摘要
主要围绕火星探测器在地球上空200 km处飞离地球开始一直到火星入轨点的转移轨道段轨道设计所做的轨道任务分析、摄动因素分析及近地轨道火星探测器姿态所受干扰力矩进行理论与仿真研究.一般情况下,火星探测器受到的摄动力与中心天体引力相比是很小的,但摄动力的长期累积作用不可忽视.轨道摄动研究已经成为轨道确定、观测预报、轨道改进和轨道设计等工作的基础,有利于寻找最佳的轨道修正位置,可显著减少轨道修正次数,从而降低火星探测器的燃料消耗.
Orbit tasks and perturbing factors about an orbit design of a Mars prober flying from an orbit at 200km above the Earth to an injection point of a target planet（Mars） are analyzed and simulated.Perturbing moments influenced on attitude of the Mars prober running on the Near-Earth orbit are studied and simulated.Usually,the perturbing force acting on the Mars prober is too small compared with a gravitation of a primary celestial body,but long-term cumulative effect of the perturbing force is great significant,so that it isn’t neglected.The study on orbit perturbation already became a research fundament of orbit determination,orbit observation,orbit prediction,orbit improvement and orbit design;it is convenient to find the optimal position of orbit correction in order to decrease orbit adjustment frequency to reduce fuel consumption of Mars prober
出处
《测试技术学报》
2011年第3期189-194,共6页
Journal of Test and Measurement Technology
关键词
火星探测
任务分析
转移轨道
摄动因素
Mars exploration
task analysis
transfer orbit
perturbing factor
