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751.
星间DOWRT中的相对论效应分析与修正 总被引:1,自引:1,他引:0
推导了双向单程测距与时间同步(DOWRT,Dual One-Way Ranging/Time Synchronization)的解耦方程,分析了空间动态下DOWRT法的计算方法及相对论效应在测距和时间比对中的影响,提出了带有相对论效应修正的DOWRT算法,最后分别仿真分析了低轨编队飞行卫星和导航星座中的距离与时间同步测量中相对论效应引起的误差.结果表明:卫星间采用DOWRT测量方法时,由相对论效应引起的低轨短基线编队飞行卫星间距离测量误差为米级、时间同步误差为亚皮秒级,而在导航星座测量中引起近百米级距离测量误差和高达微秒级的时间同步误差.因此为了实现导航卫星间高精度距离与时间同步测量,必须进行相对论效应修正. 相似文献
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753.
Since its invention by a race car driver Dan Gurney in 1960s, the Gurney flap has been used to enhance the aerodynamics performance of subsonic and supercritical airfoils, high-lift devices and delta wings. In order to take stock of recent research and development of Gurney flap, we have carried out a review of the characteristics and mechanisms of lift enhancement by the Gurney flap and its applications. Optimum design of the Gurney flap is also summarized in this paper. For the Gurney flap to be effective, it should be mounted at the trailing edge perpendicular to the chord line of airfoil or wing. The flap height must be of the order of local boundary layer thickness. For subsonic airfoils, an additional Gurney flap increases the pressure on the upstream surface of the Gurney flap, which increases the total pressure of the lower surface. At the same time, a long wake downstream of the flap containing a pair of counter-rotating vortices can delay or eliminate the flow separation near the trailing edge on the upper surface. Correspondingly, the total suction on the airfoil is increased. For supercritical airfoils, the lift enhancement of the Gurney flap mainly comes from its ability to shift the shock on the upper surface in the downstream. Applications of the Gurney flap to modern aircraft design are also discussed in this review. 相似文献
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755.
The Two Wide-angle Imaging Neutral-atom Spectrometers (TWINS) NASA Mission-of-Opportunity 总被引:3,自引:0,他引:3
D. J. McComas F. Allegrini J. Baldonado B. Blake P. C. Brandt J. Burch J. Clemmons W. Crain D. Delapp R. DeMajistre D. Everett H. Fahr L. Friesen H. Funsten J. Goldstein M. Gruntman R. Harbaugh R. Harper H. Henkel C. Holmlund G. Lay D. Mabry D. Mitchell U. Nass C. Pollock S. Pope M. Reno S. Ritzau E. Roelof E. Scime M. Sivjee R. Skoug T. S. Sotirelis M. Thomsen C. Urdiales P. Valek K. Viherkanto S. Weidner T. Ylikorpi M. Young J. Zoennchen 《Space Science Reviews》2009,142(1-4):157-231
Two Wide-angle Imaging Neutral-atom Spectrometers (TWINS) is a NASA Explorer Mission-of-Opportunity to stereoscopically image the Earth’s magnetosphere for the first time. TWINS extends our understanding of magnetospheric structure and processes by providing simultaneous Energetic Neutral Atom (ENA) imaging from two widely separated locations. TWINS observes ENAs from 1–100 keV with high angular (~4°×4°) and time (~1-minute) resolution. The TWINS Ly-α monitor measures the geocoronal hydrogen density to aid in ENA analysis while environmental sensors provide contemporaneous measurements of the local charged particle environments. By imaging ENAs with identical instruments from two widely spaced, high-altitude, high-inclination spacecraft, TWINS enables three-dimensional visualization of the large-scale structures and dynamics within the magnetosphere for the first time. This “instrument paper” documents the TWINS design, construction, calibration, and initial results. Finally, the appendix of this paper describes and documents the Southwest Research Institute (SwRI) instrument calibration facility; this facility was used for all TWINS instrument-level calibrations. 相似文献
756.
本文介绍了惯性组合标定“6位置12点采样”的编排方案,可补偿测试设备调平、对北误差的影响,测试过程简单合理。此外介绍了对组合性能有特殊意义的ωe、g自检及迭代求解方法,并以此作为求算标准偏差的依据。 相似文献
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758.
基于压力敏感漆(PSP)实验技术研究了具有双射流、圆孔和扇形孔的气膜冷却系统在主流湍流度为6%,吹风比分别为0.5,0.8,1.0,1.2和1.5时的冷却特性.圆孔平均气膜冷却效率在吹风比为0.8到1.5范围内逐渐降低;而双射流和扇形孔在整个实验范围内随吹风比的增大而升高,这表明双射流很好地抑制了射流与壁面的吹离.在同等条件下,双射流气膜冷却效率优于圆孔,而低于扇形孔.实验条件下的数值模拟结果清楚地表明了圆孔、双射流和扇形孔分别形成的肾形涡系、反肾形涡系和弱肾形涡系是形成各自气膜冷却特性的主要因素. 相似文献
759.
Jae-Ik Park Han-Earl ParkSang-Young Park Kyu-Hong Choi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
A relative navigation and formation control algorithm for satellite formation flying was developed, and a hardware-in-the-loop (HIL) simulation testbed was established and configured to evaluate this algorithm. The algorithm presented is a relative navigation estimation algorithm using double-difference carrier-phase and single-difference code measurements based on the extended Kalman filter (EKF). In addition, a state-dependent Riccati equation (SDRE) technique is utilized as a nonlinear controller for the formation control problem. The state-dependent coefficient (SDC) form is formulated to include nonlinearities in the relative dynamics. To evaluate the relative navigation and control algorithms developed, a closed-loop HIL testbed is configured. To demonstrate the performance of the testbed, a test formation flying scenario comprising formation acquisition and keeping in a low earth orbit (LEO) has been established. The relative navigation results from the closed-loop simulations show that a 3D RMS of 0.07 m can be achieved for position accuracy. The targeted leader–follower formation flying in the along-track separation of 100 m was maintained with a mean position error of approximately 0.2 m and a standard deviation of 0.9 m. The simulation results show that the HIL testbed is capable of successful demonstration of the GPS-based satellite autonomous formation flying mission. 相似文献
760.
为获得低温动态加载下老化后HTPB推进剂强度准则,开展了低温动态加载下不同热老化时间后HTPB推进剂单轴与准双轴拉伸试验,根据试验结果获得的力学性能参数,基于双剪强度理论构建了推进剂强度极限线及故障包络线。研究发现:随着温度的降低和热老化时间的延长,HTPB推进剂强度极限线范围变大,即推进剂强度增强;随着热老化时间的延长,HTPB推进剂故障包络线缩小,即推进剂抵抗破坏能力逐渐减弱。研究结果可为低温点火条件下战术导弹药柱结构完整性分析提供数据支持。 相似文献