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3

https://sci.esa.int/documents/33960/35865/1567260128466-JUICE_Red_Book_i1.0.pdf ESA JUICE Red book, chapter 5.1.4 page 89 The inclination will be increased by several Callisto flybys. Interesting that the JUICE team had a tradeoff - higher inclination but less Callisto mapping (becase the flybys would be over the same region), or less inclination but flybys ...


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I think you're correct that it's using repeated gravitational fly-bys in a synchronized orbit to do it. Starting at 4:57 in the video, where the "high inclination orbits" portion of the mission begins, it's clear that each inclination change coincides with the orbiter meeting one of the moons. It then does the same trick in reverse to get back to ...


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You can get the same efficiency in the ascending or descending node, it's just that you would need to apply the force in the opposite position if you wanted to switch from ascending to descending and vise versa.


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I ran into a similar issue in the past using a universal variable implementation of Lambert's method, and came to similar conclusions as you. As the TOF decreases and DV increases, there is a point where the solver will fail to converge due to numerical issues. It is not due to a fundamental error in the equations themselves, but comes from numerical ...


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Although it has been already answered briefly, I would like to add some extra information (increasing the inclination) about on the N/S maneuvers. Well the location of the thruster firing is highly depends on the maneuver type. If the maneuver is: North, then you should fire your thrusters while the satellite passes from ascending node in order to do more ...


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I've got a set of Keplerian orbital elements $e_0$, $a_0$, $i_0$, $\omega_0$, $\Omega_0$, and $\theta_0$, and I'd like to get to a different orbit with orbital elements $e$, $a$, $i$, $\omega$, $\Omega$, and $\theta$. How do I calculate (a) the amount of delta-v I'll need for this maneuver or set of maneuvers, and (b) which maneuver or set of maneuvers I ...


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What you're looking for is Lambert's problem, which is used both for trajectory design and orbit determination, and to produce porkchop plots. Your hunch that this is not a simple problem is correct. pykep has a solver for Lambert's problem that supports multiple revolutions as well as solvers for various related problems such as low-thrust trajectories.


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The Oberth effect exists because imparting a fixed change in momentum increases kinetic energy more when traveling at a faster speed than at a slower speed. This is due to the fact that kinetic energy is proportional to the square of velocity. Let's look at an example. Assume your spacecraft has a mass of 1 kg, and you have a rocket engine that can provide a ...


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