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601.
针对立方星轨道机动能力约束,提出一种基于相对轨道根数动力学模型的多脉冲机动规划算法。对于相对轨道面内各分量之间的控制耦合问题,基于“先控制相对形状、后修正迹向距离”的策略,提出了满足速度增量约束的多脉冲机动规划算法;分析了近地轨道 J 2 摄动和大气阻力摄动对相对轨道的影响,并基于线性化的状态转移模型提出了迭代优化策略,以降低立方星在摄动影响下的轨道机动误差。仿真结果表明,所提出的多脉冲机动规划算法在不同任务条件下均可获得有效的机动规划,迭代优化策略可有效地提高终点位置的精度,在基于高精度轨道递推搭建的任务仿真中也验证了算法的有效性,可用于立方星编队构建和重构任务。 相似文献
602.
Jianguo Yan Fei Li Qinghui Liu Jinsong Ping Zhen Zhong Jinling Li 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
High accuracy differenced phase delay can be obtained by observing multiple point frequencies of two spacecraft using the same beam Very Long Baseline Interferometry (VLBI) technology. Its contribution in lunar spacecraft precision orbit determination has been performed during the Japanese lunar exploration mission SELENE. In consideration that there will be an orbiter and a return capsule flying around the moon during the Chinese lunar exploration future mission Chang’E-3, the contributions of the same beam VLBI in spacecraft precision orbit determination and lunar gravity field solution have been investigated. Our results show that the accuracy of precision orbit determination can be improved more than one order of magnitude after including the same beam VLBI measurements. There are significant improvements in accuracy of low and medium degree coefficients of lunar gravity field model obtained from combination of two way range and Doppler and the same beam VLBI measurements than the one that only uses two way range and Doppler data, and the accuracy of precision orbit determination can reach meter level. 相似文献
603.
In this paper, the problem of fast low-energy halo-to-halo transfers between Sun–planet systems is discussed under ephemeris constraints. According to the structure of an invariant manifold, employing an invariant manifold and planetary gravity assist to save fuel consumption is analyzed from the view of orbital energy. Then, a pseudo-manifold is introduced to replace the invariant manifold in such a way that more transfer opportunities are allowed. Fast escape and capture can be achieved along the pseudo-manifold. Furthermore, a global searching method that is based on patched-models is proposed to find an appropriate transfer trajectory. In this searching method, the trajectory is divided into several segments that can be designed under simple dynamical models, and an analytical algorithm is developed for connecting the segments. Earth–Mars and Earth–Venus halo-to-halo transfers are designed to demonstrate the proposed approach. Numerical results show that the transfers that combine the pseudo-manifolds and planetary gravity assist can offer significant fuel consumption and flight time savings over traditional transfer schemes. 相似文献
604.
我国中继卫星系统在交会对接任务中的应用 总被引:1,自引:0,他引:1
我国中继卫星系统在交会对接任务中得到了成功应用,显著提升了测控通信覆盖率,充分体现了中继卫星系统在交会对接任务测控通信中发挥的重要作用.结合中继卫星系统特点,分析交会对接任务对中继卫星系统的任务需求;探讨了中继卫星捕获跟踪用户目标、对用户目标测定轨、着陆场直升机缝隙通信等关键技术;最后总结了中继卫星系统抗雨衰影响、多目标支持能力、应急支持能力等方面的经验做法,并提出了后续改进和完善的建议. 相似文献
605.
基于小偏差理论,推导了三体动力学模型的误差线性模型,并将此假设下的控制归纳为终端固定的有限时间调节器问题。在此基础上,进一步利用该最优控制方法推导了晕轨道周期内的连续小推力控制方案,验证了控制加速度及状态量的收敛。同时针对整周期控制方式在超调后状态量收敛速度慢的问题,通过分段连续推力控制模式(Sectional Continuous Thrust Control,SCTC)来近似瞬时脉冲推力控制模式,给出了最短分段控制时间的计算方法。实验表明,SCTC模式加快了轨道状态的收敛速度。对于km级入轨偏差,通过1次控制即可使实际轨道收敛至标称轨道。 相似文献
606.
针对推扫电荷耦合器件(CCD)相机成像特点,根据太阳同步回归轨道卫星轨道设计方法,给出了CCD光学对地观测卫星的轨道高度设计方案,并分析了所设计轨道的地面光照条件。结果表明设计方案合理可行。 相似文献
607.
608.
A. von Engeln Y. AndresC. Marquardt F. Sancho 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
The GRAS radio occultation instrument is flying on Metop-A and belongs to the EPS (EUMETSAT Polar System). GRAS observes GPS satellites in occultation. Within this work, validation of GRAS closed-loop bending angle data against co-located ECMWF profiles extracted from model fields and occultations from the COSMIC constellation of radio occultation instruments is shown. Results confirm the high data quality and robustness, where GRAS shows lower bending angle noise against ECMWF than COSMIC and in terms of occultations per day, one GRAS ≈ two COSMIC satellites. This is partly due to the operational setup of EPS. For the investigation we focus on two observation periods where updates in the ECMWF (March 2009) and COSMIC processing (October 2009) have improved the statistics further. Bending angles biases agree to within 0.5% against ECMWF and to within 0.1% against COSMIC after the updates for altitudes between 8 and 40 km. In addition, we also analyze the impact of the Metop orbit processing on the derived GRAS bending angle data, where different GPS and Metop orbit solutions are analyzed. Results show that a batch based orbit processing would improve in particular the bending angle bias behavior at higher altitudes. Requirements for the operational processing of GRAS data are briefly outlined, options to ease the use of other positioning system satellites in the near future are discussed. A simplified analysis on the observation of several of these systems, e.g. GPS and Galileo, from one platform shows that about 16% of occultations are found within 300 km, ±3 h, thus providing similar information. A constellation of 2 GRAS like instruments would have only about 10% close-by. 相似文献
609.
美国载人航天商业运输的发展 总被引:2,自引:1,他引:1
研究了美国载人航天商业运输的发展现状和趋势。美国在取消星座计划之后,实施商业乘员和货物项目,将依靠商业运输器实现"国际空间站"的乘员和货物运输,以缩短"后航天飞机"时代(航天飞机退役后)运输的断档期。美国商业乘员和货物项目包括商业轨道运输服务(COTS)计划、商业再补给服务(CRS)计划和商业乘员开发(CCDev)计划... 相似文献
610.
针对月球探测中月面上升和下降段的实时轨道确定问题,提出基于三向测量的实时自适应当前统计方法。首先,通过自适应当前统计模型描述探测器月面上升下降过程,其次,综合利用三向数据进行测量更新,最后,通过UKF滤波算法完成实时轨道确定。由于自适应当前统计模型具有良好的适应性,该方法能对探测器月面上升和下降段进行有效定位,通过嫦娥五号探测器实际上升和下降过程数据进行测试,结果表明,文章提出的基于三向测量的实时自适应当前统计方法比传统的几何定位方法具有更好的抗差性,对深空目标探测具有一定的工程应用价值。 相似文献