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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 drift.

the time (TIME) at the next waypoint (WPT).

the ground speed.

relative motion of the gimbals

the drift.

the time (TIME) at the next waypoint (WPT).

the ground speed.

relative motion of the gimbals

The INS POSITION will, when not corrected by other navigation systems, have a position error, that:

on the average increases with 1.5 NM per hour.

will oscillate around a constant value.

increases linearly with 0.5 NM per hour.

on the average increases with 1.5 NM per hour.

will oscillate around a constant value.

increases linearly with 0.5 NM per hour.

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:

no damping and a period of about 84 minutes.

damping and a period of about 84 minutes

no damping and a period of about 84 minutes.

damping and a period of about 84 minutes

Schuler loop oscillations of a stable INS (Inertial navigation SYSTEMS) platform that was not quite level will cause:

A bounded velocity error and an unbounded distance error

Unbounded errors

Bounded (bestimmte) errors

Oscillatory errors of random and irregular duration

A bounded velocity error and an unbounded distance error

Unbounded errors

Bounded (bestimmte) errors

Oscillatory errors of random and irregular duration

How is is a position CALCULATED in a strapdown system?

Accelerations are measured in an aircraft axis sytem, transformed into an earth referenced axis system by using the attitude information from the RLG's and then integrated two times to yield a position.

Accelerations measured by the accelerometers are integrated one time to yield a velocity in an aircraft axis system, which is transformed into a groundspeed in an earth referenced axis system, which is integrated to yield the position.

Accelerations measured by the accelerometers are integrated two times to yield a distance in an aircraft axis system, that is transformed by using the attitude data from the RLG's into a position in an earth referenced axis system

Accelerations measured by the accelerometers are integrated two times to yield a position.

Accelerations are measured in an aircraft axis sytem, transformed into an earth referenced axis system by using the attitude information from the RLG's and then integrated two times to yield a position.

Accelerations measured by the accelerometers are integrated one time to yield a velocity in an aircraft axis system, which is transformed into a groundspeed in an earth referenced axis system, which is integrated to yield the position.

Accelerations measured by the accelerometers are integrated two times to yield a distance in an aircraft axis system, that is transformed by using the attitude data from the RLG's into a position in an earth referenced axis system

Accelerations measured by the accelerometers are integrated two times to yield a position.

Compared with a traditional platform SYSTEM, a strapdown system:

has a comparable accuracy.

has more moving parts.

is more expensive to maintain.

is more sensitive to handling damage.

has a comparable accuracy.

has more moving parts.

is more expensive to maintain.

is more sensitive to handling damage.

Compared with a conventional gyro, a laser gyro:

has lower maintenance cost.

has a fairly long starting cycle

is influenced by temperature

consumes a lot of power

has lower maintenance cost.

has a fairly long starting cycle

is influenced by temperature

consumes a lot of power

The primary source of ERRORS in a ring laser gyro is due to:

Imperfections in the mirrors

Wander of the dither motor

Fringe pattern measurement

Poor adjustment of the servo motor

Imperfections in the mirrors

Wander of the dither motor

Fringe pattern measurement

Poor adjustment of the servo motor

Alignment of a strapdown inertial system does not START with a 'standby' mode as a platform system does, because:

the gyro's need no time to warm-up and speed up

the accelerometers need not to be 'nulled'.

absence of a platform means no erection time.

the digital computers of the strapdown system are of a later generation and therefore faster.

the gyro's need no time to warm-up and speed up

the accelerometers need not to be 'nulled'.

absence of a platform means no erection time.

the digital computers of the strapdown system are of a later generation and therefore faster.

The reason for gently vibrating (dithering) the Ring Laser Gyro (RLG) is...

because one laser-beam can "lock-in" to the other at low rates of rotation.

because one laser-beam can "lock-in" to the other at high rates of rotation.

because one laser-beam can "lock-in" to the other at low rates of rotation.

because one laser-beam can "lock-in" to the other at high rates of rotation.

How long does alignment of an IRS (Laser Gyro) typically take at mid-latitudes?

10 min

2 min

20 min

30 min

10 min

2 min

20 min

30 min

Which statement below is true when comparing a Ring Laser Gyro (RLG) to a Fibre Optic Gyro (FOG)?

The FOG is lighter, cheaper, but has more instrument error.

The FOG is lighter, cheaper, and has less instrument error.

The RLG and FOG are quite similar in most respects.

The fibre optics make the FOG more rugged.

The FOG is lighter, cheaper, but has more instrument error.

The FOG is lighter, cheaper, and has less instrument error.

The RLG and FOG are quite similar in most respects.

The fibre optics make the FOG more rugged.

In an Inertial Reference SYSTEM (IRS), how are the major components mounted?

Gyros and accelerometers are fixed to the aircraft structure

Gyros and accelerometers are fixed on a stable platform.

Gyros are fixed to a stable platform and accelerometers are 'strapped-down'.

Gyros are 'strapped-down' and accelerometers are fixed relative to North, East and vertical position of the aircraft.

Gyros and accelerometers are fixed to the aircraft structure

Gyros and accelerometers are fixed on a stable platform.

Gyros are fixed to a stable platform and accelerometers are 'strapped-down'.

Gyros are 'strapped-down' and accelerometers are fixed relative to North, East and vertical position of the aircraft.

Strapdown SYSTEMS:

show Schuler oscillations, like platform systems.

measure the aircraft's magnetic heading.

have the same type of gyroscopes as platform systems.

can navigate without accelrometers.

show Schuler oscillations, like platform systems.

measure the aircraft's magnetic heading.

have the same type of gyroscopes as platform systems.

can navigate without accelrometers.

A triangular ring laser gyro EMPLOYS:

2 lasers, 2 fully silvered mirrors and a partially silvered mirror

1 laser, 1 fully silvered mirror and 2 partially silvered mirrors

2 lasers, 1 fully silvered mirror and 2 partially silvered mirrors

1 laser, 2 fully silvered mirrors and a partially silvered mirror

2 lasers, 2 fully silvered mirrors and a partially silvered mirror

1 laser, 1 fully silvered mirror and 2 partially silvered mirrors

2 lasers, 1 fully silvered mirror and 2 partially silvered mirrors

1 laser, 2 fully silvered mirrors and a partially silvered mirror

INS: current platforms no longer use a flux valves, but are equipped with what?

they are equipped with a variation memory where all variations worldwide are stored in a microchip, => The INS computer receives true north reference from the INS platform, can calculate the MN direction by using the variation of the variation memory

INS: How you can determine the wind vector with the INS system?

Input from the Air data computer to the INS is the TAS. compares TAS with the GS results in the wind vector, with direction and strength

INS: Max. allowed position error of the INS is?

position error of an INS is 1.5 NM/h

INS: Which type of platform is sometimes called ,,Ghost Platform"?

The strap down system is sometimes called Ghost Platform due to the fact that it operates without any gimbal or torquer

INS: How is it possible to improve the accuracy of teh measured position of teh aircraft relative to the earth significanly?

The accuracy of the calculated position of the aircraft relative to the earth increased significantly by additional use of GPS, DME and VOR signals

Temperature Definition

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air Temperature is the kinetic energy of air molecules

Wie heisst künstlicher Horizont beim Airbus

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EFIS

Wie heisst der Bildschirm bei Airbus, wo die Informationen über die Systeme drauf sind?

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ECAM

Parallax Whats that?

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Ein Bild sieht anders aus, wenn ich es von verschiedenen Seiten/Winkeln her betrachte ==> Im Airbus darf man den weissen Punkt nicht sehen => Dann sitzt man richtig

WIe kann man die Parallaxe verhindern?

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2x Mal das gleiche Instrument einbauen, gerade davor sitzen, Zeiger auf das Zifferblatt, Digital, Instrument etwas zum Piloten hin abwinkeln

2 Instruments Arrangement

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1. Air Data Instruments: Airspeed, Vertical Speed Indicator, Barometric Altimeters 2.Gyro Instruments: Horizont, Pitch, Kompass

Air pressure

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p = F/A (Pa)

Density

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Measure of mass per volume p= m/ V

Since water is the ightest molecule in an air parcel, humid air is

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less dense than dry air

Ideal flow is:

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1. Frictionless 2. Incompressible 2. Steady

Bernoulli says

that the total energy of a flow remains constant along a streamline

Dynamischer Druck

\(q = {1 \over 2} * v^2 * p \)

ISA

Standart ATmosphere is an atmospheric model of how the pressure, temperature, density and viscosity of the Earth's atmosphere change over a wide range of altitudes