木星系探测及行星穿越任务轨迹初步设计
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摘要
基于我国未来木星系探测任务需求,初步设计了任务轨迹。以目前的发射能力,要实现木星的环绕探测必将利用行星借力,需设计借力轨迹。首先将脉冲变轨的轨迹设计问题转化为参数优化问题,在满足2029—2032年间发射并且飞行时间不超过7年的约束条件下,使用PSO算法对发射时刻、借力时刻、深空机动时刻、到达时刻等参数进行优化,使得探测器需提供的总速度增量最小。探测器进入木星系后,利用木卫3借力捕获至环木大椭圆轨道,又利用木卫4构造共振借力,最终捕获至木卫4的环绕轨道。在此基础上,还考虑了天王星飞越的拓展任务,天王星探测器在到达木星时与木星系探测器分离,利用木星借力可无消耗飞往天王星,并在2043年完成天王星的飞越探测任务。
The trajectories of the Chinese Jovian mission is designed. Gravity assist is needed to achieve circumjovian missions, for current launch capability is not enough. With the launch window between 2029 and 2032 and the flight time not exceeding 7 years, the trajectory with gravity assists and impulsive maneuvers is formulated by some parameters such as the time of launch, gravity assist, maneuver and arrival, and the Particle Swam Optimization(PSO) algorithm is applied to optimize these parameters so that the total velocity increment is minimum. After entering Jovian system, the spacecraft is captured to a big circumjovian elliptical orbit by using gravity assist of the Ganymede. And then resonant gravity assist orbits are constructed to capture the spacecraft to the orbit of the Callisto. Based on the Jovian mission, an expansion mission of Uranus flyby was considered. The Uranus detector, which is released from the Jovian system detector when arriving at Jupiter, will fly to the Uranus after Jovian gravity assist with no fuel consumption and flied by Uranus before 2043,it can provide reference for the future task of deep space exploration in China.
The trajectories of the Chinese Jovian mission is designed. Gravity assist is needed to achieve circumjovian missions, for current launch capability is not enough. With the launch window between 2029 and 2032 and the flight time not exceeding 7 years, the trajectory with gravity assists and impulsive maneuvers is formulated by some parameters such as the time of launch, gravity assist, maneuver and arrival, and the Particle Swam Optimization(PSO) algorithm is applied to optimize these parameters so that the total velocity increment is minimum. After entering Jovian system, the spacecraft is captured to a big circumjovian elliptical orbit by using gravity assist of the Ganymede. And then resonant gravity assist orbits are constructed to capture the spacecraft to the orbit of the Callisto. Based on the Jovian mission, an expansion mission of Uranus flyby was considered. The Uranus detector, which is released from the Jovian system detector when arriving at Jupiter, will fly to the Uranus after Jovian gravity assist with no fuel consumption and flied by Uranus before 2043,it can provide reference for the future task of deep space exploration in China.
引文
[1] DIEHL R,KAPLAN D,PENZO P. Satellite tour design for the Galileo mission[C]//21st Aerospace Sciences Meeting. Reno,NV:American Institute of Aeronautics and Astronautics,1983.
[2] ONEIL W,MITCHELL R. Galileo mission overview[C]//21st Aerospace Sciences Meeting. Reno,NV:American Institute of Aeronautics and Astronautics,1983.
[3] JOHNSON T V. The Galileo mission[J]. Scientific American,1995,273(6):44-51.
[4] NYBAKKEN R. The Juno mission to Jupiter—a pre-launch update[C]//Aerospace Conference,2011. Big Sky,MT,USA:IEEE,2011.
[5] BUFFINGTON B. Trajectory design for the Europa Clipper mission concept[C]//AIAA/AAS Astrodynamics Specialist Conference.[S.l]:AIAA,2014.
[6] YANG C,BAOYIN H X,LI J F. Trajectory analysis and design for a Jupiter exploration mission[J]. Chinese Astronomy and Astrophysics,2013,37(1):77-89.
[7] BROUCKE R. The celestial mechanics of gravity assist[C]//Astrodynamics Conference. Minneapolis,MN:AIAA,1988.
[8] SIMS J A,LONGUSKI J M,STAUGLER A J. V∞leveraging for interplanetary missions:multiple-revolution orbit techniques[J].Journal of Guidance,Control,and Dynamics,1997,20(3):409-415.
[9] SIMS J,LONGUSKI J. Analysis of V(infinity)leveraging for interplanetary missions[C]//Astrodynamics Conference.[S. l]:American Institute of Aeronautics and Astronautics,Inc,1994
[10] LANTUKH D V,RUSSELL R P,CAMPAGNOLA S. V-Infinity leveraging boundary-value problem and application in spacecraft trajectory design[J]. Journal of Spacecraft and Rockets,2015,52(3):697-710.
[2] ONEIL W,MITCHELL R. Galileo mission overview[C]//21st Aerospace Sciences Meeting. Reno,NV:American Institute of Aeronautics and Astronautics,1983.
[3] JOHNSON T V. The Galileo mission[J]. Scientific American,1995,273(6):44-51.
[4] NYBAKKEN R. The Juno mission to Jupiter—a pre-launch update[C]//Aerospace Conference,2011. Big Sky,MT,USA:IEEE,2011.
[5] BUFFINGTON B. Trajectory design for the Europa Clipper mission concept[C]//AIAA/AAS Astrodynamics Specialist Conference.[S.l]:AIAA,2014.
[6] YANG C,BAOYIN H X,LI J F. Trajectory analysis and design for a Jupiter exploration mission[J]. Chinese Astronomy and Astrophysics,2013,37(1):77-89.
[7] BROUCKE R. The celestial mechanics of gravity assist[C]//Astrodynamics Conference. Minneapolis,MN:AIAA,1988.
[8] SIMS J A,LONGUSKI J M,STAUGLER A J. V∞leveraging for interplanetary missions:multiple-revolution orbit techniques[J].Journal of Guidance,Control,and Dynamics,1997,20(3):409-415.
[9] SIMS J,LONGUSKI J. Analysis of V(infinity)leveraging for interplanetary missions[C]//Astrodynamics Conference.[S. l]:American Institute of Aeronautics and Astronautics,Inc,1994
[10] LANTUKH D V,RUSSELL R P,CAMPAGNOLA S. V-Infinity leveraging boundary-value problem and application in spacecraft trajectory design[J]. Journal of Spacecraft and Rockets,2015,52(3):697-710.