基于多轨迹预测的飞机近地防撞技术研究

针对飞机近地飞行安全问题,提出了一种基于多轨迹预测的飞机近地防撞技术实现方法。建立了飞机近地防撞功能触发的架构逻辑和评价标准,设计了一套六自由度多轨迹实时预测的轨迹预估算法和防撞控制算法,将近地防撞模型与飞机模型结合起来,在数字仿真环境中验证整套算法的合理性。结果表明,基于多轨迹预测的飞机近地防撞算法实时性好,飞行轨迹预测准确性高,逻辑架构鲁棒性强,易于成果转化,具有很高的工程应用价值。     

An improved prediction model for corner stall in axial compressors with dihedral effect

Corner stall predictions are important and difficult in axial compressors. However, all of the prediction models have proved to be ineffective for advanced compressor blades, which tend to use the combined sweep and dihedral. As for the prediction parameter DL, although it effectively modeled the effects of the adverse pressure gradient and secondary flow, it failed to predict the corner stall of curved blades because the model failed to consider the intersection of the boundary layer at the corner region. In this paper, the shape factor gradient Ψ of the boundary layer at the corner region was investigated by numerically studying specially shaped expansion pipes under different adverse pressure gradients. The improved prediction parameter DJ was presented based on the model of Ψ and the circumferential pressure gradient ξ. A comparison of the critical range of the prediction parameters DL and DJ was investigated using the NACA65 cascade database, which was established by a numerical method. Then, the stall criterion was validated according to the experimental results of various test facilities with different blade geometries and experimental conditions. The results show that the improved prediction parameter is able to predict the corner separation/stall flows and is in good agreement with the experimental results for axial compressors with three-dimensional designed blades.     

Impact point prediction guidance based on iterative process for dual-spin projectile with fixed canards

The fixed canards configuration of a dual-spin projectile makes it difficult to apply the traditional guidance law. In this study, a modified impact point prediction guidance strategy based on an iterative process was developed for a class of dual-spin projectiles with fixed canards, to reduce the impact point dispersion. The guidance strategy is dependent on the modified projectile linear theory to rapidly predict the flight states and the impact point. For projectiles with control applied to the trajectory, the modified projectile linear theory method is known to achieve poor impact point prediction. To improve the prediction accuracy, improvements were made to the modified projectile linear theory by considering the products of the yaw rate and other small quantities. The guidance strategy is based on the iterative process for the continuous adjustment of the expected output of the roll angle of the course correction fuze, to minimize the direction error between the predicted impact point and target location. Studies were conducted on a model dual-spin projectile configuration to demonstrate the guidance details. The numerical simulations indicate that the proposed guidance strategy can effectively reduce the projectile impact point dispersion.     

A prediction model of short-term ionospheric foF2 based on AdaBoost

In this paper, the AdaBoost-BP algorithm is used to construct a new model to predict the critical frequency of the ionospheric F2-layer (foF2) one hour ahead. Different indices were used to characterize ionospheric diurnal and seasonal variations and their dependence on solar and geomagnetic activity. These indices, together with the current observed foF2 value, were input into the prediction model and the foF2 value at one hour ahead was output. We analyzed twenty-two years’ foF2 data from nine ionosonde stations in the East-Asian sector in this work. The first eleven years’ data were used as a training dataset and the second eleven years’ data were used as a testing dataset. The results show that the performance of AdaBoost-BP is better than those of BP Neural Network (BPNN), Support Vector Regression (SVR) and the IRI model. For example, the AdaBoost-BP prediction absolute error of foF2 at Irkutsk station (a middle latitude station) is 0.32 MHz, which is better than 0.34 MHz from BPNN, 0.35 MHz from SVR and also significantly outperforms the IRI model whose absolute error is 0.64 MHz. Meanwhile, AdaBoost-BP prediction absolute error at Taipei station from the low latitude is 0.78 MHz, which is better than 0.81 MHz from BPNN, 0.81 MHz from SVR and 1.37 MHz from the IRI model. Finally, the variety characteristics of the AdaBoost-BP prediction error along with seasonal variation, solar activity and latitude variation were also discussed in the paper.     

Investigation of the relationship between ionospheric foF2 and earthquakes

Variations of the ionospheric F2 region critical frequency (foF2) have been investigated statistically before earthquakes during 1980–2008 periods in Japan area. Ionosonde data was taken from Kokubunji station which is in the earthquake preparation zone for all earthquakes. Standard Deviations and Inter-Quartile Range methods are applied to the foF2 data. It is observed that there are anomalous variations in foF2 before earthquakes. These variations can be regarded as ionospheric precursors and may be used for earthquake prediction.     

40CrNi2Si2MoVA钢机械加工与喷丸试样旋转弯曲疲劳寿命的预测方法

为了预测机械加工及喷丸强化后40CrNi2Si2MoVA钢试样在室温下的旋转弯曲疲劳寿命,结合商用有限元软件ABAQUS和疲劳寿命分析软件FE-SAFE对不同数值计算方法的适用性及准确性进行比较,提出了喷丸强化40CrNi2Si2MoVA钢的寿命预测经验公式。结果表明:对于机械加工试样,选择"Brown-Miller"算法和表面残余应力用于计算可获得比较准确的预测结果;对于喷丸强化试样,高应力水平下也可选用"Brown-Miller"算法及表面残余应力,而低应力水平下则应改用"Stress-based Brown Miller"算法及最大残余应力。基于上述两种方法提出的经验公式:σmax=–64.378·lgN+1449.268,可改善40CrNi2Si2MoVA钢喷丸强化试样疲劳寿命预测的准确性。     

Motion prediction of an uncontrolled space target

Capturing an uncontrolled space target is a tremendously challenging research topic. Target capture by a space robot can be well planned according to predicted motion of the target. In this paper, motion prediction of an uncontrolled space target is studied and a motion prediction algorithm is proposed. In the proposed algorithm, firstly a method for identifying the parameters of motion state and inertial property of the target is established; and then through substituting the identified parameters into the dynamic equations of the target, the motion of the target can be predicted as the solution of the equations. In the identification of the parameters, the unscented Kalman filter (UKF) is applied. In order to support the UKF, a method for estimating noise level of the observation data is developed, so our motion prediction algorithm is noise adaptive. A practical convergent criterion is also designed to determine the time when the estimated result of the UKF is accurate enough, such that the predicted motion is credible enough. After that, the accuracy of the prediction is further improved by an optimization method. In the end of this paper, numerical simulations are done to verify the validity of the proposed motion prediction algorithm. Simulation results indicate that the proposed algorithm is able to predict the motion of the target precisely.     

基于飞行参数的舰载机拦阻力统计建模与预计

拦阻钩是舰载飞机最重要的特征部件之一，对其受载进行测量、统计建模与预计具有重要的工程意义。在飞机拦阻动力学分析基础上确定了飞行数据统计建模所需的关键参数，结合某型机载荷试飞、机舰适配性试验，实测研究了飞机拦阻实际受载特点，采用线性或非线性方法统计建立了最大拦阻力与常规飞行参数之间的拟合函数关系，并得到了最大拦阻力的预计模型。建模、验模与预计结果表明，所选关键参数合理，能够充分反映拦阻钩的受载及其主要影响因素，采用纵向过载、啮合速度和发动机高压转速等参数建立的拦阻载荷统计模型可用于拦阻着陆或着舰试验时最大拦阻力的有效预测。     

应用跟踪微分器的高超声速飞行器的反演控制

针对存在参数摄动和外部干扰等不确定性的高超声速飞行器模型，提出一种基于新型跟踪微分器的鲁棒反演控制方法。利用正切sigmoid函数和终端吸引子函数设计跟踪微分器，通过扫频测试得到了参数整定规则，并进行了对比仿真试验。在此基础上，构造一种非线性干扰观测器对模型的不确定项进行估计，增强了控制器的鲁棒性；并利用所设计的跟踪微分器对虚拟控制量进行滤波处理，解决了传统反演控制的“微分项膨胀”问题。最后，通过仿真校验了所设计控制器的有效性。