Dynamic Influence of Propellant Sloshing Estimation Using Hybrid: Mechanical Analogy and CFD

Abstract

Liquid propellant sloshing, which induces perturbations to dynamic behavior of spacecraft, is a serious problem. This paper proposes an approach based on equivalent mechanics theory and Computational Fluid Dynamics (CFD) technology to estimate the dynamic influence of propellant sloshing on spacecraft. A mechanical model was built by CFD technique and packed as a ''sloshing'' block utilized in the spacecraft Guidance Navigation and Control (GNC) simulation loop. The block takes the motion characteristics of the spacecraft as inputs and outputs perturbative force and torques induced by propellant sloshing. It is more convenient to utilize in analysis of the coupling effect between propellant sloshing dynamics and spacecraft GNC than CFD packages directly. A validation case is taken to validate the accuracy and the superiority of the approach. The deducing process is applied to practical cases, and the simulation results are presented to demonstrate the proposed approach is efficient in identifying the problems induced by sloshing and evaluating effectiveness of several typical schemes for suppressing sloshing.

Attitude maneuver control of liquid-filled spacecraft with unknown inertia and disturbances

“…Yue and Zhu (2014) presented a technique for designing command profiles for fuel-filled spacecraft; the dynamics inversion and input shaping method are used to ensure the spacecraft asymptotically tracks a desired reference output. Dong et al. (2009) combined the equivalent mechanics theory with computational fluid dynamics techniques to establish the mechanical model for a propellant sloshing aboard spacecraft, and the input shaping technique is successfully used for suppressing sloshing.…”

Fuzzy Disturbance Observer-Based Sliding Mode Control for Liquid-Filled Spacecraft With Flexible Structure Under Control Saturation

“…The associate editor coordinating the review of this manuscript and approving it for publication was Jianyong Yao . residence time and much more liquid fuel are needed for the spacecraft [16], [17]. However, due to the sloshing of the liquid fuel, the maneuverability of spacecraft is inevitably influenced, which causes the bad control performance and even the failure task [18], [19]. Therefore, the attitude stability control for LFS-FS with model uncertainties and external disturbance have been one of the important research topics.…”

“…and adaptive law(18) under κ 0 , γ 0 > 0, 0 < r < 1, and δ 1 , δ 2 > 0, then the attitude quaternion q v and the attitude angular veloticy ω will converge to small neighborhoods of origion by selecting suitable controller parameters.Proof: Define Lyapunov function candidate as…”