A Compact Power Controller for Microsat Applications

Innocenti, Gino; Arrigo, Jeanette F.

doi:10.1109/aero.2008.4526532

Cited by 4 publications

(3 citation statements)

References 9 publications

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“…Furthermore, the PCU has no access to the serial devices (reaction wheels, IMU, star tracker), but only to the analog devices (magnetic torque rods, magnetometer, and sun sensors) which are connected through the power system input/output (PSIO) module. The PCU and PSIO together comprise the Power Distribution Unit (PDU), which is described in detail in Reference [14].…”

Section: Sun-synchronous Microsatellite Designmentioning

confidence: 99%

“…Sun sensor measurements are collected on a 10.85 Hz minor cycle, with n meas (4) sets of measurements being used to develop a control command on a 0.5425 Hz major cycle which is applied during n on (14) minor cycles. The magnetorquers are commanded off during n off (2) minor cycles (as well as during the measurement minor cycles) to allow the local magnetic field to stabilize before the magnetometer measurements are taken during the measurement cycles.…”

Section: Two-axis Sun Pointingmentioning

confidence: 99%

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A simple sun-pointing magnetic controller for satellites in equatorial orbits

Sedlund¹

2009

2009 IEEE Aerospace Conference

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This paper describes a simple satellite attitude controller designed to run on a fairly low capability processor. The controller is intended to be used in a contingency mode when the spacecraft flight computer and full sensor and actuator suite are not available, making use of only analog-output sensors (three-axis magnetometer and sun sensors) and analog-input actuators (magnetic torque rods or coils). The controller is designed to keep an axis near the principal axis of maximum inertia pointed at the sun. Because control torques may only be applied in a plane perpendicular to the local geomagnetic field the control scheme uses a very low control bandwidth in conjunction with gyroscopic spin stabilization.While originally designed for a satellite in a high-inclination orbit, the spacecraft was adapted for a new mission in a nearly equatorial orbit, where purely magnetic attitude control is not typically used because the direction of the local geomagnetic field is nearly constant during an orbit. This paper reviews the design of the original controller as well as the modifications which were made to improve performance in the nearly equatorial orbit. Statistical performance results based on Monte Carlo simulations are included. 1,2

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Section: Sun-synchronous Microsatellite Designmentioning

confidence: 99%

Section: Two-axis Sun Pointingmentioning

confidence: 99%

A simple sun-pointing magnetic controller for satellites in equatorial orbits

Sedlund¹

2009

2009 IEEE Aerospace Conference

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“…The SCC interfaces directly with the Power Distribution Unit (PDU) [1], the S-band radio, and several attitude control components, i.e. the star tracker, inertial measurement unit, GPS receiver, reaction wheels.…”

Section: Introductionmentioning

confidence: 99%

A flexible COTS-based serial communications solution with high density memory storage

Greenlaw

Innocenti

Arrigo

2009

2009 IEEE Aerospace Conference

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An assembly that processes up to 16 differential serial communication channels was designed using Commercial Off The Shelf (COTS) components. The Trailblazer program needed a rapid and cost effective implementation for interfacing with large number of serial communications devices. The lack of available off-the-shelf serial communication assemblies in a 3U form factor with this capability was the motivation for this work.

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