The CONTOUR spacecraft power subsystem

Panneton, Paul E.; Mehoke, Douglas S.; Dakermanji, G.

doi:10.1109/iecec.2002.1391982

Cited by 1 publication

(2 citation statements)

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“…The selection of battery technology was reduced to two candidate chemistries, NiH2 cell technology and NiCd technology. Table 2 compares the main characteristics of both NiCd and NiH2 batteries [6]. • It has more capacity than NiCd leading to fewer recharge cycles and No memory effect.…”

Section: Storage Battery Type Estimationmentioning

confidence: 99%

“…It must prevent damage to the battery and satellite loads by protecting against an over-voltage or under-voltage condition of the power bus. Finally, it must interface with the satellite OBC&DH subsystem, providing EPS telemetry and receiving ground commands [6], [9]. The management and controller unit controls the charge/discharge process of the storage battery by controlling the output power from solar array and protect the…”

Section: Eps Configuration and Block Diagrammentioning

confidence: 99%

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Assessment of Earth Remote Sensing Microsatellite Power Subsystem Capability during Detumbling and Nominal Modes

Zahran

Okasha

Иванова

2011

International Conference on Aerospace Sciences and Aviation Tec

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The Electric Power Subsystem (EPS) is one of the most critical system on any satellite because nearly every other subsystem requires power. This makes the choice of power systems the most important task facing satellite designers. The main purpose of the Satellite EPS is to provide continuous, regulated and conditioned power to all the satellite subsystems. It has to do that withstanding the radiation, thermal cycling, and vacuum of a hostile space environment as well as the subsystem degradation over the time [1]. The EPS power characteristics are determined by both the parameters of the system itself and by the satellite orbit RI After the satellite separates from the launch vehicle (LV) to its orbit, in almost situations, all the satellite subsystems (attitude determination and control, communication, and onboard computer and data handling (OBC&DH)), take their needed power from a storage battery (SB) and solar arrays (SA) beside the consumed power in EPS management device. But at this point (separation point, detumbling mode), the satellite angular motion is high and the orientation of solar arrays with respect to the sun will change in a non-uniform way, so the amount of power generated by solar arrays will be affected. The objective of this research is to select the satellite EPS components, types; estimation the solar arrays illumination parameters and determination of the efficiency of solar arrays during both detumbling and nominal modes.

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Section: Storage Battery Type Estimationmentioning

confidence: 99%

Section: Eps Configuration and Block Diagrammentioning

confidence: 99%