This calculator is designed for aerospace engineers to compute the parameters of satellite orbits efficiently. It helps in determining orbital characteristics based on input parameters such as mass, velocity, and altitude.
All calculations are based on standard orbital mechanics equations as detailed in "Orbital Mechanics for Engineering Students" by Howard D. Curtis. All calculations rely strictly on the formulas and data provided by this source.
Using LaTeX, the formula for the orbital period is:
Where \( T \) is the orbital period, \( a \) is the semi-major axis, and \( \mu \) is the standard gravitational parameter.
Suppose we have a satellite with a mass of 500 kg, an orbital velocity of 7800 m/s, and an altitude of 200 km. Using the formulas, the calculated orbital period is approximately 90 minutes.
The orbital period is the time a satellite takes to complete one full orbit around Earth.
This calculator uses precise formulas and is suitable for most engineering applications.
Yes, by substituting the gravitational parameter for the relevant celestial body.
The gravitational parameter is a constant that represents the strength of gravity from a celestial body.
The semi-major axis can be calculated using the sum of the Earth's radius and the orbital altitude.