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| 1 | Study on effectiveness evaluation of weapon systems based on grey relational analysis and TOPSIS显示文摘To evaluate the effectiveness of weapon systems, the advantages and disadvantages of grey relational analysis and TOPSIS for multiattribute decision-making is pointed out, and an effectiveness evaluation model of weapon systems by combining grey relational analysis and TOPSIS is proposed. The model aggregates the grey relational grade and the distance to a new integrated closeness and reflects not only the trend but also the situation of the alternative. The example illuminates that the model is effective for the effectiveness evaluation of weapon systems. | Gu Hui Song Bifeng | 2009 | Journal of Systems Engineering and Electronics2009，20，1： | 53 |
| 2 | Research of low boom and low drag supersonic aircraft design显示文摘Sonic boom reduction will be an issue of utmost importance in future supersonic transport, due to strong regulations on acoustic nuisance. The paper describes a new multi-objective optimization method for supersonic aircraft design. The method is developed by coupling Seebass–George–Darden(SGD) inverse design method and multi-objective genetic algorithm.Based on the method, different codes are developed. Using a computational architecture, a conceptual supersonic aircraft design environment(CSADE) is constructed. The architecture of CSADE includes inner optimization level and out optimization level. The low boom configuration is generated in inner optimization level by matching the target equivalent area distribution and actual equivalent area distribution. And low boom/low drag configuration is generated in outer optimization level by using NSGA-II multi-objective genetic algorithm to optimize the control parameters of SGD method and aircraft shape. Two objective functions, low sonic boom and low wave drag, are considered in CSADE. Physically reasonable Pareto solutions are obtained from the present optimization. Some supersonic aircraft configurations are selected from Pareto front and the optimization results indicate that the swept forward wing configuration has benefits in both sonic boom reduction and wave drag reduction. The results are validated by using computational fluid dynamics(CFD) analysis. | Feng Xiaoqiang Li Zhanke Song Bifeng | 2014 | Chinese Journal of Aeronautics2014，27，3： | 9 |
| 3 | Aerodynamic performance enhancement forflapping airfoils by co-flow jet显示文摘Introducing active flow control into the design of flapping wing is an effective way to enhance its aerodynamic performance.In this paper,a novel active flow control technology called Co-Flow Jet(CFJ)is applied to flapping airfoils.The effect of CFJ on aerodynamic performance of flapping airfoils at low Reynolds number is numerically investigated using Unsteady Reynolds Averaged Navier-Stokes(URANS)simulation with Spalart-Allmaras(SA)turbulence model.Numerical methods are validated by a NACA6415-based CFJ airfoil case and a S809 pitching airfoil case.Then NACA6415 baseline airfoil and NACA6415-based CFJ airfoil with jet-off and jet-on are simulated in flapping motion,with Reynolds number 70,000 and reduced frequency 0.2.As a result,CFJ airfoils with jet-on generally have better lift and thrust characteristics than baseline airfoils and jet-off airfoil when Cμgreater than 0.04,which results from the CFJ effect of reducing flow separation by injecting high-energy fluid into boundary layer.Besides,typical kinematic and geometric parameters,including the reduced frequency and the positions of the suction and injection slot,are systematically studied to figure out their influence on aerodynamic performance of the CFJ airfoil.And a variable Cμjet control strategy is proposed to further improve effective propulsive efficiency.Compared with using constant Cμ,an increase of effective propulsive efficiency by22.6%has been achieved by using prescribed variable CμNACA6415-based CFJ airfoil at frequency 0.2.This study may provide some guidance to performance enhancement for Flapping wing Micro Air Vehicles(FMAV). | Tao WU Bifeng SONG Wenping SONG Wenqing YANG Zhonghua HAN | 2020 | Chinese Journal of Aeronautics2020，33，10： | 7 |
| 4 | The effects of span-wise and chord-wise flexibility on the aerodynamic performance of micro flapping-wing显示文摘The flexibility of flapping-wing strongly affects the aerodynamic performance of Flapping-wing Micro Air Vehicle (FMAV),and the deformations in span-wise and chord-wise directions are coupled together in flight.In this study,the flexible deformation is formulated in span-wise and chord-wise separately in order to analyze its effects on aerodynamic behavior.The preconditioned Navier-Stokes equations based on chimera grid are used in the computational fluid dynamics method to study the aerodynamic effects caused by flexible deformation,and the simulation results are compared with experimental test to illustrate the capability of above method.Based on our results,it is clearly showed that the span-wise flexible deformation should be limited in a small range to achieve higher aerodynamic performance and the chord-wise deformation could enhance the aerodynamic performance.The results also suggest that FMAV designers should design the flapping-wing with high stiffness leading edge to limit the span-wise deformation,and more flexible chord ribs to keep chord-wise deformation in suitable range. | YANG WenQing SONG BiFeng SONG WenPing WANG LiGuang | 2012 | Chinese Science Bulletin2012，57，22： | 6 |
| 5 | Far-field sonic boom prediction considering atmospheric turbulence effects: An improved approach显示文摘Accurate prediction of sonic boom is one of key challenges for the design of a low-boom supersonic aircraft. For most of available far-field prediction methods, the effect of atmospheric turbulence appearing in the planetary boundary layer cannot be considered, which results in remarkable inaccuracy of predicting ground-level sonic boom waveform. Although some efforts have been made to overcome the shortcoming, the turbulence effects are not yet well described so far. This article proposes an improved method by extending the two-dimensional Heterogeneous One-Way Approximation for the Resolution of Diffraction(HOWARD) equation to account for the axial and transverse convections of wind fluctuation as well as the effect of temperature fluctuation. The proposed method is validated by comparing the predictions with the flight-test data of JAXA D-SEND#1 LBM, which shows that the result of the proposed method is in better agreement with the flight-test data than that of the method without considering atmospheric turbulence effects.Then, distortion mechanism of sonic boom waveforms caused by atmospheric turbulence is analyzed by using the proposed method. It is indicated that the effect of turbulent convection makes uniform sonic-boom wavefronts irregular, which creates the condition of diffraction effect to perturb waveforms. Finally, the proposed method is applied to investigate the behavior of two types of waveforms given by the sonic boom minimization theory. Results show that a far-field waveform with a weaker initial shock is more beneficial for low-boom design of a supersonic aircraft. | Jianling QIAO Zhonghua HAN Liwen ZHANG Wenping SONG Bifeng SONG | 2022 | Chinese Journal of Aeronautics2022，35，9： | 4 |
| 6 | Landing route planning method for micro drones based on hybrid optimization algorithm显示文摘Aiming at the obstacle avoidance trajectory planning problem in the landing process of the micro drone,this paper proposes a swarm optimization algorithm that combines the dragonfly optimization method and the differential evolution method.The orthogonal learning mechanism is adopted to realize the adaptive switch between the two algorithms.In the process of landing route planning,the planning plane is first obtained by making the gliding plane tangent to the obstacle.In the planning plane,the projection of obstacle is transformed into multiple unreachable line segments.By designing an optimization model,the 3D landing route planning problem is transformed into a 2D obstacle avoidance route optimization problem.Taking the shortest route as the optimization objective,the penalty factor is introduced into the cost function to avoid the intersection of the landing route and obstacle.During the optimization process,through the orthogonal learning of the intermediate iterative results,the hybrid algorithm can adaptively select the next iterative algorithm,so it can give full play to the respective advantages of the two algorithms.The optimization results show that,compared with the single optimization algorithm,the hybrid optimization algorithm proposed in this paper can better solve the problem of landing route planning for micro-small UAVs. | Liang Shaoran Song Bifeng Xue Dong | 2021 | Biomimetic Intelligence & Robotics2021，1，1： | 3 |
| 7 | Improved method for subsystems performance trade-off in system-of-systems oriented design of UAV swarms显示文摘For the rapidly developing unmanned aerial vehicle(UAV)swarm,the system-of-systems(SoS)oriented design is a prospective conceptual design methodology due to the competence for complex mission requirements and subsystems interactions.In the SoS oriented design,the subsystems performance trade-off is the basis of design decisions.In the trade-off for surveillance missions,most previous works do not consider track reporting and mainly focus on the design of platforms.An improved method for the subsystems performance trade-off in the SoS oriented UAV swarm design is proposed.Within an improved design framework with subsystems disaggregation,this method is characterized by treating platforms,sensors,and communications as equally important subsystems,integrating operational strategies into the trade-off,and enabling the trade-off for track reporting.Those advantages are achieved by a behavior-based modular model structure for agent-based operational modeling and simulation.In addition,a method of analyzing the bounds of the communication range is also presented.Simulation experiments are conducted by using precision-based simulation replication rules and surrogate modeling methods.The results demonstrate the effectiveness of the proposed method,and show that the configuration of area partitioning changes the trade space of subsystems performances,indicating the necessity of integrating operational strategies into the conceptual design. | ZHANG Ruiwen SONG Bifeng PEI Yang YUN Qijia | 2019 | Journal of Systems Engineering and Electronics2019，30，4： | 3 |
| 8 | Aerodynamic performance of owl-like airfoil undergoing bio-inspired flapping kinematics显示文摘Natural flyers have extraordinary flight skills and their prominent aerodynamic performance has attracted a lot of attention.However,the aerodynamic mechanism of birds’flapping wing kinematics still lacks in-depth understanding.In this paper,the aerodynamic performance of owl-like airfoil undergoing bio-inspired flapping kinematics extracted from a free-flying owl wing has been numerically investigated.The overset mesh technique is used to deal with the large range movements of flapping airfoils.The bio-inspired kinematics consist of plunging and pitching movement.A pure sinusoidal motion and a defined motion composed of plunging of sinusoidal motion and pitching of the bio-inspired kinematics are selected for comparison.The other two NACA airfoils are also selected to figure out the advantages of the owl-like airfoil.It is found that the cambered owl-like airfoil can enhance lift during the downstroke.The bio-inspired kinematics have an obvious advantage in lift generation with a presence of higher peak lift and positive lift over a wider proportion of the flapping cycle.Meanwhile,the bio-inspired motion is more economical for a lower power consumption compared with the sinusoidal motion.The sinusoidal flapping motion is better for thrust generation for a higher peak thrust value in both upstroke and downstroke,while the bio-inspired kinematics mainly generate thrust during the downstroke but produce more drag during the upstroke.The defined motion has similar lift performance with the bio-inspired kinematics,while it consumes more energy and generates less thrust.The unsteady flow field around airfoils is also analyzed to explain the corresponding phenomenon.The research in this paper is helpful to understand the flight mechanism of birds and to design a micro air vehicle with higher performance. | Xinyu LANG Bifeng SONG Wenqing YANG Wenping SONG | 2021 | Chinese Journal of Aeronautics2021，34，5： | 2 |
| 9 | Ultrafast dynamics of o-fluorophenol studied with femtosecond time-resolved photoelectron and photoion spectroscopy显示文摘The ultrafast dynamics of o-fluorophenol via the excited states has been studied by femtosecond time-resolved photoelectron imaging. The photoion and photoelectron spectra taken with a time delay between 267 nm pump laser and 800 nm probe laser provide a longer-lived S1 electronic state of about ns timescale. In comparison,the spectra obtained by exciting the S2 state with femtosecond laser pulses at 400 nm and ionizing with pulses at 800 nm suggest that the S2 state has an ultrashort lifetime about 102 fs and reflects the internal conversion dynamics of the S2 state to the S1 state. | ZHENG QiuSha 1,2 ,QIN ChaoChao 1,2 ,LONG JinYou 1,2 ,TANG BiFeng 3 ,ZHANG Song 1,2* & ZHANG Bing 1,2 1 State Key Laboratory of Magnetic Resonance and Atomic and Molecular Physics,Wuhan Institute of Physics and Mathematics,Chinese Academy of Sciences,Wuhan 430071,China 2 Graduate University of the Chinese Academy of Sciences,Beijing 100049,China 3 Department of Physics,Xiaogan University,Xiaogan 432000,China | 2010 | Science China(Physics,Mechanics & Astronomy)2010，53，6： | 2 |
| 10 | Two general methods for calculating the aircraft equivalent singly vulnerable area 显示文摘 | PEI Yang SONG Bifeng | 2006 | Journal of Aircraft2006，43，5： | 1 |
| 11 | Aircraft vulnerable area decomposition method in the overlapping region of components显示文摘 | PEI Yang SONG Bifeng | 2006 | Journal of Aircraft2006，43，4： | 1 |
| 12 | Exploring Optimum Power Unit of Propulsion System for High Altitude Airship 显示文摘 | Chen Shengqi Song Bifeng Wang Haifeng | 2015 | Journal of Aerospace Engineering2015，229，2： | 1 |
| 13 | Aircraft vulnerable area decomposition method in the overlapping region of components显示文摘 | Pei Yang Song Bifeng | 2006 | Journal of Aircraft2006，43，4： | 1 |
| 14 | Modeling and flapping vibration suppression of a novel tailless flapping wing micro air vehicle显示文摘This paper establishes and analyzes a high-fidelity nonlinear time-periodic dynamic model and the corresponding state observer for flapping vibration suppression of a novel tailless Flapping Wing Micro Air Vehicle(FWMAV),named NPU-Tinybird.Firstly,a complete modeling of NPU-Tinybird is determined,including the aerodynamic model based on the quasi-steady method,the kinematic and dynamic model about the mechanism of flapping and attitude control,combined with the single rigid body dynamic model.Based on this,a linearized longitudinal pitch dynamic cycle-averaged model is obtained and analyzed through the methods of neural network fitting and system identification,preparing for the design of flapping vibration suppression observer.Flapping vibration is an inherent property of the tailless FWMAV,which arises from the influence of time-periodic aerodynamic forces and moments.It can be captured by attitude and position sensors on the plane,which impairs the flight performance and efficiency of flight controller and actuators.To deal with this problem,a novel state observer for flapping vibration suppression is designed.A robust optimal controller based on the linear quadratic theory is also designed to stabilize the closed-loop system.Simulation results are given to verify the performance of the observer,including the closed loop responses combined with robust optimal controller,the comparison of different parameters of observer and the comparison with several classic methods,such as Kalman filter,H-infinity filter and low-pass filter,which prove that the novel observer owns a fairly good suppression effect on flapping vibration and benefits for the improvement of flight performance and control efficiency. | Siqi WANG Bifeng SONG Ang CHEN Qiang FU Jin CUI | 2022 | Chinese Journal of Aeronautics2022，35，3： | 1 |
| 15 | Research on fault pat- tern recognition for aircraft fuel system with its performance sim- ulation 显示文摘 | Wang Haifeng Song Bifeng Wan Fangyi | 2011 | IEEE Computer Society2011，，： | 1 |
| 16 | A Direct Simulation Method for Calculating Multiple-hit Vulnerability of Aircraft with Overlapping Components显示文摘当部件之间发生重叠时,飞机多击中易损性分析通常分两步来进行。第一步是通过'易损面积分解法'来确定飞机的独立存在状态,第二步利用以Markov Chain为代表的精确方法(或采用可以避免组合爆炸问题的Monte Carlo法)计算飞机累积杀伤概率。为了避免复杂的'易损面积分解',本文提出计算飞机多击中易损性的直接模拟法。该方法中,利用随机方法产生多击中的打击点,采用Bernoulli试验来确定每条射击线打击下的部件杀伤或非杀伤状态,结合杀伤树来检验一次模拟中飞机的存在状态。当模拟次数足够多时,飞机多击中易损性便可通过统计方法获得。分析表明,所提出的直接模拟法:与Markov Chain法相比,可以达到很高的精度;可以同样解决组合爆炸问题;可以避免复杂的'易损面积分解',直接计算飞机多击中易损性。此外,本文的另一重要发现是,工程简化算法(二项式简化法或泊松简化法)在计算精度方面比较差,需要谨慎使用。 | Pei Yang Song Bifeng Han Qing Ou Baiyu | 2009 | Chinese Journal of Aeronautics2009，22，6： | 1 |
| 17 | A numerical integration method in affinespace and a method with high accuracy for computingstructural system reliability显示文摘 | SONG Bifeng | 1992 | Computer&Structures1992，42，2： | 1 |
| 18 | Internal Component Layout Optimization Method for Aircraft Safety Design显示文摘 | Pei Yang Song Bifeng | | 0，，： | 1 |
| 19 | Solving the Combinatorial Explosion Problem when Calculating the Multiple Hit Vulnerability of Aircraft 显示文摘 | PEI Yang SONG Bifeng | 2006 | Journal of Aircraft (S0021-8669)2006，43，4： | 1 |
| 20 | Shot Line Geometric Description Method for Aircraft Vulnerability Calculation显示文摘本文提出了一种飞机易损性计算中的射击线几何描述方法。首先,将给定打击方向上的飞机暴露面积划分为三个子区域:非易损区域、非重叠易损区域和重叠易损区域。然后,把飞机的独立存在状态划分为三类:杀伤状态、中间状态和非杀伤状态,利用射击线扫描法,对以上三个子区域中的飞机存在状态参数进行分析。最后,该方法提供两类射击线几何描述数据:(1)每个子区域内部件的易损面积和暴露面积,这些数据主要用于计算部件的单击中易损性;(2)飞机的独立存在状态及各个状态对应的面积,这些数据主要用于计算飞机的单/多击中易损性。算例分析表明,所提出的方法通过跟踪射击线运动路径,可以提供飞机及部件被威胁命中部分的面积参数,从而使易损性计算更具有真实性。同时,该方法解决了目前方法在考虑部件重叠时的通用性问题,所提供的几何描述数据形式简单,易于分析人员使用。 | Pei Yang Song Bifeng Han Qing | 2009 | Chinese Journal of Aeronautics2009，22，5： | 1 |
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