Mariner Iv Revisited, or the Tale of the Ancient Mariner

Scull, John R.

doi:10.1016/b978-0-08-016841-8.50046-8

Cited by 18 publications

(5 citation statements)

References 3 publications

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“…Some missions have also been flown to verify these concepts. The Mariner IV mission employed solar vanes for achieving passive sun pointing attitude [Scull 1969]. The European Space Agency conducted experiments in which the attitude of the geostationary communication satellite OTS-2 was controlled by rotating solar panels [Renner 1979].…”

Section: Solar Radiation Pressure For Attitude Controlmentioning

confidence: 99%

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

Varma¹

2021

Preprint

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The dynamics of a satellite involves orbit and attitude motion. Both orbit and attitude motion are required to be controlled for achieving any mission objectives. This thesis examines both of these motion with a focus on formation flying and attitude stabilization using aerodynamic drag or solar radiation pressure. The concept of satellite formation flying involves the distribution of the functionality of a single satellite among several smaller, cooperative satellites. Autonomous multiple satellite formation flying space missions offer many promising possibilities for space exploration. A large quantity of fuel is typically required onboard any conventional satellite to carry out its attitude and orbital positioning, and satellite formation flying has a higher fuel requirement. As on-board fuel is a scarce commodity, it is important to have control methods requiring little or no fuel. Keeping this in mind, this thesis presents the results of using aerodynamic drag or solar radiation pressure for satellite formation flying. This methodology has potential to have significant commercial advantage as it pertains to almost negligible fuel requirements. A leader/follower formation architecture is considered for the formation flying system. The control algorithms are derived based on adaptive sliding mode control technique. Aerodynamic drag is used to accomplish multiple satellite formation flying in low Earth orbit whereas solar radiation pressure is used in geostationary orbit. Due to the nature of the aerodynamic drag, in-plane control can only be accomplished by the suitable maneuvering of the drag plates mounted on the satellites. Solar radiation pressure is able to accomplish in-plane and out-of-plane control by maneuvering of the solar flaps. Efficacy of the control methodology in performing various scenarios of formation flying including formation reconfiguration is validated by numerical simulation in both the cases. The numerical results demonstrate the effectiveness of the proposed control techniques for satellite formation flying using aerodynamic drag or solar radiation pressure. Formation flying accuracies of less than 5 m are achieved in both the cases. Next, this thesis investigates the use of aerodynamic drag or solar radiation pressure for satellite attitude control. In the case of the aerodynamic drag stabilized satellite, the drag plates are considered to be attached to the satellite while the solar flaps are fixed to the satellite in the case of the solar radiation pressure stabilized satellite. In both the cases, the control algorithm is developed based on adaptive sliding mode control technique. The effectiveness of this methodology is numerically evaluated under various scenarios including the pressure of failure/fault in the solar flaps or drag plates attached to the satellite. The satellite attitude is stabilized within reasonable limits in all the cases thereby demonstrating robust performance in the presence of external disturbances.

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Section: Solar Radiation Pressure For Attitude Controlmentioning

confidence: 99%

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

Varma¹

2021

Preprint

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“…In the past, researchers have considered various types of control surface configurations including trailing cone, reflector-collector, weathervane tail, mirror arrays, solar paddles, and solar sails for producing solar control forces [1]. For the control of geostationary communication satellites in the Mariner IV mission [2] and the OTS-2 mission of the European Space Agency [3], Solar vanes and flaps were utilized.…”

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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“…(Readers may refer to Pande and Venkatachalam, 1 and references therein for different kinds of solar control surfaces.) In the Mariner IV mission 2 and the OTS-2 mission of the European Space Agency, 3 solar vanes and flaps were employed for the control of geostationary communication satellites.…”

Section: Introductionmentioning

confidence: 99%

ℒ₁ adaptive attitude control of satellites in elliptic orbits using solar radiation pressure

Lee

Singh

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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The development of an ℒ1 adaptive control system for the control of satellites in elliptic orbits using solar radiation pressure is the subject of this article. The nonaffine-in-control spacecraft model includes the gravity gradient torque, the control torque produced by two solar flaps, and external time-varying disturbance torque. The objective is to control the pitch angle of the spacecraft using the solar flaps. The design is based on the ℒ1 adaptive control theory for the control of nonlinear nonautonomous uncertain systems. The control system includes an adaptation law based on the state prediction error. Unlike traditional adaptive systems, the control input is obtained by filtering an estimated control signal through a low-pass filter. In the closed-loop system, the designed adaptive law accomplishes large angle maneuver. A special feature of the control system using filtered signal is that it is possible to select large adaptation gains for fast adaptation and to obtain quantifiable performance bounds. Simulation results are presented which show that in the closed-loop system, precise pitch angle control is accomplished, despite parameter uncertainties and external disturbance input in the model.

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Mariner Iv Revisited, or the Tale of the Ancient Mariner

Cited by 18 publications

References 3 publications

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

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

ℒ₁ adaptive attitude control of satellites in elliptic orbits using solar radiation pressure

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Mariner Iv Revisited, or the Tale of the Ancient Mariner

Cited by 18 publications

References 3 publications

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

Control of satellites using environmental forces : aerodynamic drag / solar radiation pressure

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

ℒ1 adaptive attitude control of satellites in elliptic orbits using solar radiation pressure

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ℒ₁ adaptive attitude control of satellites in elliptic orbits using solar radiation pressure