Dynamics and control of a spacecraft with a moving pulsating ball in a spherical cavity

Vreeburg, J.P.B.

doi:10.1016/s0094-5765(97)00095-7

Cited by 30 publications

(3 citation statements)

References 7 publications

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“…Its disadvantages, beside occasional failure, are that the repertoire of manoeuvres is small and their execution is slow. At NLR a different type of model for the liquid effects (slosh) has been developed (Vreeburg 1997). It consists of a mass with variable shape, internal flow and degrees of freedom that should allow representing characteristic features of liquid behaviour.…”

Section: Spacecraft Control and Liquid Sloshingmentioning

confidence: 99%

Liquid Dynamics from Spacelab to Sloshsat

Vreeburg¹

2008

Microgravity Sci. Technol

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The European participation in manned spaceflight had a strong impact on research in the natural sciences because weightlessness became available as experimental condition. Preparation for Spacelab required many decisions on organization, funding and allocation of resources. Lessons were learned from results obtained in precursors like Skylab or in unmanned programs such as TEXUS. ESA with scientists from the major disciplines instituted Working Groups that acted as consultant bodies. European experiment hardware has been realized by industry using specifications and not, traditionally, by evolution in a laboratory. The development of the Fluid Physics Module preceded many instruments for liquid research in space. The training of Payload Specialists for the operation of the FPM included theory of fluids and laboratory instruction. The dynamics of spacecraft with a partially filled tank can be studied in weightlessness only. Observation of the liquid behaviour inside the tank is a challenging problem but the momentum of the rigid part of the spacecraft can be tracked accurately. Analytical expressions for transient liquid flow in a moving tank should be identified, together with the tank motion. A validated model of liquid momentum transfer during spacecraft manoeuvres will make many missions more efficient and less costly. Sloshsat FLEVO was flown to provide reference data for this purpose.

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Section: Spacecraft Control and Liquid Sloshingmentioning

confidence: 99%

Liquid Dynamics from Spacelab to Sloshsat

Vreeburg¹

2008

Microgravity Sci. Technol

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“…In recent years, the large-amplitude slosh models were proposed and improved to meet with the demand of the development of spacecraft. Detailedly, a constraint-surface model has been validated to be suitable for the modeling of in-orbit large-amplitude slosh dynamics (Berry and Tegart, 1975; Zhou and Huang, 2015; Liu et al, 2020); a moving pulsating ball model was proposed by Vreeburg (1997), and its practicability has been validated by the in-orbit flight tests of the “Slohsat FLEVO” satellite; a 3DOF-rigid-pendulum model was proposed, on the base of the spherical pendulum model, to investigate more comprehensive nonlinear motion modes of a liquid in spherical propellant tanks (Liu et al, 2019). In recent years, some new numerical computation methods for large-amplitude liquid slosh, being important techniques for the validation of nonlinear EMMs, also have achieved great progress (Huang et al, 2018; Nguyen-Thanh et al, 2019; Tang and Yue, 2017).…”

Section: Introductionmentioning

confidence: 99%

Wave-based attitude control of in-orbit spacecraft with large-amplitude slosh

Liu

Yue

et al. 2022

Journal of Vibration and Control

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This paper aims to reach high-quality attitude control and large-amplitude slosh suppression when a typical liquid-filled spacecraft executes three-axial large-angle maneuvers, by applying a wave-based attitude controller (WBAC). First, the sloshing dynamics is modeled by using a spherical pendulum, whose motion is expressed by splitting its coordinates. Thus, the large-amplitude lateral sloshing and the rotary sloshing as well as the over-all rigid motion of a liquid with respect to the tank in spacecraft can be approximately described. Second, the dynamics equations of system in terms of hybrid coordinate for the liquid-filled spacecraft are derived via the Lagrangian formulation. Third, an improved WBAC for three-axial large-angle maneuvers of in-orbit liquid-filled spacecraft is designed by adding a derivative control law and a gravity-gradient-torque compensation law to a wave-based control law. Simulations of three-axial large-angle maneuver demonstrate good performance of the WBAC in shortening completion time of attitude maneuvering, suppressing the jitter in the angular velocity of spacecraft, and accelerating the large-amplitude slosh suppression, simultaneously. The results indicate the potential applications of the proposed WBAC in the large-angle attitude maneuvering of liquid-filled spacecraft when there exists large-amplitude liquid slosh.

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“…The research of modeling and computer simulation in the filed of space technology has been explored since 1960s and the relative theory and techniques were founded [1]. Dynamic modeling for the object being studied has become the basic step in system design and analysis [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Solid Launcher Dynamical Analysis and Autopilot Design

Sun¹

2011

IJIGSP

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The dynamics of a small solid launch vehicle has been investigated. This launcher consists of a liquid upper stage and three fundamental solid rocket boosters aligned in series. During the ascent flight phase, lateral jets and grid fins are adopted by the flight control system to stable the attitude of the launcher. The launcher is a slender and aerodynamically unstable vehicle with sloshing tanks. A complete set of six-degrees-of-freedom dynamic models of the launcher, incorporation its rigid body, aerodynamics, gravity, sloshing, mass change, actuator, and elastic body, is developed. Dynamic analysis results of the structural modes and the bifurcation locus are calculated on the basis of the presented models. This complete set of dynamic models is used in flight control system design. A methodology for employing numerical optimization to develop the attitude filters is presented. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics, propellant slosh, and flex. Later a control approach is presented for flight control system of the launcher using both State Dependent Riccati Equation (SDRE) method and Fast Output Sampling (FOS) technique. The dynamics and kinematics for attitude stable problem are of typical nonlinear character. SDRE technique has been well applied to this kind of highly nonlinear control problems. But in practice the system states needed in the SDRE method are sometimes difficult to obtain. FOS method, which makes use of only the output samples, is combined with SDRE to accommodate the incomplete system state information. Thus, the control approach is more practical and easy to implement. The resulting autopilot can provide stable control systems for the vehicle.

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Dynamics and control of a spacecraft with a moving pulsating ball in a spherical cavity

Cited by 30 publications

References 7 publications

Liquid Dynamics from Spacelab to Sloshsat

Liquid Dynamics from Spacelab to Sloshsat

Wave-based attitude control of in-orbit spacecraft with large-amplitude slosh

Solid Launcher Dynamical Analysis and Autopilot Design

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