high requirements on the accuracy of the prediction and the analysis of satellite motion. On the one hand, accurate orbit propagation models are needed for the design and the preparation of a mission. On the other hand, these models are needed for the mission data analysis itself, thus allowing for the identification of unexpected disturbances, couplings, and noises which may affect the scientific signals. We present a numerical approach for Solar Radiation Pressure modelling, which is one of the main contributors for nongravitational disturbances for Earth orbiting satellites. The here introduced modelling approach allows for the inclusion of detailed spacecraft geometries, optical surface properties, and the variation of these optical surface properties (material degradation) during the mission lifetime. By using the geometry definition, surface property definitions, and mission definition of the French MICROSCOPE mission we highlight the benefit of an accurate Solar Radiation Pressure modelling versus conventional methods such as the Cannonball model or a Wing-Box approach. Our analysis shows that the implementation of a detailed satellite geometry and the consideration of changing surface properties allow for the detection of systematics which are not detectable by conventional models. Meike List, Stefanie Bremer, Benny Rievers, and Hanns Selig Copyright © 2015 Meike List et al. All rights reserved. Heat Flux at the Surface of Metal Foil Heater under Evaporating Sessile Droplets Thu, 26 Nov 2015 14:02:33 +0000 http://www.hindawi.com/journals/ijae/2015/391036/ Evaporating water drops on a horizontal heated substrate were investigated experimentally. The heater was made of a constantan foil with the thickness of 25 μm and size of 42 × 35 mm2. The temperature of the bottom foil surface was measured by the infrared (IR) camera. To determine the heat flux density during evaporation of liquid near the contact line, the Cauchy problem for the heat equation was solved using the temperature data. The maximum heat flux density is obtained in the contact line region and exceeds the average heat flux density from the entire foil surface by the factor of 5–7. The average heat flux density in the region wetted by the drop exceeds the average heat flux density from the entire foil surface by the factor of 3–5. This fact is explained by the heat influx from the foil periphery to the drop due to the relatively high heat conductivity coefficient of the foil material and high evaporation rate in the contact line region. Heat flux density profiles for pairs of sessile droplets are also investigated. Igor Marchuk, Andrey Karchevsky, Anton Surtaev, and Oleg Kabov Copyright © 2015 Igor Marchuk et al. All rights reserved. An Approximate Optimal Maximum Range Guidance Scheme for Subsonic Unpowered Gliding Vehicles Mon, 23 Nov 2015 16:06:10 +0000 http://www.hindawi.com/journals/ijae/2015/389751/ This study investigates the maximum gliding range problems of subsonic unpowered gliding vehicles and proposes an approximate optimal maximum range guidance scheme. First, the gliding flight path angle corresponding to constant dynamic pressure is derived. A lift-to-drag ratio inversely proportional to the dynamic pressure is then proven. On this basis, the calculation method of an optimal dynamic pressure (ODP) profile with a maximum throughout the flight is presented. A guidance scheme for tracking the ODP profile, which uses the flight path angle as control variable, is then designed. The maximum ranges of the unpowered gliding vehicle obtained by the proposed guidance scheme and pseudospectral method are compared. Results show that the guidance scheme provides an accurate approximation of the optimal results, and the errors are less than 2%. The proposed guidance scheme is easy to implement and is not influenced by wind compared with numerical schemes. Dao-Chi Zhang, Qun-Li Xia, Qiu-Qiu Wen, and Guan-qun Zhou Copyright © 2015 Dao-Chi Zhang et al. All rights reserved. Dynamics of the Space Tug System with a Short Tether Thu, 19 Nov 2015 16:27:29 +0000 http://www.hindawi.com/journals/ijae/2015/740253/ The dynamics of the space tug system with a short tether similar to the ROGER system during deorbiting is presented. The kinematical characteristic of this system is significantly different from the traditional tethered system as the tether is tensional and tensionless alternately during the deorbiting process. The dynamics obtained based on the methods for the traditional tethered system is not suitable for the space tug system. Therefore, a novel method for deriving dynamics for the deorbiting system similar to the ROGER system is proposed by adopting the orbital coordinates of the two spacecraft and the Euler angles of ROGER spacecraft as the generalized coordinates instead of in- and out-plane librations and the length of the tether and so forth. Then, the librations of the system are equivalently obtained using the orbital positions of the two spacecraft. At last, the geostationary orbit (GEO) and the orbit whose apogee is 300 km above GEO are chosen as the initial and target orbits, respectively, to perform the numerical simulations. The simulation results indicate that the dynamics can describe the characteristic of the tether-net system conveniently and accurately, and the deorbiting results are deeply affected by the initial conditions and parameters. Jiafu Liu, Naigang Cui, Fan Shen, and Siyuan Rong Copyright © 2015 Jiafu Liu et al. All rights reserved. Control System Design for a Ducted-Fan Unmanned Aerial Vehicle Using Linear Quadratic Tracker Wed, 18 Nov 2015 07:55:57 +0000 http://www.hindawi.com/journals/ijae/2015/364926/ Tracking control system based on linear quadratic (LQ) tracker is designed for a ducted-fan unmanned aerial vehicle (UAV) under full flight envelope including hover, transition, and cruise modes. To design the LQ tracker, a system matrix is augmented with a tracking error term. Then the control input can be calculated to solve a single Riccati equation, but the steady-state errors might still remain in this control system. In order to reduce the steady-state errors, a linear quadratic tracker with integrator (LQTI) is designed to add an integral term of tracking state in the state vector. Then the performance of the proposed controller is verified through waypoint navigation simulation under wind disturbance. Junho Jeong, Seungkeun Kim, and Jinyoung Suk Copyright © 2015 Junho Jeong et al. All rights reserved. Adaptive Integrated Guidance and Fault Tolerant Control Using Backstepping and Sliding Mode Tue, 17 Nov 2015 08:46:12 +0000 http://www.hindawi.com/journals/ijae/2015/253478/ A new method of integrated guidance and control for homing missiles with actuator fault against manoeuvring targets is proposed. Model of the integrated guidance and control system in the pitch plane with actuator fault and some uncertainty is developed. A control law using combination of adaptive backstepping and sliding mode approaches is designed to achieve interception in the presence of bounded uncertainties and actuator fault. Simulation results show that new approach has better performance than adaptive backstepping and has good performance in the presence of actuator fault. Mohsen Fathi Jegarkandi, Asghar Ashrafifar, and Reza Mohsenipour Copyright © 2015 Mohsen Fathi Jegarkandi et al. All rights reserved. A Reconstruction Algorithm for Blade Surface Based on Less Measured Points Thu, 12 Nov 2015 08:00:06 +0000 http://www.hindawi.com/journals/ijae/2015/431824/ A reconstruction algorithm for blade surface from less measured points of section curves is given based on B-spline surface interpolation. The less measured points are divided into different segments by the key geometric points and throat points which are defined according to design concepts. The segmentations are performed by different fitting algorithms with consideration of curvature continuity as their boundary condition to avoid flow disturbance. Finally, a high-quality reconstruction surface model is obtained by using the B-spline curve meshes constructed by paired points. The advantage of this algorithm is the simplicity and effectivity reconstruction of blade surface to ensure the aerodynamic performance. Moreover, the obtained paired points can be regarded as measured points to measure and reconstruct the blade surface directly. Experimental results show that the reconstruction blade surface is suitable for precisely representing blade, evaluating machining accuracy, and analyzing machining allowance. Jia Liu, Ji Zhao, Xu Yang, Jiming Liu, Xingtian Qu, and Xin Wang Copyright © 2015 Jia Liu et al. All rights reserved. Optimal Configuration of Virtual Links for Avionics Network Systems Sun, 08 Nov 2015 14:02:17 +0000 http://www.hindawi.com/journals/ijae/2015/329820/ As the bandwidth and scalability constraints become important design concerns in airborne networks, a new technology, called Avionics Full Duplex Switched Ethernet (AFDX), has been introduced and standardized as a part 7 in ARNIC 664. However, since previous research interests for AFDX are mainly bounded for analyzing the response time where flows information is given, configuration problem for both Maximum Transmission Unit (MTU) and Bandwidth Allocation Gap (BAG) over virtual links in AFDX networks has not been addressed yet even though it has great impact on required bandwidth. Thus, in this paper, we present two configuration approaches to set MTU and BAG values on virtual links efficiently while meeting the requirement of AFDX. The first is to search available feasible configuration (MTU, BAG) pairs to satisfy application requirements as well as AFDX switch constraints, and the second is to get an optimal pair to minimize required bandwidth through well-known branch-and-bound algorithm. We analyze the complexity of the proposed algorithm and then evaluate the proposed algorithm by simulation. Finally, we prove that the proposed schemes are superior to general approach in the aspects of speed and required bandwidth in AFDX networks. Dongha An, Kyong Hoon Kim, and Ki-Il Kim Copyright © 2015 Dongha An et al. All rights reserved. Guidance Law Design for a Class of Dual-Spin Mortars Wed, 28 Oct 2015 08:50:15 +0000 http://www.hindawi.com/journals/ijae/2015/952076/ To minimize the cost and maximize the ease of use, a class of dual-spin mortars is designed which only rely on GPS receiver and geomagnetic measurements. However, there are some problems to be solved when the range is small, such as low correction authority and trajectory bending. Guidance law design for this mortar is detailed. Different guidance laws were designed for the ascending and descending segments, respectively. By taking variable parameter guidance law in the vertical plane and using compensation in the lateral plane, the problems mentioned above were resolved. Roll angle resolving algorithms with geomagnetic measurements were demonstrated and the experiment results proved to be effective. In order to verify the effectiveness, Seven-Degrees-of-Freedom (7-DOF) rigid ballistic model were established and hardware in the loop simulation was introduced. After the transform function of the actuator was obtained, the control model of the shell was improved. The results of the Monte Carlo simulation demonstrate that the guidance law is suitable and the mortar can be effectively controlled. Qing-wei Guo, Wei-dong Song, Yi Wang, and Zhi-cai Lu Copyright © 2015 Qing-wei Guo et al. All rights reserved. A Sliding Mode LCO Regulation Strategy for Dual-Parallel Underactuated UAV Systems Using Synthetic Jet Actuators Tue, 27 Oct 2015 08:36:41 +0000 http://www.hindawi.com/journals/ijae/2015/795348/ A sliding mode control- (SMC-) based limit cycle oscillation (LCO) regulation method is presented, which achieves asymptotic LCO suppression for UAVs using synthetic jet actuators (SJAs). With a focus on applications involving small UAVs with limited onboard computational resources, the controller is designed with a simplistic structure, requiring no adaptive laws, function approximators, or complex calculations in the control loop. The control law is rigorously proven to achieve asymptotic regulation of both pitching and plunging displacements for a class of systems in a dual-parallel underactuated form, where a single scalar control signal simultaneously affects two states. Since dual-parallel underactuated systems cannot be expressed in a strict feedback or cascade form, standard backstepping-based control techniques cannot be applied. This difficulty is mitigated through careful algebraic manipulation in the regulation error system development, along with innovative design of the sliding surface. A detailed model of the UAV LCO dynamics is utilized, and a rigorous analysis is provided to prove asymptotic regulation of the pitching and plunging displacements. Numerical simulation results are provided to demonstrate the performance of the control law. N. Ramos-Pedroza, W. MacKunis, and M. Reyhanoglu Copyright © 2015 N. Ramos-Pedroza et al. All rights reserved. Equilibrium Positions for UAV Flight by Dynamic Soaring Thu, 22 Oct 2015 13:01:20 +0000 http://www.hindawi.com/journals/ijae/2015/141906/ Dynamic soaring is a special flying technique designed to allow UAVs (unmanned aerial vehicles) to extract energy from wind gradient field and enable UAVs to increase the endurance. In order to figure out the energy-extraction mechanisms in dynamic soaring, a noninertial wind relative reference frame of aircraft is built. In the noninertial frame, there is an inertial force which is created by gradient wind field. When the wind gradient and the components of airspeed are positive, inertial force makes positive work to the aircraft. In the meantime, an equilibrium position theory of dynamic soaring is proposed. At the equilibrium positions, the increased potential energy is greater than the wasted kinetic energy when the aircraft is flying upwards. The mechanical energy is increased in this way, and the aircraft can store energy for flight. According to the extreme value theory, contour line figures of the maximum function and the component of airspeed are obtained to find out the aircraft’s lifting balance allowance in dynamic soaring. Moreover, this equilibrium position theory can also help to conduct an aircraft to acquire energy from the environment constantly. Bingjie Zhu, Zhongxi Hou, Shangqiu Shan, and Xinzhu Wang Copyright © 2015 Bingjie Zhu et al. All rights reserved. Frequencies of Transverse and Longitudinal Oscillations in Supersonic Cavity Flows Tue, 20 Oct 2015 12:13:00 +0000 http://www.hindawi.com/journals/ijae/2015/751029/ A supersonic flow over a rectangular cavity is known to oscillate at certain predominant frequencies. The present study focuses on the effect of the cavity length-to-depth () ratio on the frequency for a free-stream Mach number of 1.7. The pressure oscillations are measured by changing the ratio from 0.5 to 3.0, and the power spectral density is calculated from the temporal pressure signals for each ratio. The results demonstrate that the spectral peaks for an ratio of less than ~1 and greater than ~2 are accounted for by the feedback mechanisms of the transverse and longitudinal oscillations, respectively. The results also demonstrate that the spectral peaks in the transition (1 <~ <~ 2) are accounted for by either of the two feedback mechanisms of transverse and longitudinal oscillations; that is, the flows under the transition regime oscillate both transversely and longitudinally. Taro Handa, Kazuya Tanigawa, Yusuke Kihara, Hiroaki Miyachi, and Hatsuki Kakuno Copyright © 2015 Taro Handa et al. All rights reserved. Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box Mon, 19 Oct 2015 10:55:52 +0000 http://www.hindawi.com/journals/ijae/2015/473926/ Based on the wing-box structure, a model was established to analyze the strength of the scale model for the composite wing. Firstly, different failure criteria were set to determine damage onset of the components. The continuum damage variables were adopted in the stiffness degradation rule. Secondly, the interface elements were placed along the interface between the beam flange and the skin to investigate the effects of bonding strength on the ultimate load-carrying capacity of the wing-box. The failure modes of the wing-box structure were studied by using the nonlinear finite element method. The effect of flange’s width on the strength of wing-box was discussed based on the prediction method. The results indicated that the ultimate load-carrying capacity varied distinctly with the change of flange’s width. However, the bonding strength had limited effect on the model strength as the flange’s width increases to the critical value. The research methods and results of the study can serve as reference for the strength analysis on the scale model of composite wing as well as the determination of principles adopted in the design of the scale model for wing spar. Shiyong Sun, Rui Yang, Zibin Yan, and Wei Qian Copyright © 2015 Shiyong Sun et al. All rights reserved. Asymmetric Barrier Lyapunov Function-Based Wheel Slip Control for Antilock Braking System Sun, 18 Oct 2015 13:08:43 +0000 http://www.hindawi.com/journals/ijae/2015/917807/ As an important device of the aircraft landing system, the antilock braking system (ABS) has a function to avoid aircraft wheels self-locking. To deal with the strong nonlinear characteristics, complex nonlinear control schemes are applied in ABS. However, none of existing control schemes focus on the braking operating status, which directly reflects wheels self-locking degree. In this paper, the braking operating status region is divided into three regions: the healthy region, the light slip region, and the deep slip region. An ABLF-based wheel slip controller is proposed for ABS to constrain the braking system operating status in the healthy region and the light slip region. Therefore the ABS will be prevented from operating in the deep slip region. Under the proposed control scheme, self-locking is avoided completely and zero steady state error tracking of the wheel optimal slip ratio is implemented. The Hardware-In-Loop (HIL) experiments have validated the effectiveness of the proposed controller. Xiaolei Chen, Zhiyong Dai, Hui Lin, Yanan Qiu, and Xiaogeng Liang Copyright © 2015 Xiaolei Chen et al. All rights reserved. Decentralized State Estimation Algorithm of Centralized Equivalent Precision for Formation Flying Spacecrafts Based on Junction Tree Sun, 18 Oct 2015 13:07:14 +0000 http://www.hindawi.com/journals/ijae/2015/714302/ As centralized state estimation algorithms for formation flying spacecraft would suffer from high computational burdens when the scale of the formation increases, it is necessary to develop decentralized algorithms. To the state of the art, most decentralized algorithms for formation flying are derived from centralized EKF by simplification and decoupling, rendering suboptimal estimations. In this paper, typical decentralized state estimation algorithms are reviewed, and a new scheme for decentralized algorithms is proposed. In the new solution, the system is modeled as a dynamic Bayesian network (DBN). A probabilistic graphical method named junction tree (JT) is used to analyze the hidden distributed structure of the DBNs. Inference on JT is a decentralized form of centralized Bayesian estimation (BE), which is a modularized three-step procedure of receiving messages, collecting evidences, and generating messages. As KF is a special case of BE, the new solution based on JT is equivalent in precision to centralized KF in theory. A cooperative navigation example of a three-satellite formation is used to test the decentralized algorithms. Simulation results indicate that JT has the best precision among all current decentralized algorithms. Mengyuan Dai, Hua Mu, Meiping Wu, and Zhiwen Xian Copyright © 2015 Mengyuan Dai et al. All rights reserved.