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931.
932.
933.
大型客机起飞着陆过程噪声辐射特性对比分析 总被引:4,自引:1,他引:3
基于准稳态假设和分布点声源模型,并采用最新发展的噪声源半经验参数预测公式,发展和完善了用于飞机飞行过程中噪声辐射预测的计算模型和方法。该计算方法能够预测飞机起飞、着陆过程中的适航噪声,并能够对飞机不同噪声源的噪声辐射特性(声级、频谱特性和指向性等)进行计算分析。以某大型客机为对象,对飞机进场着陆过程和起飞过程中飞机噪声源进行了计算分析,计算结果表明,飞机进场着陆和起飞过程中,不同噪声源对远场噪声级的影响有明显的差异,起飞过程中发动机风扇噪声源是最主要的噪声辐射源,而在进场着陆过程中飞机机体噪声(包括起落架和襟翼等)是重要的飞机噪声源。文中也给出了不同噪声源频谱特性和指向特性等。 相似文献
934.
《中国航空学报》2020,33(5):1433-1443
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. 相似文献
935.
《中国航空学报》2019,32(8):1967-1981
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. 相似文献
936.
Xiukuan Zhao Baiqi Ning Libo Liu Gangbing Song 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
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. 相似文献
937.
Tuba Karaboga Murat Canyilmaz Osman Ozcan 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(8):2022-2030
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. 相似文献
938.
939.
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。 相似文献
940.
Bang-Zhao Zhou Xiao-Feng Liu Guo-Ping Cai Yun-Meng Liu Pan Liu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(1):496-511
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. 相似文献