Solar Pressure Attitude Stabilization of Earth-Pointing Spacecraft

Pande, K. C.; Venkatachalam, R.

doi:10.1109/taes.1981.309125

Cited by 22 publications

(18 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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%

“…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]. 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].…”

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

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

Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

show abstract

“…proposed for the single axis (pitch) attitude control of satellites using the SRP. [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.…”

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

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

“…In order to stabilize this periodic linear time-varying (LTV) system, some tools have been developed to extend the H 1 synthesis problem while some mixed H 2 and H 1 . 9,10) Sometimes, designers focus on using solar radiation pressure (SRP) for attitude control of satellites. Using SRP for attitude control of high-altitude satellites and interplanetary probes has been proposed.…”

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.

View full text Add to dashboard Cite

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.

show abstract

Solar Pressure Attitude Stabilization of Earth-Pointing Spacecraft

Cited by 22 publications

References 8 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

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

Contact Info

Product

Resources

About