Nonlinear decoupling sliding mode control and attitude control of spacecraft

Singh, Sahjendra N.; Iyer, Ashok

doi:10.1109/7.42079

Cited by 67 publications

(18 citation statements)

References 24 publications

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“…Form (1) and (7) we can write a relation between external moment acting on the body about its mass center and angular momentum as [9]- [11]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

“…The relation above with an angular momentum H  and external moment M  is the rotational equation of motion of a rigid body in a circular orbit [9]- [10]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

“…Relation between angular velocity  and attitude angles and their rates for circular orbit can be written as [9]:…”

Section: Advances In Spacecraft Systems and Orbit Determination 158mentioning

confidence: 99%

“…The angular velocity of the body-fixed reference frame B with basis vectors 123 ,, bbb   is given as [9]:…”

Section: Rigid Body In Circular Orbitmentioning

confidence: 99%

“…The rotational equation of motion of a rigid body in an inertial reference frame N about center of mass is [9]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

See 4 more Smart Citations

Design of Sliding Mode Attitude Control for Communication Spacecraft

Abdulhamitbilal¹,

Jafarov²

2012

Advances in Spacecraft Systems and Orbit Determination

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“…Form (1) and (7) we can write a relation between external moment acting on the body about its mass center and angular momentum as [9]- [11]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

“…The relation above with an angular momentum H  and external moment M  is the rotational equation of motion of a rigid body in a circular orbit [9]- [10]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

“…Relation between angular velocity  and attitude angles and their rates for circular orbit can be written as [9]:…”

Section: Advances In Spacecraft Systems and Orbit Determination 158mentioning

confidence: 99%

“…The angular velocity of the body-fixed reference frame B with basis vectors 123 ,, bbb   is given as [9]:…”

Section: Rigid Body In Circular Orbitmentioning

confidence: 99%

“…The rotational equation of motion of a rigid body in an inertial reference frame N about center of mass is [9]:…”

Section: Rigid Body Dynamicsmentioning

confidence: 99%

See 3 more Smart Citations

Design of Sliding Mode Attitude Control for Communication Spacecraft

Abdulhamitbilal¹,

Jafarov²

2012

Advances in Spacecraft Systems and Orbit Determination

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Adaptive attitude control for spacecraft systems with sensor and actuator attacks

Sun

Hou

2021

Adaptive Control & Signal

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This paper is addressed with the attitude stabilization problem for spacecraft systems with external disturbances in physical layer and sensor and actuator attacks (SAAs) in cyber layer. Some state-dependent attacks are implanted in system measurement data channels and control input commands. Two stable adaptive backstepping controllers are constructed for two different assumption conditions with sensor attack, in which a compensation term in each controller is included to eliminate the effects of SAAs and recover the ideal system performance. Under the proposed control schemes, the system states can asymptotically converge to zero even if SAAs and external disturbances are co-existing.The validity of the developed scheme is demonstrated via a simulation example.

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Neuro-genetic adaptive attitude control

Dracopoulos

Jones

1994

Neural Comput & Applic

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Nonlinear decoupling sliding mode control and attitude control of spacecraft

Cited by 67 publications

References 24 publications

Design of Sliding Mode Attitude Control for Communication Spacecraft

Design of Sliding Mode Attitude Control for Communication Spacecraft

Adaptive attitude control for spacecraft systems with sensor and actuator attacks

Neuro-genetic adaptive attitude control

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