What are the G forces leaving Earth orbit? Announcing the arrival of Valued Associate #679: Cesar Manara Planned maintenance scheduled April 23, 2019 at 00:00UTC (8:00pm US/Eastern)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?
Announcing the arrival of Valued Associate #679: Cesar Manara
Planned maintenance scheduled April 23, 2019 at 00:00UTC (8:00pm US/Eastern)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 Apr 2 at 19:31
Bob516Bob516
2,0631423
$endgroup$
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 Apr 2 at 19:31
Bob516Bob516
2,0631423
$endgroup$
$begingroup$
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
Apr 2 at 20:17
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 Apr 2 at 19:31
Bob516Bob516
2,0631423
$endgroup$
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 Apr 2 at 19:31
Bob516Bob516
2,0631423
asked Apr 2 at 19:31
Bob516Bob516
2,0631423
asked Apr 2 at 19:31
Bob516Bob516
2,0631423
asked Apr 2 at 19:31
Bob516Bob516
2,0631423
asked Apr 2 at 19:31
Bob516Bob516
2,0631423
2,0631423
$begingroup$
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
Apr 2 at 20:17
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
Apr 2 at 20:17
$begingroup$
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
Apr 2 at 20:17
$begingroup$
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
Apr 2 at 20:17
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 0.6g, increasing as fuel mass is exhausted, and finishing up around 1.45g, according to this graph from the Apollo 11 flight evaluation report:
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
There was some vibration noticed by the crew during the S-IVB burns. For subjective impressions, the best source is the crew debriefings done after each mission, though in this case they're surprisingly varied.
In the debriefing for Apollo 11, Aldrin said it was a "rougher ride than the S-II" (second stage, which presumably 'averaged out' the roughness of each individual engine across the set of five, and had more structure between the engines and the crew cabin to damp vibrations through) and Armstrong said it was "a little rattly all the time". (These comments were in regard to the orbital insertion phase of the S-IVB but were probably applicable to the TLI as well.)
The crew of Apollo 10 found it a little rougher, with Stafford saying "Where the S-IC stage and the S-II stage were completely smooth, the S-IVB growled, rattled, and rolled during the whole burn. But you could actually feel little vibrations."
Conrad on Apollo 12 was more positive: "S-IVB ignition was smooth. The ride on the S-IVB was very nice."
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
$endgroup$
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.
What were the G forces experienced by the Apollo astronauts during the translunar injection burn?
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 above leaves off and increase somewhat as the fuel was depleted. It would also jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
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.
edited Apr 2 at 22:42
uhoh
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
$endgroup$
3
$begingroup$
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
Apr 2 at 21:26
1
$begingroup$
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
Apr 2 at 21:37
$begingroup$
@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
uhoh That looks fine, thanks.
$endgroup$
– Greg
Apr 3 at 20:54
add a comment |
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2 Answers
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active
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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 0.6g, increasing as fuel mass is exhausted, and finishing up around 1.45g, according to this graph from the Apollo 11 flight evaluation report:
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
There was some vibration noticed by the crew during the S-IVB burns. For subjective impressions, the best source is the crew debriefings done after each mission, though in this case they're surprisingly varied.
In the debriefing for Apollo 11, Aldrin said it was a "rougher ride than the S-II" (second stage, which presumably 'averaged out' the roughness of each individual engine across the set of five, and had more structure between the engines and the crew cabin to damp vibrations through) and Armstrong said it was "a little rattly all the time". (These comments were in regard to the orbital insertion phase of the S-IVB but were probably applicable to the TLI as well.)
The crew of Apollo 10 found it a little rougher, with Stafford saying "Where the S-IC stage and the S-II stage were completely smooth, the S-IVB growled, rattled, and rolled during the whole burn. But you could actually feel little vibrations."
Conrad on Apollo 12 was more positive: "S-IVB ignition was smooth. The ride on the S-IVB was very nice."
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
$endgroup$
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 0.6g, increasing as fuel mass is exhausted, and finishing up around 1.45g, according to this graph from the Apollo 11 flight evaluation report:
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
There was some vibration noticed by the crew during the S-IVB burns. For subjective impressions, the best source is the crew debriefings done after each mission, though in this case they're surprisingly varied.
In the debriefing for Apollo 11, Aldrin said it was a "rougher ride than the S-II" (second stage, which presumably 'averaged out' the roughness of each individual engine across the set of five, and had more structure between the engines and the crew cabin to damp vibrations through) and Armstrong said it was "a little rattly all the time". (These comments were in regard to the orbital insertion phase of the S-IVB but were probably applicable to the TLI as well.)
The crew of Apollo 10 found it a little rougher, with Stafford saying "Where the S-IC stage and the S-II stage were completely smooth, the S-IVB growled, rattled, and rolled during the whole burn. But you could actually feel little vibrations."
Conrad on Apollo 12 was more positive: "S-IVB ignition was smooth. The ride on the S-IVB was very nice."
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
$endgroup$
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 0.6g, increasing as fuel mass is exhausted, and finishing up around 1.45g, according to this graph from the Apollo 11 flight evaluation report:
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
There was some vibration noticed by the crew during the S-IVB burns. For subjective impressions, the best source is the crew debriefings done after each mission, though in this case they're surprisingly varied.
In the debriefing for Apollo 11, Aldrin said it was a "rougher ride than the S-II" (second stage, which presumably 'averaged out' the roughness of each individual engine across the set of five, and had more structure between the engines and the crew cabin to damp vibrations through) and Armstrong said it was "a little rattly all the time". (These comments were in regard to the orbital insertion phase of the S-IVB but were probably applicable to the TLI as well.)
The crew of Apollo 10 found it a little rougher, with Stafford saying "Where the S-IC stage and the S-II stage were completely smooth, the S-IVB growled, rattled, and rolled during the whole burn. But you could actually feel little vibrations."
Conrad on Apollo 12 was more positive: "S-IVB ignition was smooth. The ride on the S-IVB was very nice."
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
$endgroup$
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 0.6g, increasing as fuel mass is exhausted, and finishing up around 1.45g, according to this graph from the Apollo 11 flight evaluation report:
For a Mars mission, it would depend entirely on the design of the spacecraft doing it, but it probably would be comparable.
There was some vibration noticed by the crew during the S-IVB burns. For subjective impressions, the best source is the crew debriefings done after each mission, though in this case they're surprisingly varied.
In the debriefing for Apollo 11, Aldrin said it was a "rougher ride than the S-II" (second stage, which presumably 'averaged out' the roughness of each individual engine across the set of five, and had more structure between the engines and the crew cabin to damp vibrations through) and Armstrong said it was "a little rattly all the time". (These comments were in regard to the orbital insertion phase of the S-IVB but were probably applicable to the TLI as well.)
The crew of Apollo 10 found it a little rougher, with Stafford saying "Where the S-IC stage and the S-II stage were completely smooth, the S-IVB growled, rattled, and rolled during the whole burn. But you could actually feel little vibrations."
Conrad on Apollo 12 was more positive: "S-IVB ignition was smooth. The ride on the S-IVB was very nice."
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
edited Apr 2 at 22:29
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
answered Apr 2 at 19:42
Russell BorogoveRussell Borogove
89.7k3300385
89.7k3300385
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.
What were the G forces experienced by the Apollo astronauts during the translunar injection burn?
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 above leaves off and increase somewhat as the fuel was depleted. It would also jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
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.
edited Apr 2 at 22:42
uhoh
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
$endgroup$
3
$begingroup$
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
Apr 2 at 21:26
1
$begingroup$
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
Apr 2 at 21:37
$begingroup$
@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
uhoh That looks fine, thanks.
$endgroup$
– Greg
Apr 3 at 20:54
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.
What were the G forces experienced by the Apollo astronauts during the translunar injection burn?
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 above leaves off and increase somewhat as the fuel was depleted. It would also jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
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.
edited Apr 2 at 22:42
uhoh
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
$endgroup$
3
$begingroup$
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
Apr 2 at 21:26
1
$begingroup$
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
Apr 2 at 21:37
$begingroup$
@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
uhoh That looks fine, thanks.
$endgroup$
– Greg
Apr 3 at 20:54
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.
What were the G forces experienced by the Apollo astronauts during the translunar injection burn?
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 above leaves off and increase somewhat as the fuel was depleted. It would also jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
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.
edited Apr 2 at 22:42
uhoh
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
$endgroup$
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.
What were the G forces experienced by the Apollo astronauts during the translunar injection burn?
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 above leaves off and increase somewhat as the fuel was depleted. It would also jump 13% when the LOX/LH2 ratio switched from 4.5:1 to 5.0:1.
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.
edited Apr 2 at 22:42
uhoh
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
edited Apr 2 at 22:42
uhoh
41.1k19156519
edited Apr 2 at 22:42
uhoh
41.1k19156519
edited Apr 2 at 22:42
uhoh
41.1k19156519
41.1k19156519
answered Apr 2 at 20:49
GregGreg
1,04739
answered Apr 2 at 20:49
GregGreg
1,04739
answered Apr 2 at 20:49
GregGreg
1,04739
1,04739
3
$begingroup$
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
Apr 2 at 21:26
1
$begingroup$
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
Apr 2 at 21:37
$begingroup$
@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
uhoh That looks fine, thanks.
$endgroup$
– Greg
Apr 3 at 20:54
add a comment |
3
$begingroup$
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
Apr 2 at 21:26
1
$begingroup$
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.
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– Greg
Apr 2 at 21:37
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@Greg I've added your comment back into your answer, does that look okay?
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– uhoh
Apr 2 at 22:42
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uhoh That looks fine, thanks.
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– Greg
Apr 3 at 20:54
3
3
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That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
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– Mark
Apr 2 at 21:26
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That graph cuts off before the part the question is asking about -- it shows every burn prior to the Trans-Lunar Injection burn.
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– Mark
Apr 2 at 21:26
1
1
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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
Apr 2 at 21:37
$begingroup$
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.
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– Greg
Apr 2 at 21:37
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@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
@Greg I've added your comment back into your answer, does that look okay?
$endgroup$
– uhoh
Apr 2 at 22:42
$begingroup$
uhoh That looks fine, thanks.
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– Greg
Apr 3 at 20:54
$begingroup$
uhoh That looks fine, thanks.
$endgroup$
– Greg
Apr 3 at 20:54
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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.
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– Uwe
Apr 2 at 20:17