共查询到20条相似文献,搜索用时 93 毫秒
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本文对于地平仪光学系统的设计思想提出了一个新的观点,它把光学系统看做地平仪整系统的一个有机部分,分析了光学设计与整系统的弦宽变动误差和随机检测误差之间的关系。按照这种思想对于光学系统进行了理论分析和参数优化,给出了优化的光学系统参数及其重要性能指标。本文对于探索地平仪光学系统的设计方法是有益的。 相似文献
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提出了一种大相时孔径轻小型光学系统的设计方案,给出了设计方案及热分析结果.光学系统工作谱段500~800nm,视场角9°,相对孔径1/1.2,光学系统设计结果良好,弥散斑直径在两个像元尺寸之内,能够满足光学系统对能量集中度和弥散斑的要求.基于光学热补偿理论对光学系统进行了无热化分析和消热设计.通过分析不同温度下的传递函... 相似文献
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小视场红外光学系统设计 总被引:4,自引:0,他引:4
从红外光学系统的视场设计出发 ,分析了浸没透镜的厚度和曲率半径对光学特性的影响 ,介绍了小视场红外光学系统的设计方法 ,给出了弯月镜和浸没透镜的设计结果 ,试验表明小视场红外光学系统的设计是成功的 相似文献
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针对国家发明专利《基于集成式共用主镜的双视场立体成像光学系统》(发明专利号:ZL2009 1 0243273.8)中所设计的光学系统,进行了杂散辐射的仿真分析及抑制。为了实现较大基高比的立体测绘,满足内方位元素的高稳定度,以实现对图像的高精度校正,采用了集成式共用主镜的双视场立体成像光学系统,它具有结构紧凑、轻量化及热稳定性好等特点。针对该光学系统独特的光学系统结构型式并实现其工程化,通过仿真并根据杂散光的传播路径进行了分类总结分析,通过采取有效的杂散光抑制措施,光学系统最终的杂散光系数为1.1075%,满足系统的使用要求。 相似文献
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The problem of the transportation of the results of experiments and observations to Earth every so often appears in space research. Its simplest and low-cost solution is the employment of a small ballistic reentry spacecraft. Such a spacecraft has no system of control of the descent trajectory in the atmosphere. This can result in a large spread of landing points, which make it difficult to search for the spacecraft and very often a safe landing. In this work, a choice of a compromise scheme of the flight is considered, which includes the optimum braking maneuver, adequate conditions of the entry into the atmosphere with limited heating and overload, and also the possibility of landing within the limits of a circle with a radius of 12.5 km. The following disturbing factors were taken into account in the analysis of the accuracy of landing: the errors of the braking impulse execution, the variations of the atmosphere density and the wind, the error of the specification of the ballistic coefficient of the reentry spacecraft, and a displacement of its center of mass from the symmetry axis. It is demonstrated that the optimum maneuver assures the maximum absolute value of the reentry angle and the insensitivity of the trajectory of descent with respect to small errors of orientation of the braking engine in the plane of the orbit. It is also demonstrated that the possible error of the landing point due to the error of specification of the ballistic coefficient does not depend (in the linear approximation) upon its value and depends only upon the reentry angle and the accuracy of specification of this coefficient. A guided parachute with an aerodynamic efficiency of about two should be used at the last leg of the reentry trajectory. This will allow one to land in a prescribed range and to produce adequate conditions for the interception of the reentry spacecraft by a helicopter in order to prevent a rough landing. 相似文献
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航天材料基因工程及其若干关键技术 总被引:1,自引:1,他引:0
材料基因工程的理念和将空间环境与效应纳入到航天材料研制全流程的思路将对航天材料的开发带来颠覆性的革命。文章在对国内外材料基因组计划和航天材料需求分析的基础上,首先对航天材料基因工程的内涵进行阐述,进而对基于航天材料基因工程的航天材料研制流程进行分析,最后结合空间环境效应及材料基因工程,从计算工具、试验工具、数字化数据三个维度,提出空间多因素环境与航天材料的耦合作用机理、航天材料空间多因素环境效应等效评价方法、空间复杂使役环境下航天材料性能演化模型、航天材料空间环境效应数据库、基于材料基因工程的航天材料设计模型、航天材料研制的不确定性及优化方法等关键技术和发展方向。 相似文献
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The BOKZ-M60 star sensor (Unit for Measuring Star Coordinates) is intended for determining the parameters of the orientation of the axes of the intrinsic coordinate system relative to the axes of the inertial system by observations of the regions of the stellar sky. It is convenient to characterize an error of the single determination of the orientation of the intrinsic coordinate system of the sensor by the vector of an infinitesimal turn of this system relative to its found position. Full-scale ground-based tests have shown that, for a resting sensor the root-mean-square values of the components of this vector along the axes of the intrinsic coordinate system lying in the plane of the sensor CCD matrix are less than 2″ and the component along the axis perpendicular to the matrix plane is characterized by the root-mean-square value of 15″. The joint processing of one-stage readings of several sensors installed on the same platform allows us to improve the indicated accuracy characteristics. In this paper, estimates of the accuracy of systems from BOKZ-M60 with two and four sensors performed from measurements carried out during the normal operation of these sensors on the Resurs-P satellite are given. Processing the measurements of the sensor system allowed us to increase the accuracy of determining the each of their orientations and to study random and systematic errors in these measurements. 相似文献
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镁铝贫氧推进剂的能量分析 总被引:5,自引:0,他引:5
利用冲压发动机热力计算程序,对镁铝中能贫氧推进剂的能量特性进行了系统研究,并探讨了高能级分对该类贫氧推进剂能量性能的影响,研究结果表明,在镁铝中能贫氧推进剂中增加镁粉含量(或减少铝粉含量)贫氧推进剂的比冲下降,在一定空燃比范围内,增加空燃比有助于提高冲压发动机的比冲。提高贫氧推进剂中CL-20和硼粉含量,可以显著提高共能量,而采用叠氮类含能粘合剂取代惰性粘合剂时贫氧推进剂的比冲降低。 相似文献
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舱压对载人航天器密封舱姿态光学敏感器安装精度影响分析 总被引:1,自引:1,他引:0
姿态光学敏感器是航天器在轨姿态控制的重要部件,其安装精度直接影响航天器的姿态控制精度。为了研究舱压对载人航天器密封舱姿态光学敏感器安装精度的影响,以某载人航天器密封舱外安装的姿态光学敏感器为研究对象,通过对其安装精度要求、安装状态与舱体变形情况的分析,提出了一种敏感器在设计阶段布局的分析方法。在地面进行了模拟充压试验,验证了分析方法的有效性。根据分析和试验结果在型号后续设计中进行了相应的布局改进,改进结果满足了敏感器安装精度要求并经过了飞行试验验证。 相似文献
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The problem of optimal control is considered for the motion of the center of mass of a spacecraft in a central Newtonian gravitational field. For solving the problem, two variants of the equations of motion for the spacecraft center of mass are used, written in rotating coordinate systems. Both the variants have a quaternion variable among the phase variables. In the first variant this variable characterizes the orientation of an instantaneous orbit of the spacecraft and (simultaneously) the spacecraft location in this orbit, while in the second variant only the instantaneous orbit orientation is specified by it. The suggested equations are convenient in the respect that they allow the general three-dimensional problem of optimal control by the motion of the spacecraft center of mass to be considered as a composition of two interrelated problems. In the first variant these problems are (1) the problem of control of the shape and size of the spacecraft orbit and (2) the problem of control of the orientation of a spacecraft orbit and the spacecraft location in this orbit. The second variant treats (1) the problem of control of the shape and size of the spacecraft orbit and the orbit location of the spacecraft and (2) the problem of control of the orientation of the spacecraft orbit. The use of quaternion variables makes this consideration most efficient. The problem of optimal control is solved on the basis of the maximum principle. Several first integrals of the systems of equations of the boundary value problems of the maximum principle are found. Transformations are suggested that reduce the dimensions of the systems of differential equations of boundary value problems (without complicating them). Geometrical interpretations are given to the transformations and first integrals. The relation of the vectorial first integral of one of the derived systems of equations (which is an analog of the well-known vectorial first integral of the studied problem of optimal control) with the found quaternion first integral is considered. In this paper, which is the first part of the work, we consider the models of motion of the spacecraft center of mass that employ quaternion variables. The problem of optimal control by the motion of the spacecraft center of mass is investigated on the basis of the first variant of equations of motion. An example of a numerical solution of the problem is given. 相似文献
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以互联网卫星上首次使用的新型高密度排插型电缆组件为研究对象,介绍了集成式排插型电连接器的制造技术要求和工作原理,从电连接器结构分析出发,研究影响该类型电缆的安装因素。首次提出了新型高密度排插型电缆的安装方法,阐述了该类型电缆的弯曲半径要求、绑扎要求、紧固力矩值要求和使用专用工装的拆卸方法。经过分系统的实际在轨性能测试验证,该安装技术可以显著降低新型高密度排插型电缆组件在大通量、高饱和度信号传输状态下性能下降的现象,成功解决了该类型电缆在卫星狭小空间下的安装与拆卸难题,提高了该类型电缆在卫星狭小空间内的安装精度和分系统的在轨可靠性,为该新型高密度排插型电缆组件的安装在后续卫星批量应用提供了技术指导和工艺基础。 相似文献
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《受活》这部作品以写实和荒诞的笔调,在历史和现实中回环往复,书写了历史与现实中存在的乌托邦幻想与冲动,以及这些乌托邦行为给底层人们带来的苦难,并通过对人物心灵的剖析透视了乌托邦梦想的困境。在对残疾人与圆全人两个世界的对比中,作者肯定了受活人的生存状态,表达了对那种自由自在以及纯洁的心灵世界的向往与追求。 相似文献
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Multipole Models of the Earth's Magnetic Field 总被引:2,自引:0,他引:2
To develop a mathematical model of rotational motion of an artificial satellite about its center of mass under the action of various forces (magnetic, Lorentz, etc.) caused by the geomagnetic field, it is necessary to know the induction of the Earth's magnetic field (EMF) as a function of the radius vector of a given point in the near-Earth space. Because the EMF possesses a complex structure and the above-mentioned functional dependence is unavailable in explicit analytic form, a set of approximate models of the EMF should be used. The simplest such model—a right dipole (aligned with the axis of rotation)—does not enable one to reveal in detail the influence of diurnal EMF rotation on the rotational motion of a satellite. The next EMF approximation—an inclined magnetic dipole—does not suffer from the above-mentioned drawback. However, it is shown that not all corrections to the magnetic induction of the EMF of the same order of magnitude are taken into account in the course of transformation from the model of aligned dipole to the model of inclined dipole. So, to develop the EMF model accurately accounting for the absence of axial symmetry of the EMF with respect to the axis of diurnal rotation of the Earth, in general, the effect of the quadrupole component of the geomagnetic potential on the EMF induction (and, probably, even the components of higher orders) must be taken into consideration. By using the International Geomagnetic Reference Field IGRF-2000, the multipole models of the EMF, corresponding to quadrupole, octupole, and higher-order approximations, were constructed and studied in this work. The EMF potential is expressed in terms of its multipole tensors. As a result, projections of the induction and induction gradient of EMF in the center of mass of the satellite onto the axes of the orbital coordinate system can be written in convenient and concise form. The expressions for the first four multipole tensors through the known geomagnetic constants are found. A method for estimating the reliability of these models is put forward, and the regions of applicability of the quadrupole and octupole models are drawn on the plane of orbital parameters. 相似文献