Instrumentation: Air Data and Gyros
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Flashcards
What action should be taken with a Gyro Magnetic compass if the synchronising unit appears to be unserviceable in flight?
Select 'Free' or 'DG' and use the compass in the gyro mode
The "sensor part" of the flux-valve is:
The turning errors of the direct reading compass, when relating to the Northern Hemisphere will ...
The primary physical property that a flux valve uses is:
A pilot wishes to turn right on to a southerly heading with 20° BANK at a latitude of 20° North. Using a direct reading compass, in order to achieve this he must stop the turn on an approximate heading of :
An aircraft is on the take-off run on a runway heading of 045° in the southern hemisphere. Compass deviation is zero and the airfield on the agonic line. What will be the indications on a direct reading compass?
A gyromagnetic compass or heading reference unit is an assembly which always consists of :
1. A directional gyro
2. A vertical axis gyro
3. An earth's magnetic field detector
4. A pitch control
5. A synchronising control
The correct combination is:
1, 3 and 5
In a turn from 045° to 315° through North, in the Southern Hemisphere, the movement of the magnet system of a direct reading compass, when VIEWED from above, and the effect of liquid swirl caused by the movement, are:
The main components of the gyromagnetic compass are:
1. flux valve,
2. magnetic compass,
3. error detector (selsyn),
4. amplifier,
5. gyro unit,
6. heading indicator
1 3 4 5 6
The errors of the gyromagnetic compass systems are in principle the same as the errors of its two heading sensors, the flux valve and the directional gyro, but:
A factor giving a large error on a direct indicating compass would be
Gyro: Space Tied Platform
teh platform is kept horizontal if only a short time of platform control is considered => not considered for longer flight takes
Gyro: Earth Tied Platform
Parallel to the idealized surface of the earth => Schuler tuning is responsible to keep it parallel to the idealized surface of the earth
Gyro: Which type pf platform is suitable for aircraft pruposes, which is not suitable (earth tied/ spaced tied)
A platform (INS/IRS) for aircraft purposes has to be earth tied A space tied platform system is necessary for vehicles which operates in space
Gyro: How is an AHRS stabilized relative to earth if compared with an INS/IRS?
An AHRS is stabilized to the earth by means of gyros, liquid level switches or accelerometers and a computer. => Output signal of the liquid level is connected to the torquer The Schuler tuning which stabilizes and controls INS/IRS is not suitable for AHR
Gyro: What is the task of an AHRS cutout system?
The task of the AHRS cutout system is to switch off the erection system in case of too high accelerations/decelerations and during turns to avoid large errors
Gyro: Compare teh accuracy of an AHRSwith the accuracy of an INS/IRS?
the accuracy of an INS/IRS is significant higher if compared with an AHRS
Gyro: How is it possible to improve teh accuracy of an AHRS by means of an angular speed computer?
The more inputs from different sources the AHRS receives, the better are the results. Therefore its accuracy increases with the use on an angular speed computer
Gyro: In case an INS/IRS is equipped with TDF gyros. How many of these TDF gyros have to be use at least?
If TDF gyros are used, 2 of them have to be in use at least
Gyro: In case an INS/IRS is equipped with SDF gyros. How many of these SDF gyros have to be use at least?
If SDF gyros are used, 3 of them have to be in use at least
Gyro: Why is it not possible to equip and to operate an INS with two TDF gyros when their spin axis orientation would be vertical?
Because if two TDF gyros with a vertical spin axis were in use, they would measure the same two axes, and the third axis is not taken into account
Gyro: What important technical criterion has to be taken into account when an INS would be equipped with two TDF gyros with their spinning axis parallel to the surface of the earth like a DG
If two TDF gyros with their spinning axis parallel to the surface of the earth like a DG, their axes have to perpendicular to each other
What is known as the "Schuler Period" has a length of...
The accelerometers in an Inertial Navigation SYSTEM (INS) are mounted on a platform that is..
In an Inertial Navigation SYSTEM (INS), the main causes of Cumulative Distance errors are:
In order to align an inertial navigation SYSTEM (INS), it is required to insert the local geographical coordinates. This enables the INS to:
The mathematical tool used in the fundamental inertial navigation principle is (all of them will be used in the computer, but only one refers to the fundamental principle):
Coarse levelling of a gimballed Inertial Navigation SYSTEM (INS) is carried out by:
In a Stable INS (Inertial Navigation SYSTEMS) platform the second stage of integration of the output from the E - W accelerometer
Stabilisation of a gyro platform about the vertical (azimuth) axis, is given by a:
The selections available on an INS (Inertial Naviagation Systems) Mode Select UNIT are, in order:
In a north aligned INS (Inertial Navigation SYSTEMS), the East gyro can drive:
As a RESULT of the failure of the central air data computer (CADC), the inertial navigation system (INS) will no longer provide information about:
The INS POSITION will, when not corrected by other navigation systems, have a position error, that:
In order to keep the vertical line with a pendulous SYSTEM, while an inertial platform system (INS) is operating on board an aircraft, it is necessary to use control loops with the following characteristics:
Schuler loop oscillations of a stable INS (Inertial navigation SYSTEMS) platform that was not quite level will cause:
How is is a position CALCULATED in a strapdown system?
Compared with a traditional platform SYSTEM, a strapdown system:
Compared with a conventional gyro, a laser gyro:
The primary source of ERRORS in a ring laser gyro is due to:
