An overview of the Hubble Space Telescope Pointing Control System design and operation

Quinn, Dave; Beals, G. A.; Nelson, John D.; Nurre, G. S.

doi:10.2514/6.1992-4616

Cited by 2 publications

(1 citation statement)

References 3 publications

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“…Space observatories require precise attitude control and pointing accuracy to achieve desired diffractionlimited optical performance. For example, the Hubble and James Webb Space Telescopes require 7 milliarcsec [1] and 15 milliarcsec [2] pointing accuracies, respectively. A range of emerging science missions such as Asteria [3], Exo-C [4] and technologies such as laser communication [5], precision formation flying [6], and interferometric imaging [7], place stringent requirements on pointing error and stability.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Attitude Control of a Spacecraft with Distributed Actuation of Solar Arrays

Nakka¹,

Chung²,

Allison

et al. 2019

Journal of Guidance, Control, and Dynamics

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This article presents a novel control architecture and algorithm for precision attitude control of a one-degree-of-freedom dynamic model of a spacecraft. To achieve a parametric model-based control design approach for this new spacecraft actuation and control architecture, the nonlinear dynamics of the open-loop plant are modeled as an Ordinary Differential Equation (ODE)-Partial Differential Equation (PDE) system. The ODE describes the spacecraft single-axis rigid-body rotation, and the PDE describes the spatially continuous flexible dynamics of the solar array including an allocation for a multi-input distributed piezoelectric actuation system bonded on the solar array. This distributed actuation system is called strain-actuated solar arrays. Based on this plant model, a nonlinear ODE-PDE feedback controller for attitude trajectory tracking and slewing is presented with detailed stability proofs. From an end-to-end point of view, the controller drives the distributed piezoelectric actuator patches with voltages that induce bending deflections in the solar arrays, causing controlled reaction torques on the bus to yield target-following motions and precision spacecraft attitude control. The proposed algorithm can be extended to any distributed actuation system with appropriate control input to actuator input mapping.The benefits and limitations of the proposed attitude control method using strain actuation

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Section: Introductionmentioning

confidence: 99%

Nonlinear Attitude Control of a Spacecraft with Distributed Actuation of Solar Arrays

Nakka¹,

Chung²,

Allison

et al. 2019

Journal of Guidance, Control, and Dynamics

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show abstract

A spacecraft attitude stabilization system with low-power magnetic torquers

Polites¹,

Quarles²,

Kadebek³

et al. 2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper describes a spacecraft attitude stabilization system that uses a set of 12 lowpower magnetic torquers. The low-power magnetic torquer consists of a hard magnetic-material rod inside a solenoid. Discharging a capacitor through the solenoid winding generates a current pulse that changes the magnetic dipole moment of the rod when required. The interaction of this magnetic dipole moment with the Earth's magnetic field creates a torque on the rod that can stabilize the attitude of a spacecraft in a low Earth orbit. Computer simulation results show that a system of 12 low-power magnetic torquers with a combined mass of 3.5 kg or about 8 lb can stabilize a 1400 kg or 3000 lb spacecraft in a 600 km circular orbit to a local vertical orientation in five to ten orbits. With initial rates of 1 deg/s or less in each axis, the peak power dissipated in the low-power magnetic torquers is 440 mW or less, the average power prior to settling is 125 mW or less and the average power after settling is about 2 mW or less.

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An overview of the Hubble Space Telescope Pointing Control System design and operation

Cited by 2 publications

References 3 publications

Nonlinear Attitude Control of a Spacecraft with Distributed Actuation of Solar Arrays

Nonlinear Attitude Control of a Spacecraft with Distributed Actuation of Solar Arrays

A spacecraft attitude stabilization system with low-power magnetic torquers

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