Design of Optical System for Small Long-Life Star Sensor

In order to realize a high-precision and continuous working function of a star sensor,we propose a new optical system design.Considering the difficulty of the manufacturing process,the entire optical system uses a complicated Petzval structure.In this paper,the key design elements of the optical system applied for star sensors are presented and the most important performance parameters are given.The ground test results show that the system can maintain excellent detection performance on a near-surface atmospheric platform.This study provides an optical system design scheme for a high-precision and continuous operating star sensor,as well as the theoretical basis for future in-atmosphere and continuous star detection technology.

Integrated Design and Accuracy Analysis of Star Sensor and Gyro on the Same Benchmark for Satellite Attitude Determination System

As an important sensor in the navigation systems,star sensors and the gyro play important roles in spacecraft attitude determination system.Complex environmental factors are the main sources of error in attitude determination.The error influence of different benchmarks and the disintegration mode between the star sensor and the gyro is analyzed in theory.The integrated design of the star sensor and the gyro on the same benchmark can effectively avoid the error influence and improves the spacecraft attitude determination accuracy.Simulation results indicate that when the stars sensor optical axis vectors overlap the reference coordinate axis of the gyro in the same benchmark,the attitude determination accuracy improves.

Study on the method of precision adjustment of star sensor

Star sensors are indispensable spatial measurement sensors for high-resolution earth observation and astronomical observations, and the demand for high measurement accuracy of satellite sensors continues to increase; thus, the star sensor optical machine adjustment error cannot be ignored. The commonly used installation error correction method cannot solely meet the precision analysis requirements. In this paper, the relationship between the optical machine installation and the star sensor measurement error is analyzed, and several common adjustment error correction methods are compared. An adjustment method for optical machines is proposed to meet the requirements of very high precision star sensors. The assembly precision requirements of the investigated very high precision star sensor are analyzed considering the whole machine, and then the optical components are controlled through optical precision adjustments to satisfy the precision requirements. Finally, through the complete machine calibration, the star sensor precision adjustment for an optical machine structure is verified. This method meets the requirements of very high precision sensors and is suitable for the precision adjustment of optical machine structures, which is of practical significance to improve the precision of star sensors.

Space luminous environment adaptability of missile-borne star sensor

To solve the problem of stray interference to star point target identification while a star sensor imaging to the sky,a study on space luminous environment adaptability of missile-borne star sensor was carried out.By Plank blackbody radiation law and some astronomic knowledge,irradiancies of the stray at the star sensor working height were estimated.By relative astrophysical and mathematics knowledge,included angles between the star sensor optical axis point and the stray at any moment were calculated.The calculation correctness was verified with the star map software of Stellarium.By combining the upper analysis with the baffle suppression effect,a real-time model for space luminous environment of missile-borne star sensor was proposed.By signal-noise rate(SNR)criterion,the adaptability of missile-borne star sensor to space luminous environment was studied.As an example,a certain type of star sensor was considered when imaging to the starry sky on June 22,2011(the Summer Solstice)and September 20,2011(August 23 of the lunar year,last quarter moon)in Beijing.The space luminous environment and the adaptability to it were simulated and analyzed at the star sensor working height.In each period of time,the stray suppression of the baffle is analyzed by comparing the calculated included angle between the star sensor optical axis point and the stray with the shielded provided by system index.When the included angle is larger than the shielded angle and less than 90°,the stray is restrained by the baffle.The stray effect on star point target identification is analyzed by comparing the irradiancy of 6 magnitude star with that of the stray on star sensor sensitization surface.When the irradiancy of 6 magnitude star is 5 times more than that of the stray,there is no effect on the star point target identification.The simulation results are identical with the actual situation.The space luminous environment of the missile-borne star sensor can be estimated real-timely by this model.The adaptability of the star sensor to space luminous environment can be analyzed conveniently.A basis for determining the relative star sensor indexes,the navigation star chosen strategy and the missile launch window can be provided.

An Approach to Star Map Simulation for Star Sensor Considering the Effect of Image Motion

To test high resolution and dynamic performance of star sensor, a method of consideration image motion on Modeling the motion blur of star sensor is proposed. Firstly, image motion geometric model based on the rotation of Starlight vector is studied. Secondly, with the help of the normal distribution of static star image energy model, introducing the star image motion speed, obtaining the energy distribution function of moving stars, implementing high dynamic simulation of star map. Finally, establishing the simulation environment, through adjusting input parameters such as integral time, rate of change of three attitude angle, the launch time, location, then, important simulation data of stars observed by star sensor in orbit can quickly be obtained, such as navigation stars information, value and direction of image motion, intensity distribution, signal to noise ratio. This work is very important to research and evaluate the star image motion compensation algorithm.

Application study of DSP and CPLD technology on the star sensor

On the basis of analyzing CCD signals timing and star image processing, a new design and a special parallel architecture for improving star image processing are presented in this paper. In the design, the operation moving the data in expanded windows, including the star, to the on-chip memory of DSP is arranged in the invalid period of CCD frame signal. While the CCD saves the star image to memory, DSP processes the data in the on-chip memory. This parallelism greatly improves the efficiency of processing. DSP HOLD mode and CPLD technology are used to make a shared memory between CCD and DSP. The five lightest stars in the star acquisition stage are acquired in only 35 ms. In 43 μs, the data in five expanded windows including stars are moved into the internal memory of DSP, and in 16 ms, five star coordinates are achieved in the star tracking stage.

Image Smearing Modeling and Verification for Strapdown Star Sensor

To further extend study on celestial attitude determination with strapdown star sensor from static into dynamic field, one prerequisite is to generate precise dynamic simulating star maps. First a neat analytical solution of the smearing trajectory caused by spacecraft attitude maneuver is deduced successfully, whose parameters cover the geometric size of optics, three-axis angular velocities and CCD integral time. Then for the first time the mathematical law and method are discovered about how to synthesize the two formulae of smearing trajectory and the static Gaussian distribution function （GDF） model, the key of which is a line integral with regard to the static GDF attenuated by a factor 1/Ls （Ls is the arc length of the smearing trajectory） along the smearing trajectory. The dynamic smearing model is then obtained, also in an analytical form. After that, three sets of typical simulating maps and data are simulated from this dynamic model manifesting the expected smearing effects, also compatible with the linear model as its special case of no boresight rotation. Finally, model validity tests on a rate turntable are carried out, which results in a mean correlation coefficient 0.920 0 between the camera images and the corresponding model simulated ones with the same parameters. The sufficient similarity verifies the validity of the dynamic smearing model. This model, after pa- rameter calibration, can serve as a front-end loop of the ground semi-physical simulation system for celestial attitude determination with strapdown star sensor.

Accelerometer Bias and Star Sensor Installation Error Joint Calibration for the SINS/CNS Integrated Navigation System Using Attitude Maneuver

The integrated strap-down inertial nav igation system/olelestial navigation system(SINS/CNS)i an important autonomous navigation method with efective concealment and high predision.Both accelerometer biss and star ensor installation error ame important factors that aflect the performanoe of this mavigation system,which needl to be calibratexd and compensatedl.A new acelerometer bias and star sensor installation error joint calibration method for the SINS/CNS integrated navigation system i propoeed.In this newly propoeed method,the installation error of star sensor is augmented to the state vector,and the star vector,nadir angle,horkzontal poeition error and velbcity error ame ueed a8 measurementa to calbrate the two errors mentioned above.Simulations show that both accelerometer bias and star sensor installation enror an be calibratedl efectively.

Autonomous satellite constellation orbit determination using the star sensor and inter-satellite links data

A method of autonomous orbit determination for a satellite constellation using a star sensor combined with inter satellite links(ISLs) is studied.Two types of simulated observation data,Three-Satellite Constellation ISLs and background stellar observations by a CCD star sensor,are first produced.Based on these data,an observation equation is built for the constellation joint autonomous orbit determination,in which the simulations are run.The accuracy of this method with different orbital determination models are analyzed and compared with regard to the effect of potential measurement errors.The results show that autonomous satellite constellation orbit determination using star sensor measurement and ISLs data is feasible.Finally,this paper arrives at several conclusions which contribute to extending this method to a more general satellite constellation.

A method of autonomous orbit determination for satellite using star sensor

In this paper a method of autonomous orbit determination using star sensor is studied. By building relatively consummate dynamical models which simulate attitude motion of satellite and observation from satellite to background stars, the simulant computation of this method is executed, and it is shown that the method of autonomous orbit determination is feasible. Academic and calculation analyses have been done for the relation between the direction of star sensor with respect to satellite-body coordinate system and the accuracy of autonomous orbit determination.

临近空间星敏感器观星能力研究

临近空间飞行器对星敏感器需求日益增加,与空间应用环境相比,临近空间包含大气消光、天空背景光、高速、高温和高动态等影响星敏感器观星能力的新环境.对影响临近空间星敏感器观星能力的因素进行逐级分解,得出视场、灵敏度、星点信噪比和图像处理算法等因素对观星能力的影响机理,并针对信噪比与环境因素和设计因素的关系进行量化分析,在此基础上提出临近空间星敏感器整机参数设计方法.针对特定需求开展原理样机的设计与试验验证,试验数据验证了原理样机能够满足应用需求.

一种基于虚拟星敏感器的卫星姿态确定方法

对于配置多个星敏感器的卫星,采用常规的定常增益卡尔曼滤波方法进行姿态确定时,存在滤波定常增益矩阵众多、系统复杂的问题,为了简化滤波系统设计,统一定常增益矩阵,提出一种基于虚拟星敏感器的姿态确定方法.给出一种计算量小、适合星载计算机在轨实时计算的星敏感器时间滞后补偿及相对基准标定算法,将星敏感器的输出数据统一到当前星时,同时将星敏感器的测量基准统一.基于单星敏/双星敏的输出数据构造虚拟星敏感器(安装矩阵为单位阵)的输出数据,设计统一的定常增益矩阵进行姿态确定.仿真结果表明,本方法与常规的定常增益卡尔曼滤波方法姿态确定精度相当,从而验证该方法有效,且具有重要的工程应用价值.

星敏感器热稳定性地面验证技术

受空间复杂热环境影响,星敏感器姿态测量结果存在轨道周期的光轴热漂移低频误差,因此需对星敏感器进行热设计并进行热稳定性试验验证。文章提出星敏感器热稳定性试验总体方案,并建立热稳定性试验系统;依据航天器真空热环境试验规范,提出星敏感器热稳定性试验判据与条件;针对试验系统误差提出控制方法并针对某型星敏感器开展热稳定性试验,结果表明星敏感器光轴热漂移量为0.114(″)/℃,满足设计指标要求。试验验证了该星敏感器热设计的有效性。

大口径热不敏星敏感器光机设计与分析

为满足大口径长焦距星敏感器的需求,对一种大口径热不敏星敏感器进行光机设计,根据指标要求,对热不敏系统进行光机热集成分析。使用MSC.Patran软件对主次镜结构施加温度载荷,计算出主次镜结构的热弹性变形,先利用MSC.Nastran软件计算热变形后节点的刚体位移,再利用Sigft光机接口软件分析得到变形后主次镜表面的Zernike多项式系数。将结果导入Zemax中,预判镜片面型变化以及刚体位移对弥散斑、光轴漂移量及波像差的影响。最后通过在20℃±5℃的温度范围内装调测试验证了系统性能满足指标要求以及光机热集成分析的准确性,提供了一套准确快捷的光机热集成分析流程。

基于双特征的短波红外星图识别算法

在短波红外波段进行昼夜测星有望实现近地空间全天时自动导航,其中,星图识别算法是实现全天时导航的关键技术之一。传统的三角形算法在导航星数增多的情况下,由于其匹配特征维度低,在识别时容易出现冗余匹配、误匹配的情况。针对这一问题,提出了一种基于双特征的短波红外星图识别算法,该算法选取三角形的面积与外切圆半径双高维特征作为匹配特征,通过构建面积特征的K矢量索引,应用K矢量查找法降低匹配识别的计算复杂度。此外,还提出一种优化的观测三角形的选择策略,减少了匹配过程中的计算量,提高算法的识别速度。实验表明,星点位置噪声低于2像素时,算法的平均识别率优于95%;伪星数未超过50%时,平均识别率可达87.6%;并通过实际观星试验验证了所提算法的可行性,与改进的三角形算法相比,该算法在识别速度、识别率以及抗噪声能力等方面都有明显优势。

LIS模式下基于双主星集合匹配的星图识别方法

为提高折射星图中非折射星的识别成功率,提出了一种大视场星敏感器高鲁棒性星图识别方法。首先,筛选基础星表,实现导航星库均匀化,采用分组快速搜索算法,提高星对角距特征匹配速度。其次,提出一种基于双主星集合的星点匹配算法,通过匹配、验证、确认三个阶段,多次检验星点集合中的导航星序号,提高星图识别算法的鲁棒性。仿真结果表明,在星点位置噪声、星等噪声、伪星和缺失星等干扰环境下,所提算法与传统的三角形-金字塔混合算法相比,抗干扰能力更强。在含有6颗折射星的干扰条件下,所提算法的非折射星识别成功率仍高于95.6%,较传统算法识别率提升31%。

一种结合角距特征的改进栅格星图识别算法

针对栅格算法易受邻域星点影响导致误匹配的问题,提出了一种结合角距特征的改进栅格星图识别算法。首先介绍了改进栅格算法的原理,其次设计了融合栅格识别模式和星角距识别模式的算法实现流程,最后开展了基于不同视角下的大视场仿真星图的算法试验验证和性能分析。结果表明,由于角距特征具有旋转不变性和不易受观测星邻域星点分布影响等特点,结合角距特征对失效观测星进行再匹配的改进栅格算法,在兼顾存储量需求小、运行速度快等优势的同时,识别率和鲁棒性也得到了提升,最高识别率可达98.88%,在位置噪声干扰以及缺失星干扰下,改进算法的识别率仍可保持在95%,说明算法鲁棒性强,具有较好的应用前景。

近地轨道高精度一体式星敏感器热设计及仿真验证

某型高精度一体式星敏感器指向精度高,对温度变化非常敏感。其所处近地轨道外热流复杂多变,一体式结构和内热源集中的综合因素不仅导致散热设计困难,而且镜头直接受到内热源发热影响难以保障指向精度。首先,结合轨道参数,安装布局获得星敏感器平均吸收外热流。然后,通过分析外热流与内热源工作情况,采用被动热控和主动热控相结合的热设计方法,并对星敏感器散热面的位置与大小进行设计与计算。最后,根据轨道环境和热控措施并利用热仿真软件进行热分析验证。仿真结果表明,安装法兰温度为19.82℃~20.10℃,镜头轴向温差小于2.23℃,周向温差小于0.48℃,电路盒温度为19.10℃~23.49℃,满足热控指标。通过合理的热控设计保证了极高精度星敏感器的稳定工作条件,星敏感器的热设计合理有效。

CM-1卫星星敏感器在轨测量精度初步评价

星敏感器是目前主流的高精度姿态测量仪器,在轨运行期间星敏感器会产生系统误差、高频误差和低频误差。文章进行了陆地生态系统碳监测卫星(CM-1卫星)星敏感器系统误差与高频误差的计算,分析了星敏1a与1b的光轴夹角误差与卫星星下点纬度的变化规律,基于傅里叶变换对光轴夹角低频误差进行建模,并以此来反映两星敏感器的低频误差。在轨数据表明,星敏1a旋转至星敏1b以及星敏1a旋转至2的系统误差分别为(6.906′,-12.569′,-1.552′)和(-4.540′,-27.199′,13.522′)。星敏数据中精度最高的是星敏1a/1b融合数据,三轴误差分别为0.505″、0.633″和0.800″。同组的星敏1a和1b精度类似,星敏1a三轴误差分别为0.990″、0.981″和16.731″,星敏2a三轴误差分别为0.888″、1.022″和15.156″。星敏2精度稍差,三轴误差分别为2.061″、2.382″和27.231″;星敏1a与1b光轴夹角误差(3σ)为2.50″,光轴夹角低频和高频误差分别为2.046″和1.470″。在相邻轨道星下点纬度相同时光轴夹角误差基本相同。

基于多图超分辨率重建的精细导星仪星点质心定位精度提升方法

精细导星仪的星点质心定位精度决定了空间天文望远镜的视轴姿态解算精度,为了提升精细导星仪的星点质心定位精度,提出了一种基于深度小波循环神经网络的星图超分辨率重建方法。首先,借助微扫描技术获取亚像素错位低分辨率星图序列,采用小波编码器提取低分辨率星图的小波域特征,通过小波系数约束低分辨率星图的噪声,并将亚像素错位星图序列配准过程融入到网络学习中。其次,利用卷积门循环神经单元对所提取的多星图序列特征进行融合。最后,使用逆小波解码器对多特征融合模块输出的小波域特征进行解码,从而实现基于低分辨率星图序列的去噪与超分辨率重建。实验结果表明,分别采用平方加权质心法求取原始星图和超分辨率重建后星图中的各星点的质心位置,相比于前者,后者的各星点平均质心定位精度和稳定度在X方向分别提升了64.76%和19.15%,在Y方向分别提升了75.35%和26.14%。