Optimal solar pressure attitude control of spacecraft—II

Venkatachalam, R.; Pande, K. C.

doi:10.1016/0094-5765(82)90011-x

Cited by 20 publications

(13 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Case A. Attitude control, effect of solar aspect angle 0 : 0 ¼ 30 and 90 [deg], (20,10,40) [deg], and disturbance input d a ¼ 0…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The design of solar pressure control systems for two-axis attitude control of satellite has been used in works by Pande and Venkatachalam. [18][19][20] The SRP control systems obtained in Pande and Venkatachalam 19 and Venkatachalam and Pande 20 are based on the linear quadratic optimization and gradient techniques for satellites in circular orbits. Researchers have also considered design of three-axis SRP attitude control systems.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

Lee

Singh

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

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.

show abstract

“…Case A. Attitude control, effect of solar aspect angle 0 : 0 ¼ 30 and 90 [deg], (20,10,40) [deg], and disturbance input d a ¼ 0…”

Section: Simulation Resultsmentioning

confidence: 99%

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:

View full text Add to dashboard Cite

show abstract

“…In addition, an algorithm for stabilising the system is outlined as proposed by Hermes [74]. A simple two-surface solar controller has also been described and applied to the attitude control of a spacecraft [75,76]. A proportional plus derivative control law for attitude control of non-rigid body spacecraft is found in Fenton [77].…”

Section: A Literature Review For the Attitude Control Problemmentioning

confidence: 99%

Neuro-genetic adaptive attitude control

Dracopoulos

Jones

1994

Neural Comput & Applic

View full text Add to dashboard Cite

“…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%

“…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]. 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].…”

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

View full text Add to dashboard Cite

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

show abstract

Optimal solar pressure attitude control of spacecraft—II

Cited by 20 publications

References 1 publication

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

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

Neuro-genetic adaptive attitude control

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

Contact Info

Product

Resources

About