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1.
《中国航空学报》2020,33(2):407-417
Multi-faults detection is a challenge for rolling bearings due to the mode mixture and coupling of multiple fault features, as well as its easy burying in the complex, non-stationary structural vibrations and strong background noises. In this paper, a method based on the flexible analytical wavelet transform (FAWT) possessing fractional scaling and translation factors is proposed to identify multiple faults occurred in different components of rolling bearings. During the route of the proposed method, the proper FAWT bases are constructed via genetic optimization algorithm (GA) based on maximizing the spectral correlated kurtosis (SCK) which is firstly presented and proved to be efficient and effective in indicating interested fault mode. Via using the customized FAWT bases for each interested fault mode, the original vibration measurements are decomposed into fine frequency subbands, and the sensitive subband which enhances the signal-to-noise ratio (SNR) is selected to exhibit the fault signature on its envelope spectrum. The proposed method is tested via simulated signals, and applied to analyze the experimental vibration measurements from the running roller bearings subjected to outrace, inner-race and roller defects. The analysis results validate the effectiveness of the proposed method in identifying multi-faults occurred in different components of rolling bearings. 相似文献
2.
Rebecca La Norcia Dario Spiller Fabio Curti Christian Circi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(11):3409-3425
A study on reconfiguration manoevres applied to a tetrahedral formation in highly elliptical orbits is proposed, by using a propellantless solution. The manoeuvring strategy consists in exploiting certain environmental forces, specifically those provided by solar radiation pressure and atmospheric drag, by actively controlling the satellites’ attitudes. Through inverse dynamics particle swarm optimization the optimal attitudes required for the manoeuvres are evaluated, whereas the configuration’s evolution is simulated by a high-fidelity orbital simulator. The goal of the reconfiguration problem is to find an optimal control in order for the four spacecraft to reach a desired configuration in a specified portion of orbit, where the desired configuration is evaluated by a shape and size geometric parameter. By increasing the manoeuvring time and the satellites’ area to mass ratio, all the case studies considered are successfully verified. 相似文献
3.
Bai Chenyuan Li Juan Wu Ziniu 《中国航空学报》2014,27(5):1037-1050
By using a special momentum approach and with the help of interchange between singularity velocity and induced flow velocity, we derive in a physical way explicit force formulas for twodimensional inviscid flow involving multiple bound and free vortices, multiple airfoils, and vortex production. These force formulas hold individually for each airfoil thus allowing for force decomposition, and the contributions to forces from singularities(such as bound and image vortices,sources, and doublets) and bodies out of an airfoil are related to their induced velocities at the locations of singularities inside this airfoil. The force contribution due to vortex production is related to the vortex production rate and the distance between each pair of vortices in production, thus frameindependent. The formulas are validated against a number of standard problems. These force formulas, which generalize the classic Kutta–Joukowski theorem(for a single bound vortex) and the recent generalized Lagally theorem(for problems without a bound vortex and vortex production) to more general cases, can be used to identify or understand the roles of outside vortices and bodies on the forces of the actual body, optimize arrangement of outside vortices and bodies for force enhancement or reduction, and derive analytical force formulas once the flow field is given or known. 相似文献
4.
《中国航空学报》2020,33(2):688-700
To improve the resolution and accuracy of Direct Position Determination (DPD), this paper investigates the problem of positioning multiple emitters directly with a single moving Rotating Linear Array (RLA). Firstly, the geometry of the RLA is formulated and analysed. According to its geometry, the intercepted noncoherent signals in multiple interception intervals are modeled. Correspondingly, the MUltiple SIgnal Classification (MUSIC) based noncoherent DPD approach is proposed. Secondly, the synchronous coherent pulse signals are individually considered and formulated. And the coherent DPD approach which aims for localizing this special type of signal is presented by stacking all array responses at different interception intervals. Besides, we also derive the constrained Cramér-Rao Lower Bound (CRLB) expression for both noncoherent and coherent DPD with RLA under the constraint that the altitudes of the emitters are known. At last, computer simulations are included to examine the performance of the proposed approach. The results demonstrate that the localization accuracy and resolution of DPD with single moving linear array can be significantly improved by the array rotation. In addition, coherent DPD with RLA further improves the resolution and increases the maximum emitter number that can be localized compared with the noncoherent DPD with RLA. 相似文献
5.
研究绳系结构和绳索预紧力对全模颤振双索悬挂系统刚体模态频率的影响。首先,基于绳索并联机构理论,对双索悬挂系统进行静力学建模,引入加权矩阵,推导了双索悬挂系统静刚度模型;其次,建立双索悬挂系统无阻尼振荡方程,分析双索悬挂系统刚体模态频率变化规律;进而,搭建了双索悬挂系统地面样机,开展系统模态频率测试试验,研究系统刚体模态频率的影响因素及其变化规律;最后,参考试验结果修正所建数学模型。结果表明,随着绳索预紧力的增加,系统刚体模态频率呈上升趋势,但各阶刚体模态的固有频率上升速率不同,平动模态的固有频率受绳索预紧力影响比转动模态小得多;在转动模态方面,滚转模态的固有频率最大且上升快;在平动模态方面,升沉模态的固有频率大于横侧滑模态的固有频率;双索经过的机身前后滑轮与飞机模型质心之间的相对位置变化会不同程度地影响支撑系统俯仰模态、偏航模态的固有频率,但几乎不影响其滚转模态的固有频率。研究发现,通过控制悬挂绳索预紧力的大小,合理设计机身上的滑轮安装位置,能够有效降低双索悬挂系统刚体模态频率。研究结果对于优化设计全模颤振双索悬挂系统具有指导意义。 相似文献
6.
《中国航空学报》2016,(3):754-762
An efficient method for blind classification of space–time block codes(STBCs) based on fourth-order cumulants is proposed for a single receiver antenna.This paper presents a model of received STBCs signals in multiple input single output(MISO) communication systems and applies the characteristics of coding matrices to derive analytical expressions for the fourth-order cumulants to be used as the basis of an algorithm.The fourth-order cumulants at various delay vectors present non-null values that depend on the transmitted STBCs.Tests of nullity are accomplished by hypothesis testing.The proposed algorithm avoids the need for a priori information of modulation scheme,channel coefficients,and noise power.Consequently,it is well suited for non-cooperative scenarios.Simulations show that this method performs well even at low signal-to-noise ratios(SNRs). 相似文献
7.
Jie Wang Cuichun Li Xiuyun Meng 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(8):2517-2533
As the lighter-than-air (LTA) flight vehicle, the stratospheric airship is a desirable platform to provide communication and surveillance services. During the ascent from sea-level to the mission altitude, the volume of the lifting gas may change significantly, which will result in the change of the center-of-buoyancy (CB). A general calculation method is developed to specify CB for the stratospheric airship with a double-ellipsoid hull and an arbitrary number of the gas cells. The cross-section-integral (CSI) method is used as a basic calculation scenario to specify CB. Considering the complexity in determining the boundary between the helium and air in the gas cell, a searching algorithm is put forward and the specification of CB can be conducted by the iterative calculation. As an important application, the stable condition of the pitch angle is analyzed when the change of CB is involved. Under different initial configurations, the stable pitch angle of the stratospheric airship during the ascent is specified and compared, which shows the advantages of the multi-gas-cell configuration. The results of this paper may provide an important reference for the engineering application of the stratospheric airship. 相似文献
8.
Firstly, a multi-field coupling finite element formulation of composited beam laminated with the photostrictive actuators is developed in this paper. Moreover, an optimal fuzzy active control algorithm is also proposed on the basis of the combination of optimal control and fuzzy one.This method opens a new avenue to resolve the contradiction between the linear system control method and nonlinear actuating characteristics of photostrictive actuators. The desired control for suppressing multi-modal vibration of photoelectric laminated beam is firstly obtained through optimal control and then the fuzzy control is used to approach the desired mechanical strain induced by photostrictive actuators. Thus, the multi-mode vibration control of beam is realized.In the design process of optimal fuzzy controller, the design of fuzzy control is independent of optimal control. The simulation results demonstrate that the proposed control method can effectively realize multi-modal vibration control of photoelectric laminated beams, and the control effect of optimal fuzzy control is better than that of optimal state feedback control. 相似文献
9.
在大气多路径和噪声的条件下,高斯白噪声会造成滑动频谱方法获得的弯曲角与真值之间的偏离,无法获得较好的反演结果.为此,文章提出了一种改进的滑动频谱方法,即利用信号的振幅和谱能量信息对滑动频谱方法进行修正,削弱了信号中噪声的影响,与真值较为接近.分别用改进前后两种方法对中华卫星三号计划(Constellation Observing System for Meteorology,Ionosphere and Climate,COSMIC)的掩星进行反演,并将其折射率计算结果和通过全谱反演方法获得的折射率一起,与欧洲中期天气预报中心( European Centre for Medium-Range Weather Forecasts,ECMWF)的分析场资料进行了统计比较.结果表明:改进的滑动频谱方法删除了信号中的部分噪声,减少了系统偏差;与全谱反演方法进行比较,发现两者具有相当的反演精度. 相似文献
10.
为确定2A16-O铝合金板材在不同温度及应变率下的成形极限曲线(FLCs),应用改进Hollomon公式获取满足外插可靠度的拟合应力应变,通过有限元分析(FEA)不同椭圆度的椭圆凹模胀形破裂位置,优化工艺参数得到指定应变路径下的成形极限点,建立了液体压力与等效应变及应变率的公式,推导出压力变化率与应变率的定量关系。以应变率控制的椭圆凹模胀形与单拉试验相结合,获得2A16-O铝合金板材在不同温度及应变率下的FLCs,为定量分析应变率的影响规律和评判理论预测方法的准确性提供了依据。 相似文献