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捷联惯组历次测试数据反映了捷联惯组的逐次通电稳定性,它是引起制导工具误差的主要影响因素。本文采用建立捷联惯组历次测试数据灰色模型的方法对其逐次通电稳定性的变化趋势进行预测。通过仿真计算,验证了利用该方法进行短期预测的有效性。 相似文献
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针对高机动短时间飞行的飞行器,介绍了一种根据它相对2颗导航卫星的伪距离和伪速度信息,估计捷联惯导系统定位和定速度误差的方法.考虑到由确定飞行器相对每颗星的径向距离和速度的非线性方程施加的约束,根据这些误差矢量长度最小值的条件确定误差值.用空间解析几何法得出了计算捷联惯导系统误差估值的最终算法,这种算法能给出非线性最小值问题的精确解. 相似文献
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针对某型光纤(FOG)捷联惯组(SINS)的轻量化设计要求,采用了空间五点减振的布局方案。基于弹性中心理论计算了空间五点减振系统的弹性中心和偏心量,在捷联惯组存在质心偏移的情况下,增设第五点减振器可以将减振系统的弹性中心和捷联惯组惯性测量系统质心之间的偏心量减少到1.42mm。从刚体动力学出发对振动耦合的解耦条件进行了讨论,指出捷联惯组在惯性主轴偏移的情况下,空间五点减振系统无法实现角振动的解耦,但是通过调整IMU结构布局的质心,或通过调整减振器的刚度比,都可以实现线振动和角振动的解耦。用有限元方法对上述两种解耦方案下捷联惯组的冲击响应进行了计算,仿真结果表明,调节质心和调整减振器刚度两种方法对于降低IMU振动耦合的效果均较为理想,由线冲击引起的角振动降低了约29~100倍。 相似文献
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捷联式制导系统中四元数的保范递推计算 总被引:1,自引:0,他引:1
推导了捷联式制导系统中四元数的保持范数不变的递推计算公式,并对公式的误差传递进行分析,证明其计算误差随迭代次数线性增长. 相似文献
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本文在阐述了重复技术的优点及捷联制导的重复方法(十二面体方法及非正交系方法)后,提出了自己的重复方法。该法有下列特点:1.不仅提高系统的可靠性,而且提高系统的精度;2.影响制导精度的最关键元件应在最佳安装方向上多套重复,影响可靠性的关键元件可考虑正交或非正交重复;3.本文提出极差检验故障方法,推导了精度与失效率公式,该方法计算简单、工作可靠;4.应用以上理论,捷联制导装置中增加一个纵向加速度表及一个二自由度陀螺,制导误差可降低到1/2~(1/2)倍,失效率可降低两个数量级。 相似文献
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本文针对目前战术导弹广泛使用捷联系统这个现状,以及对大机动飞行器采用姿态角误差反馈进行控制有时出现的奇异问题,提出并研究了基于四元数进行大机动战术导弹姿态控制系统的设计问题.首先,给出了大机动飞行情况下基于四元数描述的弹体动力学模型,然后,基于非线性控制系统综合方法设计了姿态控制系统,并验证了系统的稳定性.研究结果表明,基于四元数进行姿态控制系统的设计,既解决了姿态角表示法存在的奇异性问题,又可减少捷联计算机的计算量,对战术导弹具有重要实际意义.最后,通过数值仿真验证了本文提出方法的有效性. 相似文献
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基于Labwindows/CVI的捷联惯导测试软件设计 总被引:1,自引:0,他引:1
研究基于Labwindows/CVI的捷联惯导测试软件应用于激光陀螺(光纤陀螺)和石英加速度计组成的捷联惯性导航系统.对满足系统功能的CVI程序的关键编写要点作了详细介绍,主要包括多串口硬件实现及其初始化、超时等待处理,定时器使用,数据发送、接收和统计特性计算,数据实时显示更新,图形界面的生成、属性页切换实现、曲线图的... 相似文献
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Changes in body fluids, electrolytes, and muscle mass are manifestations of adaptation to space flight and readaptation to the 1-g environment. The purposes of this paper are to review the current knowledge of biomedical responses to short- and long-duration space missions and to assess the efficacy of countermeasures to 1-g conditioning. Exercise protocols, fluid hydration, dietary and potential pharmacologic measures are evaluated, and directions for future research activities are recommended. 相似文献
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Space robotic systems are expected to play an increasingly important role in future space activities. Nevertheless, dynamics modeling and motion planning of a space robot are much more complex than those of a fixed-base robot, due to the dynamic coupling between the manipulator and its base. On the other hand, in order to assure the success of on-orbital missions, many experiments are required to verify the key algorithms on the ground before the space robot is launched. In this paper, the main research achievements on dynamics modeling, path planning, and ground verification are reviewed, and future studies are recommended. Firstly, we summarize the essential modeling concepts, and deduce the kinematics and dynamics equations of a space robot. Secondly, the main motion planning approaches are discussed. Then, different ground verification systems, including the air-bearing table, neutral buoyancy, airplane flying, free-falling motion, suspension system, and hybrid system, are introduced. Finally, the future research trends are forecasted. 相似文献
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The identification of trajectories that target a precise location and approach vector during planetary entry is sensitive to the quality of the startup arc supplied to iterative path planning and guidance algorithms. These sensitivities are especially evident when multi-body effects are significant; low-energy spacecraft trajectories that dwell near the gravitational boundary of two bodies, for instance, are more susceptible to third-body effects. Dynamical sensitivities are also significant when maneuvers are scheduled within a region of space susceptible to multi-body effects. The present study considers precision entry targeting from the perspective of the multi-body problem. 相似文献
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《Acta Astronautica》1999,44(5-6):219-225
The spacecraft flights to the Near-Earth asteroid in order to give an impact influence on the asteroid, correct its orbit and prevent the asteroid’s collision with the Earth are analyzed.In the first part, the impulse flights are analyzed in the Lambert approach. There are determined the optimal trajectories maximizing the asteroid deviation from the Earth.In the second part, the flights with the chemical and electric-jet engines are analyzed. The high thrust is used to launch the spacecraft from the geocentric orbit, and the low thrust is applied for the heliocentric motion. On the base of optimal impulse transfer, the optimal low thrust trajectories are determined using Pontryagin maximum principle.The numerical results are given for the flight to the asteroid Toutatis. Parameters of the spacecraft impact on the asteroid are determined. The asteroid deviation from the Earth caused by the spacecraft influence is presented. 相似文献
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液体推进剂空间推进系统静态数学模型 总被引:4,自引:2,他引:4
针对采用液体推进剂火箭发动机的空间推进系统,推导了系统液路和气路的通用积分形式方程。对不同部件,根据其特点进行方程简化,给出了以压力为自变量表示流量的部件静态数学模型。这为开展空间推进系统的静态仿真研究奠定了基础。 相似文献