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

Zahran M.; Okasha M.; Ivanova Galina A.

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

Journal of power electronics, v.6 no.1, 2006년, pp.18 - 28

Zahran M. (Electronics Research Institute, NRC Blg., El-Tahrir St., National Authority for Remote Sensing and Space Science) , Okasha M. (National Authority for Remote Sensing and Space Science) , Ivanova Galina A. (Yuzhnoye State Design office)

Abstract ▼ AI-Helper

The Electric Power Subsystem (EPS) is one of the most critical systems on any satellite because nearly every 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 withstand radiation, thermal cycling and vacuums in hostile space environments, as well as subsystem degradation over time. The EPS power characteristics are determined by both the parameters of the system itself and by the satellite orbit. After satellite separation from the launch vehicle (LV) to its orbit, in almost all situations, 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) besides the consumed power in the EPS management device. At this point (separation point, detumbling mode), the satellite's angular motion is high and the orientation of the solar arrays, with respect to the Sun, will change in a non-uniform way, so the amount of power generated by the solar arrays will be affected. The objective of this research is to select satellite EPS component types, to estimate solar array illumination parameters and to determine the efficiency of solar arrays during both detumbling and normal operation modes.

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가설 설정

. Energy balance during the mission life.

제안 방법

A power subsystem and its component characteristics are estimated and studied. The sizing of an Earth remote sensing microsatellite power supply is presented with a direct energy transfer configuration.
Orbit dynamics, attitude dynamics and kinematics are analysed by developing a MATLAB based software program. The program takes into consideration orbit and solar array illumination patterns during the active lifetime of the satellite in orbit operation. Orbit perturbations and injection inaccuracies are also considered.
The proposed satellite is Sunsynchronous with local time of passing the ascending node 10 hours and 30 minutes. The altitude of the circular orbit is ~670km, inclination ~98°, period of satellite orbit -lOOmin, approximately like the orbit of the satellite in (1).
The satellite's orbital parameters that affect the EPS operation are simulated during the lifetime to estimate the illumination coefficient of the EPS solar array, taking into consideration the space environment and orbital perturbation. The most critical period of the sat_이lite EPS operation starts from the sat_이lite separation from the launch vehicles up until it reaches the steady state (oriented) operation.
in the MATLAB. This program simulated changes in angle to a normal solar array plan with consideration of Sun direction, eclipse time and local time of ascension. The illumination coefficient is calculated with consideration of the orbital perturbations and accuracy of satellite separation from the launch vehicle.

대상 데이터

The designers must be aware of the various power subsystems available for use on the satellite Figure 1 shows the most suitable power sources onboard the satellite, depending on the information about the onboard equipment (OBE) average power requirements and satellite design lifetime. The satellite under this study is an Earth remote sensing microsatellite, in the S_니asynchronous orbit with a planned five year lifetime. Applying such information to the EPS selection chart we can conclude that the most s_너itable primary source for the proposed satellite is the photovoltaic (solar arrays).

참고문헌 (14)

TERMA A/S Space Division, 'Power Management and distribution Systems', www.terma.com
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Wertz, J. and Larson, W., Eds., Space Mission Analysis and Design. Boston, Kluwer Academic Publishers, 1991
ManTech for Multi-Junction Solar Cells, http://www.afrl.af.mil/techconn/index.htm
Spectrolab Inc. 12500 Gladstone Avenue, Sylmar, California 91342 USA, www.spectrolab.com
Paul E. Panneton and Jason E. Jenkins, 'The MSX Spacecraft Power Subsystem', Johns Hopkins APL Technical Digest, Volume 17, Number 1 (1996)
S.R. Cvetkovic and G.J. Robertson, 'Spacecraft Design Considerations for Small Satellite Remote Sensing', IEEE Transaction on Aerospace and Electronic Systems, Vol. 29, No. 2, April 1993
Masoum, Mohamed A.S. and Dehbonei, Hooman, 'Design, Construction and Testing of a Voltage-based Maximum Power Point Tracker (VMPPT) for Small Satellite Power Supply', 13th Annual AIAA/USU Conference on Small Satellites, SSC99-XII-7
Andy Bradford, Luis M Gomes, Prof. Sir Martin Sweeting and Gokhan Yuksel, Cem Ozkaptan, Unsal Orlu, 'BILSAT-1: A Low-Cost, AGILE, Eearth Observation Microsatellite for TURKEY', 53rd International Astronautical Congress October 2002/Houston, Texas
Greg Merritt and John Opiela, 'Satellite Power Systems Sizing', www.tsgs.utexas/tadp/1995/spects/power
You zheng, Gong ke, 'Tsinghua Micro/Nanosatellite research and it's application', 13th Annual AIAA/USU Conference on Small Satellites, SSC99-IX-3
D. A. Vallado, Fundamentals of Astrodynamics and Applications. NY: McGraw-Hill, 1997
Peter C. Hughes. Spacecraft Attitude Dynamics. John Wiley and Sons, New York, 1986
James R. Wertz, editor. Spacecraft Attitude Determination and Control. Kluwer Academic Publishers, Dordrecht, 2000

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