Surprisingly, given dark enough skies, it is possible, armed with a telescope or with a stationary camera (and in some instances, binoculars), to spot some of the satellites nestling in the geostationary ring (known as a Clarke orbit, after Arthur C. Clarke who first suggested the usefulness of such an orbit).
Strictly speaking, a geostationary satellite would be in an orbit of 0 degrees inclination, zero eccentricity and a mean motion of 1.002701 revolutions per day or a period of 1436 minutes per revolution. The Earth rotates once in about 23 hours and 56 minutes (1436 minutes); the remaining 4 minutes allow the Earth to rotate further, compensating for the apparent change in position of the Sun. This arises from the movement of the Earth in it's orbit about the Sun. In fact most geostationary satellites are really geosynchronous. Having mean motions between 0.9 to 1.1 revolutions per day they are allowed to drift across a box before corrections are made by on board thrusters. The size of this box is dictated by mission requirements. For example the box for a TV broadcast satellite is determined by the beamwidth of the reception dishes used.
The drift from the ideal position arises due to anomalies in the Earth's gravitational field, at this altitude atmospheric drag is not a consideration. The gravitational influence of the Moon provides an out-of-plane force too, which gradually increases the orbital inclination towards that of the Moon about the Earth (which itself varies between 18 and 29 degrees). The satellite now tends to describe a figure-of-eight ground track; ground controllers aim to restrict this to the box mentioned earlier given that enough orbit-keeping fuel remains. This wandering has been allowed to grow unchecked in the case of a few communications satellites in order to provide better coverage of the polar regions which is otherwise poor (from the poles a geostationary satellite would almost graze the horizon). Net connectivity to US research stations in the Antarctic was achieved in this manner.
Due to the popularity of this orbit (geostationary slots over many regions are highly crowded and greatly valued) some agencies deorbit their satellites into a graveyard orbit some 500 to 1000 km above their operational altitude. This would be the ideal situation but as noted by Antonin Vitek on SeeSat-L, the final graveyard orbit is dictated by the remaining fuel on board as indicated by examples of some geosats he references. Failure to put these geo-sats in a graveyard orbit would put some of the valuable active satellites at risk once station-keeping fuel was exhausted and the dead satellites are at the mercy of the gravitational forces described above.
Why put the geosat into a higher orbit for "disposal"? SeeSat-L subscriber, Daryl Bahls points to a NASA report, "Guidelines & Assessment Procedures for Limiting Orbital Debris.
Most of these birds are communications satellites of one description or another. A common early design is that of a spin stabilized cylinder. The Hughes HS376 series are typical: the main body being some 3 meters long and 2 meters in diameter. This grows to around 6 meters in length once on orbit with the extension of the communications antennae and an extra skirt of solar panels. These supplement the cells which already cover the main body, making a very nice specular reflector. This skirt and the main body rotate about the long axis, typically at around 55 r.p.m., whilst the antenna and equipment shelf are despun so as to maintain contact with their ground targets.The Intelsat 603 satellite (left) which was rescued during the STS-49, shuttle mission (May 1992) is a Hughes HS type satellite. Here the skirt and communications antennae are still in their unfurled launch positions. An attitude gas thruster is visible on the left lower side of the satellite. After installing a new perigee kick motor (the original failed to fire, stranding the craft) this satellite was placed into its operating orbit using a new supersynchronous insertion method. Whereas most geosynchronous satellites are delivered to orbit via a geo-stationary transfer orbit (that is an initial orbit of around 300 by 36000 km where the perigee is then raised to 36000 km), here the initial orbit was around 300 by 82000 km. A series of burns both lowered the apogee and raised the perigee until the 36000km high orbit was attained. The newer geo-sats (left) are three-axis stabilized and considerably larger than the earlier generation. They maintain a given attitude through the use of thrusters and/or spinning momentum wheels. This design allows the use of larger solar arrays. In turn, the larger solar arrays allows increasing the transmitter power output of the satellite and transmission of the signal to smaller ground receiver antenna. Multiple transponders are used to focus transmission of the signal to discrete areas of the globe.
Unlike objects in low Earth orbit, geostationary satellites are visible throughout every night of the year, only entering the Earth's shadow for up to 70 minutes per day, around a couple of weeks either side of each equinox. During the same period the satellite tends to brighten over several days, twice a year, when the satellites orientation favors the 'beaming' of the Sun in the direction of the observer.
Typically the satellite will be in the mag. +11 to +14 range (or dimmer), but brightening by several magnitudes when the geometry is favourable (around mag. +5 to +6 is not untypical). One satellite is reported to have briefly been visible to the naked eye at mag. +3 !
Two line elements can be obtained for nearly all these satellites, bar the classified US military ones such as the MAGNUM/VORTEX signals intelligence and the DSP early warning satellites. Grouped elsets of geosats are available from the U.S. Department of Defense (DoD)'s Space-Track.org website, and T.S. Kelso's site. These elements can be used to generate a series of positions for the satellite in right ascension and declination (RA and dec) for the time of observation. Keep in mind that these geosats are basically fixed above a given point in the sky and as the Earth moves, the RA and dec will be continually changing. This can then be plotted on star map to form a finder chart; the guide stars will help identify the satellites location.
An alternative is to find the satellite's azimuth and altitude above the local horizon in your prediction program and set your optical aid to this constant value. Turning off the motor of a driven telescope will maintain the satellite in the field of view whilst the stars drift in and out courtesy of the Earth's rotation. By either doing this or tracking the stars instead during a wide angle photographic exposure one can provide a nice illustration of the geostationary ring as either the satellites are fixed and the stars trail, or vice versa. As pointed out above it is more rewarding to carry this out around the Spring and Fall equinoxes when the satellite will be more apparent. Observations over successive nights before and after this time will allow you to view the brightening of the object, plus its entry and exit from the Earth's shadow. Of course this will also avoid the disappointment of searching for it whilst it is in eclipse!
The BWGS has been involved in observations of Insat 1B (83-069B). In April 1994 this satellite exhibited an interesting light curve which possessed a maximum of mag. +5.6 dropping to invisibility, with a secondary maximum of mag. +9. The flash period was some 38 seconds.
Photometry by A. B. Giles and K. M. Hill of the University of Tasmania (reported in SpaceFlight, Vol. 31, September 1989) indicated the rotation rates of the Aussat A1 and A2 HS376-type satellites (85076B/15993 and 85109C/16275). When the light curve of each satellite (during the brightening period around the equinoxes) was analyzed, frequencies corresponding to various surface features (such as solar cells and thermal radiator mirrors) were evident.
Though three-axis stabilized satellites may become more abundant there are sufficient spin stabilized satellites available for various studies; the spin rates can yield insight into perturbing forces, whilst the reflected solar spectrum could infer the degree of degradation of the solar cells.
More recent observations may be found in the SeeSat-L archives.
Bill Livingston has developed a method to take time elapsed photos of geostationary satellites using basic camera equipment.
Paul Maley, who is an experienced satellite observer, has produced an excellent web site on satellite observing.
Jason Hatton's Centaur Rocket Boosters Page
Jonathan McDownell's Geo-Sat Log helps identify the longitudinal location of the various Geo-Sats.
Antonin Vitek's Space 40 Encylopedia of Satellite Data. While this resource is in the Czech language, much information can be gleaned such as the orbital parameter trends which are provided along with links on the satellite's background information and more. Just start with the launch year in question by selecting the appropriate calendar date in the upper left window. If you know the International Launch Number of the satellite also select the launch year and then the respective COSPAR number.
Ted Molczan's GEOLong program provides the longitudinal order of geosats.
Links: to the VSO Home Page, observing guide, shuttle details, satellite predictions.