Difference between revisions of "Geosynchronous Orbit (Math)/ru"

Revision as of 12:36, 16 September 2014

This page or section is in need of being brought up to date. Please help Kerbal Space Program Wiki by fixing inaccurate or outdated information. * This looks more like a tutorial, should it be moved? Even if not, this should be either merged with Stationary orbit or moved to Synchronous orbit (Math). This formula works for all (circular) orbits, as t isn't given; a is then the SMA - body's radius.

Формулы

So, in order to calculate the geostationary orbit around any given body, we must first create an equation with the force of gravity and the centripetal force.The force of gravity is equal to:

${\displaystyle F_{G}={\frac {G\cdot M_{1}\cdot M_{2}}{r^{2}}}}$

where G is the gravitational constant (${\displaystyle 6.67384\cdot 10^{-11}{\frac {m^{3}}{kg\cdot s^{2}}}}$), M₁ is the mass of the body, M₂ is the mass of the satellite, and r is the distance between the center of mass of the planet and that of the satellite.

Now, because in a geostationary orbit the gravitational force is the same as the centripetal force, we can put them in opposite sides of the equation:

${\displaystyle F_{G}={\frac {G\cdot M_{1}\cdot M_{2}}{r^{2}}}=M_{2}\cdot {\frac {v^{2}}{r}}=F_{C}}$

The masses of the satellite cancel out, so we are left with:

${\displaystyle {\frac {G\cdot M_{1}}{r^{2}}}={\frac {v^{2}}{r}}}$

So, no matter how large your satellite is, the geostationary altitude will be the same.

We know that velocity is equal to distance divided by time. In this case, the distance is the circumference of your orbit, which is 2πr, and time in this instance is your orbital period, or one day for the planetary body. So, we now have:

${\displaystyle v={\frac {2\cdot \pi \cdot r}{t}}}$

But we are dealing with velocity squared, so we square our equation and get:

${\displaystyle v^{2}={\frac {4\cdot \pi ^{2}\cdot r^{2}}{t^{2}}}}$

Plugging that back into the original equation, we get:

${\displaystyle {\frac {G\cdot M_{1}}{r^{2}}}={\frac {4\cdot \pi ^{2}\cdot r^{2}}{t^{2}\cdot r}}}$

The r² cancels out the r in the denominator and becomes a plain old r. Thus, we have:

${\displaystyle {\frac {G\cdot M_{1}}{r^{2}}}={\frac {4\cdot \pi ^{2}\cdot r}{t^{2}}}}$

We now multiply by r²:

${\displaystyle G\cdot M_{1}={\frac {4\cdot \pi ^{2}\cdot r^{3}}{t^{2}}}}$

And multiply by t²/4π²:

${\displaystyle r^{3}={\frac {G\cdot M_{1}\cdot t^{2}}{4\cdot \pi ^{2}}}}$

And by taking the cube root of that, we arrive at our answer (well, sort of):

${\displaystyle r={\sqrt[{3}]{\frac {G\cdot M_{1}\cdot t^{2}}{4\cdot \pi ^{2}}}}}$

But remember how r is the distance from the center of mass of the planet to that of the satellite? Well, it turns out that, unlike satellites, the center of mass of a planet is rather far away from its surface:

${\displaystyle a={\sqrt[{3}]{\frac {G\cdot M_{1}\cdot t^{2}}{4\cdot \pi ^{2}}}}-R_{p}}$

Where ${\displaystyle a}$ is the altitude from the sea level of the planet, and ${\displaystyle R_{p}}$ is the radius of the planet. This formula calculates the altitude above sea level for any given orbital period ${\displaystyle t}$. To get the height for a stationary orbit, the orbital period must be as long as the sidereal rotation period, the time of a full revolution of the planet relative to the sky.

Always remember to subtract the radius of the planet from your answer once you find altitude.

Note: You probably noticed that the gravitational constant is in three units at once, two of them to a negative power. Don't panic, it will all work out when you plug in real numbers.

Обратите внимание

• Видеоролик о выводе на геосинхронную орбиту.