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What is the required burn to keep a satellite at a Lagrangian point?
Island Perimeter
What is the required burn to keep a satellite at a Lagrangian point?
What is the flight plan to get Gaia in orbit around the Sun–Earth $L_2$ Lagrangian point?Minimum Delta V to a staging area in cislunar space for a vertical space gunWhat are reasons to put Gaia space telescope into L2 Lagrangian point of Sun-Earth system?Do we sufficiently understand mechanics of Lagrange point stationkeeping for EML2 rendezvous and assembly?What does the Sun-Earth-Moon system look like from the Sun-Earth L-2 point?Low Energy Transfer within Earth-Moon systemAre (some) Halo Orbits actually Stable?Does the Milky Way have a Lagrangian point?What determines the orbital speed around a massless Lagrangian point?How far would the Mars L1 Lagrangian Point be from Mars?
$begingroup$
When a satellite reaches a Lagrangian point, it has a non-zero velocity $v_1$ because of the transfer orbit in which it had already been. What burn, say, $Delta v$, one needs if the satellite is about to be kept at that Lagrangian point? Given velocity $v_2$ after the burn applied to the spacecraft, shall we have $v_2 = 0$, i.e., $Delta v = -v_1$?
lagrangian-points velocity
asked 3 hours ago
RoboticistRoboticist
1484
$endgroup$
add a comment |
$begingroup$
When a satellite reaches a Lagrangian point, it has a non-zero velocity $v_1$ because of the transfer orbit in which it had already been. What burn, say, $Delta v$, one needs if the satellite is about to be kept at that Lagrangian point? Given velocity $v_2$ after the burn applied to the spacecraft, shall we have $v_2 = 0$, i.e., $Delta v = -v_1$?
lagrangian-points velocity
asked 3 hours ago
RoboticistRoboticist
1484
$endgroup$
$begingroup$
This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago
add a comment |
$begingroup$
When a satellite reaches a Lagrangian point, it has a non-zero velocity $v_1$ because of the transfer orbit in which it had already been. What burn, say, $Delta v$, one needs if the satellite is about to be kept at that Lagrangian point? Given velocity $v_2$ after the burn applied to the spacecraft, shall we have $v_2 = 0$, i.e., $Delta v = -v_1$?
lagrangian-points velocity
asked 3 hours ago
RoboticistRoboticist
1484
$endgroup$
When a satellite reaches a Lagrangian point, it has a non-zero velocity $v_1$ because of the transfer orbit in which it had already been. What burn, say, $Delta v$, one needs if the satellite is about to be kept at that Lagrangian point? Given velocity $v_2$ after the burn applied to the spacecraft, shall we have $v_2 = 0$, i.e., $Delta v = -v_1$?
lagrangian-points velocity
lagrangian-points velocity
asked 3 hours ago
RoboticistRoboticist
1484
asked 3 hours ago
RoboticistRoboticist
1484
asked 3 hours ago
RoboticistRoboticist
1484
asked 3 hours ago
RoboticistRoboticist
1484
asked 3 hours ago
RoboticistRoboticist
1484
1484
$begingroup$
This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago
add a comment |
$begingroup$
This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago
$begingroup$
This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago
$begingroup$
This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago
add a comment |
1 Answer
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$begingroup$
For those Lagrangian points which are unstable, L1, L2 and L3, there is no equilibrium, and any movement off the point will accelerate further away, towards the Sun or Earth. For them, you would need to counteract v1 (and any gravitational forces undergone along the way) in order to reach a rest velocity with respect to the Lagrangian point plus you would have to use thrusters to remain there.
For stable Lagrangian points, L4 and L5, you would need to simply meet the required orbit parameters. There will still be a burn to match the orbit.
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
$endgroup$
add a comment |
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1 Answer
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1 Answer
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$begingroup$
For those Lagrangian points which are unstable, L1, L2 and L3, there is no equilibrium, and any movement off the point will accelerate further away, towards the Sun or Earth. For them, you would need to counteract v1 (and any gravitational forces undergone along the way) in order to reach a rest velocity with respect to the Lagrangian point plus you would have to use thrusters to remain there.
For stable Lagrangian points, L4 and L5, you would need to simply meet the required orbit parameters. There will still be a burn to match the orbit.
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
$endgroup$
add a comment |
$begingroup$
For those Lagrangian points which are unstable, L1, L2 and L3, there is no equilibrium, and any movement off the point will accelerate further away, towards the Sun or Earth. For them, you would need to counteract v1 (and any gravitational forces undergone along the way) in order to reach a rest velocity with respect to the Lagrangian point plus you would have to use thrusters to remain there.
For stable Lagrangian points, L4 and L5, you would need to simply meet the required orbit parameters. There will still be a burn to match the orbit.
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
$endgroup$
add a comment |
$begingroup$
For those Lagrangian points which are unstable, L1, L2 and L3, there is no equilibrium, and any movement off the point will accelerate further away, towards the Sun or Earth. For them, you would need to counteract v1 (and any gravitational forces undergone along the way) in order to reach a rest velocity with respect to the Lagrangian point plus you would have to use thrusters to remain there.
For stable Lagrangian points, L4 and L5, you would need to simply meet the required orbit parameters. There will still be a burn to match the orbit.
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
$endgroup$
For those Lagrangian points which are unstable, L1, L2 and L3, there is no equilibrium, and any movement off the point will accelerate further away, towards the Sun or Earth. For them, you would need to counteract v1 (and any gravitational forces undergone along the way) in order to reach a rest velocity with respect to the Lagrangian point plus you would have to use thrusters to remain there.
For stable Lagrangian points, L4 and L5, you would need to simply meet the required orbit parameters. There will still be a burn to match the orbit.
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
answered 2 hours ago
Rory AlsopRory Alsop
10.3k24373
10.3k24373
add a comment |
add a comment |
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This will be a little hard to answer because satellites are usually put in orbits that move around Lagrange points (e.g. halo orbits), not exactly at them. Either way these tend to be unstable both because of orbital mechanics and because realistic orbits of the Earth, Moon, and other bodies are elliptical, not circular and so there are always perturbations. Also, satellites can try to approach these halo orbits along manifolds which can require very little delta-v to "slide into" halo orbits. It's a complicated topic.
$endgroup$
– uhoh
2 hours ago