| Page 2 of 2 |
[ 21 posts ] |
Prediction: by year 2100 earth to mars in 19 days
Prediction: by year 2100 earth to mars in 19 days
| Author | Message |
|---|---|
|
Moon Mission Member ![]()
Joined: Tue Feb 10, 2004 2:56 am
Posts: 1104 Location: Georgia Tech, Atlanta, GA |
campbelp2002 wrote: Dr_Keith_H wrote: why aren't we burning this stuff already? That's not really the hitch: you don't care about power consumption, since you can always haul your own fission plant along with you. The reason we don't have a drive is that we're never able to keep the reaction going for more than a few seconds -- I think the record *might* be a minute, but I'm not sure. _________________ American Institute of Aeronautics and Astronautics Daniel Guggenheim School of Aerospace Engineering In Memoriam... Apollo I - Soyuz I - Soyuz XI - STS-51L - STS-107 |
| Back to top |
|
|
Moon Mission Member ![]() ![]()
Joined: Tue Oct 05, 2004 5:38 pm
Posts: 1361 Location: Austin, Texas |
spacecowboy wrote: The reason we don't have a drive is that we're never able to keep the reaction going for more than a few seconds -- I think the record *might* be a minute, but I'm not sure. |
| Back to top |
|
|
Spaceflight Trainee ![]()
Joined: Tue Jul 20, 2004 4:36 am
Posts: 35 Location: Pasadena, CA |
whonos wrote: when used in Boron-11/Hydrogen fusion has an exhaust velocity of 11800000 m/s (specific impulse of over 1.2 million seconds). With a 1g burn, it would take 4 days 13 hours to get to Mars on furthest approach; a mere 2 days 1.5 hours on closest approach. For the furthest approach, ~28% of the spacecraft would be fuel; closest, ~14%. These are the fastest times possible with any propulsion technology (not counting warp drives), as they entail accelerating at 1g until half way then turning around and decelerating at 1g for the other half. This implies that your ship will have a thrust to weight of 1 (or thrust to mass of 9.8N/kg if you prefer.) If your whole ship masses a ton you will need to produce 9800N thrust at a Ve of 11,800,000 which implies 0.8g/s of propellant. Your exhaust will be helium at a temperature of about 100,000,000K. Now, I don't know if the ideal gas law extends to those temperatures, but if it does 0.8g of helium at that temperature would have a volume of ~1600m^3 at one atmosphere pressure. Your engine will have to be huge or high pressure, or both. It will not be light. I guess I'm comfortable with my prediction of 19 days, although the method might be fusion drives at less than 1g acceleration. |
| Back to top |
|
|
Spaceflight Trainee ![]()
Joined: Tue Jul 20, 2004 4:36 am
Posts: 35 Location: Pasadena, CA |
I looked around on the web and found this lecture that talks about D-He3 fusion.
http://fti.neep.wisc.edu/neep533/SPRING ... ture28.pdf Looking at the chart on page 4 you get T/W=0.001 at Ve=10^6 m/s. Even my low performance engine with Ve=10^5 and T/W=50 looks iffy. |
| Back to top |
|
|
Space Walker ![]() ![]()
Joined: Wed Aug 11, 2004 2:05 pm
Posts: 173 |
what about accelerating and decelerating at 3Gs? How long can the body withstand such loading without harm?
_________________ Thank you very much Mister Roboto For helping escape when I needed most Thank you Thank you |
| Back to top |
|
|
Moon Mission Member ![]()
Joined: Tue Feb 10, 2004 2:56 am
Posts: 1104 Location: Georgia Tech, Atlanta, GA |
Who said anything about 3g accelerations? I, at least, was talking about a 1g constant burn -- did I miss something?
Edit: here is an interesting article. _________________ American Institute of Aeronautics and Astronautics Daniel Guggenheim School of Aerospace Engineering In Memoriam... Apollo I - Soyuz I - Soyuz XI - STS-51L - STS-107 |
| Back to top |
|
|
|
Page 2 of 2 |
[ 21 posts ] |
Who is online
Users browsing this forum: No registered users and 18 guests |





Gabitasoft Interactive. All Rights Reserved.