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331.
The Ulysses spacecraft has been the first to orbit the Sun over its poles and to explore the heliosphere at these high heliolatitudes.
It has now completed two fast latitude scans, one at solar minimum and one at solar maximum. Since its launch in October 1990,
this mission has led to several surprising discoveries concerning energetic particles, cosmic rays, Jovian electrons, the
solar wind, the heliospheric magnetic field and the global features of the heliosphere. This review addresses mainly the propagation
and modulation of cosmic rays and other charged particles, from both an observational and theoretical point of view, with
emphasis on what has been learned from exploring the inner heliosphere to high heliolatitudes. This is done for solar minimum
and maximum conditions. The review is concluded with a summary of the main scientific discoveries and insights gained so far
from the Ulysses mission. 相似文献
332.
黄维扬 《南京航空航天大学学报》1992,(5)
计算了含中心裂纹的矩形板(高为2H,宽为2W)的应力强度因子。板的对称面内距离为2y_0的两点承受大小相等方向相反的一对集中力P作用。采用的分析方法是含待定常数的复应力函数与广义变分原理相结合的方法。此复应力函数精确地满足裂纹表面的边界条件,其余边界条件由广义变分原理近似地满足。 当H=2W,y_0=0.3W,a=(0.2-0.45)W(a为半裂纹长度),计算结果表明,应力强度因子近似为一个常值,它取1.938P/(πW)~(1/2),相对误差小于0.75%。 若采用上述几何尺寸的试件测试疲劳裂纹扩展常数,将可大大简化试验程序和试验数据处理工作。 相似文献
333.
PROPAGATIONCHARACTERISTICSOFACIRCULARMULTILAYERCHIRALDIELECTRICWAVEGUIDEHuaRongxi;ShenZhongxiang(DepartmentofElectronicEngine... 相似文献
334.
研讨了辐射温度计的标定方法,提出了1种新的标定法-分度函数法;并以Ge光电池为例,导出其分度函数的具体形式,同时估算了分度误差。 相似文献
335.
研究采用“直接升力控制系统”,在俯仰角保持不变(θ=const)的情况下,空中加油时飞机的飞行动力学和飞行控制问题。采用F-15飞机(静不安定飞机)参数,完成了飞机空中加油过程线代模型的建立和运动关系的推导;进行了空中加油闭环过程的计算机模拟;结果证明这种方法是有效的。 相似文献
336.
337.
与传统的射频链路相比,自由空间光通信FSOC(Free Space Optical Communication)系统是对现有无线通信技术的有力补充,为了抑制大气湍流对信号光束带来的相位噪声和强度波动,有必要对通信信道状况进行实时监测。首先介绍了基于光斑质心漂移的大气折射率结构常数测量方法,利用大口径接收靶面和窄带滤光片,结合实时图像处理算法,实现了大气折射率结构常数的全天候实时监测。将大气折射率结构常数和光强闪烁指数进行了比较分析,测量结果表明它们的包络之间具有很好的线性关系,进一步验证了实时测量系统的可靠性。 相似文献
338.
R. Hoogendoorn E. Mooij J. Geul 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(1):167-181
Predictions of the impact time and location of space debris in a decaying trajectory are highly influenced by uncertainties. The traditional Monte Carlo (MC) method can be used to perform accurate statistical impact predictions, but requires a large computational effort. A method is investigated that directly propagates a Probability Density Function (PDF) in time, which has the potential to obtain more accurate results with less computational effort. The decaying trajectory of Delta-K rocket stages was used to test the methods using a six degrees-of-freedom state model. The PDF of the state of the body was propagated in time to obtain impact-time distributions. This Direct PDF Propagation (DPP) method results in a multi-dimensional scattered dataset of the PDF of the state, which is highly challenging to process. No accurate results could be obtained, because of the structure of the DPP data and the high dimensionality. Therefore, the DPP method is less suitable for practical uncontrolled entry problems and the traditional MC method remains superior. Additionally, the MC method was used with two improved uncertainty models to obtain impact-time distributions, which were validated using observations of true impacts. For one of the two uncertainty models, statistically more valid impact-time distributions were obtained than in previous research. 相似文献
339.
This paper proposes a model-based prognostics method that couples the Extended Kalman Filter (EKF) and a new developed linearization method. The proposed prognostics method is developed in the context of fatigue crack propagation in fuselage panels where the model parameters are unknown and the crack propagation is affected by different types of uncertainties. The coupled method is composed of two steps. The first step employs EKF to estimate the unknown model parameters and the current damage state. In the second step, the proposed efficient linearization method is applied to compute analytically the statistical distribution of the damage evolution path in some future time. A numerical case study is implemented to evaluate the performance of the proposed method. The results show that the coupled EKF-linearization method provides satisfactory results: the EKF algorithm well identifies the model parameters, and the linearization method gives comparable prediction results to Monte Carlo (MC) method while leading to very significant computational cost saving. The proposed prognostics method for fatigue crack growth can be used for developing predictive maintenance strategy for an aircraft fleet, in which case, the computational cost saving is significantly meaningful. 相似文献
340.
Kenath Arun S.B. Gudennavar A. Prasad C. Sivaram 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(1):567-570
One of the unresolved questions currently in cosmology is that of the non-linear accelerated expansion of the universe. This has been attributed to the so called Dark Energy (DE). The accelerated expansion of the universe is deduced from measurements of Type Ia supernovae. Here we propose alternate models to account for the Type Ia supernovae measurements without invoking dark energy. 相似文献