Question 64-1 : To obtain the instantaneous speed from the accelerations it is necessary to 1 integrate once the acceleration in time2 know the initial position 3 know the initial speedthe combination that regroups all of the correct statements is ? [ Control visibility ]

Question 64-2 : In an inertial navigation system the principle used to obtain position is 1 single integration of acceleration according to time2 double integration of acceleration according to time3 single integration of speed according to time4 double integration of speed according to timethe combination that ?

2 or 3.

Question 64-3 : Considering a strapdown inertial system the operating principle requires the use of at least ?

3 laser gyros and 3 accelerometers.

Question 64-4 : Compared with a stabilised platform inertial system a strapdown inertial system 1 has a longer alignment phase in time2 has a shorter alignment phase in time3 is more reliable in time4 is less reliable in timethe combination that regroups all of the correct statements is ?

2 3.

Question 64-5 : A strapdown inertial system consists in ?

Question 64-6 : In an inertial navigation system integrating once the speed in gives ?

A distance travelled.

Question 64-7 : An inertial navigation system ins is ?

Question 64-8 : A ring laser gyro can measure ?

Rotation about its sensitive axis.

The ring laser gyro is a rate sensing gyro and senses the rate of rotation around its axis

Question 64-9 : The data that needs to be inserted into an inertial reference system in order to enable the system to make a successful alignment for navigation is ?

Aircraft position in latitude and longitude or airport icao identifier.

Question 64-10 : The alignment phase of a gyro stabilized platform consists in ?

Levelling the platform and determining its orientation.

The alignment phase consists of getting the platform into the local horizontal and determining its alignment with respect to true north

Question 64-11 : A laser gyro can measure ?

A rotation motion.

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

Question 64-12 : A ring laser gyro is ?

A device which measures angular movements.

The ring laser gyro is a rate sensing gyro and senses the rate of rotation around its axis

Question 64-13 : Considering a strapdown inertial system the iru inertial reference unit measures ?

Accelerations and angular rates.

The irs measures both angular and linear accelerations

Question 64-14 : The alignment time of a strapdown inertial system takes longer time when the aircraft is ?

At a high latitude.

Question 64-15 : An inertial navigation system ?

Can operate as stand alone equipment without any interface with other navigation equipments.

Question 64-16 : In an inertial navigation system the principle used to obtain the change in speed is ?

Single integration of acceleration according to time.

Question 64-17 : The characteristics of the earth which are being used during the alignment of an ins platform are ?

Earth rotation and gravity.

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 ie in the local horizontalthe 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

Question 64-18 : In a strapdown inertial system the accelerations are measured in a trihedron which is fixed regarding to the ?

Aircraft's trihedron pitch roll and yaw axis .

Question 64-19 : In a stabilised platform inertial system the accelerations are measured in a trihedron which is nb 'aircraft trihedron' = pitch roll and yaw axis ?

Free from the aircraft trihedron.

Question 64-20 : On the ins control panel the rotary knob can be selected to off nav or att positions the correct statement is ?

Nav is the normal system setting the att position is the back up position in case of failure of the navigation function.

Question 64-21 : The position data lat long computed by an irs can be used by the ?

Fms.

Question 64-22 : The accuracy of the altitude computed by a stand alone inertial system ?

Decreases exponentially with flight time.

Some irs use baro altitude to stabilise the inertial reference height and use mixed baroir for vertical rate the irs altitude calculation is not an output of the irs

Question 64-23 : The output data of an irs include 1 present position lat long 2 tas3 attitude4 ground speedthe combination regrouping all the correct statements is ?

1 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

Question 64-24 : The drift of the gyroscopes of a stand alone inertial system ?

Is the main error source.

Question 64-25 : Considering a stabilised platform inertial system this platform 1 can be servo controlled in azimuth2 is kept levelled during alignment phase only3 is always kept levelledthe combination that regroups all of the correct statements is ?

1 3.

Question 64-26 : Comparing the radio navigation system and the inertial navigation system 1 the radio position is accurate when in dme range2 the radio position may be obtained whatever the position on the earth3 the inertial position may be obtained whatever the position on the earththe combination regrouping ?

1 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 accurateradio navigation system = vor adf or rmiradio position = vor or adf or rmi bearing + dme distancewith a dme distance your position is accurate

Question 64-27 : An inertial reference and navigation system is a 'strapdown' system when ?

The gyroscopes and the accelerometers are fixed regarding to the aircraft's body axes co ordinate system.

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

Question 64-28 : If the navigation function of an ins is inoperative and the control rotary switch is set to att the output data of the ins is are ?

Attitude and heading.

Question 64-29 : The alignment of a strapdown inertial system consists in ?

Measuring the earth rotation and local gravitation to position the reference trihedron.

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

Question 64-30 : The position error of a stand alone inertial system ?

Increases along the time.

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 sourcesthe increase in position error over each hour is increasing linearly or as time increases the error increases by the same amount over each hour

Question 64-31 : The position error of a stand alone inertial system is ?

Small a few minutes after initialisation and increases along the flight.

Question 64-32 : The output data of an irs include 1 present position lat long 2 altitude3 ground speed4 true headingthe combination regouping all the correct statements is ?

1 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

Question 64-33 : The attitude data computed by an irs can be used by the ?

Auto pilot system.

Question 64-34 : If the position data lat long is no longer computed an irs the affected system s is are ?

The fms.

Question 64-35 : The energy required to operate a strapdown inertial system is supplied by ?

The electrical system.

Question 64-36 : When the rotary knob on the ins control panel is set to 'nav' mode it is ?

The normal operating mode allowing use of all the functions of the system.

Question 64-37 : The alignment of a gyro stabilized inertial platform consists in positionning the platform relative to ?

The vertical axis and true north.

Question 64-38 : In an inertial navigation system a tas input ?

Required to provide a wind direction and velocity read out.

Revised ecqb04 october 2017this 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 iasmach numberaltitude and oat'

Question 64-39 : The platform of an inertial navigation system ins is maintained at right angles to the local vertical by applying corrections for the effects of ?

Aircraft manoeuvres earth rotation transport wander and coriolis.

Question 64-40 : In an inertial navigation system ins ground speed gs is calculated ?

By integrating measured acceleration.

The starting point for an inertial reference system is accelerationin order to sense linear acceleration the inertial system uses mechanical inertial accelerometersso if acceleration is known then speed can be calculated and if speed is known then distance can be calculatedthe mathematical process that reduces acceleration to speed and speed to distance is called integration