Kepler's third law of planetary motion says that the average distance of a planet from the Sun cubed is directly proportional to the orbital period squared. Newton found that his gravity force law could explain Kepler's laws. Since Newton's law of gravity applies to any object with mass, Kepler's laws can be used for any object orbiting another object. Let's look at satellites orbiting a planet.
If you have two satellites (#1 and #2) orbiting a planet, Kepler's third law says:
If you have measured the orbital period of one satellite around a planet, you can then easily find how long it would take any other satellite to orbit the planet in any size oribt. Kepler's third law can be simplified down to
|period #1||=||period #2 × Sqrt[(distance #1/distance #2)3]|
|period #1||=||period #2 × (distance #1/distance #2)3/2.|
Those of you with a scientific calculator (one that does powers, trig functions, scientific notation, etc.) will want to use the formula on the last line (remember that 3/2 = 1.5). Those with a calculator that just has a square root button will want to use the formula on the second-to-last line.
If the satellite is orbiting the Sun, then the relation can be greatly simplified with an appropriate choice of units: the unit of years for the orbit period and the distance unit of astronomical units. In this case, the reference ``satellite'' is the Earth and Kepler's third law becomes period = distance3/2. Let's use this to find out how long it takes to explore the solar system.
Let's go to Mars! The relative positions of Earth and Mars must be just right at launch so that Mars will be at the right position to greet the spacecraft when it arrives several months later. These good positionings happen once every 780 days (the synodic period of Mars). The spacecraft must be launched within a time interval called the ``launch window'' that is just few of weeks long to use a Hohmann orbit for the spacecraft's path. The Earth is at the perihelion (point closest to the Sun) of the spacecraft orbit (here, 1.0 A.U.) and Mars is at the aphelion (point farthest from the Sun---here, 1.52 A.U.).
Kepler's third law relates the semi-major axis of the orbit to its sidereal period. The major axis is the total length of the long axis of the elliptical orbit (from perihelion to aphelion). For the Mars journey, the major axis = 1.52 + 1.0 A.U. = 2.52 A.U. The semi-major axis is one-half of the major axis, so divide the major axis by two: 2.52/2 = 1.26 A.U. Now apply Kepler's third law to find the orbital period of the spacecraft = 1.263/2 = 1.41 years. This is the period for a full orbit (Earth to Mars and back to Earth), but you want to go only half-way (just Earth to Mars). Travelling from Earth to Mars along this path will take (1.41 / 2) years = 0.71 years or about 8.5 months.
When the craft is launched, it already has the Earth's orbital velocity of about 30 kilometers/second. Since this is the speed for a circular orbit around the Sun at 1.0 A.U., a reduction in the spacecraft's speed would make it fall closer to the Sun and the Hohmann orbit would be inside the Earth's orbit. Since you want to go beyond the Earth's orbit, the spacecraft needs an increase in its speed to put it in an orbit that is outside the Earth's orbit. It will slow down gradually as it nears aphelion.
At aphelion the spacecraft will not be travelling fast enough to be in a circular orbit at Mars' distance (1.52 A.U.) so it will need to arrive at aphelion slightly before Mars does. Mars will then catch up to it. But the spacecraft will be moving much too fast to be in a circular orbit around Mars, so it will need to slow down to go in orbit around Mars.
On its journey to Mars, the spacecraft's distance from the Sun is continuously monitored to be sure the craft is on the correct orbit. Though the spacecraft responds mostly to the Sun's gravity, the nine planets' gravitational pulls on the spacecraft can affect the spacecraft's path as it travels to Mars, so occasional minor firings of on-board thrusters may be required to keep the craft exactly on track.
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last updated: 12 May 2001