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The Apollo Lunar Module (LM / ˈ l ɛ m /), originally designated the Lunar Excursion Module (LEM), was the lunar lander spacecraft that was flown between lunar orbit and the Moon's surface during the United States' Apollo program. It was the first crewed spacecraft to operate exclusively in the airless vacuum of space, and remains the only ...
The design of the saturable inductor current sensor is similar to that of a closed-loop Hall-effect current sensor; the only difference is that this method uses the saturable inductor instead of the Hall-effect sensor in the air gap. Saturable inductor current sensor is based on the detection of an inductance change. The saturable inductor is ...
Apollo Command Module primary guidance system components Apollo Lunar Module primary guidance system components Apollo Inertial Measurement Unit. The Apollo primary guidance, navigation, and control system (PGNCS, pronounced pings) was a self-contained inertial guidance system that allowed Apollo spacecraft to carry out their missions when communications with Earth were interrupted, either as ...
Actuator Sensor Interface (AS-Interface or ASi) is an industrial networking solution (Physical Layer, Data access Method and Protocol) used in PLC, DCS and PC-based automation systems. It is designed for connecting simple field I/O devices (e.g. binary ON/OFF devices such as actuators, sensors, rotary encoders, analog inputs and outputs, push ...
Transposition, docking, and extraction (often abbreviated to transposition and docking) was a maneuver performed during Apollo lunar landing missions from 1969 to 1972, to withdraw the Apollo Lunar Module (LM) from its adapter housing which secured it to the Saturn V launch vehicle upper stage and protected it from the aerodynamic stresses of launch.
An inrush current limiter is a device or devices combination used to limit inrush current. Passive resistive components such as resistors (with power dissipation drawback), or negative temperature coefficient (NTC) thermistors are simple options while the positive one (PTC) is used to limit max current afterward as the circuit has been operating (with cool-down time drawback on both).
The propulsion system for the descent stage of the lunar module was designed to transfer the vehicle, containing two crewmen, from a 60-nautical-mile (110 km) circular lunar parking orbit to an elliptical descent orbit with a pericynthion of 50,000 feet (15,000 m), then provide a powered descent to the lunar surface, with hover time above the lunar surface to select the exact landing site.
Attitude control (spacecraft): Horizon sensor, Earth sensor, Moon sensor, Satellite Sensor, Sun sensor; Catadioptric sensor; Chemoreceptor; Compressive sensing; Cryogenic particle detectors; Dew warning; Diffusion tensor imaging; Digital holography; Electronic tongue; Fine Guidance Sensor; Flat panel detector; Functional magnetic resonance ...