Time-Optimal Pitch Control of Satellites Using Solar Radiation Pressure

Pande, K. C.; Davies, M. S.; Modi, V. J.

doi:10.2514/3.62135

Cited by 27 publications

(17 citation statements)

References 3 publications

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“…(13), (42), (48), and (49). The integration is carried out using International Mathematical and Statistical Library (IMSL) routine DDASPG based on the Petzoid-Gear BDF method.…”

Section: Resultsmentioning

confidence: 98%

“…Here = 3 is the relative degree of the unperturbed system (13). The objective is to find a SMC law u such that w has no effect on the output.…”

Section: Theorem 1 [32]: Disturbance Rejectionmentioning

confidence: 99%

“…These configurations have been suggested for sun-pointing satellites [7,8] and gravity-oriented satellites . Spinning [6][7][8][9][10][11][12][13] and Nomenclature a semi-major axis A surface area of solar flap exposed to impinging photons C 2 s pAr/(I x 2 ), a dimensionless solar parameter e orbital eccentricity h i control parameters, i = 1,2 i orbit inclination with respect to the equatorial planê i,ĵ,k unit vectors along the satellite body-fixed axes X, Y, Z, respectively I k principal centroidal moment of inertia of satellite about k-axis, k = x,y,z K (I y −I z )/I x ; satellite mass distribution parameter n j unit vector along normal to the surface of solar flap-j p nominal solar radiation pressure constant at 1 AU from the sun p i , q i control parameters, i = 1,2 r distance between the center of pressure of the solar flap from the system center of mass R orbital radius R E earth radius s j unit vector of the incoming light from the sun on the solar flap-j O-X o ,Y o ,Z o coordinate axes in the local vertical frame O-X,Y,Z satellite body coordinate frame s angle between the equatorial and ecliptic planes L satellite pitch angle with respect to orbital frame satellite pitch angle with respect to inertial framẽ satellite pitch angle tracking error with respect to inertial frame j in-plane angular rotation of the solar flap-j earth gravitational constant control parameter solar aspect angle or the angle between the direction of the sun and the nodal line d , s , t, a a fraction of impinging photons diffusely reflected, specularly reflected, transmitted, and absorbed, respectively angle with respect to the inertial axis Y I /a 3 , mean orbital rate ( · )j ( · ) for jth solar flap, j = 1,2 ( · ) o ( · ) at = 0 ( · ) , ( · ) d( · )/d and d 2 ( · )/d 2 , respectively |( · )| max absolute maximum amplitudes of ( · )…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

Patel¹,

Kumar²,

Behdinan³

2009

Acta Astronautica

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“…(13), (42), (48), and (49). The integration is carried out using International Mathematical and Statistical Library (IMSL) routine DDASPG based on the Petzoid-Gear BDF method.…”

Section: Resultsmentioning

confidence: 98%

“…Here = 3 is the relative degree of the unperturbed system (13). The objective is to find a SMC law u such that w has no effect on the output.…”

Section: Theorem 1 [32]: Disturbance Rejectionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

Patel¹,

Kumar²,

Behdinan³

2009

Acta Astronautica

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“…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 nutation damping and attitude control of a dual-spin satellite using multiple solar plates has been considered [7]. For the time-optimal pitch angle control, a SRP controller has been designed [8]. The three-axis attitude control and attitude stabilization of Earth-pointing satellites using solar torque have been treated [9,10].…”

Section: Introductionmentioning

confidence: 99%

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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Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure

Srinivasan

Lee

Singh

2015

Progress in Systems Engineering

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Time-Optimal Pitch Control of Satellites Using Solar Radiation Pressure

Cited by 27 publications

References 3 publications

Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

Variable structure control for satellite attitude stabilization in elliptic orbits using solar radiation pressure

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

Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure

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