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t. e. 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. The motion of these objects is usually calculated from Newton's laws of motion and the law of universal gravitation.
Clohessy–Wiltshire equations. The Clohessy–Wiltshire equations describe a simplified model of orbital relative motion, in which the target is in a circular orbit, and the chaser spacecraft is in an elliptical or circular orbit. This model gives a first-order approximation of the chaser's motion in a target-centered coordinate system.
Order of planets from the Sun: (Mercury, Venus, Earth, Mars, Jupiter, Saturn, Uranus, Neptune, Pluto) See also: Planetary mnemonic. obsolete (per the IAU definition of planet): M ost V egetables E at M ore J uice S o U sually N ever P ee 1. M y V ery E ducated M other J ust S erved U s N ine P otatoes 1.
Orbital state vectors. In astrodynamics and celestial dynamics, the orbital state vectors (sometimes state vectors) of an orbit are Cartesian vectors of position ( ) and velocity ( ) that together with their time (epoch) ( ) uniquely determine the trajectory of the orbiting body in space. [1]: 154. Orbital state vectors come in many forms ...
Applied mechanics – describes the behavior of a body, in either a beginning state of rest or of motion, subjected to the action of forces. [21] Applied mechanics, bridges the gap between physical theory and its application to technology. It is used in many fields of engineering, especially mechanical engineering and civil engineering.
Aerospace engineering– is the primary field of engineeringconcerned with the development of aircraftand spacecraft.[13] It has two major and overlapping branches: Aeronautical engineering and Astronautical Engineering. Avionicsengineering is similar, but deals with the electronicsside of aerospace engineering.
Newton's theorem simplifies orbital problems in classical mechanics by eliminating inverse-cube forces from consideration. The radial and angular motions, r (t) and θ1 (t), can be calculated without the inverse-cube force; afterwards, its effect can be calculated by multiplying the angular speed of the particle.
In other words, the rocket must exhaust mass opposite the spacecraft's acceleration direction, with such exhausted mass called propellant or reaction mass. [12]: Sec 1.2.1 [13] For this to happen, both reaction mass and energy are needed. The impulse provided by launching a particle of reaction mass with mass m at velocity v is mv.