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931.
932.
通过对其自主稳定回路及间隙描述函数频率特性的分析,对间隙装配调试及检测技术提出改进措施,并设计了测隙装置,完善了装配工艺. 相似文献
933.
针对隐式极限状态方程的可靠性分析,提出了一种基于失效域样本模拟的高效线抽样法。该法采用马尔可夫链来快速得到失效域中的条件样本,利用这些失效域中的样本可以得到线抽样的重要方向,并且这些样本还可以作为线抽样的样本,来得到隐式极限状态方程失效概率的估计值。由于该法可以较准确地得到线抽样方法的重要方向,因此线抽样的效率可以得到提高,另外失效域的样本又可以作为线抽样的样本,从而进一步降低所提方法的计算工作量。算例表明所提算法的计算精度和效率均高于传统线抽样方法。 相似文献
934.
Kugusheva A. D. Kalegaev V. V. Vlasova N. A. Petrov K. A. Bazilevskaya G. A. Makhmutov V. S. 《Cosmic Research》2021,59(6):446-455
Cosmic Research - The results of an analysis of the space–time characteristics and dynamics of precipitations of magnetospheric electrons with energies in the range from 0.1 to 0.7 MeV are... 相似文献
935.
Cosmic Research - An Erratum to this paper has been published: https://doi.org/10.1134/S0010952521120030 相似文献
936.
Rain.L 《中国航天(英文版)》2008,(1)
THE FOURTH BEIDOU NAVIGATION EXPERIMENTAL SATELLITE LAUNCHED The fourth Beidou experimental navigation satellite was launched into snace aton a LM-3A launch vehicle at Xichang Satellite Launch Center on February 3 at 00:28(Beijing Time).24 minutes later,the satellite separated from the launch vehicle and 相似文献
937.
Rain.L 《中国航天(英文版)》2008,(2)
FY-3A,the first satellite of China's new generation of polar-orbiting meteorological satellites,was launched into space atop a modified LM-4C launch vehicle.The satellite separated from the rocket 19 minutes after the takeoff.Flying at an altitude of 807km with an inclination of 98.8 degrees,the satellite circles in polar orbit 14 times everyday,covering the whole globe twice a day. FY-3A has a design lifetime of three years.Weighing 2295kg,the three-axis stabilized satellite is equipped with 11 remote s... 相似文献
938.
The mass loss of spacecraft polyimide films under the action of atomic oxygen and vacuum ultraviolet radiation 总被引:1,自引:0,他引:1
The threshold values of the annual fluence of atomic oxygen (F AO ≈ 1020 cm?2), as well as the ratios of the energy-flux density of vacuum ultraviolet radiation of the solar spectrum to the flux density of atomic oxygen (Φ ν /Φ AO ≈ 8 × 10?15 mJ) were determined, which are characterized the influence of the synergistic effect on the mass loss of Kapton-H, PM-A, and PM-1E polyimide films, which are spacecraft materials. 相似文献
939.
940.
T. Hopf S. KumarW.J. Karl W.T. Pike 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
It is often necessary for space-borne instrumentation to cope with substantial levels of shock acceleration both in the initial launch phase, as well as during entry, descent and landing in the case of planetary exploration. Current plans for a new generation of penetrator-based space missions will subject the associated on-board instrumentation to far greater levels of shock, and ways must therefore be found to either ruggedize or else protect any sensitive components during the impact phase. In this paper, we present an innovative method of shock protection that is suited for use in a number of planetary environments, based upon the temporary encapsulation of said components within a waxy solid which may then be sublimated to return the instrument back to its normal operation. We have tested this method experimentally using micromachined silicon suspensions under applied shock loads of up to 15,000g, and found that these were able to survive without incurring damage. Furthermore, quality factor measurements undertaken on these suspensions indicate that their mechanical performance remains unaffected by the encapsulation and subsequent sublimation process. 相似文献