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In-orbit AODCS performance of Sumbandilasat an earth observation satellite

dc.contributor.authorSteyn W.H.
dc.date.accessioned2011-10-13T16:58:56Z
dc.date.available2011-10-13T16:58:56Z
dc.date.issued2010
dc.identifier.citation61st International Astronautical Congress 2010, IAC 2010
dc.identifier.citation9
dc.identifier.citationhttp://www.scopus.com/inward/record.url?eid=2-s2.0-79959459427&partnerID=40&md5=0dec58c9d10909c378e8e89f55c2274b
dc.identifier.urihttp://hdl.handle.net/10019.1/16915
dc.description.abstractThe paper describes the commissioning and in-orbit performance results of the attitude and orbit determination and control system to support the multi-spectral earth observation imager payload of the SumbandilaSAT microsatellite. The satellite has been designed as a single string mission with little redundancy due to mass and volume restrictions and early in the mission the Z-axis reaction wheel was permanently lost due to a power switch failure. The paper will demonstrate how full 3-axis stability is achieved without the use this wheel. The pushbroom imager is still able to scan target areas accurately using a forward motion compensation method (FMC4), simultaneously doing a roll offset manoeuvre for cross track scanning. Target tracking by pointing the high data rate S-band antenna is also successfully demonstrated, while allowing the satellite to freely rotate around the antenna boresight during these periods. The satellite has a Y-body mounted main solar panel and the attitude control system must ensure a sufficient level of solar energy collected during the sunlit part of each orbit. The control actuators employed are 3-axis magnetic torquer rods and X/Y reaction wheels. During initial detumbling and safe mode operations, a magnetic control law is used to bring the satellite to a sun pointed Y-Thompson spinning attitude for maximum power collection. From this sun-pointed, spinning attitude an intermediate control mode is entered where the Y-reaction wheel is utilised as a momentum wheel, to absorb the body spin rate and to inertially stabilise the momentum vector initially towards the sun direction and finally aligned with the orbit normal. During this mode the magnetic rods are used to maintain the momentum vector in size and steer the pressesion direction while doing nutation damping. The pitch angle is controlled using the Y-wheel, to keep the main imager payload as close as possible to an earth pointed attitude and thermally stabilise the telescope. Finally, the nominal attitude control mode is enabled when a low Y-momentum biased X/Y reaction wheel and magnetic controller is enabled, to: 1) ensure a nominal nadir pointing attitude to collect a sufficient level of solar energy, 2) do target tracking during view finder use or during imaging download communication with ground stations and 3) implement pushbroom imager FMC4 scanning. During the nominal mode magnetic rods are used to maintain the Y-wheel angular momentum, dump the X-wheel momentum and zero any yaw angle offsets. The in-orbit performance will be presented of newly developed 2-axis sun and earth sensors, an autonomous star tracker and SGPS receiver. A Butane resistojet propulsion system's performance will be discussed, showing the results of circularising and raising an eccentric 490 by 505 km initial orbit. Copyright ©2010 by the International Astronautical Federation. All rights reserved.
dc.subjectAutonomous star trackers
dc.subjectBoresight
dc.subjectControl actuators
dc.subjectControl modes
dc.subjectCross-track scanning
dc.subjectEarth observation satellites
dc.subjectEarth observations
dc.subjectEarth sensor
dc.subjectGround stations
dc.subjectHigh data rate
dc.subjectIn-orbit
dc.subjectMagnetic control
dc.subjectMagnetic rods
dc.subjectMaximum power
dc.subjectMicro satellite
dc.subjectMode operation
dc.subjectMomentum vectors
dc.subjectMomentum wheels
dc.subjectMulti-spectral
dc.subjectOrbit determination
dc.subjectPitch angle
dc.subjectPower switches
dc.subjectPropulsion system
dc.subjectPushbroom imager
dc.subjectReaction wheels
dc.subjectSolar panels
dc.subjectSpin rate
dc.subjectTorquer rods
dc.subjectYaw angles
dc.subjectAttitude control
dc.subjectButane
dc.subjectControl rods
dc.subjectControl theory
dc.subjectFlight dynamics
dc.subjectMagnetism
dc.subjectMomentum
dc.subjectMotion compensation
dc.subjectNavigation
dc.subjectObservatories
dc.subjectPropulsion
dc.subjectReaction intermediates
dc.subjectSatellite antennas
dc.subjectSatellites
dc.subjectSolar energy
dc.subjectSolar radiation
dc.subjectSpatial variables control
dc.subjectStar trackers
dc.subjectTarget tracking
dc.subjectTextile industry
dc.subjectWheels
dc.subjectOrbits
dc.titleIn-orbit AODCS performance of Sumbandilasat an earth observation satellite
dc.typeConference Paper
dc.description.versionConference Paper


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