Circular Orbits (e = 0)

Circular Orbits (\(e = 0\))#

Setting \(e = 0\) in the orbit equation, Eq. (113) yields:

(120)#\[r = \frac{h^2}{\mu}\]

The radius of an orbit with \(e = 0\) is constant, so the orbit is a circle. The velocity is also constant:

(121)#\[v_{\text{circular}} = \sqrt{\frac{\mu}{r}}\]

The time required to complete one orbit is known as the orbital period. Because the speed of a circular orbit is constant, the period is simply the circumference divided by the velocity:

(122)#\[T = \frac{2\pi r}{\sqrt{\mu/r}} = \frac{2\pi}{\sqrt{\mu}}r^{3/2}\]

The specific energy of a circular orbit is:

(123)#\[E_{\text{circular}} = -\frac{\mu}{2r}\]

The specific energy of the circular orbit is negative. As the orbit radius goes up, the energy increases and gets closer to zero. Thus, a given launch vehicle with a certain amount of fuel can launch a large payload to an orbit with a small radius, or a small payload to an orbit with a large radius.

Low Earth Orbit#

Many manned spacecraft and unpopulated satellites occupy ideally circular orbits around the Earth. These orbits typically fall between altitudes of 150 km (100 miles) and 2000 km (1200 miles). These orbits are called low earth orbits, or LEO. The lower of these altitudes is substantially above the bulk of the drag-inducing atmosphere. The higher altitude is less than the altitude of the Van Allen radiation belts, a dangerous region of space extending from about 1000 km outwards.

../_images/Comparison_satellite_navigation_orbits.svg

Fig. 37 A comparison of satellite navigation orbits. cmglee, CC BY-SA 3.0, via Wikimedia Commons#

Geostationary Equatorial Orbit#

If a satellite remains at a constant location above the earth’s equator, then the orbit is a circular geostationary equatorial orbit, or GEO. For GEO, the radial vector from the center of the earth to the satellite must have the same angular velocity as the surface of the earth.

The angular velocity of the earth’s surface is calculated by dividing the circular distance for one revolution, \(2\pi\) radians, by the time taken for one rotation about the axis through the poles. This length of time is called the the sidereal day and is equal to approximately 23.93 hours.

The familiar, 24-hour, day is called the synodic day or solar day. The solar day is the time that it takes for the Sun to reach its maximum height in the sky on consecutive days. This is slightly longer than the sidereal day, because the Earth is also moving around the sun as it rotates. If the Earth were fixed in space relative to the sun, the synodic and sidereal days would be equal length.

Using the duration of the sidereal day, we find an inertial angular velocity of the Earth of:

(124)#\[\omega_E = \unit{72.9218\times 10^{-6}}{rad/s}\]

The radius of GEO is

(125)#\[r_{\text{GEO}} = \sqrt[3]{\frac{\mu}{\left(\omega_E\right)^2}} = \sqrt[3]{\frac{398,600}{\left(72.9218\times10^{-6}\right)^2}} = \unit{42,164}{km}\]

The altitude of GEO is then:

(126)#\[z_{\text{GEO}} = \unit{35,768}{km} = \unit{22,241}{mi}\]

The speed at GEO is:

(127)#\[v_{\text{GEO}} = \unit{3.075}{km/s}\]