Lunar spacecraft powered descent control using higher-order sliding mode techniques

Orr, Jeb S.; Shtessel, Yuri B.

doi:10.1016/j.jfranklin.2011.06.015

Cited by 12 publications

(23 citation statements)

References 9 publications

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“…It should be noted that in large and massive spacecraft or launchers with a liquid propellant rocket, several heavy and complex components as well as fuel tanks are located in the body not presented (or attached) at the rotatable nozzle. Therefore, the mass properties of the liquid propellant rocket are negligible in comparison with the body's, and as a result, the dynamical interaction between the movable nozzle and body will be very small (1,18,22,23). 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.…”

Section: July 2017 the Aeronautical Journalmentioning

confidence: 99%

“…An impulsive orbital manoeuvre Gimbaled-thruster based nonlinear attitude control… (i.e., retrofiring before an atmospheric re-entry) is used to generate a velocity increment v by using a large thrust force. During the burning of a rocket, thrust vector misalignment from the CM always exists and is inescapable (1) . This misalignment produces a large disturbance torque that tends to divert the orientation of spacecraft and thrust vector from the desired inertial direction.…”

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: Introductionmentioning

confidence: 99%

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

et al. 2017

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“…With the strong robustness against uncertainties, SMC has been widely studied in advanced guidance and control of aerospace vehicles [15,[20][21][22][23][24]. It is well known that control inputs are discontinuous due to the utilization of sign function existing in the conventional SMC to dominate uncertainties and disturbances [25][26][27].…”

Section: Exploration Rovers A) and Opportunity (Mars Exploration Rovementioning

confidence: 99%

Finite-time super-twisting sliding mode control for Mars entry trajectory tracking

Zhao

Yang

et al. 2015

Journal of the Franklin Institute

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“…Many (higher-order) sliding mode disturbance observer designs are based on sliding mode control techniques [18][19][20][21].…”

mentioning

confidence: 99%

“…For these methods, the required switching gain for guaranteeing convergence is a monotonically increasing function of the uncertainty bound, or the corresponding bound for uncertainty derivatives [18][19][20][21]. Although the observations provided by disturbance observers are always continuous, the filtering process in first-order sliding mode disturbance observer, and the integration process in super-twisting disturbance observer can only attenuate instead of totally rejecting chattering in the observations [19].…”

mentioning

confidence: 99%

Incremental Sliding-Mode Fault-Tolerant Flight Control

Wang

Kampen

Chu

et al. 2019

Journal of Guidance, Control, and Dynamics

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This paper proposes a novel control framework that combines the recently reformulated incremental nonlinear dynamic inversion with (higher-order) sliding mode controllers/observers, for generic multi-input/multi-output nonlinear systems, named incremental sliding mode control. As compared to the widely used approach that designs (higher-order) sliding mode controllers/observers based on nonlinear dynamic inversion, the proposed incremental framework can further reduce the uncertainties whilst requiring less model knowledge. Since the uncertainties are reduced in the incremental framework, theoretical analyses demonstrate that the incremental sliding mode control can passively resist a wider range of perturbations with reduced minimum possible control/observer gains. These merits are validated via numerical simulations for aircraft command tracking problems, in the presence of sudden actuator faults and structural damages.

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Lunar spacecraft powered descent control using higher-order sliding mode techniques

Cited by 12 publications

References 9 publications

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

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

Finite-time super-twisting sliding mode control for Mars entry trajectory tracking

Incremental Sliding-Mode Fault-Tolerant Flight Control

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