Current Situation and Trend of Mars Orbiting Exploration
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摘要:基于火星环绕探测的任务需求，围绕行星际转移及环火飞行的约束条件和环境特点，首先分析了火星环绕探测任务面临的主要技术难点，结合火星环绕器的任务要求和功能特点，总结了火星环绕探测的关键技术和解决途径，主要有自主安全捕获控制、长日凌自主管理、高速测控数传一体化、多码率自适应中继通信等技术。随后综述了环绕探测平台功能及技术的发展历程、趋势和创新性，具体有对地通信速率、导航与变轨能力、结构承载与推进系统等，根据未来火星探测需求，分析了环绕平台需要发展的新能力。最后，对未来环绕探测方向进行了分析。Abstract:Based on the mission requirements of Mars orbiting exploration, and the constraints and environmental characteristics of interplanetary transfer and flight around Mars, the main technical difficulties of Mars orbiting exploration missions were analyzed. Based on the mission requirements and functional characteristics of Tianwen-1 orbiter, key technologies and solutions for Mars orbiting exploration were summarized, which mainly include autonomous security control for Mars orbit insert, autonomous management of long solar transit, integration of measurement control and data transmission, and multiple communication rates adaptive relay communication. Then, the development history, trend and innovation of the functions and technologies of the Mars orbiting exploration platform were reviewed, including Mars-to-Earth communication rate, navigation and orbital transformation capability, structural load-carrying and propulsion system. According to the future requirements of Mars exploration, the new capabilities that the orbiting exploration platform needs to develop were analyzed. Finally, the future direction of Mars orbiting exploration was analyzed.
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Key words:
- Mars/
- orbiting exploration/
- orbiting platform/
- technology development
Highlights● As an important exploration form, orbiting exploration can obtain Martian surface topography, global image, surface geological structure, meteorological information and other exploration data by means of remote sensing. ● Through remotely-sensed image, a safe landing site can be selected for Mars Rover. ● The Mars Orbiter of Tianwen-1 integrated three functions of “orbiting, transporting and relaying” to maximize exploration efficiency. ● The independent management capability of Mars orbiter is constantly improving. ● The new capabilities of Mars orbiter for future Mars sampling and return missions are presented. -
表 1人类已经发射的火星探测器统计表
Table 1Statistics of Mars probes launched by mankind
探测器类型 国家 成功/次 部分成功/次 失败/次 合计/次 飞越 苏联 6 6 美国 3 2 5 环绕器 苏联 1 5 6 美国 5 2 7 日本 1 1 印度 1 1 阿联酋 1 1 着陆器 苏联 1 1 2 美国 7 1 8 环绕器
着陆器
（巡视器）苏/俄 3 4 7 美国 2 2 欧洲
航天局2 2 中国 1 1 合计 20 7 22 49 
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表 2火星探测器中低增益天线发展情况
Table 2Development of low-gain antennas in Mars probes
探测器 低增益天线 中增益天线 设计考虑 “水手”系列 收发共用，波束 ± 45°，轴向7 dBi 收发共用，波束 ± 18°，轴向14 dBi 飞行过程发动机工作期间对地全覆盖 “海盗”系列 收发共用，波束 ± 45°，轴向7 dBi 收发共用，波束 ± 18°，轴向14 dBi 飞行过程发动机工作期间对地全覆盖 “火星全球勘测者” 收发分开，波束 ± 40°，轴向6.5 dBi 飞行过程发动机工作期间对地全覆盖 “奥德赛” 接收，波束 ± 41°，轴向7 dBi 发射，波束 ± 14°，轴向16.5 dBi 飞行过程发动机工作期间对地全覆盖 “火星勘测轨道器” 收发共用，波束 ± 35°，轴向8 dBi 飞行过程发动机工作期间对地全覆盖 “天问一号”火星环绕器 收发分开，波束 ± 50°，轴向5 dBi 仅发射，波束 ± 25°，轴向5 dBi 关键阶段对地全覆盖 下载:
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表 3火星环绕器捕获控制策略
Table 3Mars orbit insert control strategy
探测器 发动机 轨道 轨控策略 关机条件 奥德赛 轨控703 N
姿控22 N近火点高度405 km
倾角93°在点火过程中，探测器姿态保持匀角速率 速度变化量达到目标值ΔV，同时点火时间满足：
1115~1 225 s火星快车 轨控400 N
姿控10 N近火点高度380 km
倾角25°姿态保持匀角速率
或姿态保持沿迹反方向速度变化量达到目标值ΔV，点火时为：标称点火时间至1.1倍标称点火时间 火星勘探
轨道器轨控6 × 170 N
姿控22 N近火点高度518 km
倾角93.5°姿态保持匀角速率 速度变化量达到目标值ΔV，点火时为：标称点火时间至1.1倍标称点火时间 “天问一号”火星环绕器 轨控3 000 N
姿控120 + 25 N近火点高度400 km
倾角11°姿态保持匀角速率
或惯性定向速度变化量达到目标值ΔV，点火时为：0.9倍标称点火时间至1.1倍标称点火时间 下载:
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