军用侦察卫星星座技术研究

【作者】 王海丽；

【导师】 戴金海；

【作者基本信息】 国防科学技术大学 ， 飞行器设计， 2001， 博士

【摘要】 军用侦察卫星星座是指由多颗侦察卫星构成的一个卫星群，它们通过协同工作来完 成在一定时间、空间分辨率约束下的情报、监视和侦察（ISR）任务。本文认为卫星协 同与自治的研究是进行军用侦察卫星星座研究的一个重要领域，因此论文围绕卫星协同 与自治的一些关键问题进行研究。 卫星精密轨道预报是卫星动力学研究的基础，而成熟的通用工程仿真平台，如 MATRIXx、MATLAB的应用将使仿真计算的效率与可靠性提高。本文利用MATRIXx 对卫星精密轨道预报进行了仿真实现，并讨论了MATRIXx在航天动力学的应用问题。 卫星星座是多颗卫星进行协同的主要形式，本文讨论了仿真与解析相结合的全球覆盖卫 星星座的设计方法，同时提出了卫星星座空间观测的区域覆盖与全球覆盖判别算法，并 进行了证明，在此基础上，对美国天基红外系统（SBIRS）进行了性能推测与分析。σ 星座构型是解决侦察卫星星座区域覆盖的有效方法，本文在二体假设和考虑地球J2项 影响两种情况下对σ星座进行了设计。本文还利用仿真方法对在轨运行的低轨卫星星座 的性能损失情况进行了分析。 三星时差定位星座由三颗具有一定几何构型的卫星协同完成对目标的定位。本文讨 论了三星时差定位星座对固定目标定位的两种定位方法：利用单个观测时刻数据的定位 和利用多个观测时刻数据的定位。论文利用非线性Kalman滤波设计了三星时差定位星 座对运动目标的定位定速算法；根据定位误差的解析公式，利用仿真方法分析了三星时 差定位星座的星座构型和卫星高度等因素对定位精度的影响规律，并依据定位精度影响 规律，研究了三星时差定位星座的星座设计问题。 卫星轨道机动是卫星自治的首要条件，它是相位保持、相位机动、交会对接的基础。 本文提出了基于零控流型的卫星轨道机动方法，并对此方法所涉及的具体问题进行了研 究。本文利用卫星精密轨道预报的结果作为基准轨道，解决了控制基准的问题；利用H_∞ 控制理论和 PWPF调制器解决了轨控小发动机常推力控制问题。更多还原

【Abstract】 The reconnaissance satellite constellation is constituted by some reconnaissance satellites, which cooperate with each other in accomplishing the missions of Intelligence, Surveillance and Reconnaissance (ISR). The dissertation considers cooperation and autonomy are important domains to study the reconnaissance satellite constellation, and some key problems in the domains of cooperation and autonomy are studied in the dissertation.High precision orbit propagation is the basis of the study of orbital dynamics, and the application of general engineering simulation platform, such as MATRIXx, MATLAB, will increase the efficiency and reliability of simulation. A simulation system of High precision orbit propagation is constructed in the integrated environment of MATRIXx, and some problems on the applications of MATRIXx in aerodynamics are discussed. Satellite constellation is a major shape for satellites to cooperate. The method to design global coverage satellite constellation is discussed with the help of simulation analysis. The dissertation presents algorithms of global coverage and regional coverage for satellites to observe space, and these algorithms are proved with the help of aggregate. Space-Based Infrared System are conjectured and analyzed based on these algorithms. The shape of o constellation is an efficient way to program the missions of regional coverage of reconnaissance satellite constellation, the methods to design o constellation are discussed in case of Two-Body or J2 influence. The losses of performance of LEO constellation are analyzed with the help of simulation.Tri-satellites time-difference localization constellation is made up of three satellites restricted by some geometry shape. Two methods to position one fixing object are discussed, one makes use of data observed in one single time, the other makes use of data observed in one period of time. The localization of mobile object is accomplished by nonlinear Kalman filter. Based on the formulae of localization errors, the rules are analyzed, which describe the relationship between the localization precision and the constellation factors, such as constellation shape, the height of satellite. The method to design the constellation is presented with the help of these rules.Orbital maneuver is the primary condition for satellite autonomy, and it is the basis of phase keeping, phase maneuver and rendezvous. The dissertation presents a new method for Orbital maneuver based on Zero Effort Miss Steering, and many problems in this method are studied. The problem of control benchmark is solved by the use of HPOP, and the problem of constant thrust control is solved by H control theory and PWPF modulator.更多还原