AEROSPACE SHANGHAI, Volume. 41, Issue 5, 113(2024)
Indirect Method of Energy-optimized Plane Trajectory Optimization for Electric Propulsion of Mars Orbit Insertion
Figures & Tables(11)
Fig. 2. Moving trajectories of the probe during and after orbit insertion when Tmax=2 N
Fig. 3. Relationship between the optimal thrust direction and the velocity direction over time when Tmax=2 N
Fig. 4. Moving trajectory of the probe during orbit insertion when Tmax=490 N
Fig. 5. Relationship between the optimal thrust direction and the velocity direction over time when Tmax=490 N
Fig. 6.
Fig. 7.
Table 1.
Comparison of the orbital parameters before and after probe orbit insertion when<i> T</i><sub>max</sub>=2 N View tableView in ArticleTable 1.
Comparison of the orbital parameters before and after probe orbit insertion when<i> T</i><sub>max</sub>=2 N 轨道参数 双曲线参数 实际椭圆轨道参数 目标椭圆轨道参数 半长轴/km 42 802.16 53 691.90 53 689.90 偏心率 1.116 8 0.925 685 0.925 686 近火点半径/km 5 000 3 990.10 3 989.90 近火点幅角/(°) 181.70 153.60 —
Table 2.
Comparison of the orbital parameters before and after probe orbit insertion when<i> T</i><sub>max</sub>=490 N View tableView in ArticleTable 2.
Comparison of the orbital parameters before and after probe orbit insertion when<i> T</i><sub>max</sub>=490 N 轨道参数 双曲线参数 实际椭圆轨道参数 目标椭圆轨道参数 半长轴/km 3 251.85 53 687.90 53 689.90 偏心率 2.537 6 0.925 687 0.925 686 近火点半径/km 5 000 3 989.70 3 989.90 近火点幅角/(°) 180.12 156.77 —
Table 3.
<bold>Comparison of the orbital parameters before and after the probe orbit insertion when <i>T</i><sub>max</sub>=490 N</bold>，<bold>and <i>V</i><sub>2</sub>=3.628 km/s</bold> View tableView in ArticleTable 3.
<bold>Comparison of the orbital parameters before and after the probe orbit insertion when <i>T</i><sub>max</sub>=490 N</bold>，<bold>and <i>V</i><sub>2</sub>=3.628 km/s</bold> 轨道参数 双曲线参数 实际椭圆轨道参数 目标椭圆轨道参数 半长轴/km 3 251.85 53 690.23 53 689.90 偏心率 2.488 4 0.925 684 0.925 686 近火点半径/km 4 840.3 3 990.01 3 989.90 近火点幅角/(°) 180.12 205.14
Table 4.
<bold>Comparison of the orbital parameters before and after the probe orbit insertion when <i>T</i><sub>max</sub>=2 N</bold>，<bold>and <i>V</i><sub>2</sub>=1 km/s</bold> View tableView in ArticleTable 4.
<bold>Comparison of the orbital parameters before and after the probe orbit insertion when <i>T</i><sub>max</sub>=2 N</bold>，<bold>and <i>V</i><sub>2</sub>=1 km/s</bold> 轨道参数 双曲线参数 实际椭圆轨道参数 目标椭圆轨道参数 半长轴/km 42 802.21 167 098.29 53 689.90 偏心率 1.233 6 0.976 134 0.925 686 近火点半径/km 10 000 3 987.90 3 989.90 近火点幅角/(°) 182.03 200.51 —
Tools
Get Citation
Copy Citation Text
Haiyang LI, Xiaowen DUAN, Yingjie ZHAO, Tongjie LIU, Xi LU. Indirect Method of Energy-optimized Plane Trajectory Optimization for Electric Propulsion of Mars Orbit Insertion[J]. AEROSPACE SHANGHAI, 2024, 41(5): 113
Paper Information
Category: Innovation and Exploration
Received: Feb. 23, 2024
Accepted: --
Published Online: Jan. 15, 2025
The Author Email:
© Copyright 2018-2021 | Chinese Laser Press.
All Rights Reserved 沪ICP备15018463号-20