The Frontiers of Society, Science and Technology, 2020, 2(12); doi: 10.25236/FSST.2020.021203.
Zhang Junqi 1, Su Hongyu 2, Ji Yuxing 3, Fu Si 4, Yu Elai 5
1 International Department, the Affiliated High School of Scnu, Guangzhou 510630, China
2 Xiamen Foreign Language School, Xiamen, Fujian 361000, China
3 Qingdao No.2 Middle School, Qingdao, Shandong 266061, China
4 CIS program
5 Culver Academies, Culver, Indiana, 1300 Academy Rd, United States
There are three main steps in the process: First to Launch spacecraft into circular orbit around the Earth. And then accelerate the spacecraft at the appropriate point in its orbit around the Earth to transfer the spacecraft orbit into an elliptical orbit around the Sun such that the aphelion of the spacecraft orbit is at Mars’s orbit and perihelion is at the earth’s orbit. When the spacecraft approaches Mars, slow the spacecraft the correct amount so that it enters orbit around Mars. After that, we will discuss sensitivity and uncertainty during the whole trip. Finally, we will conclude all the data and approaches.
Hohmann transfer orbit, Kepler's third law, Kepler’s third law, Newton's law of gravitation, Newton's second law
Zhang Junqi, Su Hongyu, Ji Yuxing, Fu Si, Yu Elai. Hohmann Transfer Orbiting Applying into the Space Traveling. The Frontiers of Society, Science and Technology (2020) Vol. 2 Issue 12: 9-15. https://doi.org/10.25236/FSST.2020.021203.
[1] Myron Kayton. HOHMANN TRANSFER ORBIT DIAGRAM, Avionics Navigation Systems.
[2] Hironori A et al (1997). Nonlinear dynamics of the tethered satellite systems in the station keeping phase .J Guidance, Control, & Dynamics, vol. 20, no.2, pp.403-406