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991.
G. Huang Q. ZhangH. Li W. Fu 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Over 60% clocks on board of the GPS satellites are working longer than their designed life. Therefore realizing their stabilities in a long time scales is essential to GPS navigation and positioning plus IGS time scale maintaining. IGS clock products from 2001 to 2010 are used to analyze the GPS satellite clock qualities such as frequency stabilities and clock noise level. We find out that for the clocks of Block IIA satellites the frequency stabilities and clock noise are 10 times worse than that of the Block IIR and IIR-M satellites. Moreover, the linear relationships between frequency stabilities and clock residuals have been deduced with an accuracy of better than 0.02 ns. Specially, it is noticed that the clock of the PRN27 is instable and the relationship between the frequency stability and residuals is at least a quadratic curve. Therefore, we suggested that GPS satellite clocks should be weighted by their quality levels in application, and the observations of the Block IIA should not be used for real-time positioning which required precision better than one meter. 相似文献
992.
Xiao-tian Zhang Guang-hui Jia Hai Huang 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Breakup model is the key area of space debris environment modeling. NASA standard breakup model is currently the most widely used for general-purpose. It is a statistical model found based on space surveillance data and a few ground-based test data. NASA model takes the mass, impact velocity magnitude for input and provides the fragment size, area-to-mass ratio, velocity magnitude distributions for output. A more precise approach for spacecraft disintegration fragment analysis is presented in this paper. This approach is based on hypervelocity impact dynamics and takes the shape, material, internal structure and impact location etc. of spacecraft and impactor, which might greatly affect the fragment distribution, into consideration. The approach is a combination of finite element and particle methods, entitled finite element reconstruction (FER). By reconstructing elements from the particle debris cloud, reliable individual fragments are identified. Fragment distribution is generated with undirected graph conversion and connected component analysis. Ground-based test from literature is introduced for verification. In the simulation satellite targets and impactors are modeled in detail including the shape, material, internal structure and so on. FER output includes the total number of fragments and the mass, size and velocity vector of each fragment. The reported fragment distribution of FER shows good agreement with the test, and has good accuracy for small fragments. 相似文献
993.
Yibin Yao Rui Zhang Weiwei Song Chuang Shi Yidong Lou 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Given the severe effects of the ionosphere on global navigation satellite system (GNSS) signals, single-frequency (SF) precise point positioning (PPP) users can only achieve decimeter-level positioning results. Ionosphere-free combinations can eliminate the majority of ionospheric delay, but increase observation noise and slow down dual-frequency (DF) PPP convergence. In this paper, we develop a regional ionosphere modeling and rapid convergence approach to improve SF PPP (SFPPP) accuracy and accelerate DF PPP (DFPPP) convergence speed. Instead of area model, ionospheric delay is modeled for each satellite to be used as a priori correction. With the ionospheric, wide-lane uncalibrated phase delay (UPD) and residuals satellite DCBs product, the wide-lane observations for DF users change to be high-precision pseudorange observations. The validation of a continuously operating reference station (CORS) network was analyzed. The experimental results confirm that the approach considerably improves the accuracy of SFPPP. For DF users, convergence time is substantially reduced. 相似文献
994.
引入相似理论对月球车的轮土交互系统进行研究,建立了月壤-车轮交互系统的地面力学相似模型,针对原位月壤内聚力较小的特点,提出了一种无需改变车轮尺寸、以模拟月壤为土壤介质的模型试验方法,对月面重力环境下月球车轮的牵引性能进行预测.利用室内土槽试验和颗粒流仿真相结合的方法对该模型试验方法的有效性进行验证,验证结果与模型试验的理论分析结果较为接近,表明该法具有较好的可行性和有效性,可考虑用于预测月球车的月面牵引性能. 相似文献
995.
在长期的航天器编队飞行中传统的基于线性相对运动模型设计编队保持轨道的方法会引起较多的燃料消耗.首先采用摄动法解析地求得了考虑二阶非线性项时椭圆轨道相对运动模型的周期性条件和周期解;然后以此周期解为参考轨道设计了基于Lyapunov稳定的PD保持控制律.仿真结果表明:基于椭圆轨道非线性相对运动模型的周期解较基于椭圆轨道线性相对运动模型的周期解,精度明显提高;以前者为参考轨道的保持控制与以后者为参考轨道的保持控制相比,燃耗明显降低. 相似文献
996.
民用飞机发动机吊挂部段静力试验与静强度分析 总被引:1,自引:0,他引:1
根据民用飞机发动机吊挂部段静力试验技术需求,研制了一套用于吊挂部段静力试验的试验系统,解决了吊挂支持模拟、加载边界模拟等关键技术,完成了吊挂应急着陆、航向侧移两种危险工况试验,并结合试验台架-吊挂有限元分析模型对吊挂进行了静强度分析.试验结果表明,试验系统工作稳定可靠,吊挂在应急着陆等工况下未发生有害塑性变形,其强度、刚度满足设计要求.对比显示:试验最大应力与有限元分析相对误差均小于8%,验证了分析模型的准确性.试验结果可作为民用飞机发动机吊挂部段强度性能的评定依据,有限元建模方法可应用于吊挂部段改型设计. 相似文献
997.
飞船降落伞系统的可靠性建模 总被引:2,自引:0,他引:2
飞船降落伞系统中设计有主伞包开关判别和速度判别两个主伞系状态监测装置,这使得飞船降落伞系统具有其自身特点.主伞包开关判别和速度判别装置各自具有两类任务可靠性,且它们各自的监测范围不同.采用冷贮备模型描述飞船降落伞系统可靠性时,需基于一定的假设,不能准确地描述飞船降落伞系统的可靠性.为此,在分析飞船降落伞系统自身特点和冷贮备模型局限性的基础上,采用事件树方法,建立了飞船降落伞系统的可靠性事件树和更为准确的可靠性数学模型.该模型更具一般性,能更准确地反映飞船降落伞系统的可靠性. 相似文献
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