Transfer between elliptical orbits

Question

For circular orbits the most efficient transfer is achieved with a hohmann transfer or a bi-elliptic transfer.

But what is the most efficient way to transfer between elliptical orbits?

I assume in the general case this isn't easily solvable (correct me if I'm wrong) but for the reduced case where only one orbit is elliptical:

I would (intuitively) assume that the optimal transfer is either the red or the blue one but I don't know how to calculate this myself.

Googling my question title I found these two links which probably answer my question but aren't publicly accessible and this paper though this only seems to talk about circular orbits.

Answer 1

It is my belief that a bitangential transfer between two coplanar orbits is best. For such a transfer, no direction change is needed at departure or arrival since velocity vectors are parallel at these two points.

The red orbit pictured above is tangent to the circular departure orbit as well as the elliptical destination orbit.

Here's a picture of many possible bitangential transfer orbits:

As with the earlier illustration, possible transfer orbits are colored, departure and destination orbits black.

For all these, the departure and arrival Vinfinity sum to very close to the same quantity (if my arithmetic's correct).

However, if the circular departure orbit is earth's and the elliptical destination orbit is an asteroid's, the longest transfer is the best. This makes rendezvous at the asteroid's aphelion. At this point the departure Vinf is at a maximum and arrival Vinf is at a minimum. But the big departure Vinf is largely mitigated by the Oberth benefit since earth has a deep gravity well. So of the two orbits you illustrate, the red one is less.

I write about these sorts of transfers at Tangent Ellipses. I made a spreadsheet looking at these orbits. A caveat: The spreadsheet is very complicated and no one has reviewed it. I am not confident it's error free. With that disclaimer out of the way, here's a link to it.

You may be interested in this often cited paper by Shoemaker and Helin: Earth-Approaching Asteroids as Targets for Exploration. The delta Vs they list assume a bitangential transfer with rendezvous at the asteroid's aphelion.

Answer 2

I can give you an upper bound for the necessary $\Delta v$, between all elliptical orbits, regardless of inclination. You can always do a bi-elliptical transfer, performed by almost reaching escape velocity, then do a close to 0 $\Delta v$ manoeuvre at infinity, and then fall back to insert into the target orbit. Both the large burns are done at periapse. You can then always do the transfer in:

$$\sqrt{\frac{2\mu}{r_{p1}}}-\sqrt{\mu\left(\frac{2}{r_{p1}}-\frac{2}{r_{a1}+r_{p1}}\right)}+\sqrt{\frac{2\mu}{r_{p2}}}-\sqrt{\mu\left(\frac{2}{r_{p2}}-\frac{2}{r_{a2}+r_{p2}}\right)}$$ or better.

where $r_a$ and $r_p$ are radius of apoapse and periapse for the two orbits, and $\mu$ is the gravitational parameter.

By the way, the red one is the most efficient one on your illustration. If the orbits are coplanar and one is circular, your manoeuvre can be performed in:

$$\left|\sqrt{\mu\left(\frac{2}{r_{a2}}-\frac{2}{r_{a2}+r_{p2}}\right)}-\sqrt{\mu\left(\frac{2}{r_{a2}}-\frac{2}{r_{a2}+r_{1}}\right)}\right|+\left|\sqrt{\mu\left(\frac{2}{r_{1}}-\frac{2}{r_{a2}+r_{1}}\right)}-\sqrt{\frac{\mu}{r_{1}}}\right|$$

Answer 3

I don't know the answer for certain, but am willing to hazard a guess that the most efficient way of transferring between a circular orbit and an elliptical orbit, assuming for a moment that they are coplanar, remains a single Hohmann transfer.

Here's why: Nominally, a Hohmann transfer takes you from one circular orbit to another. For every point on an elliptical orbit, there exists a circular orbit which intersects that point with the body moving in the same direction (though not at the same velocity). A Hohmann transfer works by first turning your orbit from circular to elliptical, then back into a circular orbit.

Changing the eccentricity of an orbit requires a burn delivering the proper velocity change (including the burn attitude) at the appropriate point in the orbit. This is done at the end of a traditional Hohmann transfer orbit to re-circularize the orbit at the desired distance from the barycenter, which becomes our new orbital radius. Once our orbit is circular, we could, in principle, apply another burn to change to a different elliptical orbit with the semi-major axis being the circular orbit's radius. By allowing the time between the burns to go to 0 and recalculating the second de-circularization burn based on the new point in the orbit at which it happens, we can turn these two burns into a single burn.

Thus, by tuning the Hohmann re-circularization impulse, it should be possible to transform your Hohmann transfer orbit directly into an elliptical orbit of the desired shape, while maintaining the Hohmann transfer's (delta-v) efficiency in getting between the two corresponding circular orbits.

It follows from the same line of reasoning that this should work equally well whether none, either or both of the endpoint orbits involved are circular or elliptic. (If the origin orbit is elliptical, you simply, at some point during the first burn, are instantaneously in a circular orbit.)

Answer 4

Between the two orbits you have labeled here, the red one will take less ΔV. In this case, what matters is preforming as much burn as far away from the body as possible, similar to how a bi-elliptic transfer works. I don't know if some other burn may preform better than one of these two, as the delta v equation I used only relates a change in semi-major axis length to delta V expended at an apsis.

If we say this is an orbit around earth, going from a 7*10^6 meter circular orbit to a higher elliptical orbit with periapsis at 2*10^7 and apoapsis at 7*10^7, then the red transfer will take ~11500 m/s ΔV and the blue transfer will take ~14100 m/s ΔV.

I made a desmos graph so that you can play around with different orbits around different bodies to see the effects on the ΔV here, and also made a (slightly) more general case of two ellipse orbits, given an aligned apoapsis, periapsis, and orbital plane here

Answer 5

there is some direct and indirect method to solve the problem, for direct solution, we need to achieve the first derivative of delta V versus of the independent parameters. For the indirect method, we need a numerical solution such as GA and PSO. There is some paper which have already solved some numerical example. However, I am publishing a paper in which I solved lots of different cases to find an appropriate fitting function.

Answer 6

My belief is a gravity assist for orbits higher than the moon or just straight up launching on a steep trajectory then do a circularisation burn to reach orbit. If Perigee needs to be raised furthur, a burn at apoapapsis will do it.

If you are going from low orbits to a high orbit, you can first do a burn at perigee to raise your apogee to your desired orbit, then burn at apoapapsis to raise your perigee. This will maximize the use of the oberth effect which states burning at perigee is more efficient than burning at apogee. If the burn is long, splitting it into 2 can also reduce the Delta-V needed.

If you are going from a low circular orbit to high elliptical, the best way is to burn at perigee to raise your apogee then burn at apogee to raise your perigee.

Answer 7

I am not sure that the bitangential transfer between two coplanar orbits is exist, we have to check that the focus of the transfer orbit is the same as center of attraction.