In orbital mechanics, the time of flight (TOF) is half of the orbital period of the entire ellipse. Lambert's theorem states that the time of flight is a function of a, r0 + r, and c. This means that the orbit can be transformed to any shape desired as long as the semi-major axis a, r0 + r, and c are held constant. The time of flight can be determined by putting the above equation in terms of mean anomaly and eccentric anomaly. A more general equation can be used if the satellite passes through periapsis. Kepler's equation is one approach to calculating orbits. Kepler's equations relate... Show more In orbital mechanics, the time of flight (TOF) is half of the orbital period of the entire ellipse. Lambert's theorem states that the time of flight is a function of a, r0 + r, and c. This means that the orbit can be transformed to any shape desired as long as the semi-major axis a, r0 + r, and c are held constant. The time of flight can be determined by putting the above equation in terms of mean anomaly and eccentric anomaly. A more general equation can be used if the satellite passes through periapsis. Kepler's equation is one approach to calculating orbits. Kepler's equations relate position to time for the different kinds of orbits. Show less
In orbital mechanics, the time of flight (TOF) is half of the orbital period of the entire ellipse.
Lambert's theorem states that the time of flight is a function of a, r0 + r, and c. This means that the orbit can be transformed to any shape desired as long as the semi-major axis a, r0 + r, and c are held constant. The time of flight can be determined by putting the above equation in terms of mean anomaly and eccentric anomaly. A more general equation can be used if the satellite passes through periapsis. Kepler's equation is one approach to calculating orbits. Kepler's equations relate position to time for the different kinds of orbits.
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