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51.
由于导弹飞控系统的高度非线性、时变性和不确定性,如何设计导弹高性能鲁棒控制系统是一项关键技术。利用模糊逻辑很强的知识综合和推理等特点,基于模糊控制和H∞鲁棒控制方法,建立了一种模糊参数化的增益调参飞控系统鲁棒设计方法,并利用线性矩阵不等式(LMI)技术,将鲁棒增益调参控制器设计转化成了相应的LMI凸优化问题,解决了复杂鲁棒控制器的求解问题。并将该方法应用于导弹鲁棒控制系统设计,仿真结果表明了该设计方法有效性。模糊逻辑、鲁棒控制以及线性矩阵不等式技术的有机结合可以设计具有全局稳定性及鲁棒性能要求的高性能导弹飞控系统。 相似文献
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本文分析了可编程逻辑器件出现竞争冒险的原因,介绍了在数字系统设计过程中常用的几种消除竞争冒险的措施。 相似文献
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Aircraft robust multidisciplinary design optimization methodology based on fuzzy preference function
This paper presents a Fuzzy Preference Function-based Robust Multidisciplinary Design Optimization (FPF-RMDO) methodology. This method is an effective approach to multidisciplinary systems, which can be used to designer experiences during the design optimization process by fuzzy preference functions. In this study, two optimizations are done for Predator MQ-1 Unmanned Aerial Vehicle (UAV): (A) deterministic optimization and (B) robust optimization. In both problems, minimization of takeoff weight and drag is considered as objective functions, which have been optimized using Non-dominated Sorting Genetic Algorithm (NSGA). In the robust design optimization, cruise altitude and velocity are considered as uncertainties that are modeled by the Monte Carlo Simulation (MCS) method. Aerodynamics, stability and control, mass properties, performance, and center of gravity are used for multidisciplinary analysis. Robust design optimization results show 46% and 42% robustness improvement for takeoff weight and cruise drag relative to optimal design respectively. 相似文献
56.
Altab Hossain Ataur Rahman Jakir Hossen A.K.M.P. Iqbal M.I. Zahirul 《Aerospace Science and Technology》2011,15(8):595-605
This paper describes the potentials of an aircraft model without and with winglet attached with NACA wing No. 65-3-218. Based on the longitudinal aerodynamic characteristics analyzing for the aircraft model tested in low subsonic wind tunnel, the lift coefficient (CL) and drag coefficient (CD) were investigated respectively. Wind tunnel test results were obtained for CL and CD versus the angle of attack α for three Reynolds numbers Re (1.7×105, 2.1×105, and 2.5×105) and three configurations (configuration 1: without winglet, configuration 2: winglet at 0° and configuration 3: winglet at 60°). Compared with conventional technique, fuzzy logic technique is more efficient for the representation, manipulation and utilization. Therefore, the primary purpose of this work was to investigate the relationship between lift coefficients and drag coefficients with free-stream velocities and angle of attacks, and to illustrate how fuzzy expert system (FES) might play an important role in prediction of aerodynamic characteristics of an aircraft model with the addition of winglet. In this paper, an FES model was developed to predict the lift and drag coefficients of the aircraft model with winglet at 60°. The mean relative error of measured and predicted values (from FES model) were 6.52% for lift coefficient and 4.74% for drag coefficient. For all parameters, the relative error of predicted values was found to be less than the acceptable limits (10%). The goodness of fit of prediction (from FES model) values were found as 0.94 for lift coefficient and 0.98 for drag coefficient which were close to 1.0 as expected. 相似文献
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提出通过模型参数的模糊比例积分自适应调节,以校正基于模型的飞控系统故障检测中的系统数学模型偏差。针对模型中误差差较大的迎角导数值,将俯仰角加速度的测量值与教学模型估计值之差作为比例积分调节的反馈量,动态实时校正数学模型参数。 相似文献
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魏铁进 《郑州航空工业管理学院学报(管理科学版)》2000,18(3):61-63
对INTERNET网检工具逻辑算符进行分析和比较。在此基础上,提出制定和优化检索表达式的方法。 相似文献
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王崇 《郑州航空工业管理学院学报(管理科学版)》2014,(1):134-138
实质意义上的权力制约肇始于权力分化之后,历经以道德制约权力、以权力制约权力、以社会制约权力等经典范式,体现了权力制约活动从关注权力执掌者、权力本体到关注权力归属者不断演变的内在逻辑。植根于我国国情的权力制约实践在伦理学、社会学途径方面与西方存有共性,但于政治学途径却存有个性。实现我国权力制约的语境化既需要体现权力制约的普遍性规律,更需要把握马克思主义政治观视域下权力制约的特殊性。 相似文献