Orbiter-Forum [IMFD] From Europa to Earth
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 01-10-2013, 08:14 AM #16 dgatsoulis ele2png user Quote: Originally Posted by Tommy  In the above case, the Oberth Effect doesn't come in to play anyway - the energy required to escape the moon will provide all the dVf you need, so you won't need a prograde burn at Earth. Any burn you do make there will be an alignment burn - and that's the worst time for alignment burns. If your IMFD solution is using too much fuel, you haven't set it up correctly - this flight should only require one main burn - the Moon Ejection. After that it's just MCC's. I thought that by mentioning the Oberth effect, a two burn solution was already implied. Perhaps I should have clarified: I'm talking about a two burn solution, in which the Oberth effect does come into play. One burn to drop from the moon to Earth and a second one at periapsis. Last edited by dgatsoulis; 01-10-2013 at 09:12 AM.
 01-10-2013, 09:56 AM #17 Tommy Orbinaut What I am saying is that simply escaping the Moon in a manner that would give you a suitiably low Earth Pe, you will already have enough velocity to leave Earth and get to Mars. To drop your Perigee to anywhere low enough to matter, you will need to escape the Moon with more than enough residual energy to make the Mars transfer. It's not an easy set-up, and you'll have to choose your launchtime a bit carefully - Brighton's got a fair bit of Latitude so you are limited to what parking orbit you can launch into. You want set the values in Target Intercept(SRC= Earth, TGT = Mars) to minimize the dV in Orbit Eject while watching the dVp value and node location in Slingshot and Map. Look for a date when the dvF values in both Orbit Eject and Slingshot are low, keep an eye on the RInc in Slingshot, and the node is at or near the Earth's SOI. This allows you to make the final alignment to the sling plane quite cheaply since velocity is low, but accuracy is high (can be iffy much farther out than SOI). This is only true for the Earth-Moon pair, and due to the large relative size of the Moon. If you were leaving Io, for Earth, the Oberth Effect would be more more important and TransX would be easier to use. There is, actually, a way to use IMFD for this using two burns (a hohman transfer to LJO, then use the Oberth Effect during the sling) but it is far too complicated to describe in a post! In that case, I'd go with TransX as being simpler! For most slingshots, TransX is better because it let's you plan several stages, where IMFD is much more "one step at a time". IMFD can't, for instance, be used to plan an EJS sling unless you luck onto a window or use something else to find one. IMFD is more accurate, but TransX's system of multiple stages let's you plan much more complex trajectories. Last edited by Tommy; 01-10-2013 at 10:00 AM.
 01-10-2013, 06:48 PM #18 dgatsoulis ele2png user Quote: Originally Posted by Tommy  What I am saying is that simply escaping the Moon in a manner that would give you a suitiably low Earth Pe, you will already have enough velocity to leave Earth and get to Mars. To drop your Perigee to anywhere low enough to matter, you will need to escape the Moon with more than enough residual energy to make the Mars transfer. It's not an easy set-up, and you'll have to choose your launchtime a bit carefully - Brighton's got a fair bit of Latitude so you are limited to what parking orbit you can launch into. You want set the values in Target Intercept(SRC= Earth, TGT = Mars) to minimize the dV in Orbit Eject while watching the dVp value and node location in Slingshot and Map. Look for a date when the dvF values in both Orbit Eject and Slingshot are low, keep an eye on the RInc in Slingshot, and the node is at or near the Earth's SOI. This allows you to make the final alignment to the sling plane quite cheaply since velocity is low, but accuracy is high (can be iffy much farther out than SOI). Would you mind posting a screenshot of the Target Intercept and Slingshot programs, so I can understand a little bit better about what kind of trajectory you are talking about? Just the initial setup. What I would like to see is the escape vector oV and the shape of the trajectory in the Slingshot program and the escape vector oV in the Course\Target Intercept program. Is the trajectory similar to your Moon to Mars tutorial, in the IMFD manual tutorials and playbacks?
 01-12-2013, 11:59 AM #19 sigsig Orbinaut You should set Src=Jupiter Tgt=Earth in Target Intercept and optimize your delta-v. Now open slingshot program an set Src=Europa and Ref=Jupiter, minimize PeT (some seconds is Ok) as shown on my screenshot changing TEj. Now copy Tej to Target Intercept. You should now reoptimize PeT in Slingshot Program. Repeat this procedure until PeT is minimum and both TEj are equal. In my experience Jupiter is too much massive to tray slingshoting around it at low altitude. So in my arrangement you will optimize your delta-v taking profit of the velocity of Europa.
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 01-12-2013, 02:44 PM #21 ADSWNJ Scientist Quote: Originally Posted by dgatsoulis  You are right to think that the slingshot program is the solution. I recorded a quick video showing you how to do it, but my mic was on "mute" (Not the first time this happens). Still you will be able to see the setup. Try it and come back with any questions you might have. Orbiter 2010 Europa to Earth with IMFD (Direct) - YouTube Perform the first correction when you are outside of Jupiter's SOI. I would really love to see you redo this video with your commentary. I have played with both TransX and IMFD in the past to do simple maneuvers and hops from one planet to another. Never done a slingshot or an aerobrake, etc. I would love to understand this tool through your commentary and see how you explain each of the values you are manipulating.
 01-12-2013, 03:14 PM #22 C3PO Donator Quote: Originally Posted by dgatsoulis  My disagreement with Tommy is about a single burn solution for a Moon→Mars journey, where I claim that using one burn to drop to low perigee and escape wastes fuel. That may be true for Europa --> Earth but I'm not convinced it's better for Earth -->Mars. Europa orbits deep in Jupiter's massive SOI, but that's not the case with the Moon. If you look at OrbitMFD when you are at Europa's Sma but not close to it, more than 99.5% of the gravity is from Jupiter. But if you do the same in Earth orbit, 67% of the gravity is from the Sun. This means that you enter Earth's SOI as you drop in from lunar orbit. Relative to the Sun, the Moon's orbital speed isn't that much different to the Earth's, but the Earth's mass should give you a good slingshot as you arrive from (almost) outside it's gravity well. Additionally you can utilize the Oberth effect by doing a part of the burn at periapsis as you swing by the Earth.
 01-12-2013, 03:54 PM #23 dgatsoulis ele2png user Quote: Originally Posted by C3PO  That may be true for Europa --> Earth but I'm not convinced it's better for Earth -->Mars. Europa orbits deep in Jupiter's massive SOI, but that's not the case with the Moon. If you look at OrbitMFD when you are at Europa's Sma but not close to it, more than 99.5% of the gravity is from Jupiter. But if you do the same in Earth orbit, 67% of the gravity is from the Sun. This means that you enter Earth's SOI as you drop in from lunar orbit. Relative to the Sun, the Moon's orbital speed isn't that much different to the Earth's, but the Earth's mass should give you a good slingshot as you arrive from (almost) outside it's gravity well. Additionally you can utilize the Oberth effect by doing a part of the burn at periapsis as you swing by the Earth. Yes, but then we are not talking about a single burn solution. Just to throw in some numbers: For a heliocentric transfer orbit from Earth's orbital distance to Mars' orbital distance that costs 2.8 km/s (pretty close to a Hohmann transfer) the single burn solution for the Injection ΔV from a Low Lunar Orbit (10 km alt) is ~1.7 km/s For the same transfer, the most efficient 2 burn solution is this: 1st burn from LLO ~0.85 km/s with the vector opposite of the moon's orbital path to drop to a perigee of ~150 km. (the Geocentric trajectory is still an elliptical orbit, with the apogee at the moon's distance and the perigee at 150km above the surface of the Earth). At perigee the velocity of the ship would be ~10.9 km/s The velocity needed for a 2.8 km/s heliocentric transfer orbit at 150 km alt above Earth's surface is the square root of the square of the escape velocity of that altitude plus the square of the transfer orbit ΔV. So the ΔV for the second burn is Vinj - Vpe = 11.4-10.9=0.5 km/s Total ΔV = 0.85+0.5=1.35 km/s saving ~0.35 km/s from the single burn solution. In theory there is an even cheaper 3 burn solution, but it's not practical for the Earth Moon system, since the apogee of the first burn is higher than Earth's SOI. The way to do it is to go to a high apoapsis in the first burn, there make a second retrograde burn to lower the periapsis and then the third burn at periapsis for the injection. This kind of solution is better suited for more massive planets. It worked great for flytandem in a Titan→Saturn→Jupiter→Earth flight. You can find the thread here. Last edited by dgatsoulis; 01-12-2013 at 04:42 PM.
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 01-12-2013, 05:17 PM #24 C3PO Donator You could add all the DV in the Lunar ejection burn. That would mean that the Geocentric transfer orbit would have a apogee higher than the Moon's orbit. But that would be less efficient then the 2 burn solution.
 01-12-2013, 05:30 PM #25 dgatsoulis ele2png user Quote: Originally Posted by C3PO  You could add all the DV in the Lunar ejection burn. That would mean that the Geocentric transfer orbit would have a apogee higher than the Moon's orbit. But that would be less efficient then the 2 burn solution. Not only that. Even for single burn solutions, every single burn solution that doesn't have the moon's orbital altitude as the perigee of the Earth escape trajectory is going to be inefficient. It's as simple as this: The best time to raise your apoapsis is when you are at periapsis. In this case we want to raise our apoapsis to a hyperbola, but the same rule applies.
 01-12-2013, 05:58 PM #26 Max Pain Orbinaut Quote: Originally Posted by dgatsoulis  Just to throw in some numbers: For a heliocentric transfer orbit from Earth's orbital distance to Mars' orbital distance that costs 2.8 km/s (pretty close to a Hohmann transfer) the single burn solution for the Injection ΔV from a Low Lunar Orbit (10 km alt) is ~1.7 km/s For the same transfer, the most efficient 2 burn solution is this: 1st burn from LLO ~0.85 km/s with the vector opposite of the moon's orbital path to drop to a perigee of ~150 km. (the Geocentric trajectory is still an elliptical orbit, with the apogee at the moon's distance and the perigee at 150km above the surface of the Earth). At perigee the velocity of the ship would be ~10.9 km/s The velocity needed for a 2.8 km/s heliocentric transfer orbit at 150 km alt above Earth's surface is the square root of the square of the escape velocity of that altitude plus the square of the transfer orbit ΔV. {image} So the ΔV for the second burn is Vinj - Vpe = 11.4-10.9=0.5 km/s Total ΔV = 0.85+0.5=1.35 km/s saving ~0.35 km/s from the single burn solution. Very nice! I think I have to learn TransX in order to do such maneuvers. Ever since I read the Rolling Stones, I wanted to do such a thing in Orbiter.
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 01-19-2013, 01:58 PM #28 dgatsoulis ele2png user @ Tommy Please look at the pic again. There is a fundamental flaw in the method you propose. You are not thinking about the direction the excess velocity relative to the Moon is applied. There is no case that you go from the initial green orbit to the red "direct sling" trajectory and not waste fuel relative to the "direct" method. Period. Yes my example was "two dimensional", but only to simplify the calculation. As you saw I used a 1.7 km/s example for the ΔV needed to eject from the Moon, which in itself embeds a typical large plane change (~30°). The ideal burn with no plane change is about 1.52 km/s from a 50 km circular orbit around the Moon. The worst case scenario, where a 90° plane change is needed, requires an ~1.9 km/s ejection burn from the same (50 km) altitude lunar orbit. Comparing the worst "direct" case (90° plane change) to the best "direct sling" case (no plane change) and there is still a difference of at least 250 m/s for the ejection burn. The numbers above are for a 2.8 km/s ΔV Earth-Mars transfer (oV in Course\Target intercept program). Quote: As with all flights, no single solution is ALWAYS best. Moon - Mars direct will be best once in a while, but Moon - Earth - Mars sling will be best most of the time. No, dropping to a low perigee -without using a two burn solution- will ALWAYS be worse than leaving directly from the Moon's orbital altitude. I guess we could settle this with an IMFD scenario in Orbiter. When you find the time, place a DG anywhere you want on the Moon, setup a Mars transfer and post the IMFD plan with your "direct sling" method, dropping to a low perigee and escaping Earth. (Left MFD course\target intercept program, right MFD Slingshot program). According to you, it should look something like the pic above. Please also post the ΔV you needed to make the ejection burn from lunar orbit and the altitude of that orbit. I submit to you that within the same lunar month from your ejection burn, (either a few days before of a few days after), there will be a much cheaper single burn solution that will leave directly from the Moon's orbital altitude, will have approximately the same TOF and will look similar to this:

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