Attitude dynamics of satellites orbiting an asteroid

Misra, A. K.; Panchenko, Yulia

doi:10.1007/bf03256495

Cited by 34 publications

(19 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For this study, satellite attitude dynamics derived in Refs. [14,15] are considered. (Readers may refer to [14,15] for the details.)…”

Section: Attitude Dynamics Of Asteroid-orbiting Spacecraftmentioning

confidence: 99%

“…Additionally, researchers have analyzed the attitude dynamics of spacecraft in asteroids' gravitational fields [14][15][16][17][18][19]. The authors showed that irregularly-shaped asteroids can cause attitude resonance [14][15][16] and chaotic phenomenon [17]. The authors of [18] found natural Sun-synchronous orbits with Sun-tracking attitude motions for an orbit-attitude coupled system around a small rotating body [18].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

WITHDRAWN: Composite Immersion and Invariance Based Adaptive Attitude Control of Asteroid-Orbiting Spacecraft in Elliptic Orbit

Lee¹,

Singh²

2021

Preprint

View full text Add to dashboard Cite

This paper proposes a new composite noncertainty-equivalence adaptive (CNCEA) control system for the attitude (roll, pitch, and yaw angle) control of a spacecraft in an orbit around a uniformly rotating asteroid based on the immersion and invariance (I&I) theory. For the design, it is assumed that the asteroid's gravitational parameters and the spacecraft's inertia matrix are not known. In contrast to certainty-equivalence adaptive (CEA) or noncertainty-equivalence adaptive (NCEA) systems, the CNCEA attitude control system's composite identifier uses the attitude angle tracking error, a nonlinear state-dependent vector function, and model prediction error for parameter estimation. The Lyapunov analysis shows that in the closed-loop system, the Euler angles asymptotically track the reference attitude trajectories. Interestingly, there exist two parameter error-dependent attractive manifolds, to which the closed-loop system's trajectories converge. Moreover, the composite identifier using two types of error signals provides stronger stability properties in the closed-loop system. Simulation results are presented for the attitude control of a spacecraft orbiting in the vicinity of the asteroid 433 Eros. These results show precise nadir pointing attitude regulation, despite uncertainties in the system.

show abstract

“…For this study, satellite attitude dynamics derived in Refs. [14,15] are considered. (Readers may refer to [14,15] for the details.)…”

Section: Attitude Dynamics Of Asteroid-orbiting Spacecraftmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

WITHDRAWN: Composite Immersion and Invariance Based Adaptive Attitude Control of Asteroid-Orbiting Spacecraft in Elliptic Orbit

Lee¹,

Singh²

2021

Preprint

View full text Add to dashboard Cite

show abstract

“…We also can obtain the pitch controller response as Figure 32. Compared with the attitude stability analysis in references [10][11][12][13], closed-loop controllers are proposed to make the spacecraft attitude angles tracking the desired attitude as (42) and reach the null state as time increases. Moreover, from simulation results one can obtain the control law neutralizing the effects of asteroid shape and mass distributions and orbital eccentricity as well as external disturbances and uncertainties described as (43).…”

Section: Adaptive Backstepping Sliding Mode Controlmentioning

confidence: 99%

“…Riverin and Misra have proposed the attitude motion of the spacecraft depending heavily on the shape of the asteroid and the rotational state [12]. Then Misra and Panchenko have found the radius for which resonant pitch oscillations, considering the general three-dimensional attitude motion in 2006 [13]. Riverin and Misra have examined the spacecraft pitch motion assuming the spacecraft is in an equatorial orbit but spacecraft attitude control algorithms have not been perfectly investigated.…”

Section: Introductionmentioning

confidence: 99%

Attitude Analysis and Robust Adaptive Backstepping Sliding Mode Control of Spacecrafts Orbiting Irregular Asteroids

Liang

2014

Mathematical Problems in Engineering

View full text Add to dashboard Cite

Attitude stability analysis and robust control algorithms for spacecrafts orbiting irregular asteroids are investigated in the presence of model uncertainties and external disturbances. Rigid spacecraft nonlinear attitude models are considered and detailed attitude stability analysis of spacecraft subjected to the gravity gradient torque in an irregular central gravity field is included in retrograde orbits and direct orbits using linearized system model. The robust adaptive backstepping sliding mode control laws are designed to make the attitude of the spacecrafts stabilized and responded accurately to the expectation in the presence of disturbances and parametric uncertainties. Numerical simulations are included to illustrate the spacecraft performance obtained using the proposed control laws.

show abstract

“…This point mass model can be improved by considering the orbit-attitude coupling, especially in the case of a large-sized spacecraft. The dynamical model with orbit-attitude coupling can also improve the traditional attitude dynamics near asteroids [12][13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

Stabilization of coupled orbit–attitude dynamics about an asteroid utilizing Hamiltonian structure

2017

Astrodyn

View full text Add to dashboard Cite

The gravitationally coupled orbit-attitude dynamics, also called the full dynamics, in which the spacecraft is modeled as a rigid body, is a high-precision model for the motion in the close proximity of an asteroid. A feedback control law is proposed to stabilize relative equilibria of the coupled orbit-attitude motion in a uniformly rotating second degree and order gravity field by utilizing the Hamiltonian structure. The feedback control law is consisted of potential shaping and energy dissipation. The potential shaping makes the relative equilibrium a minimum of the modified Hamiltonian by modifying the potential artificially. With the energy-Casimir method, it is theoretically proved that an unstable relative equilibrium can always be stabilized in the Lyapunov sense by the potential shaping with sufficiently large feedback gains. Then, the energy dissipation leads the motion to converge to the relative equilibrium. The proposed stabilization control law has a simple form and is easy to implement autonomously, which can be attributed to the utilization of natural dynamical behaviors in the controller design.

show abstract

Attitude dynamics of satellites orbiting an asteroid

Cited by 34 publications

References 4 publications

WITHDRAWN: Composite Immersion and Invariance Based Adaptive Attitude Control of Asteroid-Orbiting Spacecraft in Elliptic Orbit

WITHDRAWN: Composite Immersion and Invariance Based Adaptive Attitude Control of Asteroid-Orbiting Spacecraft in Elliptic Orbit

Attitude Analysis and Robust Adaptive Backstepping Sliding Mode Control of Spacecrafts Orbiting Irregular Asteroids

Stabilization of coupled orbit–attitude dynamics about an asteroid utilizing Hamiltonian structure

Contact Info

Product

Resources

About