Analysis on Eliminate Calibration and Disturbance of Digital Sun Sensor 数字式太阳敏感器标定与抗干扰分析
Analysis of Principle and Accuracy Reliability of High Accurate Sun Sensor 高精度太阳敏感器原理与精度可信度分析
The sun sensor is widely used in satellite attitude determination subsystems. 太阳敏感器是卫星上常用的一种姿态敏感器。
Calibration of transform matrix between sun sensor measurement and cubic prism coordinate systems 太阳敏感器测量坐标系与立方镜坐标系转换矩阵的标定
The measurement accuracy of sun sensor is mainly influenced by earth albedo. 太阳敏感器的测量精度主要受地球反照的影响。
Based on the Fraunhofer diffraction theory and a microlens, a high-performance complex optical system for a digital sun sensor is designed. 以夫朗禾费衍射理论为基础,结合微透镜,设计了一种高性能的数字式太阳敏感器复合光学系统。
The aperture-array diffraction theory provided a reliable theory for the optical system design of the sun sensor and image processing. 小孔阵列衍射理论为太阳敏感器的光学系统设计和图像处理提供了可靠的理论基础。
A new covering non-scanning mechanical system, named sun sensor is developed, a kind of valid metrical device is designed to determine vision field range of sun sensor, and to deduce the academic formula of signal measurement. 设计了非扫描机械式视场保护系统&太阳探头,研究了有效的测量装置,测量确定了太阳探头的视场范围,推导了太阳探头信号测量的理论公式。
The micro sun sensor theoretical design principles and test results are detailed in the paper. 该文给出了这种微型太阳敏感器的理论工作原理与实验测试结果。
Spacecraft Integrated Attitude Determination Based on GPS/ IMU/ Sun Sensor 基于GPS/IMU/太阳敏感器的空间飞行器组合姿态确定
The paper presents the principle of the CCD sun sensor, discusses how to use the linear CCD array to provide two-axis measurements of the sun center angular coordinate, analyzes the error of the system and establishes the error compensation model. 介绍了星载CCD太阳敏感器的工作原理,用空间几何模型阐述了线阵CCD太阳敏感器测量两轴姿态信息的方法,进行了误差分析,建立了系统的误差补偿模型。
This paper describes the design and the principle experiments of a micro digital sun sensor based on a novel diaphragm and active pixel sensor ( APS) CMOS image sensor. 对一种基于新型光线引入器和有源像素传感器(APS)CMOS图像传感器的微型数字式太阳敏感器进行了设计和原理实验研究。
The designed sun sensor, which is used on the GSMS both for the scanning synchronization controller and for the alignment guiding of cloud pictures at earth stations, has two pairs of slits and uses an equivalent detection method to generate a high accuracy sun pulse. 该太阳敏感器的光学头部由两对狭缝组成,采用平衡检测方式产生高精度的太阳脉冲,为星上扫描同步控制器和卫星地面站云图配准的引导提供基准信号。
A two-axis micro sun sensor technology was developed using optical nonlinear compensation. 该文介绍了一种采用光学非线性补偿方法的两轴微型太阳敏感器技术。
Error Analysis and Compensation for CCD Sun Sensor CCD太阳敏感器误差分析与补偿
Taking sun sensor, magnetometer and MEMS gyro as attitude sensors, the attitude determination filter was constructed and simulation was proceeded using the STK ( Satellite Tool Kit) data. 以太阳敏感器、微电子机械系统(MEMS)陀螺、磁强计为姿态敏感器件,构建了定姿滤波器并用STK(satellitetoolkit)数据进行了仿真。
A federated filter is designed to fuse information from the inertial measurement unit, the star sensor, the digital sun sensor and the digital earth sensor which compose the satellite attitude determination system. 针对由惯性测量组件、星敏感器、数字式太阳敏感器和红外地球敏感器构成的卫星姿态确定系统,提出采用联邦滤波器进行信息融合。
The principle, structure and testing results of this kind of sun sensor are introduced. 随后,介绍了这种新型太阳敏感器的工作原理、结构和工作流程、测试和标定结果。
Optical system design for a micro digital sun sensor 小孔阵列式太阳敏感器的光学系统设计
Two-axis micro sun sensor using optical nonlinear compensation 采用光学非线性补偿的两轴微型太阳敏感器
For theoretical development, the continuous and discretization models of gyros are derived meticulously through analyzing the correlations of the bias and measurement of gyro. The measure equations and relative analysis of infrared horizon sensors and digital sun sensor are also given at the same time. 分析了陀螺漂移和测量值之间的相关性,详细推导了陀螺准确的连续和离散化数学模型,同时给出并分析了红外地平仪和数字太阳角计的测量方程。
Lower power consumption, lighter mass and higher measure accuracy is the elementary requirement for sun sensor. 低功耗、轻质量以及高精度是对太阳敏感器的基本要求。
Compared to earth sensor, sun sensor and other sensors, star tracker has the advantages of high precision of measurement, low power consumption, no attitude error accumulation. And star tracker has the ability of autonomous navigation like gyroscope. 与地球敏感器、太阳敏感器等其他姿态敏感器相比,星敏感器具有测量精度高、功耗低、无漂移等优点,并且和陀螺仪一样具有自主导航的能力,非常符合目前航天发展的需要。
The principle of the attitude determination system using the measurement of infrared horizon sensors and digital sun sensor to modify the gyros 'driftbias is proposed. 提出了利用红外地平仪和数字太阳角计的测量值来修正陀螺漂移的姿态确定原理。
"Solar Simulator" is an important part of physical experiment research of conducting intelligent control, and a critical equipment of sun sensor ground simulation test and performance testing. 太阳模拟器是进行智能控制物理仿真实验重要的部分,是太阳敏感器地面模拟试验和性能测试的关键设备之一。
Sun sensor determines the coordinates of artificial satellite in sun coordinates system through the sunlight position detection, which is a key component of artificial satellite attitude determination system. 太阳敏感器是检测太阳光位置的装置,主要用于确定人造地球卫星相对于太阳坐标系的方位,是人造地球卫星的姿态控制系统的关键部件。
Sun sensor is an important component of artificial satellite attitude determination system, which is a kind of widely used sensors in the aerospace science field. 太阳敏感器是航天姿态控制系统中的重要测量部件,是在航天领域应用最广泛的一类敏感器。
In this special environment on the moon, to weaken the impact of lunar dust on the imaging, we can use optical lens camera in visual navigation as sun sensor. 在月表特殊环境下,为了减弱月尘对成像的影响,可以使用视觉导航中透镜式相机作为太阳敏感器。
According to the overall scheme, the sun sensor and the fiber gyro are chosen to be the attitude sensor, and the multi sensors data interface is designed. 依据仿真系统总体方案要求,选用太阳敏感器和光纤陀螺作为姿态敏感器,并完成多敏感器的数据接口设计。