全文获取类型
收费全文 | 985篇 |
免费 | 103篇 |
国内免费 | 189篇 |
专业分类
航空 | 665篇 |
航天技术 | 259篇 |
综合类 | 206篇 |
航天 | 147篇 |
出版年
2024年 | 2篇 |
2023年 | 11篇 |
2022年 | 20篇 |
2021年 | 18篇 |
2020年 | 37篇 |
2019年 | 38篇 |
2018年 | 46篇 |
2017年 | 58篇 |
2016年 | 53篇 |
2015年 | 48篇 |
2014年 | 52篇 |
2013年 | 35篇 |
2012年 | 68篇 |
2011年 | 64篇 |
2010年 | 47篇 |
2009年 | 62篇 |
2008年 | 42篇 |
2007年 | 69篇 |
2006年 | 55篇 |
2005年 | 36篇 |
2004年 | 36篇 |
2003年 | 27篇 |
2002年 | 45篇 |
2001年 | 41篇 |
2000年 | 26篇 |
1999年 | 38篇 |
1998年 | 18篇 |
1997年 | 30篇 |
1996年 | 27篇 |
1995年 | 18篇 |
1994年 | 25篇 |
1993年 | 19篇 |
1992年 | 14篇 |
1991年 | 8篇 |
1990年 | 6篇 |
1989年 | 13篇 |
1988年 | 13篇 |
1987年 | 9篇 |
1986年 | 3篇 |
排序方式: 共有1277条查询结果,搜索用时 218 毫秒
591.
592.
建立了基于混合整数线性规划(Mixed Integer LinearProgram,MILP)的多无人机编队对敌防空火力压制协同任务分配模型,以0-1决策变量表征无人机一任务指派关系,引入连续时间决策变量来表示任务的执行时间,并通过对决策变量之间的线性等式和不等式的数学描述,建立无人机之间和无人机执行任务之间合理的协同约束关系。采用商用软件CPLEX对模型求解,仿真验证了模型的合理性。 相似文献
593.
为实现飞机外表面的机器人自动化喷涂,根据飞机外表面的几何特征,提出了飞机表面喷涂轨迹的规划方案和自动化喷涂作业的定位方法。根据该方法制订了多层次的喷涂控制程序结构,包括主逻辑层、控制程序层、辅助功能层3个层次。主逻辑层负责整个程序体系运行的调度,即调用控制程序层和辅助功能层中的功能模块;控制程序层包含飞机表面的分区及相应的喷涂控制程序模块;辅助功能层包括喷涂工艺参数、运动参数、系统默认参数等内容。为快速生成多层次喷涂程序体系,提出了面向飞机外表面喷涂的离线编程技术方案。以飞机模型表面喷涂为例,验证了方法的有效性和可维护性。 相似文献
594.
现有LR(Lattice Reduction)辅助的线性预编码算法,在接收机端需要对接收到信号进行平移变换,因而仅适合于点对点的MIMO系统中,然而在广播信道条件下,由于接收机是分散的,且功率尺寸受限,不适宜采用现有的线性预编码算法。针对这一问题,文章提出了一类改进的LR辅助线性预编码算法,并给出了相应ZF和MMSE准则下的具体实现。在该算法中,信号处理主要在发送机端完成,以降低接收机端的计算量。仿真结果表明:文章提出的算法相比现有的LR辅助线性预编码算法误比特率性能更好,因而更适用于广播信道条件下的MIMO系统。 相似文献
595.
针对有源干扰背景下信号源和干扰源的个数超过线阵的自由度而产生线阵饱和现象,提出一种将约束最小冗余线阵与干扰对消技术相结合的测向方法。通过将无源状态和有源状态下线阵输出数据的协方差矩阵进行对消运算去除有源干扰和噪声分量,并对约束最小冗余线阵的波达方向(DOA)估计算法进行改进,构造了新的协方差Toeplitz矩阵,有效抑制了由阵列非均匀性导致的伪峰,提高了阵列的DOA估计性能。仿真结果表明:该算法在低信噪比背景下具有抗有源干扰能力,扩展了阵列孔径,并具有较高的测向精度和鲁棒性。 相似文献
596.
597.
598.
扇区划分是终端区空域规划的研究内容之一,划分后能覆盖不均匀的交通分布,缓解需求与容量的不平衡,从而提高空域系统的运行效率。将终端区扇区划分作为一个整数规划问题,在约束条件中考虑了间隔规则、飞行路径需求和机场跑道结构的几何约束等,根据最优解来生成终端区扇区。以某终端区算例,验证了整数规划模型的可行性。 相似文献
599.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(9):2167-2171
In this study, the impact of Earth’s magnetic field on total electron content (TEC) was studied by using statistical multiple linear regression model and co-integration method. TEC values were measured over the Turkey-Istanbul (ista) station using date of global positioning system (GPS), and the magnetic field components of the Earth were measured from Boğaziçi University, Kandilli Observatory and Earthquake Research Institute, Geomagnetic observatory Istanbul (ISK) station. This examination has been carried out during the dates of March 14–19, 2015 covering the dates of March 17–18, 2015 known in the literature as St. Patrick's Day geomagnetic storm. The three days before the storm (March 14–16) were named as quiet days, whereas the other days (March 17–19) were named as disturbed days after which the two periods were examined separately. It was observed as a result of the examination that the x-component (south-north direction) of the magnetic field had a negative impact on TEC on quiet days, whereas the impact was positive on disturbed days. However, the y-component (east–west direction) of the magnetic field had an inverse relationship of the x-component on the quiet and disturbed days. In addition, it was deduced that the impact coefficient of the x and y-component of the magnetic field was higher on disturbed days in comparison with those on quiet days. The correlation coefficient between the TEC and the components of the Earth’s magnetic field was 0.11 on quiet days and 0.95 on disturbed days. Therefore, it can be stated that the relationship of the TEC values with the geomagnetic field are higher on disturbed days. 相似文献
600.
Sreeja Nag Alan S. Li James H. Merrick 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(3):891-913
Distributed Space Missions such as formation flight and constellations, are being recognized as important Earth Observation solutions to increase measurement samples over space and time. Cubesats are increasing in size (27U, ~40?kg in development) with increasing capabilities to host imager payloads. Given the precise attitude control systems emerging in the commercial market, Cubesats now have the ability to slew and capture images within short notice. We propose a modular framework that combines orbital mechanics, attitude control and scheduling optimization to plan the time-varying, full-body orientation of agile Cubesats in a constellation such that they maximize the number of observed images and observation time, within the constraints of Cubesat hardware specifications. The attitude control strategy combines bang-bang and PD control, with constraints such as power consumption, response time, and stability factored into the optimality computations and a possible extension to PID control to account for disturbances. Schedule optimization is performed using dynamic programming with two levels of heuristics, verified and improved upon using mixed integer linear programming. The automated scheduler is expected to run on ground station resources and the resultant schedules uplinked to the satellites for execution, however it can be adapted for onboard scheduling, contingent on Cubesat hardware and software upgrades. The framework is generalizable over small steerable spacecraft, sensor specifications, imaging objectives and regions of interest, and is demonstrated using multiple 20?kg satellites in Low Earth Orbit for two case studies – rapid imaging of Landsat’s land and coastal images and extended imaging of global, warm water coral reefs. The proposed algorithm captures up to 161% more Landsat images than nadir-pointing sensors with the same field of view, on a 2-satellite constellation over a 12-h simulation. Integer programming was able to verify that optimality of the dynamic programming solution for single satellites was within 10%, and find up to 5% more optimal solutions. The optimality gap for constellations was found to be 22% at worst, but the dynamic programming schedules were found at nearly four orders of magnitude better computational speed than integer programming. The algorithm can include cloud cover predictions, ground downlink windows or any other spatial, temporal or angular constraints into the orbital module and be integrated into planning tools for agile constellations. 相似文献