The alignment phase of a gyro stabilized platform consists in ?
Program > pilot
A laser gyro can measure ?
A ring laser gyro is ?
Considering a strapdown inertial system iru inertial reference unit measures Accelerations angular rates, angular accelerations only, angular rates only, linear accelerations only. the irs measures both angular linear accelerations. 
The alignment time of a strapdown inertial system takes longer time when aircraft At a high latitude, at a high longitude, close to equator, at a location where magnetic variation greater than5 degrees. 
An inertial navigation system Can operate as stand alone equipment without any interface with other navigation equipments, can only operate when interfacing with gps equipment, can only operate when interfacing with radionavigation equipments, can only operate when communicating with ground installations. 
In an inertial navigation system principle used to obtain change in speed 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. Question Inertial Navigation 50 Answer 8
The characteristics of earth which are being used during alignment of an ins platform are Earth rotation gravity, earth magnetic field earth rotation, longitude gravity, earth rotation longitude. while aircraft stationary during align mode gravity defines local vertical the gyro stabilised platform placed perpendicular to vertical i.e. in local horizontal. the north east gyros are used to define direction in which earth rotating (east) in order to define platform's alignment relative to true north. Question Inertial Navigation 50 Answer 9
In a strapdown inertial system accelerations are measured in a trihedron which fixed regarding to Aircraft's trihedron (pitch, roll yaw axis), earth's trihedron (longitude, latitude), absolute space, earth's trihedron (x, y, z). Question Inertial Navigation 50 Answer 10
In a stabilised platform inertial system accelerations are measured in a trihedron which nb 'aircraft trihedron' = pitch roll and yaw axis Free from aircraft trihedron, fixed in absolute space, merged with aircraft's triehedron, merged with only two axis of aircraft trihedron roll axis the pitch axis. Question Inertial Navigation 50 Answer 11
On ins control panel rotary knob can be selected to off nav or att positions the correct statement Nav the normal system settingatt position the back up position in case of failure of navigation function, nav the normal system settingoff position the back up position in case of failure of navigation function, att the normal system setting, att the normal system settingnav position inhibits attitude data. Question Inertial Navigation 50 Answer 12
The position data lat long computed an irs can be used the Fms, ils receiver, adc, tcas. Question Inertial Navigation 50 Answer 13
The accuracy of altitude computed a stand alone inertial system Decreases exponentially with flight time, bounded, decreases proportionally with flight time, poor at beginning of flight. some irs use baro altitude to stabilise inertial reference height use mixed baro/ir vertical rate. the irs altitude calculation not an output of irs. Question Inertial Navigation 50 Answer 14
The output data of an irs include 1 present position lat long 2 tas3 attitude4 ground speedthe combination regrouping all correct statements , 3, 4,, 2, 3,, 2, 4, 2, 3, 4. 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 Inertial Navigation 50 Answer 15
The drift of gyroscopes of a stand alone inertial system Is main error source, not an error source, induces a position error that decreases along flight, induces a bounded position error. Question Inertial Navigation 50 Answer 16
Considering a stabilised platform inertial system this platform 1 can be servo controlled in azimuth2 kept levelled during alignment phase only3 always kept levelledthe combination that regroups all of correct statements Question Inertial Navigation 50 Answer 17
Comparing radio navigation system and inertial navigation system 1 radio position accurate when in dme range2 radio position may be obtained whatever position on earth3 inertial position may be obtained whatever position on earththe combination regrouping all correct statements pywee22 i don't understand answer about dme. if you are in dme range you will know your distance from dme but you won't be able to get an accurate position from it because you can be anywhere around 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 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 accurate. Question Inertial Navigation 50 Answer 18
An inertial reference and navigation system a 'strapdown' system when The gyroscopes the accelerometers are fixed regarding to aircraft's body axes co ordinate system, only gyroscopes, not accelerometers, are fixed regarding to aircraft's body axes co ordinate system, gyroscope the accelerometers are mounted on a stabilised patform, only gyroscopes, not accelerometers, are mounted on a stabilised platform. Easa update august 2012. old answers was the gyroscopes accelerometers are part of unit's fixture to aircraft structure (right answer). only gyros, not accelerometers, are part of unit's fixture to aircraft structure. gyros accelerometers are mounted on a stabilised platform in aircraft. gyros accelerometers need satellite information input to obtain a vertical reference. Question Inertial Navigation 50 Answer 19
If navigation function of an ins inoperative and control rotary switch set to att output data of ins are Attitude heading, position only, position attitude, attitude ground speed. Question Inertial Navigation 50 Answer 20
The alignment of a strapdown inertial system consists in Measuring earth rotation local gravitation to position reference trihedron, positionning accelerometers, positioning gyroscopes accelerometers relative to fuselage axis, positioning platform relative to local vertical true north. on an strapdown system irs fixed to aircraft, so aligment consists in measuring earth rotation local gravitation to position reference trihedron. Question Inertial Navigation 50 Answer 21
The position error of a stand alone inertial system Increases along time, remains constant, sinusoidal, increases up to 2 nm due to drift error of gyroscopes, then stabilizes. inertial navigation system (ins) one of oldest simplest forms of navigation systems. although simple, ins prone to accumulating errors over time. ins systems are based on dead reckoning techniques. dead reckoning techniques use an initial known point of origin then record measurements of acceleration or velocity over time to obtain resultant position using integration. acceleration in three dimensions measured using triaxes accelerometers whose accuracy can be heavily degraded because of different error sources. the increase in position error, over each hour, increasing linearly (or, as time increases, error increases the same amount over each hour). Question Inertial Navigation 50 Answer 22
The position error of a stand alone inertial system Small a few minutes after initialisation increases along flight, small constant along flight, large a few minutes after initialisation reduces along flight, constant along flight with an accuracy depending on accuracy of accelerometers. Question Inertial Navigation 50 Answer 23
The output data of an irs include 1 present position lat long 2 altitude3 ground speed4 true headingthe combination regouping all correct statements , 3, 4,, 2, 3,, 4,, 2, 3, 4. 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 Inertial Navigation 50 Answer 24
The attitude data computed an irs can be used the Auto pilot system, tcas, gpws, stall warning system. Question Inertial Navigation 50 Answer 25
If position data lat long no longer computed an irs affected system s are The fms, adc the tcas, fms the tcas, tcas. Question Inertial Navigation 50 Answer 26
The energy required to operate a strapdown inertial system supplied The electrical system, bleed air system, hydraulic system, a dedicated pneumatic system. Question Inertial Navigation 50 Answer 27
When rotary knob on ins control panel set to 'nav' mode it The normal operating mode allowing use of all functions of system, navigation mode allowing use of all functions of system except attitude, alignment function in flight, navigation mode allowing use of all functions of system except heading. Question Inertial Navigation 50 Answer 28
The alignment of a gyro stabilized inertial platform consists in positionning platform relative to The vertical axis true north, pitch axis only, pitch roll axis, roll axis only. Question Inertial Navigation 50 Answer 29
In an inertial navigation system a tas input Required to provide a wind direction velocity read out, not required, required polar navigation, required the automatic flight control system (afcs) to compute a heading according to track. Revised ecqb04, october 2017. this question exists with following statement 'what additional information required to be input to an inertial navigation system (ins) in order to obtain a wind information readout? tas. ias. mach number. altitude oat'. Question Inertial Navigation 50 Answer 30
The platform of an inertial navigation system ins maintained at right angles to local vertical applying corrections the effects of Aircraft manoeuvres, earth rotation, transport wander coriolis, gyroscopic inertia, earth rotation real drift, vertical velocities, earth precession, centrifugal forces transport drift, movement in yawing plane, secondary precession pendulous oscillation. Question Inertial Navigation 50 Answer 31
In an inertial navigation system ins ground speed gs calculated By integrating measured acceleration, from tas w/v from air data computer (adc), from tas w/v from rnav data, integrating gyro precession in n/s e/w directions respectively. the starting point an inertial reference system acceleration. in order to sense linear acceleration inertial system uses mechanical inertial accelerometers. so if acceleration known then speed can be calculated, if speed known then distance can be calculated. the mathematical process that reduces acceleration to speed speed to distance called integration. Question Inertial Navigation 50 Answer 32
During initial alignment of an inertial navigation system ins equipment Will not accept a ° error in initial latitude but will accept a ° error in initial longitude, will accept a ° error in initial latitude but will not accept a ° error in initial longitude, will not accept a ° error in initial latitude or initial longitude, will accept a ° error in initial latitude initial longitude. when align selected operator must enter aircraft's position to nearest tenth of a minute of latitude longitude. the latitude entered used to check alignment of platform checking topple of north east gyros due to earth rotation (earth rate) against latitude. if latitude entered correctly but longitude entered in error platform will get itself levelled aligned indicate that nav can be selected, but its plot of aircraft position will be starting from wrong place (error in longitude). Question Inertial Navigation 50 Answer 33
The average value the position error of ins inertial navigation systems according to time.5 to 2 nm/h, 2 to 5 nm/h,to2 nm/h, 6 to 8 nm/h. Question Inertial Navigation 50 Answer 34
The output data of an irs are 1 true track2 mach number3 present position lat long 4 true heading5 attitudethe combination regrouping all correct statements , 3, 4, 5, 3, 2, 5,, 2, 3, 4. 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 Inertial Navigation 50 Answer 35
After alignment of stable platform of an inertial navigation system ins output data from platform Acceleration north/south east/west, true heading attitude, latitude, longitude attitude, acceleration north/south east/west true heading, latitude, longitude true heading. Question Inertial Navigation 50 Answer 36
In an inertial reference system accelerations are measured in relation to Aircraft axis, wgs84 earth coordinates, direction of true north, local vertical at aircraft position. an irs system (strapdown system) consists in a platform attached to aircraft chassis which includes gyroscopes accelerometers. the accelerations are measured in a trihedron which fixed regarding to aircraft's trihedron (pitch, roll yaw axis). Question Inertial Navigation 50 Answer 37
The full alignment of stable platform of an inertial navigation system ins Is only possible on ground when aircraft at a complete stop, may be carried out on ground or when in straight level flight, may be carried out at any time so long as an accurate position inserted into system, may be carried out during any phase of flight. while aircraft stationary during align mode, gravity defines local vertical the gyro stabilised platform placed perpendicular to vertical i.e. in local horizontal. the north east gyros are used to define direction in which earth rotating (east) in order to define platform's alignment relative to true north. it only possible on ground when aircraft at a complete stop. Question Inertial Navigation 50 Answer 38
Which of following statements concerning aircraft positions indicated on a triple fit ins/irs on cdu correct The positions are likely to differ because they are calculated from different sources, positions will only differ if one of systems has been decoupled because of a detected malfunction, positions will only differ if an error has been made when inputting present position at departure airport, positions will be same because they are an average of three different positions. all ins/irs in an aircraft are independent. the positions each irs/ins will be slightly different. Question Inertial Navigation 50 Answer 39
A pilot accidentally turning off irs in flight and then turns it back on a few moments later following this incident It can only be used attitude reference, everything returns to normal is usable, irs usable in nav mode after a position update, no useful information can be obtained from irs. Question Inertial Navigation 50 Answer 40
Concerning operation of an ins/irs nav mode must be selected Prior to movement of aircraft off gate, when alignment procedure commenced, on runway, just prior to take off, prior to loading of passengers and/or freight.
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