Volume 19, Issue 9 (2019)                   Modares Mechanical Engineering 2019, 19(9): 2121-2128 | Back to browse issues page

XML Persian Abstract Print


Download citation:
BibTeX | RIS | EndNote | Medlars | ProCite | Reference Manager | RefWorks
Send citation to:

Navabi M, Davodi A. Modeling of Fuel Sloshing in a Spacecraft and Control it by Active Control Method Using Nonlinear Control. Modares Mechanical Engineering. 2019; 19 (9) :2121-2128
URL: http://journals.modares.ac.ir/article-15-18033-en.html
1- New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran , m_navabi@sbu.ac.ir
2- New Technologies Engineering Faculty, Shahid Beheshti University, Tehran, Iran
Abstract:   (2026 Views)
Fuel sloshing is one of the most important factors in disturb attitude of the spacecraft from desire in orbital maneuver. So, controlling this phenomenon is a critical problem in attitude control. There are active and passive control methods to control fuel sloshing. Active method has better responses to control fuel sloshing and its effect on attitude of the spacecraft in the same time; so, mostly this method is used. For this aim, it is necessary to model slosh dynamic. In this paper, slosh dynamic is modeled by a multi-pendulum model, and, then, coupled equations of the spacecraft and fuel slosh dynamic are derived. In the presented model, pendulums can move freely in 3D atmosphere, and this matter makes presented model closer to real. Coupled equations of the spacecraft and fuel slosh dynamic are nonlinear. Therefore, nonlinear control methods should be used to attitude control in more realistic mode. In this paper, two candidate Lyapunov functions are proposed; then, using these functions, controllers are obtained. The effectiveness of these controllers on attitude of the spacecraft and pendulums is described by a simulation. Although, there are some little differences in time responses based on two controllers, results of simulation illustrate good responsibility of controllers to control aims.
Full-Text [PDF 1106 kb]   (145 Downloads)    

Received: 2018/03/21 | Accepted: 2019/02/4 | Published: 2019/09/1

References
1. Agrawal BN. Dynamic characteristics of liquid motion in partially filled tanks of a spinning spacecraft. Journal of Guidance, Control, and Dynamics. 1993;16(4):636-640. [Link] [DOI:10.2514/3.21061]
2. Hervas JR, Reyhanoglu M. Thrust-vector control of a three-axis stabilized upper-stage rocket with fuel slosh dynamics. Acta Astronautica. 2014;98:120-127. [Link] [DOI:10.1016/j.actaastro.2014.01.022]
3. Biswal KC, Bhattacharrya SK, Sinha PK. Dynamic characteristics of liquid filled rectangular tank with baffles. Journal Institution of Engineers India Part Cv Civil Engineering Division. 2003;84:145-148. [Link]
4. Peterson LD, Crawley EF, John Hansman R. Nonlinear fluid slosh coupled to the dynamics of a spacecraft. AIAA Journal. 1989;27(9):1230-1240. [Link] [DOI:10.2514/3.10250]
5. Gasbarri P, Sabatini M, Pisculli A. Dynamic modeling and stability parametric analysis of a flexible spacecraft with fuel slosh. Acta Astronautica. 2016;127:141-159. [Link] [DOI:10.1016/j.actaastro.2016.05.018]
6. Li Q, Ma X, Wang T. Equvalent mechanical model for liquid sloshing during draining. Acta Astronautica. 2011;68(1-2):91-100. [Link] [DOI:10.1016/j.actaastro.2010.06.052]
7. Liu F, Yue B, Zhao L. Attitude dynamics and control of spacecraft with a partially filled flexible panels. Acta Astronautica. 2018;143:327-336. [Link] [DOI:10.1016/j.actaastro.2017.11.036]
8. Yu SX, Yun QR. Using sliding mode control method to suppress fuel sloshing of a liquid-filled spacecraft. 27th Chinese Control and Decision Conference (CCDC), 23-25 May 2015, Qingdao, China. Piscataway: IEEE; 2015. [Link] [DOI:10.1109/CCDC.2015.7162113]
9. Reyhanoglu M. Maneuvering control problems for a spacecraft with unactuated fuel slosh dynamics. Proceedings of IEEE Conference on Control Applications (CCA), 25-25 June 2003, Istanbul, Turkey. Piscataway: IEEE; 2003. [Link]
10. Navabi M, Davodi A. Modeling and control of fuel sloshing and its effect on spacecraft attitude. Journal of Space Science & Technology. 2019;11(4):11-22. [Persian] [Link]
11. Reyhanoglu M, Hervas JR. Robatically controlled sloshing suppression in point-to-point liquid container transfer. Journal of Vibration and Control. 2012;19(14):2137-2144. [Link] [DOI:10.1177/1077546312456865]
12. Hervas JR, Reyhanoglu M, Tang H. Thrust-vector control of a tree-axis stabilized spacecraft with fuel slosh dynamics. 13th International Conference on Control, Automation and Systems (ICCAS), 20-23 Oct 2013, Gwangju, South Korea. Piscataway: IEEE; 2013. [Link]
13. Navabi M, Soleymanpour S. Command filtered modular adaptive backstepping attitude control of spacecraft in presence of disturbance torque. Modares Mechanical Engineering. 2015;15(7):285-296. [Persian] [Link]
14. Navabi M, Hosseini MR. Modeling and spacecraft attitude control using reaction wheel with feedback linearization, its performance study subject to power and EULERINT. Modares Mechanical Engineering. 2018;18(1):51-61. [Persian] [Link]
15. Meirovitch L, Kwak MK. State equations for a spacecraft with maneuvering flexible appendages in terms of quasi-coordinates. Applied Mechanics Reviews. 1989;42(11S):S161-S170. [Link] [DOI:10.1115/1.3152387]
16. Navabi M, Davoodi A. 3D modeling and control of fuel sloshing in a spacecraft. IEEE 4th International Conference on Knowledge-Based Engineering and Innovation (KBEI), 22-22 Dec 2017, Tehran, Iran. Piscataway: IEEE; 2017. [Link] [DOI:10.1109/KBEI.2017.8324928]

Add your comments about this article : Your username or Email:
CAPTCHA

Send email to the article author