Robust control of a spin-stabilized spacecraft via a 1DoF gimbaled-thruster and two reaction wheels

Kouhi, Hamed; Kabganian, Mansour; Saberi, Farhad Fani; Shahravi, Morteza

doi:10.1016/j.isatra.2016.10.007

Cited by 10 publications

(6 citation statements)

References 41 publications

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“…The external disturbance rejection is not possible for an attitude control system based only on these devises. In study (33) , a large control torque has been produced by the interaction between the reaction wheels angular momentum and the spacecraft spin rate, but in this paper the use of these devices is deficient.…”

Section: July 2017 the Aeronautical Journalmentioning

confidence: 99%

“…According to the previous literatures, these performances need some thrusters (RCSs) and fuel consumption which are not efficient for a small spacecraft. Similar to (33) , in this paper a small spacecraft equipped with a gimbaled-SRM is considered in which the nozzle mass properties are not negligible with respect to the body's. Although orbital manoeuvres are performed in a three dimensional space, in some papers such as Reyhanoglu and Hervas (18) , a planar manoeuvre is considered in order to facilitate the stability analysis.…”

Section: July 2017 the Aeronautical Journalmentioning

confidence: 99%

“…The three-dimensional mathematical modelling of a two-body spacecraft is derived in Ref. 33 by whichω s as the spacecraft body angular acceleration can be calculated aṡ…”

Section: Nonlinear Dynamics Of the Planar Manoeuvrementioning

confidence: 99%

“…The three-dimensional mathematical modelling of a two-body spacecraft is derived in Ref. 33 by which as the spacecraft body angular acceleration can be calculated as where , ω n = ω s + ω r , τ ns = τ s + τ n , ρ ns = ρ no − ρ so , ρ sn = − ρ ns .…”

Section: Model Formulationmentioning

confidence: 99%

“…It is obvious that using a liquid propellant rocket is not efficient or possible for a small spacecraft for which a SRM (solid rocket motor) is used where all mass properties of the SRM (including solid fuel) will be added to the nozzle mass properties. Therefore, for a small spacecraft equipped with a SRM, the aforementioned interaction cannot be neglected and leads to nonlinear two-body dynamics (4,28,33) . Note that for large spacecraft, a TVC was used together with RCSs (1,18,26,27) and for a small spacecraft, it has been combined with the spin-stabilisation method (4) .…”

Section: Introductionmentioning

confidence: 99%

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Gimbaled-thruster based nonlinear attitude control of a small spacecraft during thrusting manoeuvre

et al. 2017

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In this paper, a novel thrusting manoeuvre control scheme is proposed for a small spacecraft which is based only on the gimbaled thrust vector control (TVC) system. The spacecraft structure is composed of a body and a gimbaled thruster where common attitude control systems such as reaction control system (RCS) and spin stabilisation are not employed. A nonlinear two-body model is considered for the characterisation of the gimbaled-nozzle spacecraft where the gimbal actuator provides the only active control input. The spacecraft attitude is affected by a large exogenous disturbance torque which is generated by a thrust vector misalignment from the centre of mass (CM). To achieve some performance goals in the both transient and steady-state modes, a new control scheme is derived based on the combination of two linear and nonlinear controllers. The proposed method ensures the attitude and thrust vector stability during an impulsive orbital manoeuvre while eliminating and rejecting an exogenous disturbance torque. The numerical simulations illustrate the applicability of this method for using in a small spacecraft and its efficiency in sustained operation.

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Section: July 2017 the Aeronautical Journalmentioning

confidence: 99%

Section: July 2017 the Aeronautical Journalmentioning

confidence: 99%

“…The three-dimensional mathematical modelling of a two-body spacecraft is derived in Ref. 33 by whichω s as the spacecraft body angular acceleration can be calculated aṡ…”

Section: Nonlinear Dynamics Of the Planar Manoeuvrementioning

confidence: 99%