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《中国航空学报》2021,34(4):32-41
Obtaining accurate development cost estimation results of general aviation aircraft is crucial for companies to adopt the best strategy in the development process. To address this problem, this paper proposes a combination of three commonly used single prediction methods. The optimal weight values of the three single prediction methods are determined by utilizing the shortest ideal point method. Ten cost datasets collected from literature are utilized for fitting and testing the combined prediction method, and the weight coefficients of the three individual prediction methods are calculated as 0.6859, 0.0035 and 0.3106, respectively. The results of this study indicate that the developed method has better fitting and estimation accuracy than that of the three individual methods, with average fitting and predicting error values of 2.60% and 6.43%, respectively. Additionally, the cost data of military and civil aircraft development from literature are collected for verification. The results further confirm that the proposed method is not only superior to the single prediction methods in terms of high precision but has wider applications. More importantly, this research can provide important reference for general aviation aircraft companies in term of product cost planning and corporate sales strategies. 相似文献
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攻击地面固定目标寻的导弹的一体化制导与控制(英文) 总被引:4,自引:1,他引:3
This paper presents a scheme of integrated guidance and autopilot design for homing missiles against ground fixed targets. An integrated guidance and control model in the pitch plane is formulated and further changed into a normal form by nonlinear coordinate transformation. By adopting the sliding mode control approach, an adaptive nonlinear control law of the system is designed so that the missile can hit the target accurately with a desired impact attitude angle. The stability analysis of the closed-loop system is also conducted. The numerical simulation has confirmed the usefulness of the proposed design scheme. 相似文献
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Measuring reliability under epistemic uncertainty:Review on non-probabilistic reliability metrics 总被引:1,自引:1,他引:0
《中国航空学报》2016,(3):571-579
In this paper, a systematic review of non-probabilistic reliability metrics is conducted to assist the selection of appropriate reliability metrics to model the influence of epistemic uncertainty. Five frequently used non-probabilistic reliability metrics are critically reviewed, i.e., evidence-theory-based reliability metrics, interval-analysis-based reliability metrics, fuzzy-interval-analysis-based reliability metrics, possibility-theory-based reliability metrics (posbist reliability) and uncertainty-theory-based reliability metrics (belief reliability). It is pointed out that a qualified reli-ability metric that is able to consider the effect of epistemic uncertainty needs to (1) compensate the conservatism in the estimations of the component-level reliability metrics caused by epistemic uncertainty, and (2) satisfy the duality axiom, otherwise it might lead to paradoxical and confusing results in engineering applications. The five commonly used non-probabilistic reliability metrics are compared in terms of these two properties, and the comparison can serve as a basis for the selection of the appropriate reliability metrics. 相似文献
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多台系统Weibull过程的Bayes统计推断方法 总被引:2,自引:0,他引:2
本文的目的是要给出多台系统Weibull过程的Bayes推断方法。获得了尺度参数、形状参数以及系统能达到的MTBF的Bayes点估计和区间估计。某些估计只涉及到一重数值积分。最后,用一个实例说明这些方法。 相似文献
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从考虑追踪器速度的大小和方向变化以及目标速度变化方面入手 ,以最优控制理论和飞行力学原理为基础 ,推导出一种考虑追踪器速度变化的最优导引律—变系数比例导引律 ,同时给出一种计算剩余时间的新方法—剩余时间函数法。对要求垂直入射的情况 ,设计了满足入射角度要求的导引律。仿真结果表明 ,应用本文的导引律在制导过程中能量消耗少 ,制导精度高 ,脱靶量小 ,其性能远优于常系数比例导引律 相似文献
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针对洲际弹道导弹,在分析加速度计测量误差和陀螺漂移误差对导弹视加速度影响的基础上,给出了中制导段惯性系统对速度和位置的误差传递模型,对给定的惯组误差系数偏差进行了纯惯性导航制导误差计算。仿真结果表明,纯惯导中制导对洲际导弹落点精度影响比较大。该算法可用于纯惯性中制导方案设计。 相似文献