Inertia Estimation of Spacecraft Based on Modified Law of Conservation of Angular Momentum

Kim, Dong Hoon; Choi, Daegyun; Oh, Hwa-Suk

doi:10.5140/jass.2010.27.4.353

Cited by 15 publications

(5 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, the inertia varies during the missions in which spacecraft mass is affected. For instance, spacecraft mass decreases due to propellant consumption during operation, de-orbiting, structural changes, and connection with movable parts (Kim et al, 2010) . It is possible to construct the functions governing the spacecraft inertia change due to some factors, such as out-gassing and propellant consumption.…”

Section: Problem Formulation and Objectivesmentioning

confidence: 99%

Output feedback attitude control of flexible spacecraft under actuator misalignment and input nonlinearities

Javaid,

Zhen,

Shahid

et al. 2023

Journal of Vibration and Control

View full text Add to dashboard Cite

The attitude tracking control problem of flexible spacecraft subjected to parameter uncertainties, time-dependent external disturbances, actuator input nonlinearity, and input actuator misalignment is investigated in this paper. Explicitly, the proposed strategy addresses the input actuator misalignment and dead-zone issues that increase the controller design difficulties. Initially, a new second-order sliding mode observer (SoSMO) using an extended state approach is developed by adding a correction function to improve observer performance to estimate unwanted system perturbations. Then, a distinct SoSMO-based integral-type sliding mode control (ISMC) structure is designed in a unified manner to guarantee the asymptotic stability of the closed-loop system. Comparative numerical simulations under input actuator misalignment, the dead-zone nonlinearity, external disturbance, and inertia uncertainty are performed to illustrate the effectiveness of the proposed controller.

show abstract

Section: Problem Formulation and Objectivesmentioning

confidence: 99%

Output feedback attitude control of flexible spacecraft under actuator misalignment and input nonlinearities

Javaid,

Zhen,

Shahid

et al. 2023

Journal of Vibration and Control

View full text Add to dashboard Cite

show abstract

“…In general, the inertia matrix of a spacecraft is measured before launch and used in attitude control. However, it can change by many reasons like the fuel consumption and structure variation (Kim et al, 2010). The mathematical expression related to the changes in inertia caused by some specific factors can be described, such as the consumption of propellant.…”

Section: Attitude Kinematics and Dynamicsmentioning

confidence: 99%

Disturbance-observer-based attitude control under input nonlinearity

Javaid

Dong

2021

Transactions of the Institute of Measurement and Control

View full text Add to dashboard Cite

A disturbance observer-based control scheme is proposed in this paper to deal with the attitude stabilization problems of spacecraft subjected to external disturbances, parameter uncertainties, and input nonlinearities. Particularly, the proposed approach addresses the dead-zone issue, a non-smooth nonlinearity affiliated with control input that significantly increases controller design difficulties. A novel nonlinear disturbance observer (NDO) is developed, which relaxes the strong assumption in conventional NDO design that disturbances should be constants or varying with slow rates. After that, a special integral sliding mode controller (ISMC) is combined with the NDO to achieve asymptotic convergence of system states. Simulations are performed in the presence of time-varying disturbances, parameter uncertainties, and dead-zone nonlinearity to justify the effectiveness of the proposed control scheme.

show abstract

“…This latter was estimated, along with the inertia parameters, through off-line least-squares filtering of the angular velocity data sampled during free platform oscillations (step 2). Indeed, platform balancing is inherently related to inertia identification [15][16][17][18], with the latter usually required to complete the former.…”

Section: Introductionmentioning

confidence: 99%

Automatic Balancing for Satellite Simulators with Mixed Mechanical and Magnetic Actuation

2022

View full text Add to dashboard Cite

Dynamic spacecraft simulators are becoming a widespread tool to enable effective on-ground verification of the attitude determination and control subsystem (ADCS). In such facilities, the on-orbit rotational dynamics shall be simulated, thereby requiring minimization of the external torques acting on the satellite mock-up. Gravity torque is often the largest among the disturbances, and an automatic procedure for balancing is usually foreseen in such facilities as it is significantly faster and more accurate than manual methods. In this note, we present an automatic balancing technique which combines mechanical and magnetic actuation by the joint use of sliding masses and magnetorquers. A feedback control is employed for in-plane balancing in which the proportional and integral actions are provided by moving the masses, while the derivative action is provided by the magnetorquers. Compared to an earlier implementation by the authors relying on shifting masses only, the novel approach is shown to reduce the in-plane unbalance by an additional 45% on average.

show abstract

Inertia Estimation of Spacecraft Based on Modified Law of Conservation of Angular Momentum

Cited by 15 publications

References 2 publications

Output feedback attitude control of flexible spacecraft under actuator misalignment and input nonlinearities

Output feedback attitude control of flexible spacecraft under actuator misalignment and input nonlinearities

Disturbance-observer-based attitude control under input nonlinearity

Automatic Balancing for Satellite Simulators with Mixed Mechanical and Magnetic Actuation

Contact Info

Product

Resources

About