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1.
The effects of parameter uncertainty on the flutter characteristics of a two-dimensional airfoil in an incompressible flow were investigated through Gegenbauer polynomial approximation. The uncertain parameters, such as the linear and cubic pitch stiffness coefficients are modeled as bounded random variables with λ-PDFs (probability density functions). With the aid of Gegenbauer polynomial approximation, the two-dimensional stochastic airfoil system is transformed at first into its equivalent deterministic one. Then the Hopf-bifurcation point is determined through the equivalent deterministic system, and the onset of the flutter, together with the flutter frequency against the probability density distribution parameter and the intensity of the random variable is explored. In addition, the ranges of the peak pitch and plunge responses against the flight speed and the PDFs of the peak pitch response are obtained. Numerical results show how the probability density distribution parameters and the intensities of random parameters affect the flutter onset speed, flutter angular frequency, the upper and lower boundaries of peak responses, and the PDFs of peak responses. 相似文献
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求解装箱问题的遗传算法 总被引:4,自引:0,他引:4
本文提出了两种求解装箱问题(BinPacking)的遗传算法。一种是简单遗传算法,它采用等长度字符代码编码方法,使用常规的遗传操作算子。另一种是混合遗传算法,它综合运用解装箱问题的FFD(FirstFitDe-creasing)近似算法和简单遗传算法。试算结果表明,由这两种遗传算法所得到的装箱方案较一些近似算法所得到的装箱方案都要好。 相似文献
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针对MIMO系统可控性和可观性矩阵的特点,建立了一种区间矩阵MIMO定常系统可控性与可观性的充要条件,并给出了详细的理论推导,最后列举实际的例子。在例中与Frobenius范数区间作了比较,结果表明,如何扰动仅作用于系数矩阵A,则「△A,△B」的Froberius范数区间地大大受到△B的限制。 相似文献
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为了在级间分离期间提供反推力,许多固体火箭发动机前端都装有一组斜切反喷管。由于反喷管的气动型面具有许多尖点,并且在超声速区有一个台阶,喷管内存在一系列激波,而且亚声速区和超声速区互相混杂。本文用时间相关法数值模拟了反喷管流场,控制议程用Mac Cormack显格式求数值解,边界参数采用物理边界条件和从双特征线方法推导来的有效的特征方法为计算,为于固壁边界点,在不同的区域采用不同的方法对计算方程组求 相似文献
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Simple solutions for hyperbolic and related position fixes 总被引:4,自引:0,他引:4
Navigation fixed from range differences to three stations and an additional piece of information are investigated. It is shown that if the additional information is the navigator altitude, or the range difference to a fourth station, the computation of the navigation fix is reduced to finding the roots of a quadratic. If the additional information is the range to another station, or that the navigator is on the Earth ellipsoid, the fix can be obtained by solving a quartic. By emphasizing the underlying geometric interpretations, these fixes and their simple solutions are made clear. The derivations also show that the same solution algorithms are applicable if the basic navigation measurements are range sums instead of range differences 相似文献
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Lee F.C. Carter R.A. Fang Z.D. 《IEEE transactions on aerospace and electronic systems》1983,(2):274-287
The stability and dynamic performances of a buck/boost regulator employing a current-injected control are examined. Small-signal models for the power state, the multiloop error processor, and the duty-cycle pulse modulator are developed. The error-processor model which incorporates the current-injected loop, the dc loop, and the compensation network permits evaluation of the effects of each individual control loop and their combined efforts toward shaping the performance characteristics of the closed-loop system. Comparisons are made between this modeling approach and earlier approaches. Some important yet subtle dissimilarities are discussed. This model predicts the constant-frequency 50-percent duty-cycle instability which is inherent to the current-injected control. 相似文献
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