全文获取类型
收费全文 | 472篇 |
免费 | 33篇 |
国内免费 | 35篇 |
专业分类
航空 | 338篇 |
航天技术 | 76篇 |
综合类 | 27篇 |
航天 | 99篇 |
出版年
2022年 | 3篇 |
2021年 | 13篇 |
2020年 | 7篇 |
2019年 | 6篇 |
2018年 | 74篇 |
2017年 | 42篇 |
2016年 | 10篇 |
2015年 | 12篇 |
2014年 | 20篇 |
2013年 | 17篇 |
2012年 | 7篇 |
2011年 | 32篇 |
2010年 | 11篇 |
2009年 | 15篇 |
2008年 | 12篇 |
2007年 | 11篇 |
2006年 | 9篇 |
2005年 | 23篇 |
2004年 | 17篇 |
2003年 | 34篇 |
2002年 | 41篇 |
2001年 | 16篇 |
2000年 | 6篇 |
1999年 | 9篇 |
1997年 | 4篇 |
1996年 | 5篇 |
1995年 | 6篇 |
1994年 | 6篇 |
1993年 | 12篇 |
1992年 | 3篇 |
1991年 | 2篇 |
1989年 | 6篇 |
1988年 | 2篇 |
1986年 | 3篇 |
1985年 | 3篇 |
1984年 | 3篇 |
1981年 | 2篇 |
1980年 | 2篇 |
1978年 | 3篇 |
1975年 | 4篇 |
1973年 | 1篇 |
1972年 | 6篇 |
1971年 | 1篇 |
1970年 | 3篇 |
1969年 | 1篇 |
1968年 | 1篇 |
1967年 | 4篇 |
1966年 | 2篇 |
1963年 | 2篇 |
1962年 | 1篇 |
排序方式: 共有540条查询结果,搜索用时 15 毫秒
51.
针对深空测控通信中GMSK体制非相干解调损失较大的难点,提出了一种改进的GMSK信号非相干维特比解调算法。通过分析相位状态网格图中相位转移规律,建立理论仿真模型。通过原理样机的研制和测试,实测数据表明:该算法具有解调损失低、实现复杂度适中的优点;相比于理论的最佳相干解调算法,在误码率1×10 -4 量级下,实测仅损失0.6 dB。目前该算法已应用于国内某深空测控通信系统GMSK体制基带设备中,并成功解调出欧空局Herschel–Planck卫星数据。 相似文献
52.
One of the most important problems for performing a good design of the spacecraft attitude control law is connected to its robustness when some uncertainty parameters are present on the inertial and/or on the elastic characteristics of a satellite. These uncertainties are generally intrinsic on the modeling of complex structures and in the case of large flexible structures they can be also attributed to secondary effects associated to the elasticity. One of the most interesting issues in modeling large flexible space structures is associated to the evaluation of the inertia tensor which in general depends not only on the geometric ‘fixed’ characteristic of the satellite but also on its elastic displacements which of course in turn modify the ‘shape’ of the satellite. Usually these terms can be considered of a second order of magnitude if compared with the ones associated to the rigid part of a structure. However the increasing demand on the dimension of satellites due to the presence for instance of very large solar arrays (necessary to generate power) and/or large antennas has the necessity to investigate their effects on their global dynamic behavior in more details as a consequence. In the present paper a methodology based on classical Lagrangian approach coupled with a standard Finite Element tool has been used to derive the full dynamic equations of an orbiting flexible satellite under the actions of gravity, gravity gradient forces and attitude control. A particular attention has been paid to the study of the effects of flexibility on the inertial terms of the spacecraft which, as well known, influence its attitude dynamic behavior. Furthermore the effects of the attitude control authority and its robustness to the uncertainties on inertial and elastic parameters has been investigated and discussed. 相似文献
53.
54.
针对ORU在轨更换任务,首先推导了空间机械臂末端自由、末端与环境接触等情况下的动力学方程,并提出了相应的接触力计算方法;其次,改进了传统的R\|C控制方法,采用加权选择矩阵代替原有的选择矩阵,实现了力控制与位置控制之间的平滑切换;最后,开发了基于Matlab/Simulink的闭环控制仿真系统,该系统由多体动力学、接触动力学、轨迹规划、力/位混合控制、3D显示等模块组成。利用该系统开展了ORU转移与安装过程的闭环控制仿真,仿真结果校验了所提方法的有效性。 相似文献
55.
Soybean cultivar selection for Bioregenerative Life Support Systems (BLSSs) – Hydroponic cultivation
R. Paradiso R. Buonomo V. De Micco G. Aronne M. Palermo G. Barbieri S. De Pascale 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
Four soybean cultivars (‘Atlantic’, ‘Cresir’, ‘Pr91m10’ and ‘Regir’), selected through a theoretical procedure as suitable for cultivation in BLSS, were evaluated in terms of growth and production. Germination percentage and Mean Germination Time (MGT) were measured. Plants were cultivated in a growth chamber equipped with a recirculating hydroponic system (Nutrient Film Technique). Cultivation was performed under controlled environmental conditions (12 h photoperiod, light intensity 350 μmol m−2 s−1, temperature regime 26/20 °C light/dark, relative humidity 65–75%). Fertigation was performed with a standard Hoagland solution, modified for soybean specific requirements, and EC and pH were kept at 2.0 dS m−1 and 5.5 respectively. 相似文献
56.
针对火星飞行器探测需求,提出了一种共轴双旋翼式火星飞行器,基于计算流体力学方法优选了桨叶翼型、平面形状和扭转角等结构参数,基于叶素动量理论建立了旋翼气动力学模型,利用数值模拟方法选择了旋翼转速、旋翼间距和桨叶安装角等飞行参数,设计了原理样机"火星飞鸟-I"的结构与控制系统。构建了火星大气环境模拟器和重力补偿与运动约束装置,开展了模拟火星环境下旋翼式飞行器地面飞行试验,验证了共轴双旋翼式火星飞行器的推进性能,展望了旋翼式火星飞行器技术的发展方向。研究成果对我国开展的火星探测工程具有重要借鉴价值。 相似文献
57.
F. De Tiberis L. Simone D. Gelfusa P. Simone R. Viola A. Santoni O. Cocciolillo M. Ziarelli F. Barletta N. Salerno M. Maffei V. Nanni 《Acta Astronautica》2011,68(5-6):591-598
This paper reports the main characteristics of the deep space transponder (DST) equipment that has been designed, developed and tested by Thales Alenia Space—Italy (TAS-I) for the European Space Agency (ESA) BepiColombo mission to Mercury. 相似文献
58.
Hugh S. Hudson 《Space Science Reviews》2011,158(1):5-41
This article broadly reviews our knowledge of solar flares. There is a particular focus on their global properties, as opposed
to the microphysics such as that needed for magnetic reconnection or particle acceleration as such. Indeed solar flares will
always remain in the domain of remote sensing, so we cannot observe the microscales directly and must understand the basic
physics entirely via the global properties plus theoretical inference. The global observables include the general energetics—radiation
in flares and mass loss in coronal mass ejections (CMEs)—and the formation of different kinds of ejection and global wave
disturbance: the type II radio-burst exciter, the Moreton wave, the EIT “wave”, and the “sunquake” acoustic waves in the solar
interior. Flare radiation and CME kinetic energy can have comparable magnitudes, of order 1032 erg each for an X-class event, with the bulk of the radiant energy in the visible-UV continuum. We argue that the impulsive
phase of the flare dominates the energetics of all of these manifestations, and also point out that energy and momentum in
this phase largely reside in the electromagnetic field, not in the observable plasma. 相似文献
59.
60.
研究了一种基于深度强化学习理论的制导控制一体化算法。不同于传统的制导控制一体化算法和制导控制回路分开设计的方法,基于深度强化学习理论的制导控制一体化算法利用深度学习强化算法生成一个智能体,智能体根据导弹的观测量生成舵偏角控制指令准确拦截目标。首先将制导控制问题转化为一个马尔可夫决策过程,然后提出了一个权衡制导精度、能量损耗和飞行时间的奖励函数,将制导控制问题转化到强化学习问题的框架中。最后采用深度确定性策略梯度算法,求解提出的强化学习问题,训练得到制导控制智能体,智能体根据导弹观测量生成舵偏角指令。通过进行大量的数值模拟,验证了提出的制导控制一体化算法的有效性和鲁棒性。 相似文献