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A space vehicle's flight is determined by application of Newton's second law of motion: =, where F is the vector sum of all forces exerted on the vehicle, m is its current mass, and a is the acceleration vector, the instantaneous rate of change of velocity (v), which in turn is the instantaneous rate of change of displacement.
The space probes Voyager 1 and Voyager 2 employ this method, and have used up about three quarters [4] of their 100 kg of propellant as of July 2015. Another method for achieving three-axis stabilization is to use electrically powered reaction wheels , also called momentum wheels, which are mounted on three orthogonal axes aboard the spacecraft.
Orbital mechanics is a core discipline within space-mission design and control. Celestial mechanics treats more broadly the orbital dynamics of systems under the influence of gravity , including both spacecraft and natural astronomical bodies such as star systems , planets , moons , and comets .
A spacecraft's attitude must typically be stabilized and controlled for a variety of reasons. It is often needed so that the spacecraft high-gain antenna may be accurately pointed to Earth for communications, so that onboard experiments may accomplish precise pointing for accurate collection and subsequent interpretation of data, so that the heating and cooling effects of sunlight and shadow ...
The reaction control and orbital maneuvering systems provide the propulsive force for orbit maintenance, position control, station keeping, and spacecraft attitude control. [5] [3] [4] In orbit, any additional impulse, even tiny, will result in a change in the orbit path, in two ways: [8]
The slew of a spacecraft is its orientation in reference to a plane or fixed position such as Earth, the Sun, another celestial body or other point in space. When moving to assume such an orientation, the spacecraft is slewing. [1] [2] [3] During spaceflight, a craft's attitude must be controlled for reasons depending on the craft's mission ...
A new generation of spacecraft now under development by NASA to replace the Space Shuttle and return astronauts to the Moon will have a manual control capability for several mission tasks, and the ease and precision with which pilots can execute these tasks will have an important effect on performance, mission risk and training costs.
A control moment gyroscope (CMG) is an attitude control device generally used in spacecraft attitude control systems. A CMG consists of a spinning rotor and one or more motorized gimbals that tilt the rotor’s angular momentum. As the rotor tilts, the changing angular momentum causes a gyroscopic torque that rotates the spacecraft. [1] [2]