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Results tagged with orbital-mechanics
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user 22816
Orbital mechanics (also called astrodynamics) is the application of ballistics and celestial mechanics to the practical problems concerning the motion of rockets and other spacecraft on an orbital or escape trajectory. For the movements of celestial bodies, use [celestial-mechanics], not this.
5
votes
How to calculate time since ascending node crossing?
If you aren't dealing with some sort of perturbation of the orbit (from atmosphere, oblateness of the Earth, the satellite thrusting), and are not dealing with extreme timescales, and are only doing …
- 5,565
5
votes
Besides hyperbolic flybys, what are all the other cases where the Oberth effect can be used?
The Oberth effect doesn't give you more delta-V. It gives you a larger change in specific orbital energy for the delta-v you decide to expend because of where you decide to expend it. Spending delta-v …
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3
votes
Accepted
How can you determine the nature of an object from its flight path angle, velocity, and radi...
Given the radial distance $r$, velocity $v$, flight path angle $\gamma$ in radians, gravitational parameter $\mu$, and specific orbital energy $\epsilon$,
the specific relative angular momentum is
$ …
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6
votes
Is there an upper velocity limit to obtain benefit of the Oberth effect for a high speed hyp...
In most star systems, if you can burn forever at 300 gees, orbital mechanics are things that happen to other people.
Coasting into the Solar System with a hyperbolic excess velocity of about $15\,000 …
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10
votes
Accepted
How to calculate the time to reach a given true anomaly?
Assumptions:
The value you are requesting is the time-of-flight from, or to the periapsis of your specified orbit to the specified True Anomaly. We will designate this value as $t$.
We have the follo …
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11
votes
Accepted
Is there a neat formula for hyperbolic Kentucky windage?
Using Perifocal polar coordinates, where the x-axis points from the central body to the periapsis, and the polar equation for conic sections:
$$r=\frac{a(1-e^2)}{1+e \cos(f)}$$
Provided paramete …
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10
votes
Accepted
What can be determined about an orbit if it passes through two points
If you only know two points on the orbit, and the mass and position of the central body, all you can determine for certain is its orbital plane.
An example of two very different orbits that pass t …
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7
votes
Accepted
Are 3 points on an orbit enough to determine the shape of it in practice?
I believe the answer is yes, given one focus, and three coplanar points on the orbit, you can define the orbital shape, and obtain semi-major axis, orbital eccentricity, and the direction of the peria …
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8
votes
Obtaining orbital state vectors given two position vectors and an eccentricity
No, one focus, two points on the orbit, and the orbital eccentricity is not enough information to determine the velocity vector.
Attached below are images of two different ellipses that share the sam …
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1
vote
Accepted
My vector math seems to be off in this 2D simulation of a solar system
In the following line:
gravHeading = createVector(otherBodyPosition.sub(this.pos)).heading();
otherBodyPosition.sub(this.pos) is already a Vector. When you try to createVector on that, you're putting …
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1
vote
Finding Earth-Centered Coordinates of Periapsis
In the situation where the orbit is not inclined, the convention generally is that the Argument of Periapsis is the angle from the Reference Direction (in your case, the x-axis) to the Periapsis.
Th …
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8
votes
Accepted
How to find the hyperbolic angle given the mean anomaly?
Like the corresponding eccentric anomaly for elliptical orbits, there is no closed-form formula for going from mean anomaly to hyperbolic anomaly.
You're going to have to use some sort of numerical m …
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3
votes
Accepted
Given r/a, what are the limits on the direction that an orbiting body could be moving (e.g. ...
There are no limits on the direction.
The Vis-viva equation will give you a speed. Assuming point-masses and sticking to classical mechanics, the Vis-Viva equation does not care at all about what di …
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5
votes
Accepted
How will JWST maintain its elliptical orbit around L2?
Basically, it would not be orbiting L2 in a Keplerian orbit sense. There is no mass at L2 for the spacecraft to orbit, you are correct in that sense.
The JWST would be in a solar orbit in that would …
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7
votes
Why do the modified equinoctial elements use the semilatus rectum?
Partial Answer:
For the extreme special case of the parabolic trajectory, where Orbital Eccentricity = $e=1$, the semi-major axis hits a singularity at $a=\pm\infty$, whereas the semi-latus rectum rem …
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