全文获取类型
收费全文 | 523篇 |
免费 | 108篇 |
国内免费 | 90篇 |
专业分类
航空 | 335篇 |
航天技术 | 177篇 |
综合类 | 50篇 |
航天 | 159篇 |
出版年
2023年 | 13篇 |
2022年 | 26篇 |
2021年 | 21篇 |
2020年 | 30篇 |
2019年 | 26篇 |
2018年 | 22篇 |
2017年 | 32篇 |
2016年 | 40篇 |
2015年 | 26篇 |
2014年 | 32篇 |
2013年 | 36篇 |
2012年 | 42篇 |
2011年 | 47篇 |
2010年 | 32篇 |
2009年 | 29篇 |
2008年 | 20篇 |
2007年 | 27篇 |
2006年 | 34篇 |
2005年 | 29篇 |
2004年 | 22篇 |
2003年 | 15篇 |
2002年 | 12篇 |
2001年 | 14篇 |
2000年 | 7篇 |
1999年 | 11篇 |
1998年 | 15篇 |
1997年 | 7篇 |
1996年 | 7篇 |
1995年 | 15篇 |
1994年 | 3篇 |
1993年 | 1篇 |
1992年 | 7篇 |
1991年 | 9篇 |
1990年 | 7篇 |
1989年 | 2篇 |
1988年 | 1篇 |
1984年 | 2篇 |
排序方式: 共有721条查询结果,搜索用时 15 毫秒
711.
There exist a large class of acoustic sources which have an underlying periodic phenomenon. Unlike the well-studied Bearings-Only Tracking(BOT) of an aperiodic acoustic source,this paper considers the problem of tracking a periodic acoustic source. For periodic acoustic tracking, the signal emission time is known. However, the true measurement reception time is unknown because it is corrupted by noise due to propagation delay. We augment the sensor’s signal reception time onto bearing measuremen... 相似文献
712.
卫星导航有源接收天线的噪声温度是导航接收系统的关键技术指标之一。针对卫星导航有源天线总体噪声温度无法测量的问题,研制了两台口面型噪声源,口面噪声源主要由辐射体、辐射体物理温度控制和温度测量仪等组成。两个口面噪声源在L和S波段分别提供高低温标准噪声温度,采用Y系数测量方法测量有源接收天线的总体天线噪声温度。测量了某卫星导航有源天线的总噪声温度,在(1.19~1.29) GHz的频率范围内,中心频率1.24 GHz上噪声温度测量结果为206 K,但是在1.266 GHz频率点上噪声温度测量大于4 000 K,说明天线与滤波器之间、滤波器与放大器之间存在设计问题或其它问题,体现出测量有源天线噪声温度的必要性。 相似文献
713.
《中国航空学报》2022,35(8):7-11
An active, compact, wideband, receiving filtenna with power adaptation for space-limited wireless platforms is presented. By organically combining a filtering antenna and a Variable Gain Amplifier (VGA), the proposed co-designed active filtenna is achieved. Its power adaptation is empowered by controlling gain of the VGA unit. A demonstrated prototype with a compact overall size is fabricated, assembled and measured. Good performances are achieved. Furthermore, in any condition, the proposed active filtenna displays outstanding impedance matching (|S11| < ?10 dB) and high passband skirt selectivity at upper and lower stopbands (Selectivity ≥ 170 dB/GHz). 相似文献
714.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(3):1711-1720
The active spacecraft potential control (ASPOC) system developed in the 1990s emits positive ions to neutralise the spacecraft potential, such as used in several missions like Geotail, Equator-S, Cluster, Doublestar and MMS. With the experience gained, the next generation of the active spacecraft potential control (ASPOC-NG) instrument has been developed over the last three years. Thereby, three emission technologies were tested including Liquid Metal Ion Source (LMIS), Liquid Metal Electron Source (LMES) and Solid Metal Electron Source (SMES). The development of the emitter module by FOTEC and the corresponding electronics control unit by IWF is presented. Optimisations were carried out with the focus on the reduction of mass and power consumption to comply with the requirements of future scientific missions. Coupling tests of the modules and the electronics control unit were performed including range, accuracy and lifetime tests. Both ASPOC-NG instruments for positive and negative charge compensation and their performance values show excellent results. 相似文献
715.
基于PSK调制的数字通信系统在无线通信工程实践中有着广泛的应用,由于受到各种条件的限制,从实际工程系统接收到的PSK数字通信信号在教学科研中不易获得,而PSK调制仿真数据则可以自己产生。在掌握通信原理和仿真技术的基础上利用Matlab实现对BPSK、DPSK、QPSK、DQPSK、8PSK、π/4-DQPSK、OQPSK等数字通信信号源的模拟仿真,可对调制体制、工作频率、传输码率、采样频率、信道特征等参数进行灵活设置,并按要求生成规定格式的DAT数据文件,可作为调制方式识别软件的训练和测试样本。结合模方谱、平方谱、四次方谱、八次方谱等谱线参数特征,同时结合星座图和眼图进行基于PSK调制的数字通信信号的调制体制判别和验证。 相似文献
716.
为提高盲源分离算法在振动源数目估计问题中的噪声鲁棒性,提出了一种基于密度峰值聚类的欠定盲源分离算法。对预处理后的信号提取单源点,通过密度峰值聚类对单源点进行聚类得到混合矩阵的估计值。通过基于压缩感知模型对源信号进行重构,得到分离信号。为验证所提算法分离准确性和噪声鲁棒性,用所提算法对不同信噪比下的仿真信号进行分离,结果显示:在信噪比不低于4 dB时,所提算法均可以准确分离出源信号,算法的准确性和鲁棒性得到验证。设计旋转部件故障诊断试验台对所提算法在实际应用中的有效性进行验证,对实测复合故障振动信号进行分离,试验结果表明该算法成功分离出观测信号中的锥齿轮和行星齿轮单一故障特征,有助于工程中旋转部件故障诊断。 相似文献
717.
718.
719.
《中国航空学报》2023,36(2):29-40
Due to the pneumatic heating and combustion effect, the scramjet engine of hypersonic vehicle faces high temperature challenge. It is necessary to comprehensively consider its thermal management and power generation together. A new Power and Thermal Management System (PTMS) combined with Supercritical Carbon Dioxide (SCO2) closed Brayton cycle and fuel vapor turbine is proposed and discussed in this paper. The new PTMS can meet the cooling requirement of hypersonic vehicle at Mach number 6–7, and avoid the coking and scrapping in the scramjet cooling channels. Compared with the PTMS only based on fuel vapor turbine, the new PTMS utilizes the waste heat of scramjet to generate more electricity. In addition, it can reduce the use of fuel sink for cooling, and the additional weight penalty can be compensated for long endurance hypersonic flight. 相似文献
720.