Difference between revisions of "Orbital Dynamics"
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where G is the [[Universal Gravitational Constant]] whose value is 6.67300 × 10<SUP>-11</SUP> m<SUP>3</SUP> kg<SUP>-1</SUP> s<SUP>-2</SUP>, <math>m_1</math> is the mass of the first body, <math>m_2</math> is the mass of the second body, and r is the distance between them. | where G is the [[Universal Gravitational Constant]] whose value is 6.67300 × 10<SUP>-11</SUP> m<SUP>3</SUP> kg<SUP>-1</SUP> s<SUP>-2</SUP>, <math>m_1</math> is the mass of the first body, <math>m_2</math> is the mass of the second body, and r is the distance between them. | ||
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| + | The centripetal force of an object that is held in rotation around a fixed point is expressed as | ||
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| + | <math>F = \frac{m_{2}V}{r}</math> | ||
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| + | where V is the linear velocity of the object, which in our case is the satellite. Notice that the velocity (and later the period) are independent of the mass of the satellite. Combining these two equations together and solving for the velocity of the satellite gives an orbital velocity of a circular orbit as | ||
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| + | <math>V = \sqrt{\frac{m_{1}G}{r}} = \sqrt{\frac{\mu G}{r}} </math> | ||
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| + | where <math>\mu = m_{1}G </math> is referred to as a gravitational parameter, for which tables can be found for the Sun and each of the planets. | ||
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| + | The circumference of a circular orbit is <math>C = 2 \pi r </math>. The period is then equal to the circumference divided by the velocity, or | ||
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| + | <math>P = \frac{C}{V} = 2 \pi \sqrt{\frac{r^3}{\mu}} </math> | ||
Revision as of 17:30, 3 May 2007
Orbital dynamics is the study of the motion of objects in the presence of gravitational forces of other bodies, due to gravity. All bodies provide a gravitational pull on other bodies surrounding it.
The motion of one body about another body due to gravity, is known as an Orbit. Orbits are described by a body of theory called "Orbital Dynamics". Kepler discovered that in Newtonian Physics, which ignore Einstein's theories of relativity, orbits are elliptical in shape, at least for the simple case of one body orbiting another body without any influence from any third body. Kepler's Laws are three equations which describe elliptical orbits, and still hold true today.
Newton's Law of Gravity
The force exerted by two bodies on each other is given by
<math>F = \frac{Gm_{1}m_{2}}{r^{2}}</math>
where G is the Universal Gravitational Constant whose value is 6.67300 × 10-11 m3 kg-1 s-2, <math>m_1</math> is the mass of the first body, <math>m_2</math> is the mass of the second body, and r is the distance between them.
The centripetal force of an object that is held in rotation around a fixed point is expressed as
<math>F = \frac{m_{2}V}{r}</math>
where V is the linear velocity of the object, which in our case is the satellite. Notice that the velocity (and later the period) are independent of the mass of the satellite. Combining these two equations together and solving for the velocity of the satellite gives an orbital velocity of a circular orbit as
<math>V = \sqrt{\frac{m_{1}G}{r}} = \sqrt{\frac{\mu G}{r}} </math>
where <math>\mu = m_{1}G </math> is referred to as a gravitational parameter, for which tables can be found for the Sun and each of the planets.
The circumference of a circular orbit is <math>C = 2 \pi r </math>. The period is then equal to the circumference divided by the velocity, or
<math>P = \frac{C}{V} = 2 \pi \sqrt{\frac{r^3}{\mu}} </math>
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