Inertially fixed pitch stabilization of satellites by solar radiation pressure

Pande, K. C.; Venkatachalam, R.

doi:10.1016/0094-5765(80)90057-0

Cited by 21 publications

(13 citation statements)

References 7 publications

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“…It is seen that similar to the previous cases, smooth regulation of the pitch angle is accomplished for each (e, i). The maximum values of the control surface deflections are about (14,17) [deg] for (e, i) = (0.05, 30 o ) and (10,11) [deg] for (e, i) = (0.3, 10 o ), respectively.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…(For simplicity in notation, the derivatives of functions with respect to θ will be denoted by overdots.) Differentiating α twice with respect to θ and using equations (1) and (5), it can be shown that [11,18,23]…”

Section: Dynamics Of Spacecraftmentioning

confidence: 99%

“…The development of an approximate, closed-form solution for libration motion and resonance of spinning satellites in the presence of solar radiation pressure has been considered [5]. In the literature, a variety of control systems have been also proposed for the attitude control of satellites using the SRP [6][7][8][9][10][11][12][13][14][15][16][17]. The solar pressure control of spinning satellite has been treated [6].…”

Section: Introductionmentioning

confidence: 99%

“…The three-axis attitude control and attitude stabilization of Earth-pointing satellites using solar torque have been treated [9,10]. Based on the Floquet theory, stabilization of the pitch attitude of a satellite in an inertially-fixed orientation using the SRP has been considered [11]. The design of solar pressure control systems for the attitude control of satellite using linear quadratic optimization and the gradient technique for minimum time control has been presented [12,13].…”

Section: Introductionmentioning

confidence: 99%

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Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Lee

Singh

2015

AIAA Guidance, Navigation, and Control Conference

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Based on the variable structure model reference adaptive control (VS-MRAC) theory, a new adaptive control system for the attitude control of satellites in elliptic orbits with uncertain dynamics, using solar radiation pressure (SRP), is derived. The nonaffine-incontrol nonlinear spacecraft model includes the gravity gradient torque, the control torque produced by two solar flaps, and external time-varying disturbance torque. The objective here is to derive a control law for the pitch attitude control using the pitch angle and pitch rate feedback. For the trajectory tracking of the pitch angle, a variable structure model reference adaptive attitude control system, including two relays and linear filters, is designed. Although, the modulation functions of the relays are functions of certain auxiliary signals, for simplicity in implementation, these functions are assigned constant values. Simulation results are presented which show that the simplified VS-MRAC law accomplishes precise attitude control of the spacecraft, despite unmodelled (unstructured) nonlinearities, parameter uncertainty and external disturbance torque in the model. NomenclatureA c , B c , h c , g g = Closed-loop system matrices a, e = Semi-major axis and eccentricity a mi , k m = Parameters of reference model S m B = Control input matrix A s , l p = Control surface area and the moment arm C s , C s = Solar parameter e 0 , e 0 , e 1 = Error signals f 0 , f 1 = Modulation functions g 0 , g a , g = Nonlinear functions I x , I y , I z = Moments of inertia of the satellite K = (I x − I y )/I z M g = Gravity gradient torque, M s , M d = Solar torque and disturbance torque i = Inclination of the orbital plane with ecliptic plane p = Solar radiation pressure, 4.65 × 10 −6 N m −2 y p , y m = Output signals * Professor, AIAA SciTech s = Laplace variable or differential operator v 0 , v 1 , v = Control input signals X b , Y b , Z b = Principal axes of the satellite α, α r = Pitch angle, reference pitch anglẽ α = Tracking error ξ i , χ i = Auxiliary signals X o , Y o , Z o = Orbital coordinates with X o along the local vertical, X o Y o defining the orbital plane δ i (i = 1, 2) = Control plate rotations θ = Orbital angle λ = Pitch attitude angle of the satellite with respect to orbital coordinates Λ f , λ i , b f = Regressor filter parameters ρ s = Reflectivity of the control surfaces φ = Location of the Sun from the line of nodes Ω = Mean orbital rate ω 1 , ω 2 , ω a = Regressor vectors θ i , Θ a , θ * i = Controller gains

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Dynamics Of Spacecraftmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Lee

Singh

2015

AIAA Guidance, Navigation, and Control Conference

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“…[6][7][8][9][10][11][12][13][14][15][16][17][18] A time-optimal SRP controller to control pitch angle has been obtained in Pande and Venkatachalam. 8 Based on a feedback linearization technique, a nonlinear SRP control law for the pitch attitude control has been presented. 11 Authors have also designed SRP control systems for the pitch angle control of uncertain models of satellites.…”

Section: Introductionmentioning

confidence: 99%

Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Lee

Singh

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Based on the [Formula: see text] adaptive control theory, a novel three-axis attitude control system for an axisymmetric spacecraft with uncertain dynamics moving in elliptic orbits, using solar radiation pressure, is derived. The nonaffine-in-control nonlinear spacecraft model includes the gravity gradient torque, the control torque produced by four solar flaps, and external time-varying disturbance moments. For the three-axis attitude control, an [Formula: see text] adaptive control system is designed, which includes a state predictor. A smooth projection algorithm is used to confine the estimated parameters within a desirable set. In the closed-loop system, the designed adaptive law accomplishes three-dimensional attitude control. A special feature of the attitude control system is that it is possible to select large adaptation gains for fast adaptation and to obtain quantifiable performance bounds. Simulation results show that in the closed-loop system, precise roll, yaw, and pitch angle control is accomplished, despite unmodeled nonlinearities, parameter uncertainty, and external disturbance inputs in the model.

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Optimal solar pressure attitude control of spacecraft—I

Pande

Venkatachalam

1982

Acta Astronautica

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Inertially fixed pitch stabilization of satellites by solar radiation pressure

Cited by 21 publications

References 7 publications

Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Solar Pressure Variable Structure Model Reference Adaptive Spacecraft Attitude Control in Elliptic Orbits

Three-axis L1 adaptive attitude control of spacecraft using solar radiation pressure

Optimal solar pressure attitude control of spacecraft—I

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