What are the G forces leaving Earth orbit?If the Apollo mandate were delivered today, would the mission vehicle(s) and profile be similar?Launch Accelerations: Values, historyHas in-space refueling been done?What does burnt Aerozine-50/N2O4 smell like?What is the escape velocity of Saturn at Enceladus distance?Would the Saturn V have been able to send more mass to TLI if it had a lower earth parking orbit?In what ways would the high elliptical orbit of Apollo “E missions” simulate lunar missions?Hypersonic Inflatable Aerodynamic Decelerator entry to Mars' atmosphereHow long is the Apollo Lunar Module extraction window?Has any human had the capability of leaving the Solar System?
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What are the G forces leaving Earth orbit?
If the Apollo mandate were delivered today, would the mission vehicle(s) and profile be similar?Launch Accelerations: Values, historyHas in-space refueling been done?What does burnt Aerozine-50/N2O4 smell like?What is the escape velocity of Saturn at Enceladus distance?Would the Saturn V have been able to send more mass to TLI if it had a lower earth parking orbit?In what ways would the high elliptical orbit of Apollo “E missions” simulate lunar missions?Hypersonic Inflatable Aerodynamic Decelerator entry to Mars' atmosphereHow long is the Apollo Lunar Module extraction window?Has any human had the capability of leaving the Solar System?
$begingroup$
What were the G forces experienced by the Apollo astronauts during the translunar injection burn? Was there a lot of vibrations during the TLI burn?
Is there estimates of the G forces an astronaut would experience leaving Earth orbit to go to Mars?
apollo-program escape-velocity trans-lunar-injection
asked 2 hours ago
Bob516Bob516
1,9351420
$endgroup$
add a comment |
$begingroup$
What were the G forces experienced by the Apollo astronauts during the translunar injection burn? Was there a lot of vibrations during the TLI burn?
Is there estimates of the G forces an astronaut would experience leaving Earth orbit to go to Mars?
apollo-program escape-velocity trans-lunar-injection
asked 2 hours ago
Bob516Bob516
1,9351420
$endgroup$
$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago
add a comment |
$begingroup$
What were the G forces experienced by the Apollo astronauts during the translunar injection burn? Was there a lot of vibrations during the TLI burn?
Is there estimates of the G forces an astronaut would experience leaving Earth orbit to go to Mars?
apollo-program escape-velocity trans-lunar-injection
asked 2 hours ago
Bob516Bob516
1,9351420
$endgroup$
What were the G forces experienced by the Apollo astronauts during the translunar injection burn? Was there a lot of vibrations during the TLI burn?
Is there estimates of the G forces an astronaut would experience leaving Earth orbit to go to Mars?
apollo-program escape-velocity trans-lunar-injection
apollo-program escape-velocity trans-lunar-injection
asked 2 hours ago
Bob516Bob516
1,9351420
asked 2 hours ago
Bob516Bob516
1,9351420
asked 2 hours ago
Bob516Bob516
1,9351420
asked 2 hours ago
Bob516Bob516
1,9351420
asked 2 hours ago
Bob516Bob516
1,9351420
1,9351420
$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago
add a comment |
$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago
$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago
$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago
add a comment |
2 Answers
2
active
oldest
votes
$begingroup$
Earth departure burns can be relatively leisurely, so the acceleration tends not to be extremely high. There is some tradeoff between doing the burn over a short timeframe to maximize the Oberth effect, versus using a smaller, lighter engine and maximizing crew comfort.
At the start of the Apollo TLI, acceleration would be about 0.7g, increasing as fuel mass is exhausted, and finishing up around 1.8g.
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
$endgroup$
add a comment |
$begingroup$
This image is from Quora because the picture I took from my Saturn V Haynes Manual was too big to upload. Anyway, you can see that the acceleration is by no means constant, but it peaks at just under 40 m/s^2, or around 4g. And it was a wild ride. In particular, when the first burn ended the entire structure, which had been compressed, snapped back. According to the Haynes Manual, astronaut Fred Haise said that when the first stage cut out he thought he was going through the instrument panel.
Space Shuttle, and I believe others like Soyuz, are designed to give a gentler ride, no more than 3g.
For a trip to Mars there would be two stages--getting into orbit, and getting to Mars. Getting into orbit would be like anything, probably around 3g. Getting to Mars would be a lot gentler, but depending on the technology. Like the ~6 m/s^2 of the Saturn's S-IVB stage followed by a lot of coasting--getting off the ground is a big deal, but once you're up there engines would be designed for efficiency rather than thrust. Or something like an ion engine with a barely perceptible acceleration for months at a time. There's nothing close to being ready to go yet, so it's too soon to say.
answered 1 hour ago
GregGreg
95738
$endgroup$
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
add a comment |
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2 Answers
2
active
oldest
votes
2 Answers
2
active
oldest
votes
active
oldest
votes
active
oldest
votes
$begingroup$
Earth departure burns can be relatively leisurely, so the acceleration tends not to be extremely high. There is some tradeoff between doing the burn over a short timeframe to maximize the Oberth effect, versus using a smaller, lighter engine and maximizing crew comfort.
At the start of the Apollo TLI, acceleration would be about 0.7g, increasing as fuel mass is exhausted, and finishing up around 1.8g.
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
$endgroup$
add a comment |
$begingroup$
Earth departure burns can be relatively leisurely, so the acceleration tends not to be extremely high. There is some tradeoff between doing the burn over a short timeframe to maximize the Oberth effect, versus using a smaller, lighter engine and maximizing crew comfort.
At the start of the Apollo TLI, acceleration would be about 0.7g, increasing as fuel mass is exhausted, and finishing up around 1.8g.
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
$endgroup$
add a comment |
$begingroup$
Earth departure burns can be relatively leisurely, so the acceleration tends not to be extremely high. There is some tradeoff between doing the burn over a short timeframe to maximize the Oberth effect, versus using a smaller, lighter engine and maximizing crew comfort.
At the start of the Apollo TLI, acceleration would be about 0.7g, increasing as fuel mass is exhausted, and finishing up around 1.8g.
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
$endgroup$
Earth departure burns can be relatively leisurely, so the acceleration tends not to be extremely high. There is some tradeoff between doing the burn over a short timeframe to maximize the Oberth effect, versus using a smaller, lighter engine and maximizing crew comfort.
At the start of the Apollo TLI, acceleration would be about 0.7g, increasing as fuel mass is exhausted, and finishing up around 1.8g.
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
answered 2 hours ago
Russell BorogoveRussell Borogove
88.4k3297382
88.4k3297382
add a comment |
add a comment |
$begingroup$
This image is from Quora because the picture I took from my Saturn V Haynes Manual was too big to upload. Anyway, you can see that the acceleration is by no means constant, but it peaks at just under 40 m/s^2, or around 4g. And it was a wild ride. In particular, when the first burn ended the entire structure, which had been compressed, snapped back. According to the Haynes Manual, astronaut Fred Haise said that when the first stage cut out he thought he was going through the instrument panel.
Space Shuttle, and I believe others like Soyuz, are designed to give a gentler ride, no more than 3g.
For a trip to Mars there would be two stages--getting into orbit, and getting to Mars. Getting into orbit would be like anything, probably around 3g. Getting to Mars would be a lot gentler, but depending on the technology. Like the ~6 m/s^2 of the Saturn's S-IVB stage followed by a lot of coasting--getting off the ground is a big deal, but once you're up there engines would be designed for efficiency rather than thrust. Or something like an ion engine with a barely perceptible acceleration for months at a time. There's nothing close to being ready to go yet, so it's too soon to say.
answered 1 hour ago
GregGreg
95738
$endgroup$
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
add a comment |
$begingroup$
This image is from Quora because the picture I took from my Saturn V Haynes Manual was too big to upload. Anyway, you can see that the acceleration is by no means constant, but it peaks at just under 40 m/s^2, or around 4g. And it was a wild ride. In particular, when the first burn ended the entire structure, which had been compressed, snapped back. According to the Haynes Manual, astronaut Fred Haise said that when the first stage cut out he thought he was going through the instrument panel.
Space Shuttle, and I believe others like Soyuz, are designed to give a gentler ride, no more than 3g.
For a trip to Mars there would be two stages--getting into orbit, and getting to Mars. Getting into orbit would be like anything, probably around 3g. Getting to Mars would be a lot gentler, but depending on the technology. Like the ~6 m/s^2 of the Saturn's S-IVB stage followed by a lot of coasting--getting off the ground is a big deal, but once you're up there engines would be designed for efficiency rather than thrust. Or something like an ion engine with a barely perceptible acceleration for months at a time. There's nothing close to being ready to go yet, so it's too soon to say.
answered 1 hour ago
GregGreg
95738
$endgroup$
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
add a comment |
$begingroup$
This image is from Quora because the picture I took from my Saturn V Haynes Manual was too big to upload. Anyway, you can see that the acceleration is by no means constant, but it peaks at just under 40 m/s^2, or around 4g. And it was a wild ride. In particular, when the first burn ended the entire structure, which had been compressed, snapped back. According to the Haynes Manual, astronaut Fred Haise said that when the first stage cut out he thought he was going through the instrument panel.
Space Shuttle, and I believe others like Soyuz, are designed to give a gentler ride, no more than 3g.
For a trip to Mars there would be two stages--getting into orbit, and getting to Mars. Getting into orbit would be like anything, probably around 3g. Getting to Mars would be a lot gentler, but depending on the technology. Like the ~6 m/s^2 of the Saturn's S-IVB stage followed by a lot of coasting--getting off the ground is a big deal, but once you're up there engines would be designed for efficiency rather than thrust. Or something like an ion engine with a barely perceptible acceleration for months at a time. There's nothing close to being ready to go yet, so it's too soon to say.
answered 1 hour ago
GregGreg
95738
$endgroup$
This image is from Quora because the picture I took from my Saturn V Haynes Manual was too big to upload. Anyway, you can see that the acceleration is by no means constant, but it peaks at just under 40 m/s^2, or around 4g. And it was a wild ride. In particular, when the first burn ended the entire structure, which had been compressed, snapped back. According to the Haynes Manual, astronaut Fred Haise said that when the first stage cut out he thought he was going through the instrument panel.
Space Shuttle, and I believe others like Soyuz, are designed to give a gentler ride, no more than 3g.
For a trip to Mars there would be two stages--getting into orbit, and getting to Mars. Getting into orbit would be like anything, probably around 3g. Getting to Mars would be a lot gentler, but depending on the technology. Like the ~6 m/s^2 of the Saturn's S-IVB stage followed by a lot of coasting--getting off the ground is a big deal, but once you're up there engines would be designed for efficiency rather than thrust. Or something like an ion engine with a barely perceptible acceleration for months at a time. There's nothing close to being ready to go yet, so it's too soon to say.
answered 1 hour ago
GregGreg
95738
answered 1 hour ago
GregGreg
95738
answered 1 hour ago
GregGreg
95738
answered 1 hour ago
GregGreg
95738
95738
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
add a comment |
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
2
2
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
$endgroup$
– Mark
30 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
$begingroup$
Dangit! I guess I didn't notice that. And my Haynes doesn't seem to give specific figures. But the S-IVB had a single engine, and they didn't try to throttle it. So the acceleration would have picked up where the graph left off and increased a bit as the fuel was depleted, then jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
$endgroup$
– Greg
19 mins ago
add a comment |
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$begingroup$
Many years ago I heard a speech of a german shuttle astronaut. He said there were very heavy vibrations caused by the solid fuel boosters. After the separation of the boosters the cryogenic liquid fuel engines thrust felt silky smooth. So the TLI burn of the third stage of the Saturn V should be smooth too.
$endgroup$
– Uwe
1 hour ago