Aplicaciones Giroscopo

Gyroscopic Technologies in Aeronautical Engineering

Topics: 1.Gyroscopic Principle 2.Sources of Power 3.Turn Indicators 1.Turn-slip indicator 2.Turn Coordinator 4.Attitude indicator 5.Heading Indicator 6.Hubble Telescope

Gyroscopic Principle
• Several flight instruments utilize the properties of a gyroscope for their operation. • The most common instruments containing gyroscopes are •the turn coordinator, heading indicator, and the attitude indicator. • Any spinning object exhibits gyroscopic properties. • A wheel or rotor designed and mounted to utilize these properties is called a gyroscope. • Two important design characteristics of an instrument gyro • are great weight for its size, or high density, • and rotation at high speed with low friction bearings. • There are twogeneral types of mountings; (the type used depends upon which property of the gyro is utilized) • A freely or universally mounted gyroscope is free to rotate in any direction about its center of gravity. Such a wheel is said to have three planes of freedom. • Restricted or semi-rigidly mounted gyroscopes are those mounted so that one of the planes of freedom is held fixed in relation to the base.There are two fundamental properties of gyroscopic action: rigidity in space and precession. Rigidity in Space Rigidity in space refers to the principle that a gyroscope remains in a fixed position in the plane in which it is spinning. Precession Precession is the tilting or turning of a gyro in response to a deflective force. The reaction to this force does not occur at the point at which it wasapplied; rather, it occurs at a point that is 90° later in the direction of rotation

Sources of Power
• In some aircraft, all the gyros are vacuum, pressure, or electrically operated. • The vacuum or pressure system spins the gyro by drawing a stream of air against the rotor vanes to spin the rotor at high speed, much like the operation of a waterwheel or turbine. • The amount of vacuum orpressure required for instrument operation varies, but is usually between 4.5 "Hg and 5.5 "Hg. • A typical vacuum system consists of an • Engine-driven vacuum pump • Relief valve • Air filter • Gauge • and tubing necessary to complete the connections. • The gauge is mounted in the aircraft’s instrument panel and indicates the amount of pressure in the system (vacuum is measured in inches of mercuryless than ambient pressure).

1- Air is drawn into the vacuum system by the engine-driven vacuum pump. 2- It first goes through a filter, which prevents foreign matter from entering the vacuum or pressure system. 3- The air then moves through the attitude and heading indicators, where it causes the gyros to spin. 4- A relief valve prevents the vacuum pressure, or suction, from exceedingprescribed limits. 5-After that, the air is expelled overboard or used in other systems, such as for inflating pneumatic deicing boots. • It is important to monitor vacuum pressure during flight, because the attitude and heading indicators may not provide reliable information when suction pressure is low. • When the vacuum pressure drops below the normal operating range, the gyroscopic instruments maybecome unstable and inaccurate

Turn Indicators
Turn-and-Slip Indicator • The gyro in the turn-and-slip indicator rotates in the vertical plane, corresponding to the aircraft’s longitudinal axis. • A single gimbal limits the planes in which the gyro can tilt, and a spring tries to return it to center. • Because of precession, a yawing force causes the gyro to tilt left or right, as viewed fromthe pilot seat. • The turn-and-slip indicator uses a pointer, called the turn needle, to show the direction and rate of turn. • When extreme forces are applied to a gyro, the gyro is displaced from its normal plane of rotation, rendering its indications invalid. Certain instruments have specific pitch and bank limits that induce a tumble of the gyro.

Turn Coordinator • The gimbal in the turn...