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← Revision 13 as of 2011-01-04 16:40:17 ⇥
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| eine erste zusammenfassung vom 10.12.2010, auf deutsch, englisch kommt auch bald. |
<<TableOfContents()>> |
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| batterie - wie temperaturbeständig sind sie? welche temperaturen halten lithiumbatterien aus? sind sie frostempfindlich? wie heiss dürfen sie werden? temperaturen - beim start fallen sie ev unter null, sonst vermutlich nicht, welche temperaturen können wir erwarten? ev. müssen wir die batterie isolieren, aber die meisten isoliermaterialien beruhen auf gaseinschluss, das ist ein problem im vakuum. vielleicht gibt es vakuumgeeignetes styropormaterial. |
== Technical Update 10.12.2010 == from the worklab on friday, 10th december, 2010 |
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| das material muss für den temperaturbereich geeignet sein. litzenkabel werden nicht so leicht spröd. |
=== battery === how temperature resistant is it? which temperatures can lithium metal batteries bear? are they frostsensitive? how hot may they get? temperature: at the start they might fall under zero, otherwise probably not. which temperatures will we have to face? |
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| die antenne ist ein dipol. wenn sich der satellit dreht, dreht sich die polsarisation. wenn der/die beobachterIn in der antennenachse ist (entlang der antennenachse), hat er/sie keinen empfang. |
maybe we have to isolate the battery. what we have to be careful about there is that most isolation materials are based on gas inclusion, which is a problem in vacuum. maybe there is vacuum proof styrofoam. |
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| wir brauchen einen vakuumkammertest. | === material === all materials used must be suitable for the temperature range; multi-wire cable does not become brittle so easily. |
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| 3 tests: rütteltest - "lautsprecher" (ein sehr lauter lautsprecher). kalt-warm-test - -40 bis +100grad schock, 30mal hintereinander. vakuumtest - materialtest, ausgasende bauteile, keine konvektion mehr |
=== antenna === the antenna is a dipol. when the satellite turns, the polarisation turns, too. if the observer is in the axis of the antenna (along the axis), s/he cannot receive anything. |
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| ua. temperaturtest, was verbrennt im vakuum? ev. mit wärmebildkamera oder temperatursensoren hotspots feststellen. beschienene und nichtbeschienene seiten können sehr unterschiedliche temperaturen haben, -40 bis +150grad? |
=== necesary tests === we need 3 tests: |
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| antenne nachführen wird notwendig sein; aufgrund der niedrigen bahn wird die sichtbare zeit sehr kurz sein. wir müssen jeden überflug nutzen, weil der satellit nicht so lang im orbit ist. die herausforderung ist es, eine steuerbare nachführung auf 2 achsen zu bauen bzw. etwas günstiges zu finden. wir müssen es nicht allzu robust machen. |
. '''vibrator test''' - with some sort of "loudspeaker"/membran |
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| wir wollen mit einem ballon mindestens einen testflug machen, um ein paar dinge auszuprobieren: datenübertragung testen, das gerät kommt wieder zurück, testen ohne so strenge gewichtsbeschränkungen, nachführung kann getestet werden, kann gut in eine veranstaltung eingebettet werden, gute öffentlichkeitswirksamkeit, geringe kosten im vergleich zum raketenstart, möglichkeit zur beteiligung von interessentInnen (signal empfangen, ballon verfolgen und bergen), wir können (ev.) einen fm-transmitter mitschicken, und jedes radiogerät ist empfänger. |
. '''temperature test''' - from -40 to +100 testing, 30times; what burns in vacuum? maybe testing with thermographic camera? localize hotspots with temperature sensors? sunlit sides can have totally different temperatures from non-sunlit sides, difference from -40 to -150? |
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| für die groundstation: empfänger: scanner plus antenne plus kabel = 200,- plus equipment zur aufnahme extra. sender: da sind noch viele fragen offen. sicher nicht handnachführung; da kommt noch mehr :) |
. '''vacuum test''' - for the material, degassing, no convection anymore (we need a vacuum chamber). |
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| gravity gradient boom: dient zur stabilsierung der ausrichtung (und da könnte dann auch eine kleine kamera dranhängen für ein wunderschönes selbstportrait); wie soll er ausgefahren werden? automatisch, mit schmelzsicherung, bimetallschalter, muscle wire. das ausklappen muss drehmomentneutral sein (zb auf einem dünnen faden testen, oder ausrechnen - henrik?). |
=== tracking the antenna === it will be necesary to track the antenna, following it automatically; due to the low orbit the time-of-sight will be relatively short. we will have to use each flyover, as the satellite wont be in orbit for so long. the challenge will be to build (or find?) a controllable autotracking device on 2 axes; it wont have to be too robust (only for a time span of 3 - 6 weeks). |
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| vielleicht lässt sich eine lagestabilisierung über magnettorquer erreichen. dafür müssen wir einen sensor anbringen, der uns sagt, wie der satellit zum magnetfeld der erde steht. |
=== balloon === we are planning to realize at least one test flight with a balloon, in order to test some things. the advantages: data transfer and transmission; we get the hardware back; we can test with the hard pressure of weitght restrictions; the autotracking for the antenna can be tested; this can easily be made into a public event; good effective event for general public; a good possibility for involvement and participation of interested people (receiving signal, tracing, following and recovert the satellite; additionally send a fm-transmitter along and each radio becomes a receiver. |
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| wäre eine telemetriebake sinvoll machbar? dadurch kriegen wir den aktuellen zustand. zb. batteriestand, minimale info zb. wenn ein anderer satellit drüberfliegt, schickt er sein rufzeichen - "mursat1". |
=== groundstation === . '''receiver''': scanner plus antenna plus cable: euro 200,-;extra costs for data storage and transmission. . '''sender''': a lot of questions open; surely no manual tracing === gravity gradient boom === gravity gradient boom: serves as a alignment stablizer for the satellite, (where a small camera could be mounted to enable the satellite to take beautiful self portraits); how can it be deployed? automatically, with melting fuse, bimetall switch, muscle wire. the deployment has to be neutral to torsional moment (for example test it with a thin thread, or calculate it - henrik?) maybe a stabiliation of position can be reached by magnetic torquers. for that we need a sensor on the satellite that tells us, how the satellite is positioned in relation to earth. === telemetric marker buoy === is a telemetric marker buoy sensefully doable? we can get data like the current stage of the battery, minimal info like when another satellite is passing, it can say "hello, world!". no, of course it will send its callsign "mursat1". |
Contents
Technical Update 10.12.2010
from the worklab on friday, 10th december, 2010
battery
how temperature resistant is it? which temperatures can lithium metal batteries bear? are they frostsensitive? how hot may they get? temperature: at the start they might fall under zero, otherwise probably not. which temperatures will we have to face?
maybe we have to isolate the battery. what we have to be careful about there is that most isolation materials are based on gas inclusion, which is a problem in vacuum. maybe there is vacuum proof styrofoam.
material
all materials used must be suitable for the temperature range; multi-wire cable does not become brittle so easily.
antenna
the antenna is a dipol. when the satellite turns, the polarisation turns, too. if the observer is in the axis of the antenna (along the axis), s/he cannot receive anything.
necesary tests
we need 3 tests:
vibrator test - with some sort of "loudspeaker"/membran
temperature test - from -40 to +100 testing, 30times; what burns in vacuum? maybe testing with thermographic camera? localize hotspots with temperature sensors? sunlit sides can have totally different temperatures from non-sunlit sides, difference from -40 to -150?
vacuum test - for the material, degassing, no convection anymore (we need a vacuum chamber).
tracking the antenna
it will be necesary to track the antenna, following it automatically; due to the low orbit the time-of-sight will be relatively short. we will have to use each flyover, as the satellite wont be in orbit for so long. the challenge will be to build (or find?) a controllable autotracking device on 2 axes; it wont have to be too robust (only for a time span of 3 - 6 weeks).
balloon
we are planning to realize at least one test flight with a balloon, in order to test some things. the advantages: data transfer and transmission; we get the hardware back; we can test with the hard pressure of weitght restrictions; the autotracking for the antenna can be tested; this can easily be made into a public event; good effective event for general public; a good possibility for involvement and participation of interested people (receiving signal, tracing, following and recovert the satellite; additionally send a fm-transmitter along and each radio becomes a receiver.
groundstation
receiver: scanner plus antenna plus cable: euro 200,-;extra costs for data storage and transmission.
sender: a lot of questions open; surely no manual tracing
gravity gradient boom
gravity gradient boom: serves as a alignment stablizer for the satellite, (where a small camera could be mounted to enable the satellite to take beautiful self portraits); how can it be deployed? automatically, with melting fuse, bimetall switch, muscle wire. the deployment has to be neutral to torsional moment (for example test it with a thin thread, or calculate it - henrik?)
maybe a stabiliation of position can be reached by magnetic torquers. for that we need a sensor on the satellite that tells us, how the satellite is positioned in relation to earth.
telemetric marker buoy
is a telemetric marker buoy sensefully doable? we can get data like the current stage of the battery, minimal info like when another satellite is passing, it can say "hello, world!".
no, of course it will send its callsign "mursat1".