(34) Orbits in Space

Synchronous Orbits

All space orbits obey the laws of Kepler and Newton. As already noted, for circular orbits Kepler's third law may be written

T = 5063 seconds R3/2 = 5063 seconds R * SQRT(R)

where T is the orbital period, * marks multiplication, R is the orbit's radius in units of Earth radii (= 6371 km) and SQRT(R) is the square root of R.

 NASA's communication  satellite TDRRS, used to relay  data from orbiting spacecraft

From this one finds that for T = 86400 sec = 24 hours, R = 6.6 Earth radii. An equatorial satellite at this distance has a period of 24 hours and therefore, as the Earth rotates, it stays above the same point on the Earth's equator. Such an orbit is ideal for a communication satellite, for then a "satellite dish" linked to it need not track it across the sky, but can stay pointed in a fixed direction.

It was the British science fiction writer Arthur Clarke who first proposed the use of this "synchronous" orbit, long before the first artificial satellites. Clarke later wrote the book "Fountains of Paradise" (set in Sri Lanka, to which he had moved) in which thin cables linked synchronous satellites to the ground. A material strong enough and light enough for such cables does not exist, and is so far beyond anything known that it is probably impossible; but it makes a good story. About 200 satellites now inhabit synchronous orbit, some owned by governments for their own use, many operated by telecommunication companies.

Atmospheric Re-entry

The Kepler formula also applies to elliptical motion, provided R is replaced by the semi-major axis a of the orbit. Over time however orbits stray from exact Keplerian ellipses because to additional forces, such as the attraction of the Moon and the Sun. For elongated ellipses, this causes the lowest point in the orbit ("perigee") to move up and down, ultimately reaching the atmosphere and causing satellite to be lost.

Atmospheric friction also causes low-altitude satellites to re-enter, sooner or later: all these, as they lose energy, descend deeper and deeper into the atmosphere, and ultimately reach denser regions, where they burn up. That was the fate of the Skylab space station in 1980: NASA had hoped to use the Space Shuttle to boost it into a higher orbit, but the shuttle was not ready on time.

Meanwhile the peak of the 11-year sunspot cycle arrived, a more active peak than NASA had hoped for, bringing a greater intensity of solar x-rays and extreme ultra-violet radiation. These radiations are absorbed in the uppermost fringes of the atmosphere, heat them up and make them expand outwards, more at "solar maximum" than at other times. Their expansion increased the air resistance ("drag") to the motion of Skylab and caused its early demise.

The Bulge of the Earth

If the Earth were a perfect sphere, orbit calculations could assume that all its mass was concentrated at its center: the force, at least outside the Earth, would have been exactly the same. However, the centrifugal force associated with the Earth's rotation makes it slightly non-spherical, wider across the equator by a few kilometers than from pole to pole.

That modifies the orbits of satellites and must be taken into account. When the orbital plane is inclined to the equator, the equatorial bulge slowly rotates it around the Earth: a line perpendicular to the orbit plane gradually traces a cone. Interestingly, there exists a situation where one can take advantage of this rotation.

 Ordinarily, a satellite's orbit is fixed in space, and as the Earth goes around the Sun, its orientation relative to the Sun constantly changes. Take for example the case of a low altitude satellite whose orbit plane contains the axis of the Earth (i.e. it passes right above the north and south poles). If in June that plane happens to be lined up with the dawn-dusk direction, i. e. the division between the sunny side of Earth from the shaded one, then in September it matches the noon-midnight direction, a rotation of 90 degrees. Note that the June orbit enjoys 24-hour sunlight, but the September orbit does not.

However certain orbits exist, passing just a few degrees from the poles, whose planes are rotated by the bulge of the Earth by exactly one rotation per year. Such "sun synchronous" orbits, can be made to always face the Sun, or always go through midnight. The DMSP satellites have such orbits (the picture here, of the aurora above the Great Lakes, was taken by one of these satellites; note Florida at bottom right), and so did Magsat.

Earth observation satellites such as Landsat and SPOT (Satellite Pour l'Observation de la Terre) also prefer sun-synchronous orbits, which ensure that images from different dates are always taken at the same time of the day. Without this, the difference in the shadows may confuse their interpretation.

Lagrangian Points

 By Kepler's 3rd law, a spacecraft going around the Sun in a circle smaller than the Earth's orbit will always have a shorter period and will move faster, and if launched from Earth its distance will grow until it and the Earth are well separated. Yet a way exists for keeping the two together.

If the spacecraft is placed between the Earth and the Sun, the opposing pull of the Earth reduces the effective pull of the Sun, allowing the spacecraft to orbit the Sun more slowly. If the distance is properly chosen, the orbital motion will match that of Earth, allowing the two to stay together throughout the Earth's annual journey around the Sun.

The point where this happens is the L1 Lagrangian point (after Joseph Lagrange, the French mathematician who pointed it out). It is about 4 times more distant than the Moon, at about 1/100 of the distance of the Sun. Click here for a calculation of the L1 distance, using results from sections (20),(21) and (M-5).

The L1 point provides a very useful position for monitoring the solar wind before it reaches Earth and for other purposes. Currently two spacecraft are stationed near L1-- ACE, studying "anomalous cosmic rays" and also observing the solar wind, and SOHO, which observes the sun. WIND which also occupied this region has moved to a new orbit.

SOHO, a joint effort by NASA and the European space agency ESA, was nearly lost in June 1998 when by accident its high-gain antenna was shifted to where it no longer pointed at Earth. It also lost power because its solar cells no longer squarely faced the Sun, and the fuel of its on-board rocket got badly chilled. Some anxious months followed, during which the controllers tried various ways of re-asserting control, even using the giant Arecibo radio telescope as a radar dish to pin-point the location of the spacecraft. Control was regained in the second half of September 1998 and the spacecraft resumed operation; unfortunately, its last gyro failed in December 1998. As of April 1999, its attitude is successfully controlled by inertia wheels, adapted for a job for which they were not originally intended.

Four more Lagrangian points exist in the Earth-Sun system, including L2, symmetric to L1 on the nightside of the Earth. NASA plans to place its "Next Generation Space Telescope" (NGST), the successor to the orbiting Hubble telescope, at or near L2. For more details about these points and on related space missions, .

Cruising through the Solar System

To escape Earth a spacecraft needs a high velocity: 8 km/s to enter low Earth orbit, 11.2 km/s to escape Earth altogether. The only known way of getting such velocities are rockets.

But even when a spacecraft escapes from Earth, it is still held by the Sun's gravity. While no longer bound to Earth, it will still orbit the Sun, at about the same distance as before. To move around the solar system, additional velocity is needed.

The hardest object to reach would be the Sun itself. Our imaginary spacecraft, freed from the Earth, would be moving like the Earth around the Sun at about 30 km/sec. The only way for it to reach the Sun is to somehow kill that velocity--for instance, by a rocket imparting 30 km/s in the opposite direction; if that were done, the spacecraft would be pulled in by the Sun. The people who propose sending nuclear waste by rocket into the Sun do not seem to know much about orbits!

Considering the great difficulty in giving a spacecraft even the 8 km/s required for a low Earth orbit, the great rocket power required for reaching distant planets is a serious obstacle. Luckily, one can often take advantage of planetary swing-by maneuvers, as discussed in the next section.

Calculation:       #34a The Distance to the L1 Point

Next Regular Stop: #35 To the Planets, to the Stars

Author and curator: David P. Stern
Last updated 3 April 1999