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Program > pilot : The alignment phase of a gyro stabilized platform consists in ?

Question 50-1 : Levelling the platform and determining its orientation aligning the platform axis with the aircraft axis pitch roll yaw aligning the platform axis with the aircraft pitch axis only aligning the platform axis with the aircraft roll axis only

.the alignment phase consists of getting the platform into the local horizontal and determining its alignment with respect to true north exemple 150 levelling the platform and determining its orientation.levelling the platform and determining its orientation.

A laser gyro can measure ?

Question 50-2 : A rotation motion an acceleration an acceleration and a rotation motion an acceleration and a speed

.the ring laser gyro is a rate sensing gyro and senses the rate of rotation around its axis the principle of a laser gyro is based on frequency difference between two laser beams rotating in opposite direction two light beams travelling a different distance in the same time because of rotation of the device rate of rotation is proportional to phase difference exemple 154 a rotation motion.a rotation motion.

A ring laser gyro is ?

Question 50-3 : A device which measures angular movements an optical accelerometers used for stabilising the ins platform a device which measures the earth rate precession

The ring laser gyro is a rate sensing gyro and senses the rate of rotation around its axis exemple 158 a device which measures angular movements.a device which measures angular movements.

Considering a strapdown inertial system the iru inertial reference unit measures ?

Question 50-4 : Accelerations and angular rates angular accelerations only angular rates only linear accelerations only

.the irs measures both angular and linear accelerations exemple 162 accelerations and angular rates.accelerations and angular rates.

The alignment time of a strapdown inertial system takes longer time when the ?

Question 50-5 : At a high latitude at a high longitude close to the equator at a location where the magnetic variation is greater than 15 degrees

exemple 166 at a high latitude.at a high latitude.

An inertial navigation system ?

Question 50-6 : Can operate as stand alone equipment without any interface with other navigation equipments can only operate when interfacing with the gps equipment can only operate when interfacing with the radionavigation equipments can only operate when communicating with ground installations

exemple 170 can operate as stand alone equipment without any interface with other navigation equipments.can operate as stand alone equipment without any interface with other navigation equipments.

In an inertial navigation system the principle used to obtain the change in ?

Question 50-7 : Single integration of acceleration according to time double integration of acceleration according to time single integration of position according to time double integration of position according to time

exemple 174 single integration of acceleration according to time.single integration of acceleration according to time.

The characteristics of the earth which are being used during the alignment of ?

Question 50-8 : Earth rotation and gravity earth magnetic field and earth rotation longitude and gravity earth rotation and longitude

.while the aircraft is stationary during the align mode gravity defines the local vertical and the gyro stabilised platform is placed perpendicular to the vertical i e in the local horizontal .the north and east gyros are used to define the direction in which the earth is rotating east in order to define the platform's alignment relative to true north exemple 178 earth rotation and gravity.earth rotation and gravity.

In a strapdown inertial system the accelerations are measured in a trihedron ?

Question 50-9 : Aircraft's trihedron pitch roll and yaw axis earth's trihedron longitude latitude absolute space earth's trihedron x y z

In a stabilised platform inertial system the accelerations are measured in a ?

Question 50-10 : Free from the aircraft trihedron fixed in absolute space merged with the aircraft's triehedron merged with only two axis of the aircraft trihedron the roll axis and the pitch axis

exemple 186 free from the aircraft trihedron.free from the aircraft trihedron.

On the ins control panel the rotary knob can be selected to off nav or att ?

Question 50-11 : Nav is the normal system setting the att position is the back up position in case of failure of the navigation function nav is the normal system setting the off position is the back up position in case of failure of the navigation function att is the normal system setting att is the normal system setting the nav position inhibits the attitude data

The position data lat long computed by an irs can be used by the ?

Question 50-12 : Fms ils receiver adc tcas

exemple 194 fms.fms.

The accuracy of the altitude computed by a stand alone inertial system ?

Question 50-13 : Decreases exponentially with flight time is bounded decreases proportionally with flight time is poor at the beginning of the flight

.some irs use baro altitude to stabilise the inertial reference height and use mixed baro/ir for vertical rate the irs altitude calculation is not an output of the irs exemple 198 decreases exponentially with flight time.decreases exponentially with flight time.

The output data of an irs include .1 present position lat long .2 tas.3 ?

Question 50-14 : 1 3 4 1 2 3 1 2 4 2 3 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 202 1, 3, 4.1, 3, 4.

The drift of the gyroscopes of a stand alone inertial system ?

Question 50-15 : Is the main error source is not an error source induces a position error that decreases along the flight induces a bounded position error

exemple 206 is the main error source.is the main error source.

Considering a stabilised platform inertial system this platform.1 can be servo ?

Question 50-16 : 1 3 1 2 2 3

exemple 210 1, 3.1, 3.

Comparing the radio navigation system and the inertial navigation system .1 ?

Question 50-17 : 1 3 1 2 2 3

Pywee22 .i don't understand the answer about the dme if you are in dme range you will know your distance from the dme but you won't be able to get an accurate position from it because you can be anywhere around the dme you can be accurate if you have a dme distance and a radial from a ground station the choice n°1 says that you are in range of a dme and that's all so your position cannot be accurate ..radio navigation system = vor adf or rmi .radio position = vor or adf or rmi bearing + dme distance.with a dme distance your position is accurate exemple 214 1, 3.1, 3.

An inertial reference and navigation system is a 'strapdown' system when ?

Question 50-18 : The gyroscopes and the accelerometers are fixed regarding to the aircraft's body axes co ordinate system only the gyroscopes and not the accelerometers are fixed regarding to the aircraft's body axes co ordinate system the gyroscope and the accelerometers are mounted on a stabilised patform only the gyroscopes and not the accelerometers are mounted on a stabilised platform

Easa update august 2012 old answers was . the gyroscopes and accelerometers are part of the unit's fixture to the aircraft structure right answer . only the gyros and not the accelerometers are part of the unit's fixture to the aircraft structure . gyros and accelerometers are mounted on a stabilised platform in the aircraft . gyros and accelerometers need satellite information input to obtain a vertical reference exemple 218 the gyroscopes and the accelerometers are fixed regarding to the aircraft's body axes co-ordinate system.the gyroscopes and the accelerometers are fixed regarding to the aircraft's body axes co-ordinate system.

If the navigation function of an ins is inoperative and the control rotary ?

Question 50-19 : Attitude and heading position only position and attitude attitude and ground speed

exemple 222 attitude and heading.attitude and heading.

The alignment of a strapdown inertial system consists in ?

Question 50-20 : Measuring the earth rotation and local gravitation to position the reference trihedron positionning the accelerometers positioning the gyroscopes and accelerometers relative to the fuselage axis positioning the platform relative to the local vertical and true north

.on an strapdown system the irs is fixed to the aircraft so the aligment consists in measuring the earth rotation and local gravitation to position the reference trihedron exemple 226 measuring the earth rotation and local gravitation to position the reference trihedron.measuring the earth rotation and local gravitation to position the reference trihedron.

The position error of a stand alone inertial system ?

Question 50-21 : Increases along the time remains constant is sinusoidal increases up to 2 nm due to the drift error of the gyroscopes then stabilizes

.inertial navigation system ins is one of the oldest and simplest forms of navigation systems although simple ins is prone to accumulating errors over time ins systems are based on dead reckoning techniques dead reckoning techniques use an initial known point of origin and then record measurements of acceleration or velocity over time to obtain resultant position using integration acceleration in three dimensions is measured using triaxes accelerometers whose accuracy can be heavily degraded because of different error sources .the increase in position error over each hour is increasing linearly or as time increases the error increases by the same amount over each hour exemple 230 increases along the time.increases along the time.

The position error of a stand alone inertial system is ?

Question 50-22 : Small a few minutes after initialisation and increases along the flight small and constant along the flight large a few minutes after initialisation and reduces along the flight constant along the flight with an accuracy depending on the accuracy of the accelerometers

exemple 234 small a few minutes after initialisation and increases along the flight.small a few minutes after initialisation and increases along the flight.

The output data of an irs include.1 present position lat long .2 altitude.3 ?

Question 50-23 : 1 3 4 1 2 3 1 4 1 2 3 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 238 1, 3, 4.1, 3, 4.

The attitude data computed by an irs can be used by the ?

Question 50-24 : Auto pilot system tcas gpws stall warning system

If the position data lat long is no longer computed an irs the affected system ?

Question 50-25 : The fms the adc and the tcas the fms and the tcas the tcas

exemple 246 the fms.the fms.

The energy required to operate a strapdown inertial system is supplied by ?

Question 50-26 : The electrical system the bleed air system the hydraulic system a dedicated pneumatic system

exemple 250 the electrical system.the electrical system.

When the rotary knob on the ins control panel is set to 'nav' mode it is ?

Question 50-27 : The normal operating mode allowing use of all the functions of the system the navigation mode allowing use of all the functions of the system except attitude the alignment function in flight the navigation mode allowing use of all the functions of the system except heading

exemple 254 the normal operating mode allowing use of all the functions of the system.the normal operating mode allowing use of all the functions of the system.

The alignment of a gyro stabilized inertial platform consists in positionning ?

Question 50-28 : The vertical axis and true north the pitch axis only the pitch and roll axis the roll axis only

exemple 258 the vertical axis and true north.the vertical axis and true north.

In an inertial navigation system a tas input ?

Question 50-29 : Required to provide a wind direction and velocity read out not required required for polar navigation required for the automatic flight control system afcs to compute a heading according to track

Revised ecqb04 october 2017..this question exists with the following statement .'what additional information is required to be input to an inertial navigation system ins in order to obtain a wind information readout . tas .ias .mach number .altitude and oat' exemple 262 required to provide a wind direction and velocity read out.required to provide a wind direction and velocity read out.

The platform of an inertial navigation system ins is maintained at right angles ?

Question 50-30 : Aircraft manoeuvres earth rotation transport wander and coriolis gyroscopic inertia earth rotation and real drift vertical velocities earth precession centrifugal forces and transport drift movement in the yawing plane secondary precession and pendulous oscillation

exemple 266 aircraft manoeuvres, earth rotation, transport wander and coriolis.aircraft manoeuvres, earth rotation, transport wander and coriolis.

In an inertial navigation system ins ground speed gs is calculated ?

Question 50-31 : By integrating measured acceleration from tas and w/v from air data computer adc from tas and w/v from rnav data by integrating gyro precession in n/s and e/w directions respectively

.the starting point for an inertial reference system is acceleration .in order to sense linear acceleration the inertial system uses mechanical inertial accelerometers .so if acceleration is known then speed can be calculated and if speed is known then distance can be calculated .the mathematical process that reduces acceleration to speed and speed to distance is called integration exemple 270 by integrating measured acceleration.by integrating measured acceleration.

During the initial alignment of an inertial navigation system ins the equipment ?

Question 50-32 : Will not accept a 10° error in initial latitude but will accept a 10° error in initial longitude will accept a 10° error in initial latitude but will not accept a 10° error in initial longitude will not accept a 10° error in initial latitude or initial longitude will accept a 10° error in initial latitude and initial longitude

.when align is selected the operator must enter the aircraft's position to the nearest tenth of a minute of latitude and longitude the latitude entered is used to check the alignment of the platform by checking the topple of the north and east gyros due to earth rotation earth rate against the latitude if the latitude is entered correctly but the longitude is entered in error the platform will get itself levelled and aligned and indicate that nav can be selected but its plot of aircraft position will be starting from the wrong place error in longitude exemple 274 will not accept a 10° error in initial latitude but will accept a 10° error in initial longitude.will not accept a 10° error in initial latitude but will accept a 10° error in initial longitude.

The average value for the position error of the ins inertial navigation systems ?

Question 50-33 : 0 5 to 2 nm/h 2 to 5 nm/h 10 to 12 nm/h 6 to 8 nm/h

exemple 278 0.5 to 2 nm/h.0.5 to 2 nm/h.

The output data of an irs are .1 true track.2 mach number.3 present position ?

Question 50-34 : 1 3 4 5 3 2 5 1 2 3 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids such as satellite the adc air data computer will compute the mach number exemple 282 1, 3, 4, 5.1, 3, 4, 5.

After alignment of the stable platform of an inertial navigation system ins ?

Question 50-35 : Acceleration north/south and east/west true heading and attitude latitude longitude and attitude acceleration north/south and east/west and true heading latitude longitude and true heading

exemple 286 acceleration north/south and east/west, true heading and attitude.acceleration north/south and east/west, true heading and attitude.

In an inertial reference system accelerations are measured in relation to ?

Question 50-36 : Aircraft axis wgs84 earth coordinates the direction of true north local vertical at the aircraft position

.an irs system strapdown system consists in a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers .the accelerations are measured in a trihedron which is fixed regarding to the aircraft's trihedron pitch roll and yaw axis exemple 290 aircraft axis.aircraft axis.

The full alignment of the stable platform of an inertial navigation system ins ?

Question 50-37 : Is only possible on the ground when the aircraft is at a complete stop may be carried out on the ground or when in straight and level flight may be carried out at any time so long as an accurate position is inserted into the system may be carried out during any phase of flight

.while the aircraft is stationary during the align mode gravity defines the local vertical and the gyro stabilised platform is placed perpendicular to the vertical i e in the local horizontal the north and east gyros are used to define the direction in which the earth is rotating east in order to define the platform's alignment relative to true north it is only possible on the ground when the aircraft is at a complete stop exemple 294 is only possible on the ground when the aircraft is at a complete stop.is only possible on the ground when the aircraft is at a complete stop.

Which of the following statements concerning the aircraft positions indicated ?

Question 50-38 : The positions are likely to differ because they are calculated from different sources the positions will only differ if one of the systems has been decoupled because of a detected malfunction the positions will only differ if an error has been made when inputting the present position at the departure airport the positions will be the same because they are an average of three different positions

.all the ins/irs in an aircraft are independent the positions for each irs/ins will be slightly different exemple 298 the positions are likely to differ because they are calculated from different sources.the positions are likely to differ because they are calculated from different sources.

A pilot accidentally turning off the irs in flight and then turns it back on a ?

Question 50-39 : It can only be used for attitude reference everything returns to normal and is usable the irs is usable in nav mode after a position update no useful information can be obtained from the irs

exemple 302 it can only be used for attitude reference.it can only be used for attitude reference.

Concerning the operation of an ins/irs the nav mode must be selected ?

Question 50-40 : Prior to movement of the aircraft off the gate when the alignment procedure is commenced on the runway just prior to take off prior to the loading of passengers and/or freight

exemple 306 prior to movement of the aircraft off the gate.prior to movement of the aircraft off the gate.

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