应急轨道飞行器的若干问题研究
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摘要
高技术局部战争、非战争军事行动等应急任务对空间支援提出了新的需求,要求飞行器以“快速响应、成本低廉、按需部署”进入空间为目标。论文以应急轨道飞行器及其相关技术为研究对象,主要研究内容如下:
进行了应急轨道飞行器的概念研究。在临近空间的基础上,给出了应急轨道的概念,重点分析了应急轨道飞行器所具有的特有优势。
研究了应急轨道飞行器对任务区域的覆盖特性。分析了圆形应急轨道轨道倾角对任务区域覆盖的影响,给出了覆盖任务区域的升交点变化范围。基于卫星覆盖带设计了应急轨道星座。利用STK仿真软件仿真分析了近圆轨道的覆盖特性。
分析了应急轨道飞行器相对于地面测控站的运动特性,提出了应急轨道飞行器捕获天线的布站要求。分析了升交点地理经度对过捷点距离的影响。
设计了一种车载的高动态测控试验系统,建立了较详细的双轴天线以及天线转台转动的数学模型,并利用Matlab和STK仿真了给定工况下天线及转台转动的角度变化。在直线模型假设下,建立了飞行器过顶的数学模型,研究了地面天线方位角的变化规律,给出了天线跟踪盲区范围的计算方法。
研究了临近空间应急轨道的光照条件。分析了轨道阳光角的变化规律,给出了飞行器体轴的太阳光照角的计算方法。研究了太阳矢量相对于飞行器本体的运动特性,给出了太阳光热收集系统聚焦镜跟踪太阳的控制方法。
给出了采用摆镜对飞行器上可见光相机的像移补偿方法,研究了基于摆镜的像移补偿算法,推导了飞行器对地球表面目标成像时摆镜旋转角度和旋转角速度的计算公式。
最后,对全文进行了总结,指出了论文的研究成果,并对下一步需要研究的内容进行了展望。
Eemergency missions such as high-tech local wars and non-war military operations has put forward new requirements for space support, which calls for vehicles access to space with fast response,low cost and deployment-on-demand as its goal. The thesis has researched responsive orbit vehicle and relevant techniques, the main contents are summarized as follows.
The concept of responsive orbit vehicle is studied. On the basis of near space, the concept of the responsive orbit is given. The unique advantages of the responsive orbit vehicle are primarily analyzed.
Coverage characteristic of mission location by responsive orbit vehicle is studied. Affection of circular orbit inclination on the mission location coverage is analyzed and the range of longitude of ascending node of orbits by which target can be covered is discussed. Based on street of cov erage, a responsive space constellation of vehicles is put forward. Coverage characteristic of near circular orbits is simulated and analyzed using STK software.
Movement characteristic of ground-based tracking is analyzed. According to the above, a request of arranging the capture antenna for TT&C of responsive orbit vehicle is suggested. Affection of longitude of ascending node on closest distance between ground station and responsive orbit vehicle is anlyzed.
An experiment system of high dynamic TT&C is designed. Mathematical model of angle movement of dual-axis antenna and turntable is derived and simulated under the given situation. Based on the straight-line motion assumption, mathematical model of responsive orbit vehicle passes is established. Change rule of azimuth angle is studied and the extent of the zenith blind zone is discussed in detail.
The condition of responsive orbit vehicle illumination is studied. Change rule of sun-orbit angle is analyzed. The calculating method of vehicle body sun-angle is given. Based on analysis of motion characteristic of sunlight in orbit, methods to resolve sun tracking is proposed.
The method of arranging a oscillating mirror frontage the optical camera is put forward for image motion compensation. A algorithm of image motion compensation is presented. The formula of oscillating mirror angle and angular velocity imaging in earth surface is derived.
Finally, the paper summarizes the work of research and points out production, and makes expectation for the contents which need to be studied in future.
进行了应急轨道飞行器的概念研究。在临近空间的基础上,给出了应急轨道的概念,重点分析了应急轨道飞行器所具有的特有优势。
研究了应急轨道飞行器对任务区域的覆盖特性。分析了圆形应急轨道轨道倾角对任务区域覆盖的影响,给出了覆盖任务区域的升交点变化范围。基于卫星覆盖带设计了应急轨道星座。利用STK仿真软件仿真分析了近圆轨道的覆盖特性。
分析了应急轨道飞行器相对于地面测控站的运动特性,提出了应急轨道飞行器捕获天线的布站要求。分析了升交点地理经度对过捷点距离的影响。
设计了一种车载的高动态测控试验系统,建立了较详细的双轴天线以及天线转台转动的数学模型,并利用Matlab和STK仿真了给定工况下天线及转台转动的角度变化。在直线模型假设下,建立了飞行器过顶的数学模型,研究了地面天线方位角的变化规律,给出了天线跟踪盲区范围的计算方法。
研究了临近空间应急轨道的光照条件。分析了轨道阳光角的变化规律,给出了飞行器体轴的太阳光照角的计算方法。研究了太阳矢量相对于飞行器本体的运动特性,给出了太阳光热收集系统聚焦镜跟踪太阳的控制方法。
给出了采用摆镜对飞行器上可见光相机的像移补偿方法,研究了基于摆镜的像移补偿算法,推导了飞行器对地球表面目标成像时摆镜旋转角度和旋转角速度的计算公式。
最后,对全文进行了总结,指出了论文的研究成果,并对下一步需要研究的内容进行了展望。
Eemergency missions such as high-tech local wars and non-war military operations has put forward new requirements for space support, which calls for vehicles access to space with fast response,low cost and deployment-on-demand as its goal. The thesis has researched responsive orbit vehicle and relevant techniques, the main contents are summarized as follows.
The concept of responsive orbit vehicle is studied. On the basis of near space, the concept of the responsive orbit is given. The unique advantages of the responsive orbit vehicle are primarily analyzed.
Coverage characteristic of mission location by responsive orbit vehicle is studied. Affection of circular orbit inclination on the mission location coverage is analyzed and the range of longitude of ascending node of orbits by which target can be covered is discussed. Based on street of cov erage, a responsive space constellation of vehicles is put forward. Coverage characteristic of near circular orbits is simulated and analyzed using STK software.
Movement characteristic of ground-based tracking is analyzed. According to the above, a request of arranging the capture antenna for TT&C of responsive orbit vehicle is suggested. Affection of longitude of ascending node on closest distance between ground station and responsive orbit vehicle is anlyzed.
An experiment system of high dynamic TT&C is designed. Mathematical model of angle movement of dual-axis antenna and turntable is derived and simulated under the given situation. Based on the straight-line motion assumption, mathematical model of responsive orbit vehicle passes is established. Change rule of azimuth angle is studied and the extent of the zenith blind zone is discussed in detail.
The condition of responsive orbit vehicle illumination is studied. Change rule of sun-orbit angle is analyzed. The calculating method of vehicle body sun-angle is given. Based on analysis of motion characteristic of sunlight in orbit, methods to resolve sun tracking is proposed.
The method of arranging a oscillating mirror frontage the optical camera is put forward for image motion compensation. A algorithm of image motion compensation is presented. The formula of oscillating mirror angle and angular velocity imaging in earth surface is derived.
Finally, the paper summarizes the work of research and points out production, and makes expectation for the contents which need to be studied in future.
引文
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[2] Lawrence A.Cooper.The Strategy of Responsive Space:Assured Access to Space Review,3rd Responsive Space Conference[C],Los Angeles,CA,2005
[3] Matthew G . Richards , Distinguishing Attributes for the Operationally Responsive Space Paradigm[C],6th Responsive Space Conference,Los Angeles,CA,2008
[4] Stuart Eves.Future Optical Surveillance Using Small Satellites[C],5th Responsive Space Conference,Los Angeles,CA,2007
[5] Tom Doyne . ORS and Tacsat Activites Including The Emerging Ors Enterprise[C],5th Responsive Space Conference,Los Angeles,CA,2007
[6]段锋.临近空间飞行器现状与发展[J].航空科学与技术,2007(6):22~25
[7] Don Knight.Concept of Operations for Operationally Responsive Space[C].4th Responsive Space Conference,Los Angeles,CA,2006
[8] John Carrico . Time Critical Targeting Using Responsive Tactical Satellite[C].4th Responsive Space Conference,Los Angeles,CA,2006
[9] RayMing Chang.SatCarrier CONOPS:A Concept of Operations for Satellite Carriers[C].7 th Responsive Space Conference,Los Angeles,CA,2009
[10] Eric Miller,Omar Medina,etc.Virtual Mission Operations Center and ORS Ground System Enterprise[C].7 th Responsive Space Conference,Los Angeles,CA,2009
[11]孙悦,赵和鹏.临近空间飞行器应用分析与展望[J].无线电工程,2008(10):26~27
[12]原野.航空、近太空和航天系统对战场的综合作用分析[J].国际太空,2008(5):11~19
[13]沈民谊,蔡镇远.卫星通信天线、馈源、跟踪系统[M].北京:人民邮电出版社,1993
[14] James R. Wertz,Richard E. Van Allen,Christopher J. Shelner.Aggressive Surveillance as a Key Application Area for Responsive Space[C] . 4th Responsive Space Conference, Los Angeles,CA, 2006
[15] Lo,M.W.“The Long Term Forecast of Station View Periods”. JPL TDA Progress Report.42-118.14,August 1994
[16]翁慧慧.遥感卫星对地覆盖分析与仿真[D].中国人民解放军信息工程大学硕士学位论文,2006
[17]闫野,任萱,陈磊.卫星对地球覆盖情况的判据及算法探讨[J].宇航学报,1999(2):55~60
[18]贺佳,郭庆.编队飞行卫星覆盖特性研究[J].电子技术应用,2005(11):53~55
[19]吴廷勇,吴诗其.区域覆盖共地面轨迹星座的优化设计[J].电子与信息学报,2006(8):1360~1363
[20]林西强,张育林.利用升交点经度进行轨道设计的方法[J].上海航天,2000(2):16~20
[21] Walker J G.Continuous whole-earth coverage by circular-orbit satellite patterns[R].Royal Aircraft Establishment Technical Report77044,1977
[22] AdamsW,Riders L.Circular polar constellation providing continuous single or multiple coverage above a specified latitude[J].The Journal of the Astronautical Sciences,1987,35(2):155~192
[23] Drain J E.Cefola P J,Castiel D.Elliptical orbit constellations- a new paradigm for higher efficiency in space systems[C].2000 IEEE Aerospace Conference Montana:IEEE,2000(7):27~35
[24]王启宇,袁建平,朱战霞.对地观测小卫星星座设计及区域覆盖性能分析[J].西北工业大学学报,2006(4),427~430
[25]张雅声,张育林.纬度带连续单重覆盖星座快速设计方法与实现[J].装备指挥技术学院学报,2004(1):55~58
[26] Scott C.Larrimore.Partially continuous earth coverage from a responsive space constellation[C].5th Responsive Space Conference,Los Angeles,CA,2007
[27]杨颖,王琦.STK在计算机仿真中的应用[M].北京:国防工业出版社,2004
[28]龚小林,李树锋,马东堂.低轨星座系统覆盖特性仿真分析[J].卫星与网络,2008:58~60
[29]胡彩波,王宏兵,胡丽丽.STK软件卫星可见性和覆盖分析[J].全球定位系统,2007(4):40~43
[30]柴霖,吴潜,雷厉.近空间高动态飞行器测控系统发展趋势分析[J].2008(1):13~18
[31]魏晨曦,焦雯.国外军用小卫星的发展及测控技术[J].2004(5):48~52
[32]杨红俊,罗巧云.美国小卫星利用天基测控系统的研究[J].飞行器测控学报,1999(4):22~27
[33]陈皓生,陈大融等.微型飞行器测控系统的研究现状和发展[J].测控技术,2002(12):1~4
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