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81.
This paper presents an experimental study of a novel K-Cor sandwich structure rein- forced with partially-cured Z-pins. The influence of pultrusion processing parameters on Z-pins characteristics was studied and the effect of Z-pins on mechanical properties was disclosed. Differential scanning calorimetry (DSC) and optical microscopy (OM) methods were employed to determine the curing degree of as-prepared Z-pins and observe the implanted Z-pins in the K-Cor structure. These partially-cured Z-pins were treated with a stronger bonding link between face sheets and the foam core by means of a hot-press process, thereby decreasing burrs and cracking defects when the Z-pins were implanted into the Rohacell foam core. The results of the out-of-plane tensile tests and the climbing drum peel (CDP) tests showed that K-Cor structures exhibited superior mechanical performance as compared to X-Cor and blank foam core. The observed results of failure modes revealed that an effective bonding link between the foam core and face sheets that was provided from partially-cured Z-pins contributed to the enhanced mechan- ical performances of K-Cor sandwich structures. 相似文献
82.
本文首先讨论了蓝牙 (Bluetooth)技术的基本概念 ,然后分析了蓝牙无线接入控制技术的特点 ,并对蓝牙无线接入技术存在的问题及发展方向提出了自己的见解 相似文献
83.
Comments on "Unbiased converted measurements for tracking" 总被引:6,自引:0,他引:6
Zhansheng Duan Chongzhao Han Rong Li X. 《IEEE transactions on aerospace and electronic systems》2004,40(4):1374
We show that there exists a compatibility problem in the derivation of the mean and covariance of the converted measurement errors in L. Mo et al. (ibid., vol.34, no.3, p.1023-7, 1998), and then present a modification to the computation of them, in which both the mean and the covariance are computed strictly conditioned on the measurements. 相似文献
84.
本文对某机型尾桨毂轴套耳片疲劳裂纹产生的根源,着重从影响产品疲劳特性的结构设计、设计选材,载荷及生产工艺等主要因素进行了分析。通过理论分析认为,引起疲劳裂纹的最大可能性是工艺加工所致。经过产品的断口分析及取样测试,确认为机械加工粗糙,有关尺寸不符合图纸要求,是这次疲劳裂纹产生的直接原因。 相似文献
85.
振动引起光纤陀螺(FOG, Fiber Optic Gyroscope)零偏误差,非线性、非高斯随机噪声及由其组成的惯性测量单元(IMU, Inertial Measurement Unit)非互易性解算误差,针对直升机航向姿态测量误差问题,提出了一种FOG IMU的机械减振与数据滤波相结合的振动抑制方法,建立了FOG IMU减振装置数学模型,通过优化设计实现线、角运动通道振动解耦,从物理上消除外界高频干扰振动源;研究实时小运算量、低时延数据滤波方法,抑制减振装置谐振干扰和惯性器件噪声,进而减小捷联解算非互易性误差.实验结果表明:采用该方法能有效地抑制外界干扰振动和系统噪声,保证FOG IMU工作稳定性和精度,为研制应用于直升机的高性能航姿导航信息与航向姿态参考系统奠定基础. 相似文献
86.
87.
Novel intelligent water drops optimization approach to single UCAV smooth trajectory planning 总被引:1,自引:0,他引:1
Trajectory planning of unmanned combat aerial vehicle (UCAV) is a rather complicated global optimum problem in UCAV mission planning. Intelligent water drops (IWD) algorithm is newly presented under the inspiration of the dynamic of river systems and the actions that water drops do in the rivers, and it is easy to combine with other methods in optimization. In this paper, we propose an improved IWD optimization algorithm for solving the single UCAV smooth trajectory planning problems in various combating environments. The water drops can act as an agent in searching the optimal UCAV trajectory. The detailed realization procedure for this novel approach is also presented. In order to make the optimized UCAV trajectory more feasible for exact flying, an efficient path smoothing method called the κ-trajectory is adopted for smoothing the single UCAV trajectory. Series experimental comparison results show the proposed IWD optimization algorithm is more effective and feasible in the single UCAV smooth trajectory planning than the basic IWD model. 相似文献
88.
89.
比例UT变换的一种比例因子自适应选取方法 总被引:1,自引:0,他引:1
将比例UT(Unscented Transform)变换应用于一般的采样策略可以解决采样的非局部效应问题,提高UKF(Unscented Kalman Filtering)的估计精度,而比例因子是其中的重要参数。文章提出了一种比例因子的自适应选取方法,将自适应的比例UT变换作用于最小偏度单形采样,并把相应的UKF应用于低轨卫星实时定轨中。仿真结果表明,这种自适应选取参数方法稳定可靠,其相应的UKF定轨精度与最佳的固定比例因子UKF的精度相当。 相似文献
90.
The paper is to integrate aerodynamic and aero-acoustic optimizatiom design of high lift devices,especially for two-element airfoils with slat.Aerodynamic analysis on flow field utilizes a high-order,high-resolution spatial differential method for large eddy simulation(LES),which can guarantee accuracy and efficiency.The aeroacoustic analysis for noise level is calculated with Ffowcs Williams-Hawkings(FW-H)integration formula.Fidelity of calculation is verified by standard models.Method of streamline-based Euler simulation(MSES)is used to obtain the aerodynamic characters.Based on the confirmation of numerical methods,detailed research has been conducted for the leading edge slat on multi-element airfoils.Various slot parameter influences on noise are analyzed.The results of the slot optimization parameters can be used in multi-element airfoil design. 相似文献