Large angle pitch attitude maneuver of a satellite using solar radiation pressure

Venkatachalam, R.

doi:10.1109/7.259519

Cited by 32 publications

(16 citation statements)

References 10 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%

“…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 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]. Based on the solution of the two-point boundary value problem, a feedback control law for large pitch angle control of spacecraft using the SRP has been obtained [14]. The feasibility of translatory control surfaces for the attitude control have been also explored [15][16].…”

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: Introductionmentioning

confidence: 99%

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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“…This can be achieved by altering the period of the oscillation using changes in sail geometry (area or center of pressure), changes to the rotational inertia of the spacecraft [9], or changes to the reflectivity of the solar sail [10]. The latter option is particularly attractive because changing the pattern of reflectivity, perhaps using liquid-crystal panels [11], can roll the spacecraft to manage the plane of the heliostable oscillation and, secondly, can superimpose a time-variation on the restoring torque to either increase or diminish the amplitude of the excursions.…”

Section: Introductionmentioning

confidence: 99%

Synchronized Orbits and Oscillations for Free Altitude Control

Ceriotti

Harkness

McRobb

2014

Journal of Guidance, Control, and Dynamics

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“…Using SRP for attitude control of high-altitude satellites and interplanetary probes has been proposed. [11][12][13][14] In some cases, proportionaldifferential (PD) controllers are used and stability is proven via linear modeling. [15][16][17] Others have used adaptive and optimal control for better application [18][19][20] and fuzzy systems have also been used for satellite attitude control.…”

Section: Introductionmentioning

confidence: 99%

Adjustable Adaptive Fuzzy Attitude Control using Nonlinear SISO Structure of Satellite Dynamics

Moradi

Esmaelzadeh

Ghasemi

2012

Trans. Japan Soc. Aero. S Sci.

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This paper presents a method for three-dimensional attitude stabilization of a satellite. The pitch loop of the satellite is controlled by a momentum wheel; whereas the roll/yaw loops are stabilized using two magnetic torques along their respective axes. In order to design an efficient controller, the stability conditions are considered based on a nonlinear model of system. An adjustable adaptive fuzzy system is proposed as the method to design the controller. The span of membership functions are tuned using errors of fuzzy inputs with respect to their references. Results show that fuzzy sets cover all variations of fuzzy inputs and optimal fuzzy output is gained. The Lyapunov synthesis method is used to prove the stability of the closed-loop system. The efficiency of the controller in converging of the position error to close to zero is also shown using some numerical simulations.

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Large angle pitch attitude maneuver of a satellite using solar radiation pressure

Cited by 32 publications

References 10 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

Synchronized Orbits and Oscillations for Free Altitude Control

Adjustable Adaptive Fuzzy Attitude Control using Nonlinear SISO Structure of Satellite Dynamics

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