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A small reaction wheel viewed in profile A momentum/reaction wheel comprising part of a high-accuracy Conical Earth Sensor to maintain a satellite's precise attitude. A reaction wheel (RW) is an electric motor attached to a flywheel, which, when its rotation speed is changed, causes a counter-rotation proportionately through conservation of angular momentum. [1]
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 ...
I used to design both Reaction Wheels and Momentum Wheels for spacecraft. Although they each have similarities between them, they are different animals. A reaction wheel imparts a instantaneous reaction torque into the spacecraft structure when accelerated / decelerated from 'coasting' RPM.
Reaction control systems are capable of providing small amounts of thrust in any desired direction or combination of directions. An RCS is also capable of providing torque to allow control of rotation (roll, pitch, and yaw). [2] Reaction control systems often use combinations of large and small thrusters, to allow different levels of response.
The following other wikis use this file: Usage on cs.wikipedia.org Reverzní Segnerovo kolo; Usage on fr.wikipedia.org Bateau pop-pop; Tourniquet de Feynman
A typical example is a space telescope that should be turned to observe a new celestial object. But also for 3-axis stabilized spacecraft for which the normal attitude is not inertially fixed the spacecraft is said to make a slew if the attitude is changed in another way and with another, mostly higher, rate than when in the basic attitude ...
Reaction wheels, inertial measurement units, and star trackers are used to maintain orientation, with cold gas thrusters to desaturate the wheels. Communications are in X-band via a 60 cm (24 in) diameter dish antenna. A 200 cm (79 in) boom extends above the spacecraft, hosting the EMAG and ELP mNLP sensors. [2]
The EELV Secondary Payload Adapter (ESPA) is an adapter for launching secondary payloads on orbital launch vehicles.. Originally developed for US launch vehicles in the 2000s to launch secondary payloads on space missions of the United States Department of Defense that used the Atlas V and Delta IV, the adapter design has become a de facto standard and is now also used for spaceflight missions ...