全文获取类型
收费全文 | 18494篇 |
免费 | 84篇 |
国内免费 | 152篇 |
专业分类
航空 | 10054篇 |
航天技术 | 5477篇 |
综合类 | 278篇 |
航天 | 2921篇 |
出版年
2021年 | 162篇 |
2018年 | 219篇 |
2016年 | 162篇 |
2014年 | 446篇 |
2013年 | 523篇 |
2012年 | 435篇 |
2011年 | 602篇 |
2010年 | 435篇 |
2009年 | 769篇 |
2008年 | 823篇 |
2007年 | 379篇 |
2006年 | 439篇 |
2005年 | 410篇 |
2004年 | 451篇 |
2003年 | 536篇 |
2002年 | 484篇 |
2001年 | 582篇 |
2000年 | 376篇 |
1999年 | 462篇 |
1998年 | 447篇 |
1997年 | 331篇 |
1996年 | 401篇 |
1995年 | 469篇 |
1994年 | 455篇 |
1993年 | 361篇 |
1992年 | 337篇 |
1991年 | 253篇 |
1990年 | 246篇 |
1989年 | 417篇 |
1988年 | 210篇 |
1987年 | 239篇 |
1986年 | 237篇 |
1985年 | 635篇 |
1984年 | 524篇 |
1983年 | 411篇 |
1982年 | 488篇 |
1981年 | 612篇 |
1980年 | 246篇 |
1979年 | 194篇 |
1978年 | 189篇 |
1977年 | 147篇 |
1976年 | 155篇 |
1975年 | 192篇 |
1974年 | 180篇 |
1973年 | 161篇 |
1972年 | 188篇 |
1971年 | 148篇 |
1970年 | 143篇 |
1969年 | 147篇 |
1967年 | 142篇 |
排序方式: 共有10000条查询结果,搜索用时 31 毫秒
1.
钝头体激波诱导燃烧是爆震研究的一个基本问题。针对化学恰当量比的H2/Air预混气在Ma=4.79和Ma=6.46时的激波诱导燃烧现象开展数值模拟研究,采用基于有限体积法的块结构自适应网格加密程序AMROC对带化学反应源项的轴对称Euler方程解耦求解,考察了数值模拟中不同形式的MUSCL重构格式、限制器类型以及化学反应机理等重要因素对模拟结果的影响。结果表明,程序能够根据设定的加密判据较好地实现网格自适应加密,减小总网格量,实现高效数值模拟。通过与实验数据的对比,表明非定常激波诱导燃烧算例的准确程度不仅取决于化学反应机理,也取决于限制器类型,而采用两种不同形式的MUSCL重构格式获得的振荡频率则几乎一致,与试验结果的误差分别为1.17%和0.97%。模拟对比经典的Jachimowski机理和近年来新发展的几种包含压力相关反应步的氢/氧反应机理,模拟结果表明:对于Ma=4.79时的非定常激波诱导燃烧模拟,经典的Jachimowski机理仍然是能够给出与实验结果最接近的反应机理;而对于Ma=6.46时的定常激波诱导燃烧模拟,几种反应机理均能给出与实验吻合较好的结果。 相似文献
2.
Houman Hakima M. Reza Emami 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(7):2151-2171
This paper presents the mission design for a CubeSat-based active debris removal approach intended for transferring sizable debris objects from low-Earth orbit to a deorbit altitude of 100 km. The mission consists of a mothership spacecraft that carries and deploys several debris-removing nanosatellites, called Deorbiter CubeSats. Each Deorbiter is designed based on the utilization of an eight-unit CubeSat form factor and commercially-available components with significant flight heritage. The mothership spacecraft delivers Deorbiter CubeSats to the vicinity of a predetermined target debris, through performing a long-range rendezvous maneuver. Through a formation flying maneuver, the mothership then performs in-situ measurements of debris shape and orbital state. Upon release from the mothership, each Deorbiter CubeSat proceeds to performing a rendezvous and attachment maneuver with a debris object. Once attached to the debris, the CubeSat performs a detumbling maneuver, by which the residual angular momentum of the CubeSat-debris system is dumped using Deorbiter’s onboard reaction wheels. After stabilizing the attitude motion of the combined Deorbiter-debris system, the CubeSat proceeds to performing a deorbiting maneuver, i.e., reducing system’s altitude so much so that the bodies disintegrate and burn up due to atmospheric drag, typically at around 100 km above the Earth surface. The attitude and orbital maneuvers that are planned for the mission are described, both for the mothership and Deorbiter CubeSat. The performance of each spacecraft during their operations is investigated, using the actual performance specifications of the onboard components. The viability of the proposed debris removal approach is discussed in light of the results. 相似文献
3.
区域导航星座能够以较低成本和较短时间获得目标区域导航能力,且地球同步轨道是构建非极区区域导航星座的重要轨道类型。提出一种基于GEO(地球静止轨道)和IGSO(倾斜地球同步轨道)的区域导航星座设计方法。基于星下点轨迹特性构造对称星座设计参数和优化参数集,并考虑地球扁率长期摄动影响,计算星座轨道参数。以导航服务区的统计GDOP(几何精度因子)为目标函数,利用差分进化算法构建星座优化模型。以印度IRNSS的7星星座为例,仿真检验了设计和优化算法的正确性,讨论了IRNSS星座优化构型和轨道类型选取。本方法采用的对称星座设计参数少,能够提升GEO/IGSO混合区域导航星座的全局优化效率,为后续非对称星座快速提供最佳星数和构型设计。 相似文献
4.
M. Naim A. Ali Pacha C. Serief 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(7):2077-2103
With the rapid growth of the number of Earth observation satellite (EOS) supporting critical applications, it is required to improve the security techniques to protect the sensitive data and images during the transmission between the satellites and the ground stations. This paper introduces a new satellite image encryption algorithm based on the Linear Feedback Shift Register (LFSR) generator, SHA 512 hash function, hyperchaotic systems, and Josephus problem. LFSR generates a matrix that is used to construct the 512-bits value of the hash function. These bits are used to set the initial values and parameters of the proposed encryption algorithm. Firstly, the six dimensions (6-D) hyperchaotic system is divided into three parts, where every two equations are considered as one part. Secondly, the 1-D hyperchaotic logistic-tent system is considered as the controller to select one part. The selected part is used to generate a matrix that is XORed with the original image. Thirdly, the scrambling operation by Josephus sequences is applied to the output of the previous step by scrambling the rows and the columns according to the selected part to produce the pre-encrypted image. Finally, if the number of iterations is less than the required number which is considered as a parameter of the secret key, the previous operations will be repeated in the pre-encrypted image; otherwise, the pre-encrypted image is considered as the final cipher image. Experimental and analyses results show that the proposed algorithm has good performance in terms of high level of security, large enough key-space, tolerance to Single Event Upsets (SEU) as well as low time complexity. 相似文献
5.
Irina V. Chernyakina 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(9):2844-2854
Ballistic design of solar sailing missions in the solar system is composed of defining the design parameters, the control programs, and the trajectories that provide performance goals of a flight. The use of a solar sail spacecraft imposes specific restrictions on mission parameters that include the degradation limit on the flight duration, the maximum temperature of solar sail's surface, the minimum distance from the Sun, the maximum angular velocity of the spacecraft's rotation and others.Many authors considered the impact of these restrictions on the design of the mission separately, but they used a sophisticated method of finding the exact optimal motion control or applied the most straightforward laws of motion control. This paper uses local-optimal control laws at the complete mathematical models of motion and functioning of solar sail spacecraft to describe a technique of designing interplanetary missions. The described method avoids the need to obtain an accurate optimal solution to the control problem and does not cause significant computational difficulties. 相似文献
6.
The results of numerical solution of the wave equations for the oblique incidence of whistling electromagnetic waves upon the night ionosphere from above have been obtained and analyzed. In the studied region of altitudes, within the wavelength scale, charged particle concentration varies drastically, and damping caused by collisions between the charged and neutral particles decreases considerably. Below, the sharp lower boundary of the ionosphere, the refractive index of the whistler wave approaches unity, and plasma turbulence transform into atmospheric electromagnetic waves. The dependences of the whistler reflection factor are found in terms of energy and horizontal magnetic component of the electromagnetic wave near the Earth’s surface on the frequency and the wave vector transverse component for the plain-layered medium model at two values of latitude. Strong dependences have been found on the wave angle of incidence and frequency. At rather small angles of incidence, the wave disturbances reach the Earth’s surface, and the module of reflection coefficient logarithm is in the range of 0.4–1. At large angles of incidence, the reflection coefficient module varies over a wide range depending on specific conditions. The obtained results explain the absence of oscillation modes of plasma magnetosphere maser in the night magnetosphere. 相似文献
7.
G. Uma P.S. Brahmanandam V.K.D. Srinivasu D.S.V.V.D. Prasad P.V.S. Rama Rao 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(7):1736-1743
In this research, it is presented the daytime amplitude scintillations recorded at VHF frequency (244 MHz) at an Indian low-latitude station, Waltair (17.7°N, 83.3°E) during seven continuous years (1997–2003). Contrary to the nighttime scintillation seasonal trends, the occurrence of daytime scintillations maximizes during summer followed by winter and the equinox seasons. The fade depths, scintillation indices and the patch durations of daytime scintillations are meager when compared with their nighttime counterparts. A co-located digital high frequency (HF) ionosonde radar confirms the presence of sporadic (Es) layers when daytime scintillations are observed. The presence of daytime scintillations is evident when the critical frequency of the Es-layer (foEs) is ≥4 MHz and Es-layers are characterized by a highly diffuse range spread Es echoes as can be seen on ionograms. It is surmised that the gradient drift instability (GDI) seems to be the possible mechanism for the generation of these daytime scintillations. It is quite likely that the spread Es-F-layer coupling is done through polarization electric fields (Ep) that develop inside the destabilized patches of sporadic E layers, which are mapped up to the F region along the field lines as to initiate the daytime scintillations through the GDI mechanism. Further, the presence of additional stratification of ionosphere F-layer, popularly known as the F3-layer, is observed on ionograms once the Es-layers and daytime scintillations are ceased. 相似文献
8.
Alireza A. Ardalan Iraj Jazireeyan Naser Abdi Mohammad-Hadi Rezvani 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(6):1537-1545
Performance of SARAL/AltiKa mission has been evaluated within 2016 altimeter calibration/validation framework in Persian Gulf through three campaigns conducted in the offshore waters of Sajafi, Imam Hassan and Kangan Ports, while the altimeter overflew the passes 470, 111 and 25 on 13 Feb, 7 March and 17 June 2016, respectively. As the preparation, a lightweight buoy was equipped with a GNSS receiver/choke-ring antenna and a MEMS-based IMU to measure independent datasets in the field operations. To obtain accurate sea surface height (SSH) time series, the offset of the onboard antenna from the equilibrium sea level was predetermined through surveying operations as the buoy was deploying in the onshore waters of Kangan Port. Accordingly, the double-difference carrier phase observations have been processed via the Bernese GPS Software v. 5.0 so as to provide the GNSS-derived time series at the comparison points of the calibration campaigns, once the disturbing effects due to the platform tilt and heave have been eliminated. Owing to comparing of the SSH time series and the associating altimetry 1?Hz GDR-T datasets, the calibration/validation of the SARAL/AltiKa has been performed in the both cases of radiometer and ECMWF wet troposphere corrections so as to identify potential land contamination. An agreement of the present findings in comparison with those attained in other international calibrations sites confirms the promising feasibility of Persian Gulf as a new dedicated site for calibration/validation of ongoing and future altimetry missions. 相似文献
9.
In the paper, the problem of designing interplanetary trajectories with several swing-bys and deep-space maneuvers is solved using the method of virtual trajectories developed by the authors. The algorithms for the calculation of both heliocentric and planetocentric trajectory arcs are presented, including the case of resonant trajectories. The results of applying the method of virtual trajectories to the problem of designing an interplanetary transfer to Jupiter are given and compared with the baseline trajectories for the Juno, Europa Clipper, and Laplace missions. 相似文献
10.
The present study investigated cognitive map development in multilevel built environments. Three experiments were conducted in complex virtual buildings to examine the effects of five between-floor structural factors that may impede the accuracy of humans’ ability to build multilevel cognitive maps. Results from Experiments 1 and 2 (of three experiments) revealed that difficulties in developing multilevel cognitive maps are not solely caused by the z-axis offset, as is suggested in the literature, but are due to the factorial combination of a between-floor overlap and a z-axis offset. Results from Experiment 2 showed that this process becomes substantially more difficult when the reference directions between different floors have an angular offset from each other. Finally, results from Experiment 3 demonstrated that confusing between-floor heading shifts in aligned buildings did not make it reliably harder to build multilevel cognitive maps. The implications of these findings are discussed in terms of theories of mental representations in multilayered three-dimensional spaces, as well as for architectural design. 相似文献