[amsat-bb] Re: Path to HEO
quadpugh at bellsouth.net
Mon Apr 29 02:03:24 PDT 2013
Hi James et all
Thanks for the very nice comments. Here are some additional thoughts
1. The Van Allen belt radiation might be our toughest challenge so
let think about an orbit 16000 KM
2. IF we were to put 3 sat up this would give us nice coverage and
longer operating time
3. There are flight heritage reaction wheels that consume < 2 watts
4. We a little luck we can start from 600 KM orbit
5. If we are really clever we might have a sat to sat relay to
extend time and range coverage.
From: James Duffey [mailto:jamesduffey at comcast.net]
Sent: Sunday, April 28, 2013 10:35 PM
To: Franklin Antonio
Cc: James Duffey; Nick Pugh; Amsat-bb at amsat.org
Subject: Re: [amsat-bb] Re: Path to HEO
Well I did a rough back of the envelope calculation for the time required to
accumulate the energy necessary to get from LEO to HEO, but there are a lot
of details that still need to be calculated. And the devil is in the
details. But this will get things started
The difference in orbital energy between a LEO and GEO is about 25 MJ/kg.
So, for a 10 kg nano sat, we would need to supply at least 250 MJ. Now I
suspect that when all is said and done, it cannot be done for that, but I
haven't done any detailed orbital transfer calculations.
OK, suppose we have Nick's 50 Watt solar panel, and lets also say that
initially half of that power can be put into propulsion, the other half
being needed for navigation, housekeeping, comm, and telemetry. You could
probably get away with more for propulsion.
So say we need to generate at least 250,000,000 (it is probably more) Joules
of energy to get from LEO to HEO. The solar panel can supply 25 Watts or 25
Joules per second. so it will take 10,000,000 seconds to generate the 250MJ
Now the satellite is only illuminated for roughly half an orbit, so we need
to double the time to 20,000,000 seconds on orbit. Now there 31,536,000
seconds in a year, so it would take 231 days to accumulate the minimum
amount of energy to get to GEO.
Well, I neglected inefficiencies in the system, such as the ability of the
ion-thruster to convert electricity into thrust and how efficiently the
batteries or capacitors can be charged and store energy. I also ignored the
drag at lower latitudes, which may be considerable. I suppose that one could
only operate the thrusters while the spacecraft is illuminated and that
would eliminate the storage problem. Say the whole system is 50% efficient,
and I am guessing here, that would make it 462 days, or 15 months.
I suppose that whether or not that is a long time, depends on your point of
view. I'll bet if the transfer burn strategy is calculated it gets even
worse. Things seldom get better. You can't do a simple Hohmann transfer, but
would need to do multiple burns, or a continuous burn over the illuminated
part of the orbit. I suppose that would produce an orbit that is not really
circular at any given time but it might all average out over all the burns.
A constant burn may be more efficient in terms of energy use that a Hohmann;
I don't remember. I do remember that one wants to burn at apogee to get the
biggest bang for the buck, and I suspect that the illuminated portion of the
orbit is not always at apogee, so the energy will not be used efficiently.
Now a GEO orbit, while a desirable goal, is not necessarily what is needed
for amateur radio communication. Something short of GEO, and even elliptical
would still be useful and only require repointing of the antenna from day to
day, and perhaps hour to hour at Apogee. Orbits significantly higher than
LEO, but lower than GEO are also very useful. Compare for example the
available time per pass between ISS and AO-7, and for that matter the RS10,
11, 12 and 13 birds.
One would need to plan how to go through the Van Allen belts, as with such a
slow burn one would spend a lot of time where the radiation is high.
All of this is not meant to be a rigorous calculation, but rather just an
indication of whether it is reasonable, and if it is worth pursuing further.
It does to seem to be within the realm of possibly, and probably should be
pursued further, at least until a real show stopper shows up. - Duffey KK6MC
Cedar Crest NM
On Apr 28, 2013, at 3:34 PM, Franklin Antonio <antonio at qti.qualcomm.com>
> At 11:14 AM 4/28/2013, Nick Pugh wrote:
>> I have just returned from a satellite conference and I think new
>> technology will now give us a path to HEO.
> I've thought for a long time that ion engines (small thrust pushing for a
long time, powered by electricity) could be of great value to us.
> Has anyone done the calculation to see how long it would take to go from
LEO to HEO with an achievable ion engine? This seems like the first thing
to calculate. If it takes less than 1 year, it seems worth serious
> There are many other hurdles, of course, such as attitude control (keeping
solar panels pointed at the sun while at the same time keeping engine
pointed in the direction we want thrust, over a long period of time). The
schemes and compromises for these issues can be worked if the basic thrust
math works out.
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