光学遥感卫星轨道设计若干关键技术研究
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摘要
遥感卫星为人类从外层空间观测地球提供了平台,利用卫星所搭载的各种传感器,人类能够及时获取地表和地球各个圈层的状态及变化信息。随着航天技术、信息技术的飞速发展,航天遥感已经进入高时间分辨率、高空间分辨率和高光谱分辨率的新阶段。
然而,卫星遥感数据的获取和信息服务又受到了卫星轨道、传感器性能、通信条件、数据分发模式乃至行业管理体制的约束,尚无法满足用户的全部要求,特别是应急情况下对遥感数据时效性和精度的要求。
鉴于卫星轨道是影响卫星数据获取能力的最重要因素,作者提出通过优化轨道设计,提升遥感数据的按需获取能力和数据质量。本文旨在通过对光学遥感卫星轨道设计中涉及的动力学基础、设计流程、覆盖指标量算、特殊类型轨道设计以及基于多目标优化算法的轨道设计等关键技术的研究,拟突破光学遥感卫星轨道设计中的几个重要瓶颈问题,为光学遥感轨道的优化设计提供理论和技术支撑。本文研究内容包括：
1.研究了卫星轨道动力学基础和遥感卫星轨道设计流程。在介绍卫星运动的时空基准和运动规律的基础上,研究了遥感卫星轨道设计的流程,阐述了遥感卫星轨道设计各阶段的主要任务,深入分析了光学轨道设计的约束条件和性能指标,探讨了它们与轨道参数的关系。
2.研究了适宜于光学遥感卫星的特殊组合轨道设计方法。特殊类型轨道的优化选择是光学遥感卫星轨道设计是一个重要步骤,论文重点研究了适宜光学遥感卫星几种特殊组合轨道的设计方法,结合典型应用给出了上述轨道的设计流程,开发了向导式光学遥感卫星轨道设计的原型系统。
3.研究了光学遥感卫星覆盖性能度量的关键技术。卫星轨道的覆盖性能量算是轨道设计中的一项重要工作。本文针对时间分辨率和覆盖范围量算两个关键指标分别提出了度量算法,可为设计方案提供准确、快速的覆盖性能量算工具。
4.研究了基于多目标优化算法的遥感卫星轨道和星座设计方法。卫星轨道设计是一个典型的约束条件下的多参数多目标优化问题,进化算法是解决多目标优化问题的一种有效手段。以改进的NSGA-Ⅱ算法为优化工具,针对单星和星座轨道进行了优化设计,本文提出了基于多目标优化算法的光学遥感卫星轨道和星座设计方法。
论文的主要特色和创新点有：
1.提出了一种满足局部区域覆盖要求的具有高时、空分辨率,且具有良好拱线静止特性的临界回归椭圆轨道设计方法。该轨道具有四个主要优势：第一,通过将近地点置于热点区域上空,可保障对局部目标成像的高空间分辨率；第二,扩展了回归系数的区间,大大缩短了轨道的回归周期,因而具有高时间分辨率；第三,由于使用临界轨道,具有良好的拱线静止特性,保证了对同一纬度目标成像时分辨率一致；第四,与轨道高度(近地点高度)相同的圆轨道相比,该轨道具有更长的工作寿命。
2.提出了基于多目标优化算法(改进的NSGA—Ⅱ算法)的遥感卫星轨道和星座设计方法。针对特殊类型轨道无法满足减灾救灾、军事行动等快速响应任务要求的问题,本文采取了基于多目标优化理论的轨道优化设计方法。根据卫星轨道设计任务的特点,本文改进了NSGA-Ⅱ算法,利用卫星覆盖性能指标的快速算法,提出了基于多目标优化算法的光学遥感卫星轨道和星座设计方法。
3.提出了光学遥感卫星覆盖性能指标量算的关键算法。针对轨道时间分辨率和覆盖范围量算两个关键指标量算问题,分别提出了顾及J2项摄动影响的光学卫星成像窗口预报和基于几何成像模型的线阵CCD卫星成像区域预报两种快速算法,为轨道的覆盖性能度量提供了工具,有效支撑了遥感卫星轨道的优化设计。
4.基于本文提出的特殊轨道设计方法,开发了向导式的光学遥感轨道设计原型系统(ODPSRSS),提高了特殊轨道设计的工作效率。
As an important data resource for earth observation, remote sensing satellite equipped with a variety of sensors can provide abundant information about the status and variation of earth surface. With the rapid development of space and information technology in recent years, space-borne remote sensing has entered a new stage of the massive sensors with high temporal resolution, spatial resolution or spectral resolution. But the remote sensing data still cannot satisfy the all demands in different applications, especially in the cases of emergency response, for the limitation of sensor performance, communication conditions, data distribution mode, and management system.
The orbit is the most important factor to impact the data acquisition of RS satellite. This dissertation aims to improve the acquisition ability of remote sensing satellite by the optimization of its orbit. The key techniques of optimized orbit design were compared and analyzed, which includes satellite dynamics, design procedures, coverage performance metrics calculation, special orbit design and multi-objectives optimization algorithm. Some key problems of orbit design were solved in the research, which could support the optimized design of optical remote sensing satellite. The detailed contents were followings:
1. The satellite orbital dynamics theory and remote sensing satellite orbit design procedures. The design procedures were introduced, the main aims of different steps were decomposed firstly; then, constraints and objectives of the design mode were presented.
2. Special orbit design methods for optical remote sensing satellites. Optimization selection is the key step in the optical satellite orbit design. The dissertation focuses on special circular orbits, elliptical orbit design methods of optical remote sensing satellite. And a prototype system of wizard tools for optical remote sensing satellite orbit were developed based on the methods represented in this dissertation.
3. The key algorithm of coverage performance metrics for optical remote sensing satellite orbit. Coverage performance of the satellite orbit is regarded as an important objective in the orbit design. Imaging temporal windows forecast algorithm considering J2perturbation and the regional forecast algorithm for CCD imaging geometric model were proposed for the two key indicators, calculation of temporal resolution and the regional coverage rate.
4. Orbit and constellation design method for optical satellite based on multi-objective optimization algorithm. Satellite orbit design is a typical multi-objective optimization problem(MOP), evolutionary algorithms is an effective tool to solve multi-objective optimization problem. NSGA-Ⅱ was selected as the optimization tool for single satellite orbit and constellation design.
The main characteristics and innovation:
1. Meeting local area coverage requirements with high temporal and spatial resolution, a critical repeat orbit elliptical orbit design method was introduced. The orbit has four major advantages:first, by placing the perigee over the hot spot areas, we can get the target's image with very high spatial resolution; second, extends the interval of the regression coefficients, greatly reducing the orbital cycle of regression, a high time resolution can be realized; third, arched line has a good stationary characteristics due to the use of the critical orbit, to ensure that the same ground resolution for targets with the same latitude; fourth, it has a longer working life compared to circular orbit with the same attitude.
2. Remote sensing satellite orbit and constellation design method based on multi-objective optimization algorithm (improved NSGA-Ⅱ algorithm) was proposed. According to the characteristics of the satellite orbit design tasks, we improved NSGA-Ⅱ algorithm, and optic remote sensing satellite orbit and constellation design method based on multi-objective optimization algorithm were proposed.
3. Key algorithm of calculating optic remote sensing satellite covering performance metricswere put forward. Count two key indicators of the amount of orbit time resolution and the amount of coverage problem, we proposed two fast algorithms, one is taking into account the J2perturbation optical satellite imaging window forecast, the other is the linear CCD Satellite imaging area forecast algorithm based on geometric imaging mode. They are the useful tools to support the optimization of the design of the remote sensing satellite orbit.
4. Based on the special orbit design method proposed in this paper, we have developed a wizard-orbit design of optical remote sensing prototype system (ODPSRSS) to improve the efficiency of the special orbit design.
然而,卫星遥感数据的获取和信息服务又受到了卫星轨道、传感器性能、通信条件、数据分发模式乃至行业管理体制的约束,尚无法满足用户的全部要求,特别是应急情况下对遥感数据时效性和精度的要求。
鉴于卫星轨道是影响卫星数据获取能力的最重要因素,作者提出通过优化轨道设计,提升遥感数据的按需获取能力和数据质量。本文旨在通过对光学遥感卫星轨道设计中涉及的动力学基础、设计流程、覆盖指标量算、特殊类型轨道设计以及基于多目标优化算法的轨道设计等关键技术的研究,拟突破光学遥感卫星轨道设计中的几个重要瓶颈问题,为光学遥感轨道的优化设计提供理论和技术支撑。本文研究内容包括：
1.研究了卫星轨道动力学基础和遥感卫星轨道设计流程。在介绍卫星运动的时空基准和运动规律的基础上,研究了遥感卫星轨道设计的流程,阐述了遥感卫星轨道设计各阶段的主要任务,深入分析了光学轨道设计的约束条件和性能指标,探讨了它们与轨道参数的关系。
2.研究了适宜于光学遥感卫星的特殊组合轨道设计方法。特殊类型轨道的优化选择是光学遥感卫星轨道设计是一个重要步骤,论文重点研究了适宜光学遥感卫星几种特殊组合轨道的设计方法,结合典型应用给出了上述轨道的设计流程,开发了向导式光学遥感卫星轨道设计的原型系统。
3.研究了光学遥感卫星覆盖性能度量的关键技术。卫星轨道的覆盖性能量算是轨道设计中的一项重要工作。本文针对时间分辨率和覆盖范围量算两个关键指标分别提出了度量算法,可为设计方案提供准确、快速的覆盖性能量算工具。
4.研究了基于多目标优化算法的遥感卫星轨道和星座设计方法。卫星轨道设计是一个典型的约束条件下的多参数多目标优化问题,进化算法是解决多目标优化问题的一种有效手段。以改进的NSGA-Ⅱ算法为优化工具,针对单星和星座轨道进行了优化设计,本文提出了基于多目标优化算法的光学遥感卫星轨道和星座设计方法。
论文的主要特色和创新点有：
1.提出了一种满足局部区域覆盖要求的具有高时、空分辨率,且具有良好拱线静止特性的临界回归椭圆轨道设计方法。该轨道具有四个主要优势：第一,通过将近地点置于热点区域上空,可保障对局部目标成像的高空间分辨率；第二,扩展了回归系数的区间,大大缩短了轨道的回归周期,因而具有高时间分辨率；第三,由于使用临界轨道,具有良好的拱线静止特性,保证了对同一纬度目标成像时分辨率一致；第四,与轨道高度(近地点高度)相同的圆轨道相比,该轨道具有更长的工作寿命。
2.提出了基于多目标优化算法(改进的NSGA—Ⅱ算法)的遥感卫星轨道和星座设计方法。针对特殊类型轨道无法满足减灾救灾、军事行动等快速响应任务要求的问题,本文采取了基于多目标优化理论的轨道优化设计方法。根据卫星轨道设计任务的特点,本文改进了NSGA-Ⅱ算法,利用卫星覆盖性能指标的快速算法,提出了基于多目标优化算法的光学遥感卫星轨道和星座设计方法。
3.提出了光学遥感卫星覆盖性能指标量算的关键算法。针对轨道时间分辨率和覆盖范围量算两个关键指标量算问题,分别提出了顾及J2项摄动影响的光学卫星成像窗口预报和基于几何成像模型的线阵CCD卫星成像区域预报两种快速算法,为轨道的覆盖性能度量提供了工具,有效支撑了遥感卫星轨道的优化设计。
4.基于本文提出的特殊轨道设计方法,开发了向导式的光学遥感轨道设计原型系统(ODPSRSS),提高了特殊轨道设计的工作效率。
As an important data resource for earth observation, remote sensing satellite equipped with a variety of sensors can provide abundant information about the status and variation of earth surface. With the rapid development of space and information technology in recent years, space-borne remote sensing has entered a new stage of the massive sensors with high temporal resolution, spatial resolution or spectral resolution. But the remote sensing data still cannot satisfy the all demands in different applications, especially in the cases of emergency response, for the limitation of sensor performance, communication conditions, data distribution mode, and management system.
The orbit is the most important factor to impact the data acquisition of RS satellite. This dissertation aims to improve the acquisition ability of remote sensing satellite by the optimization of its orbit. The key techniques of optimized orbit design were compared and analyzed, which includes satellite dynamics, design procedures, coverage performance metrics calculation, special orbit design and multi-objectives optimization algorithm. Some key problems of orbit design were solved in the research, which could support the optimized design of optical remote sensing satellite. The detailed contents were followings:
1. The satellite orbital dynamics theory and remote sensing satellite orbit design procedures. The design procedures were introduced, the main aims of different steps were decomposed firstly; then, constraints and objectives of the design mode were presented.
2. Special orbit design methods for optical remote sensing satellites. Optimization selection is the key step in the optical satellite orbit design. The dissertation focuses on special circular orbits, elliptical orbit design methods of optical remote sensing satellite. And a prototype system of wizard tools for optical remote sensing satellite orbit were developed based on the methods represented in this dissertation.
3. The key algorithm of coverage performance metrics for optical remote sensing satellite orbit. Coverage performance of the satellite orbit is regarded as an important objective in the orbit design. Imaging temporal windows forecast algorithm considering J2perturbation and the regional forecast algorithm for CCD imaging geometric model were proposed for the two key indicators, calculation of temporal resolution and the regional coverage rate.
4. Orbit and constellation design method for optical satellite based on multi-objective optimization algorithm. Satellite orbit design is a typical multi-objective optimization problem(MOP), evolutionary algorithms is an effective tool to solve multi-objective optimization problem. NSGA-Ⅱ was selected as the optimization tool for single satellite orbit and constellation design.
The main characteristics and innovation:
1. Meeting local area coverage requirements with high temporal and spatial resolution, a critical repeat orbit elliptical orbit design method was introduced. The orbit has four major advantages:first, by placing the perigee over the hot spot areas, we can get the target's image with very high spatial resolution; second, extends the interval of the regression coefficients, greatly reducing the orbital cycle of regression, a high time resolution can be realized; third, arched line has a good stationary characteristics due to the use of the critical orbit, to ensure that the same ground resolution for targets with the same latitude; fourth, it has a longer working life compared to circular orbit with the same attitude.
2. Remote sensing satellite orbit and constellation design method based on multi-objective optimization algorithm (improved NSGA-Ⅱ algorithm) was proposed. According to the characteristics of the satellite orbit design tasks, we improved NSGA-Ⅱ algorithm, and optic remote sensing satellite orbit and constellation design method based on multi-objective optimization algorithm were proposed.
3. Key algorithm of calculating optic remote sensing satellite covering performance metricswere put forward. Count two key indicators of the amount of orbit time resolution and the amount of coverage problem, we proposed two fast algorithms, one is taking into account the J2perturbation optical satellite imaging window forecast, the other is the linear CCD Satellite imaging area forecast algorithm based on geometric imaging mode. They are the useful tools to support the optimization of the design of the remote sensing satellite orbit.
4. Based on the special orbit design method proposed in this paper, we have developed a wizard-orbit design of optical remote sensing prototype system (ODPSRSS) to improve the efficiency of the special orbit design.
引文
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