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Considering an air driven artificial horizon when an airplane decelerates on ground during the landing the result is ?

Quiz > landing

exemple reponse 154
A false nose down indication. errors in the artificial horizon (suction) acceleration errors (linear acceleration) these errors are also known as 'takeoff' errors as they are most noticeable during takeoff two elements cause errors pendulous unit vanes error from the pendulous unit the pendulous unit makes rotor bottom heavy as aircraft accelerates a force from inertia of unit felt at bottom the unit tends to lag behind it tends to swing bottom of gyro towards pilot air driven rotors spin anti clockwise (when viewed from above) so this inertial force will precess through 90° in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates anti clockwise and bank indicates a false right bank error from exhaust vanes during acceleration vanes on right left sides are thrown rearward the result that right hand port more than half open the left side port more than half closed this upsets balanced exhaust of air more air being discharged from right side than from left side the reaction occurs on left side precesses through 90° and lifts up inner gimbal from point nearest pilot to indicate a false climb thus with gyro running anti clockwise a slight indication of right bank climb are obtained during an acceleration.

Other study patent: Telepilote theorique examen 49

Concerning the directional gyro the apparent drift rate due to the earth's rotation is a function of ?

exemple reponse 155
Concerning directional gyro apparent drift rate due to earth's rotation a function of A false nose down indication. errors in the artificial horizon (suction) acceleration errors (linear acceleration) these errors are also known as 'takeoff' errors as they are most noticeable during takeoff two elements cause errors pendulous unit vanes error from the pendulous unit the pendulous unit makes rotor bottom heavy as aircraft accelerates a force from inertia of unit felt at bottom the unit tends to lag behind it tends to swing bottom of gyro towards pilot air driven rotors spin anti clockwise (when viewed from above) so this inertial force will precess through 90° in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates anti clockwise and bank indicates a false right bank error from exhaust vanes during acceleration vanes on right left sides are thrown rearward the result that right hand port more than half open the left side port more than half closed this upsets balanced exhaust of air more air being discharged from right side than from left side the reaction occurs on left side precesses through 90° and lifts up inner gimbal from point nearest pilot to indicate a false climb thus with gyro running anti clockwise a slight indication of right bank climb are obtained during an acceleration.

The spin axis of the turn indicator gyroscope is parallel to the ?

exemple reponse 156
The spin axis of turn indicator gyroscope parallel to A false nose down indication. errors in the artificial horizon (suction) acceleration errors (linear acceleration) these errors are also known as 'takeoff' errors as they are most noticeable during takeoff two elements cause errors pendulous unit vanes error from the pendulous unit the pendulous unit makes rotor bottom heavy as aircraft accelerates a force from inertia of unit felt at bottom the unit tends to lag behind it tends to swing bottom of gyro towards pilot air driven rotors spin anti clockwise (when viewed from above) so this inertial force will precess through 90° in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates anti clockwise and bank indicates a false right bank error from exhaust vanes during acceleration vanes on right left sides are thrown rearward the result that right hand port more than half open the left side port more than half closed this upsets balanced exhaust of air more air being discharged from right side than from left side the reaction occurs on left side precesses through 90° and lifts up inner gimbal from point nearest pilot to indicate a false climb thus with gyro running anti clockwise a slight indication of right bank climb are obtained during an acceleration.

  • exemple reponse 157
    Parallax error due to A reading under an oblique angle. the ball centered parallax error due to a reading under an oblique angle.

  • exemple reponse 158
    What angle of bank should you adopt on attitude indicator a standard rate 'rate 1' turn while flying at an ias of 120 kt A reading under an oblique angle. the rate of turn the number of degrees your heading changes in a period of time usually one second or one minute a standard rate turn ('rate 1' typically spoken of in terms of instrument flight) performed at 180 degrees of heading change in a one minute period (3° per second) this gives a complete 360° turn in two minutes a convenient approximation the bank angle in degrees taking 15% of ias 15% of 120 kt = 18.

  • exemple reponse 159
    The term drift refers to wander of axis of a gyro in A reading under an oblique angle. for information drift the wander in horizontal plane topple the wander in vertical plane.

  • exemple reponse 160
    What causes a freely suspended space gyroscope to precess The gyro will precess when a force applied to spinning rim of gyroscope in same direction as axis of rotation. for information drift the wander in horizontal plane topple the wander in vertical plane.

  • Question 49-8

    While inertial platform system operating on board an aircraft it necessary to use a device with following characteristics in order to keep vertical line with a pendulous system With damping a period of about 84 minutes. Schuler oscillations have a period of 84 4 minutes are damped out when a gyro stabilised platform moved over surface of earth gyro control system moves it to local horizontal but it ends up oscillating about new horizontal schuler figured that it would act as if it was swinging about at end of a pendulum the period of oscillation of a pendulum depends on square root of its length schuler suggested that it would swing about as if length of pendulum was radius of earth that gives us a period of oscillation of 84 4 minutes.

  • Question 49-9

    In order to align an irs it required to insert local geographical coordinates this enables irs to 1 compare computed latitude with one entered the pilot 2 compare computed longitude with one entered the pilot 3 know longitude the combination that regoups all of correct statements With damping a period of about 84 minutes. Schuler oscillations have a period of 84 4 minutes are damped out when a gyro stabilised platform moved over surface of earth gyro control system moves it to local horizontal but it ends up oscillating about new horizontal schuler figured that it would act as if it was swinging about at end of a pendulum the period of oscillation of a pendulum depends on square root of its length schuler suggested that it would swing about as if length of pendulum was radius of earth that gives us a period of oscillation of 84 4 minutes.

  • Question 49-10

    Compared with a conventional gyro a laser gyro Has a longer life cycle. Laser gyros are used in inertial reference systems use a partially silvered mirror 2 contra rotating laser beams that go opposite direction to each other compared with a conventional gyro a laser gyro more accurate has a longer life cycle because there are no moving parts therefore no friction.

  • Question 49-11

    The mode selector of an inertial unit comprises off stby align nav att positions 1 on 'stby' unit aligns on local geographic trihedron2 'att' position used in automatic landing mode land 3 on 'nav' coordinates of start position can be entered4 platform levelled before azimuth alignment5 in cruise unit can only be used in 'nav' mode the combination regrouping all correct statements Has a longer life cycle. Laser gyros are used in inertial reference systems use a partially silvered mirror 2 contra rotating laser beams that go opposite direction to each other compared with a conventional gyro a laser gyro more accurate has a longer life cycle because there are no moving parts therefore no friction.

  • Question 49-12

    The principle of a laser gyro based on Frequency difference between two laser beams rotating in opposite direction. Two light beams travelling a different distance in same time because of rotation of device rate of rotation proportional to phase difference.

  • Question 49-13

    As a result of failure of adc inertial navigation system ins will no longer provide information about Wind direction speed. ins itself does not know wind direction velocity it only knows ground speed using true airspeed (tas) from an air data source they can easily calculate wind the ins get data (tas altitude) from an air data computer from position ins can provide information about drift can compute time at next waypoint.

  • Question 49-14

    In order to align an inertial reference system irs it required to insert local geographical coordinates this enables irs to Compare latitude it finds with that entered the operator. ins itself does not know wind direction velocity it only knows ground speed using true airspeed (tas) from an air data source they can easily calculate wind the ins get data (tas altitude) from an air data computer from position ins can provide information about drift can compute time at next waypoint.

  • Question 49-15

    Compared with a conventional gyro a laser gyro Is much more cumbersome. ins itself does not know wind direction velocity it only knows ground speed using true airspeed (tas) from an air data source they can easily calculate wind the ins get data (tas altitude) from an air data computer from position ins can provide information about drift can compute time at next waypoint.

  • Question 49-16

    The operating principle of an inertial system consists in Measuring acceleration of aircraft performing integrations to elaborate ground speed the position. the ins measures accelerations north/south accelerations east/west which go through two integrations to give distance travelled north/south east/west from initial position distances travelled north/south east/west it computes present position from change of position it computes track ground speed.

  • Question 49-17

    Compared with a stabilised platform inertial system a strapdown inertial system 1 can aligne while aircraft moving2 has a quicker alignment phase3 more reliable in time the combination that regroups all correct statements Measuring acceleration of aircraft performing integrations to elaborate ground speed the position. the ins measures accelerations north/south accelerations east/west which go through two integrations to give distance travelled north/south east/west from initial position distances travelled north/south east/west it computes present position from change of position it computes track ground speed.

  • Question 49-18

    In an inertial navigation system to know distance travelled Integrating once speed in time sufficient. distance travelled = speed x time and in 'integrating once speed in time sufficient' just formula.

  • Question 49-19

    To obtain instantaneous speed from accelerations It necessary to integrate acceleration once in time to know initial speed only. distance travelled = speed x time and in 'integrating once speed in time sufficient' just formula.

  • Question 49-20

    To obtain instantaneous position from accelerations It necessary to integrate twice acceleration in time to know initial position the initial speed. distance travelled = speed x time and in 'integrating once speed in time sufficient' just formula.

  • Question 49-21

    In a inertial navigation system integration process makes a It necessary to integrate twice acceleration in time to know initial position the initial speed. acceleration x time = change of speed speed x time = distance travelled.

  • Question 49-22

    If acceleration of an aircraft zero its velocity It necessary to integrate twice acceleration in time to know initial position the initial speed. acceleration x time = change of speed speed x time = distance travelled.

  • Question 49-23

    The time a normal alignment not a quick alignment of a strapdown inertial system It necessary to integrate twice acceleration in time to know initial position the initial speed. a rapid self alignment of a strapdown inertial system (irs) can be performed in less than 10 minutes inertial reference systems with laser gyro has caused a technological revolution in design of inertial reference navigation systems this solid state high precision angular rate sensor ideally suited highly reliable strap down system configuration it eliminates need gimbals bearings torque motors other moving parts consequently changes system operation considerably from conventional inertial navigation systems (ins).

  • Question 49-24

    The position error of a stand alone inertial system approximately 5 to 2 nm per hour. a rapid self alignment of a strapdown inertial system (irs) can be performed in less than 10 minutes inertial reference systems with laser gyro has caused a technological revolution in design of inertial reference navigation systems this solid state high precision angular rate sensor ideally suited highly reliable strap down system configuration it eliminates need gimbals bearings torque motors other moving parts consequently changes system operation considerably from conventional inertial navigation systems (ins).

  • Question 49-25

    The output data of an irs include 1 attitude2 altitude3 present position lat long 4 static air temperaturethe combination regrouping all correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids.

  • Question 49-26

    The alignment sequence of an irs consists of 1 searching the local vertical2 searching the true north3 comparison between computed longitude and one entered the pilot4 comparison between computed latitude and one entered the pilotthe combination that regroups all of correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids.

  • Question 49-27

    The output data of an irs include 1 present position lat long 2 total pressure3 static air temperature4 true headingthe combination regrouping all correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids.

  • Question 49-28

    The output data of an irs include 1 satellites status2 altitude3 drift angle4 present position lat long the combination regrouping all correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids.

  • Question 49-29

    The output data of an irs include 1 angle of attack2 altitude3 ground speedthe combination regrouping all correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids.

  • Question 49-30

    The output data of an irs include 1 number of satellites tracked2 mach number3 ground speed4 true trackthe combination regrouping all correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids (such as satellite) the adc (air data computer) will compute mach number.

  • Question 49-31

    To obtain instantaneous position from accelerations it necessary to 1 integrate twice acceleration in time2 know initial position 3 know initial speedthe combination that regroups all of correct statements 5 to 2 nm per hour. in their normal navigation mode irss provide attitude true magnetic heading acceleration vertical speed ground speed track present position wind data to appropriate airplane systems irs outputs are independent of external navigation aids (such as satellite) the adc (air data computer) will compute mach number.

  • Question 49-32

    To obtain instantaneous speed from accelerations it necessary to 1 integrate once acceleration in time2 know initial position 3 know initial speedthe combination that regroups all of correct statements 5 to 2 nm per hour. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-33

    In an inertial navigation system principle used to obtain position 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 regroups all of correct statements 5 to 2 nm per hour. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-34

    Considering a strapdown inertial system operating principle requires use of at least 3 laser gyros 3 accelerometers. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-35

    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 more reliable in time4 less reliable in timethe combination that regroups all of correct statements 3 laser gyros 3 accelerometers. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-36

    A strapdown inertial system consists in A platform attached to aircraft chassis which includes gyroscopes accelerometers. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-37

    In an inertial navigation system integrating once speed in gives A distance travelled. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-38

    An inertial navigation system ins A self contained system which operates without signals from ground. the first integration of acceleration with respect to time gives change of speed apply this to initial speed you have instantaneous speed.

  • Question 49-39

    A ring laser gyro can measure Rotation about its sensitive axis. The ring laser gyro a rate sensing gyro senses rate of rotation around its axis.

  • Question 49-40

    The data that needs to be inserted into an inertial reference system in order to enable system to make a successful alignment navigation Aircraft position in latitude longitude or airport icao identifier. The ring laser gyro a rate sensing gyro senses rate of rotation around its axis.


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