hobbsyoyo
Deity
- Joined
- Jul 13, 2012
- Messages
- 26,575
Thanks for sharing. There is a company (Tethers Unlimited) that was founded to pursue and commercialize this technology. They do offer a few products in this vain but have mostly moved on to more 'traditional' space technologies.This Hobbs' post needs moar!
https://www-istp.gsfc.nasa.gov/Education/wtether.html
Hehe, boosting an orbit using purely electricity!
How crazy is that?
A shame the magnetic force on the wire/tether causes deorbiting, or it would be a great way to get free electricity.
My goodness, a 12.5 mile or 20117 meters long cable.
Assuming low earth orbit and an orbit crossing the magnetic field lines at a 90 degree angle, we can can calculate the voltage across the wire if we assume 25 to 65 microteslas 20 miles up for the Earth's magnetic field strength.
https://en.wikipedia.org/wiki/Earth's_magnetic_field
10:00 at the Khan academy video
https://www.khanacademy.org/science...wire/v/magnetism-12-induced-current-in-a-wire
20,117 meter cable * 7800m/s orbital velocity * 0.000045? Teslas field strength = 7061 Volts of potential difference across the whole wire?
Huh, reality was 3500 Volts.
Perhaps the cable length wasn't all there, or perhaps the orbit angle wasn't perfectly perpendicular to Earth's magnetic field, or the Earth's magnetic field up there was less than 45 microteslas?
19,700 meter cable when it broke.
3500 Volts
STS-75 had an orbital period of 90.5 minutes, so 7727 m/s orbital velocity.
Earth's magnetic field was 19,700 * 7727 * x = 3500
x = 23 microteslas?
Could read the paper on it I suppose since actual scientists know a lot more.
The current-voltage characteristics of a large probe in low Earth orbit: TSS-1R results
https://agupubs.onlinelibrary.wiley.com/doi/epdf/10.1029/97GL02958
The magnetic force opposing the conducting wire's orbit through Earth's magnetic field?
https://courses.lumenlearning.com/p...gnetic-force-on-a-current-carrying-conductor/
With a constant flow of 1A of current, it would be 1* 19,700 * 0.000023 = 0.4531 Newtons applied to the entire 19,700 meter wire.
1 Newton accelerates 1 kilogram 1 meter per second every second.
Would need to know the mass of the 19,700 meter cable and attached satellite.
Only need to lower the orbital velocity from 7727m/s to 7637m/s to deorbit like the shuttle, a loss of 90m/s
https://space.stackexchange.com/que...enough-to-commit-the-space-shuttle-to-landing
Call the cable+satellite 518kg
https://space.skyrocket.de/doc_sdat/tss-1.htm
It should lose 90 meters per second in orbital velocity and start crashing into Earth after 518 / 0.4531 * 90 = 102,891 seconds or 28.5 hours conducting 1 Amp.
A bit over a day to crash.
No idea if these calculations are even close.
In reality, the thing stayed up there for over 3 days at least.
Can't seem to find how long it stayed up in Earth's orbit.
**Edit**
Sigh, it was 0.48A, not 1A
https://www.americaspace.com/2014/0...cond-flight-of-the-tethered-satellite-part-2/
=========================
I also want to plug the spinning wheels that make it so satellites and spaceships don't spin out of control.
14:25 WTH is that?!
1968 production values![]()
Materials limitations and lack of heritage have been big factors against the wide spread of these technologies. Of those factors, heritage is the far larger hurdle - as is so often the case in the space industry. There is a huge in-built tradition against trying new things.
Yup. Conversely, non velocity-vector burns are much less impactful, particular inclination changes. I have analyzed missions that wanted to do deep inclination changes and it was easier to launch a second satellite into the new orbit than to shift a satellite from one to the other.Its magic how much prograde and retrograde bursts (even with small thrust) can impact orbit at right points of orbit.
Spoiler :Managed to reach 4000 km perfect circle orbit in Orbiter with regular Atlantis Space Shuttle (with big fuel tank still attached) and manual controls (if don't get nose down quickly enough after start - will get really high but with too slow orbital speed to get around Earth) just by doing short bursts at perigee to get up apogee and at apogee to get up perigee (and oposite way to get down back on Earth, using atmosphere (precise retrograde trust at apogee and can get perigee at altitude you want
) to slow down a little bit before actual entry - going directly into Earth atmosphere from high altitude orbit would be little more unrealistic and dangerous to space ship structure that is designed to do that from 110 km orbit.