How much propellant is used up until liftoff?Challenger disaster: how full was the external tank at the time of destruction?How does the Space Shuttle's SSME engine's thrust vary after ignition?What rocket uses the largest percentage of Fuel/Oxidizer before liftoff?How much fuel was used for a Space Shuttle launch?SpaceX Falcon 9 Reusable first stage propellant for returnPropellant mass calculationHow does the mass of launchers change over time between ground and orbit?chemical propulsion with separate fuel and propellant?Is HAN-water propellant “green” enough to ever be used in a cubesat?What was the result of the propellant predictions in the last chapter of “Ignition!”?How to transport gigawatt-level power across a 100km distance?How to determine $Delta v$ loss due to gravitational pull from earthHow much fuel is necessary for 2nd stage of Falcon 9 rocket to land?
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How much propellant is used up until liftoff?
Challenger disaster: how full was the external tank at the time of destruction?How does the Space Shuttle's SSME engine's thrust vary after ignition?What rocket uses the largest percentage of Fuel/Oxidizer before liftoff?How much fuel was used for a Space Shuttle launch?SpaceX Falcon 9 Reusable first stage propellant for returnPropellant mass calculationHow does the mass of launchers change over time between ground and orbit?chemical propulsion with separate fuel and propellant?Is HAN-water propellant “green” enough to ever be used in a cubesat?What was the result of the propellant predictions in the last chapter of “Ignition!”?How to transport gigawatt-level power across a 100km distance?How to determine $Delta v$ loss due to gravitational pull from earthHow much fuel is necessary for 2nd stage of Falcon 9 rocket to land?
$begingroup$
How much of the total propellant mass (fuel+oxidizer) of the first stage/boosters is usually burnt between ignition and liftoff?
launch fuel efficiency
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
$endgroup$
add a comment |
$begingroup$
How much of the total propellant mass (fuel+oxidizer) of the first stage/boosters is usually burnt between ignition and liftoff?
launch fuel efficiency
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
$endgroup$
$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago
add a comment |
$begingroup$
How much of the total propellant mass (fuel+oxidizer) of the first stage/boosters is usually burnt between ignition and liftoff?
launch fuel efficiency
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
$endgroup$
How much of the total propellant mass (fuel+oxidizer) of the first stage/boosters is usually burnt between ignition and liftoff?
launch fuel efficiency
launch fuel efficiency
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
asked 11 hours ago
Everyday AstronautEveryday Astronaut
2,096832
2,096832
$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago
add a comment |
$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago
add a comment |
1 Answer
1
active
oldest
votes
$begingroup$
For the Space Shuttle:
Using the same approximate curves (with all their assumptions and limitations) used in the answer to How does the Space Shuttle's SSME engine's thrust vary after ignition?, we can integrate the SSME flowrates to get a startup propellant consumption of:
416 lbm LH2, 2246 lbm LO2 per engine,
and ~ 1248 lbm LH2, 6738 lbm LO2 for all three engines.
Since liftoff was virtually instantaneous after SRB ignition (certainly to the precision of these calculations) we can ignore SRB propellant usage preliftoff.
Using the ET loading numbers from Challenger disaster: how full was the external tank at the time of destruction? (LO2 1,387,457 lbm, LH2 234,265 lbm) we can calculate the % usage of ET propellant prior to liftoff as approximately 0.5% for both propellants.
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
$endgroup$
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
add a comment |
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1 Answer
1
active
oldest
votes
1 Answer
1
active
oldest
votes
active
oldest
votes
active
oldest
votes
$begingroup$
For the Space Shuttle:
Using the same approximate curves (with all their assumptions and limitations) used in the answer to How does the Space Shuttle's SSME engine's thrust vary after ignition?, we can integrate the SSME flowrates to get a startup propellant consumption of:
416 lbm LH2, 2246 lbm LO2 per engine,
and ~ 1248 lbm LH2, 6738 lbm LO2 for all three engines.
Since liftoff was virtually instantaneous after SRB ignition (certainly to the precision of these calculations) we can ignore SRB propellant usage preliftoff.
Using the ET loading numbers from Challenger disaster: how full was the external tank at the time of destruction? (LO2 1,387,457 lbm, LH2 234,265 lbm) we can calculate the % usage of ET propellant prior to liftoff as approximately 0.5% for both propellants.
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
$endgroup$
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
add a comment |
$begingroup$
For the Space Shuttle:
Using the same approximate curves (with all their assumptions and limitations) used in the answer to How does the Space Shuttle's SSME engine's thrust vary after ignition?, we can integrate the SSME flowrates to get a startup propellant consumption of:
416 lbm LH2, 2246 lbm LO2 per engine,
and ~ 1248 lbm LH2, 6738 lbm LO2 for all three engines.
Since liftoff was virtually instantaneous after SRB ignition (certainly to the precision of these calculations) we can ignore SRB propellant usage preliftoff.
Using the ET loading numbers from Challenger disaster: how full was the external tank at the time of destruction? (LO2 1,387,457 lbm, LH2 234,265 lbm) we can calculate the % usage of ET propellant prior to liftoff as approximately 0.5% for both propellants.
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
$endgroup$
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
add a comment |
$begingroup$
For the Space Shuttle:
Using the same approximate curves (with all their assumptions and limitations) used in the answer to How does the Space Shuttle's SSME engine's thrust vary after ignition?, we can integrate the SSME flowrates to get a startup propellant consumption of:
416 lbm LH2, 2246 lbm LO2 per engine,
and ~ 1248 lbm LH2, 6738 lbm LO2 for all three engines.
Since liftoff was virtually instantaneous after SRB ignition (certainly to the precision of these calculations) we can ignore SRB propellant usage preliftoff.
Using the ET loading numbers from Challenger disaster: how full was the external tank at the time of destruction? (LO2 1,387,457 lbm, LH2 234,265 lbm) we can calculate the % usage of ET propellant prior to liftoff as approximately 0.5% for both propellants.
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
$endgroup$
For the Space Shuttle:
Using the same approximate curves (with all their assumptions and limitations) used in the answer to How does the Space Shuttle's SSME engine's thrust vary after ignition?, we can integrate the SSME flowrates to get a startup propellant consumption of:
416 lbm LH2, 2246 lbm LO2 per engine,
and ~ 1248 lbm LH2, 6738 lbm LO2 for all three engines.
Since liftoff was virtually instantaneous after SRB ignition (certainly to the precision of these calculations) we can ignore SRB propellant usage preliftoff.
Using the ET loading numbers from Challenger disaster: how full was the external tank at the time of destruction? (LO2 1,387,457 lbm, LH2 234,265 lbm) we can calculate the % usage of ET propellant prior to liftoff as approximately 0.5% for both propellants.
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
edited 9 hours ago
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
answered 9 hours ago
Organic MarbleOrganic Marble
58.8k3161252
58.8k3161252
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
add a comment |
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
The external tank is loaded with 1,387,457 lb of LOX and 234,265 lb of LH2. So only 0.5 % of LOX and also of LH2 are used before liftoff.
$endgroup$
– Uwe
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@Uwe I was actually editing that into my answer as you were posting....
$endgroup$
– Organic Marble
8 hours ago
add a comment |
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$begingroup$
two percent plus or minus one percent
$endgroup$
– uhoh
10 hours ago
$begingroup$
@uhoh if my system used 3% of its prop sitting on the pad, I would be unhappy.
$endgroup$
– Organic Marble
8 hours ago
$begingroup$
@OrganicMarble we wouldn't want that. Are there any systems outside of my range? update: Oh, indeed there are!
$endgroup$
– uhoh
8 hours ago
$begingroup$
My wheelhouse is pretty narrow.
$endgroup$
– Organic Marble
8 hours ago