Abstract
Considering the requirements of traditional thruster layout, the characteristics of missions and working loads of the satellites, a thruster layout method for attitude controlling (AC) with force couple and orbit controlling (OC) with multi-thrust options is proposed. By making reasonable use of surface space and optimizing configuration quantity of thruster of the satellites, impact on orbit altitude caused by attitude control is reduced as far as possible. With different thrust options, requirements for large impulse orbit transfer and small impulse trajectory maintenance are satisfied. Mathematical simulation and in-orbit flight verification show that the proposed method is effective and feasible.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
Shi, K., Cheng, Y., Zhang, Y.: Research on configuration of attitude control thrusters. Mod. Defense Technol. 2(40), 44–49 (2012)
Cheng, Y., Zhang, Y.: Research on the spacecraft attitude control with the influence of the. Mod. Defense Technol. 5(36), 41–49 (2008)
Hu, W., **, H., Wang, Q.: Research on optimizing mounting position of satellite 490N thruster. Spacecraft Eng. 6(12), 44–47 (2013)
Xu, C.,Cui, J., Zhang, L., et al.: Application research of genetic algorithm in installation adjusting optimization of satellite engine. 2(23), 58–63 (2014)
Renwei, Z.: Satellite Orbit Attitude Dynamics and Control. Beihang University Press, Bei**g (1998)
Wang, Z.: Design and Performance Research of Orbital Control Thruster for Formation Micro-nano Satellites (2021)
Li, T., Shan, T., Liu, Z., et al.: Design of Configuration and Assembly for High Resolution Agile Remote Sensing Satellite (2022)
Guan, Z., Ruan, W., Liu, W., et al.: Study of trajectory-controlled thrust vector technology application in air defense missile. Air Space Defense 2(3) (2020)
Wei, Y., Guo, S., Zhao, J., et al.: Design characteristic and verification of propulsion system of Change-4 probe. Spacecraft Eng. 4(28) (2019)
Changfu, G.: Spacecraft Dynamics. Science and Technology Press, Bei**g (2006)
Chen, Z., Song, Z., Lyu, J., et al.: Equivalent models of liquid sloshing under the excitation of small pulse in microgravity everonment. Aerosp. Control Appl. 48(3), 84–92 (2022)
Liu, X., Nie, W., Zhang, H., et al.: Characterisics of pulse detonation rocket engine with specific impulse and small thrust demand. Aerosp. Control Appl. 48(6), 67–75 (2022)
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2024 The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
About this paper
Cite this paper
Chen, L., Zou, K., Zhang, Y., Zhang, C., Hao, J. (2024). Design and Verification of Satellite Propulsion Layout with Force Couple for AC and Multi-thrust Options for OC. In: Wang, Y., Zou, J., Xu, L., Ling, Z., Cheng, X. (eds) Signal and Information Processing, Networking and Computers. ICSINC 2023. Lecture Notes in Electrical Engineering, vol 1186. Springer, Singapore. https://doi.org/10.1007/978-981-97-2116-0_45
Download citation
DOI: https://doi.org/10.1007/978-981-97-2116-0_45
Published:
Publisher Name: Springer, Singapore
Print ISBN: 978-981-97-2115-3
Online ISBN: 978-981-97-2116-0
eBook Packages: EngineeringEngineering (R0)