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Orbital mechanics or astrodynamics is the application of ballistics and celestial mechanics to the practical problems concerning the motion of rockets, satellites, and other spacecraft.
A rocket's required mass ratio as a function of effective exhaust velocity ratio. The classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity and can thereby move due to the ...
The boost phase is the portion of the flight of a ballistic missile or space vehicle during which the booster and sustainer engines operate until it reaches peak velocity. . This phase can take 3 to 4 minutes for a solid rocket (shorter for a liquid-propellant rocket), the altitude at the end of this phase is 150–200 km, and the typical burn-out speed is 7 k
A trajectory or flight path is the path that an object with mass in motion follows through space as a function of time. In classical mechanics, a trajectory is defined by Hamiltonian mechanics via canonical coordinates; hence, a complete trajectory is defined by position and momentum, simultaneously. The mass might be a projectile or a ...
In a MIRV, the main rocket motor (or booster) pushes a "bus" into a free-flight suborbital ballistic flight path. After the boost phase, the bus maneuvers using small on-board rocket motors and a computerized inertial guidance system. It takes up a ballistic trajectory that will deliver a re-entry vehicle containing a warhead to a target and ...
The Saturn V rocket used by Apollo 8 was designated AS-503, or the "03rd" model of the Saturn V ("5") rocket to be used in the Apollo-Saturn ("AS") program. When it was erected in the Vehicle Assembly Building on December 20, 1967, it was thought that the rocket would be used for an uncrewed Earth-orbit test flight carrying a boilerplate ...
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An orbital spaceflight (or orbital flight) is a spaceflight in which a spacecraft is placed on a trajectory where it could remain in space for at least one orbit. To do this around the Earth , it must be on a free trajectory which has an altitude at perigee (altitude at closest approach) around 80 kilometers (50 mi); this is the boundary of ...