Deviation iterating approach for transfer orbit design with J2 perturbation

2011 ◽  
Author(s):  
Hong-Bo Zhang ◽  
Wei Zheng ◽  
Guo-Jian Tang
Keyword(s):  
Orbit Design ◽  
Transfer Orbit

Geosynchronous Transfer Orbit design: A practical approach

2011 ◽  
Author(s):  
E. Hernandez ◽  
J. Bolivar ◽  
Q. Wang
Keyword(s):  
Practical Approach ◽  
Orbit Design ◽  
Transfer Orbit

scholarly journals A Study on Optimal Earth-Moon Transfer Orbit Design Using Mixed Impulsive and Continuous Thrust

2010 ◽  
Vol 38 (7) ◽  
pp. 684-692 ◽  
Author(s):  
Tae-Soo No ◽  
Gyeong-Eon Jeon
Keyword(s):  
Orbit Design ◽  
Transfer Orbit

Transfer Orbit Design and Control Based on Forbes' Assumption

2010 ◽  
Vol 29-32 ◽  
pp. 1211-1216
Author(s):  
Li Li Zheng ◽  
Jian Ping Yuan ◽  
Zhan Xia Zhu
Keyword(s):  
Control Problem ◽  
Design Method ◽  
Equations Of Motion ◽  
Polar Coordinates ◽  
Keplerian Orbit ◽  
Orbit Design ◽  
Orbit Control ◽  
Transfer Orbit ◽  
And Control

In order to meet the requirements of space operation, the spacecrafts must maneuver agilely with the artifical propulsion. The orbit under artificial control is termed as Non-Keplerian orbit which does not follow Kepler’s Laws. The transfer orbit design under the continuous thrust is one of the most important topics in this new field. Shape-based method for Non-Keplerian orbit design is developed in this paper. Firstly, the equations of motion are established in polar coordinates system. And then the nondimensional variables are introduced for computation accuracy and speed, which give rise to nondimensional equations of motion. The general equation is derived with which common curves could be utilized in orbit design. In addition, the orbit design method is described based on Forbes’ velocity assumption and the formulation of the radius r with respect to time t, which is a sinusoidal function. The determination of the coefficients causes the orbit design problem to translate into an orbit control problem. The requisite thrust magnitude and direction are available via the simplified nondimensional equations of motion. In the end, an example of the transfer orbit is given. The result demonstrates that the shape-based method is feasible for the transfer orbit design or control problem under the continuous thrust, and the fuel expenditure is practicable.

scholarly journals A Study on Earth-Moon Transfer Orbit Design

2012 ◽  
Vol 13 (1) ◽  
pp. 106-116 ◽  
Author(s):  
Tae-Soo No ◽  
Ji-Marn Lee ◽  
Gyeong-Eon Jeon ◽  
Dae-Ro Lee ◽  
Ghang-Ho Kim
Keyword(s):  
Orbit Design ◽  
Transfer Orbit

scholarly journals Performance evaluation of multi-GNSSs navigation in super synchronous transfer orbit and geostationary earth orbit

2021 ◽  
Vol 2 (1) ◽  
Author(s):  
Tao Shi ◽  
Xuebin Zhuang ◽  
Liwei Xie
Keyword(s):  
Global Navigation Satellite System ◽  
Autonomous Navigation ◽  
Satellite System ◽  
Earth Orbit ◽  
Navigation Satellite ◽  
Geostationary Earth Orbit ◽  
Beidou Navigation Satellite System ◽  
Transfer Orbit ◽  
High Orbit ◽  
Global Navigation Satellite

AbstractThe autonomous navigation of the spacecrafts in High Elliptic Orbit (HEO), Geostationary Earth Orbit (GEO) and Geostationary Transfer Orbit (GTO) based on Global Navigation Satellite System (GNSS) are considered feasible in many studies. With the completion of BeiDou Navigation Satellite System with Global Coverage (BDS-3) in 2020, there are at least 130 satellites providing Position, Navigation, and Timing (PNT) services. In this paper, considering the latest CZ-5(Y3) launch scenario of Shijian-20 GEO spacecraft via Super-Synchronous Transfer Orbit (SSTO) in December 2019, the navigation performance based on the latest BeiDou Navigation Satellite System (BDS), Global Positioning System (GPS), Galileo Navigation Satellite System (Galileo) and GLObal NAvigation Satellite System (GLONASS) satellites in 2020 is evaluated, including the number of visible satellites, carrier to noise ratio, Doppler, and Position Dilution of Precision (PDOP). The simulation results show that the GEO/Inclined Geo-Synchronous Orbit (IGSO) navigation satellites of BDS-3 can effectively increase the number of visible satellites and improve the PDOP in the whole launch process of a typical GEO spacecraft, including SSTO and GEO, especially for the GEO spacecraft on the opposite side of Asia-Pacific region. The navigation performance of high orbit spacecrafts based on multi-GNSSs can be significantly improved by the employment of BDS-3. This provides a feasible solution for autonomous navigation of various high orbit spacecrafts, such as SSTO, MEO, GEO, and even Lunar Transfer Orbit (LTO) for the lunar exploration mission.

Optimal Spacecraft Orbit Design for Inertial Alignment with Ground Telescopes

2021 ◽  
Author(s):  
Adam W. Koenig ◽  
Simone D'Amico ◽  
Eliad Peretz ◽  
Wayne Yu ◽  
Sun Hur-Diaz ◽  
...  
Keyword(s):  
Orbit Design ◽  
Spacecraft Orbit

Orbit Design Optimization for Planetary Crosslink Radio Occultation

2021 ◽  
Vol 69 (5) ◽  
pp. 179-186
Author(s):  
Tomotaka Yamamoto ◽  
Satoshi Ikari ◽  
Hiroki Ando ◽  
Takeshi Imamura ◽  
Asako Hosono ◽  
...  
Keyword(s):  
Design Optimization ◽  
Radio Occultation ◽  
Orbit Design
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