PGC-A. System overview
Contents
1. be located within the aircraft in accordance with the following considerations A B C D E The ideal location for integrated inertial GNSS navigation system unit is close to the centre of mass of the aircraft The unit must be placed on a horizontal surface so that its led indicators are on the top and point in the rear direction The system is tolerant to misalignments between unit axis and longitudinal aircraft axis of up to 5 The location of GPS antenna should ensure a clear view of the sky The cables should not run adjacent to heaters exhausts or other heat sources Care must be taken to route and tie the cables away from aircraft controls and harnesses The tablet PC shall be in view of pilot and its location must provide the free access of pilot s hand to the screen However it should not create an obstruction to the field of view of the instrument panel The tablet PC should be easily installed and removed to allow flight planning and post flight analysis on the ground The commutation unit should be easily accessible and dismountable to allow battery re charging on the ground After units are properly arranged and fixed they must be connected with proper cables according to the cable labels Then the commutation unit must be connected to the board power supply circuit Portable Glass Cockpit System Overview Rev 122008 Page9 6 PGC functionality PGC A software provides the functionality of several a2. pilot navigator and 2 inertial system units to provide instruments backup Advanced configuration provides the extended system capability including networking interoperations between two computers For example the pilot navigator can perform all inflight operations and control the pilot computer display to provide better situation awareness thus pilot won t need to control the display himself Portable Glass Cockpit System Overview Rev 12 2008 Page 9 8 Approbation and Approvals The PGC A is officially approved by Russian Flight Administration and MIL helicopter plant for use as additional navigation system for Mi8 Mi17 types of helicopters in use CO JA CCI A HORS NY THEP AAs m i GawecrmTeab proscrire HI LT BC Pd ct IO H Enzaoxmaon 2006 Ag loss Konc TEVETUP OAC MEET ia ML Mante gU E pe fes ee w B B Tipmeanon ii Sn Sr OCHO YE ja COUT TACOS AFICko gi Arpestop ACU TocHHH TA Fe H rpaaciackuti ZB i 2004 t SUD JLACUORBAHU Napexrop CUBO TocHHH AH CHE H H Kymenmkman t m 2006 1 Figure 10 PGC A List of Approval The document states the following PGC A keeps its navigation functionality even if GPS data are corrupted or missed for short period of time 2 4 min The integration of INS and GPS data provides the better flight parameters determination especially while moving with low speed a he satellite data jumps due to change of constellation are smoothed wit
3. tre KEETA AT 00 00 3D42D ser Rout Es Hset SPOT AND REC 3D 2D terrain 3D map aerial image Ue EA obed ond Moni s SYNCH TR RCV Twpt Tfiy Sec Lnd P DFT a uL pem ee toned GPS SYNCH TR RCV V Twpt Tfly Sec LndP DFT VPs pwTH359 OVE ge 168 N 00 00 00 00 00 00 00 00 00 a Grid1615 x LS 11 0 5 TO0 03 1304 ua W 167 XTK 1 120 Hst EE SET Rout RWY rela sm IND REC GoTo MODE NGI MAF rep SES GoTo MODE 3D navigation instruments Navigation instruments map Figure 6 Combined View displays Portable Glass Cockpit System Overview Rev 12 2008 Page 14 6 2 Flight planning PGC A software provides the user with extensive flight planning capacity The database of routes can be formed prior the flight in the office or workshop when the portable computer is dismounted from the aircraft cockpit For the flight planning digital maps and digital terrain maps can be used Route comprises waypoints airfields approaches obstacles navigation points maps terrain All the elements of the route can be loaded from the data base or created before the flight The route is created considering the digital terrain data The flight planning software comprises approach planning options based on standard approach patterns and user updated obstacle data base The taxing and aircraft parking planning is also available The airport data ba
4. Page5 2 4 Panasonic CF 19 The Panasonic Toughbook CF 19 is a ruggedized laptop computer which was designed and tested in accordance with MIL STD 810F Panasonic Toughbook meets all the categories and levels of durability expected in the work environment of a cockpit vibration drop water and dust resistance humidity high and low temperature altitude As part of PGC A the Panasonic CF 19 provides flight data processing displaying management and recording Panasonic CF 19 runs special PGC A software to provide mission planning and flight data analysis functions Portable Glass Cockpit System Overview Rev 122008 Page6 o 3 System specification I nertial GNSS integrated system Operating rages Specification Angular velocity 300 sec Interface RS232 Acceleration 6g Update rate 50 Hz Pitch 90 Warm up time 30 sec Roll 90 Operating temperature 40 70 C Heading 0 360 Shock 20g Input voltage 8 30 V Power lt 1 5W Size 125x80x57 mm Weight 0 7 kg Panasonic CF 19 MIL STD 810F Intel Core Duo 1 06 GHz Power 60 W HDD 80 Gb Operating temperature 0 60 C RAM 1 5 Gb Storage temperature 40 60 C RS 232 Weight 2 3 kg Brightness 500 nit Portable Glass Cockpit System Overview Rev 12 20008 Page7 4 System Operation LLP EEE EEE EEE EEE TITI ITS gt ma a i RS 232 GH 27 V board eJ 12 27 V G 12 V battery charge Inertial Navigation System T
5. TeKnol Ltd Vvedenskogo str 13 B 117342 Moscow RUSSIA e mail contact teknol ru http www teknol ru Autonomous Portable Glass Cockpit System PGC A SYSTEM OVERVIEW October 2009 TeKnol TABLE OF CONTENTS Acronyms 1 Introduction 2 System Description 2 1 Inertial GNSS integrated navigation system 22 GARMIN GPS35 2 3 Commutation unit 2 4 Panasonic CF 19 3 System specification 4 System Operation 5 Deployment 6 PGC functionality 6 1 Data display 6 1 1 Primary Flight Display _ 6 1 2 Navigation Display 6 1 3 Instruments Panel 6 1 4 Combined Display 6 2 Flight planning 6 3 In flight operations 6 4 Training 6 5 Debriefing 6 6 Warnings 7 Advanced Configuration 8 Approbation and Approvals 9 System installation examples Portable Glass Cockpit System Overview Rev 12 2008 S oo N A Un a Un a A Page 2 Current document provides Portable Glass Cockpit system overview For technical details and system operation please refer to PGC A User Manual and CompaNav 2 System overview documents Acronyms GNSS Global Navigation Satellite System INS Inertial Navigation System Primary Flight Display PGC A Autonomous Portable Glass Cockpit System TAWS Terrain Awareness Warning System WPT waypoint Portable Glass Cockpit System Overview Rev 122008 Page3 o 1 Introduction PGC A is portable flight and navigation instrumentation system which is fully independent from aircraft onboard sy
6. ablet PC GPS receiver Garmin 35 Commutation unit Solid state Flight Data Recorder option Air Data Computer option External Switch NOOR N Figure 1 PGC A basic architecture The GPS receiver NMEA data and inertial sensors data are processed by the inertial navigation system microprocessor to calculate motion parameters and navigation data which are output to the tablet PC via RS 232 interface with 50 Hz rate Then the data are processed and visualized by the PGC A software If the Air Data Computer is available the airspeed data is also used for motion parameters calculation The flight data are displayed with respect to moving map and 3D digital terrain The software also calculates forecast vectors of motion acceleration motion speed and altitude vectors flight direction and provides warnings in case of dangerous flight Software is controlled by the means of touch screen display to provide quick display of the required data The same tablet PC is used for flight planning and for flight data analysis Normally the flight data is stored in the PC hard drive but as backup data storage the solid state Flight Data Recorder can be used Portable Glass Cockpit System Overview Rev 122008 Page8 o 5 Deployment System deployment is easy and does not reguire complicated installation procedures The deployment consists of three basic stages 1 Mounting 2 Unit interconnection 3 Powering up All units should
7. ction of flight In the Navigation Display can be displayed digital map or 2D terrain Planned Trajectory Turn Limitation Figure 3 Navigation Display PGC A software provides raster images georeferencing in order to create digital maps of topographical map images aerial photos and approach charts meeting the user requirements 4 Vej gu 4 Gg M USER AL ne wr AON Figure 4 Navigation display with moving map Portable Glass Cockpit System Overview Rev 12 2008 Page12 6 1 3 Instruments Panel Instruments Panel Display simulates the following standard avionics instruments Artificial horizon Heading Indicator HSI Altimeter Climb meter Ground speed indicator G meter Low altitude altimeter TAWS ROLL d V km h GPS ROLL aoad vimm GPS SYNCH TR RCV Twpt Tfly Sec tna P DFT 9 10 NGI SET Rout RWY rap Rea SPOT LND REC Go ToAnalysif Figure 5 Instrument Panel Portable Glass Cockpit System Overview Rev 12 2008 Page 13 6 1 4 Combined Display To enhance data indication flexibility and convenience several types of combined displays are provided 3D 2D 3D navigation instruments navigation instruments map see Figure 6 TAWS som ROLL coeur GPS SYNCH TR ov ee ak Sec LndP DFT V som ROLL goad Vinh GPS SYNCH TR REV Twpt Tfly Sec LndP DFT 5 rruver ka JP Eg gt M so iT T10 54 S14 da ai 220 XTK 005 ar on
8. e PGC A software is adapted for control by the means of tablet PC touch screen Along with data indication trajectory visualization TAWS and warning function during the flight the PGC provides quick route change GO TO function approach pattern display and approach director quick landing to the site marked during the flight quick obstacle marking The obstacles are marked inlfight as a point in the map After the flight the obstacle height should be set and the obstacle must be stored in the data base In the next flight the obstacle with a cone zone of danger around it will be marked in PFD as a 3D object Portable Glass Cockpit System Overview Rev 12 2008 Page17 6 4 Training The PGC A allows user getting familiar with system performance before flight A set of joysticks turns the PGC A into a compact desktop simulator As a simulator the PGC A provides two functions 1 Learning basic system operation 2 Flight preparation once flight plan is ready the pilot can perform the virtual flight following selected trajectory learning navigation over a particular area of the forthcoming flight 6 5 Debriefing All the data coming from INS can be recorded in the tablet PC The system allows simultaneous recording of more then 30 flight parameters including pitch roll heading angles speed coordinates altitude and barometric height GPS data and other The PGC A software has an advanced capacity for deb
9. h inertial data b The satellite data latency is compensated with inertial sensors data The standard GPS data rate 1Hz is increased up to 50 updates per second 4 The mobile tablet PC with bright display 10 4 500 nit provides up to 2 5 hrs of autonomous system work The system can be located in the appropriate place of the cockpit of Mi8 Mi17 helicopter providing convenient operations for flight crew The use of the PGC A does not affect the basic properties of the vessel its standard communication and navigation equipment The use of PGC A does not require to revise the helicopter flight operation manuals neither maintenance procedures In case of emergency situation the PGC A does not change the standard sequence of flight crew operations and does not handicap to abandon ship in emergency Starting 2006 the PGC A is used by helicopter operators in Russia and abroad The PGC A is operated in Nepal Afghanistan Kazakhstan for UN mission flight support Portable Glass Cockpit System Overview Rev 12 2008 Page20 9 System installation examples k Mi helicopter Portable Glass Cockpit System Overview Rev 12 2008 Page21 A Fi a 2 i ul A Lae n a i v M 5 Me i Portable Glass Cockpit System Overview Rev 12 2008 oo Page22 Mi 24 Mi 35 Portable Glass Cockpit System Overview Rev 12 2008 Page23 Yak I8T ai
10. ncludes the following units e lnertial GNSS integrated Navigation System e Garmin GPS Smart Antenna Model GPS35 LVC e Ruggedized Tablet PC CF 19 with Windows OS and special PGC A Software e Commutation unit with built in battery 2 1 Inertial GNSS integrated navigation system The integrated inertial GNSS navigation system is motion parameters data source for the PGC A The system determines position coordinates latitude longitude and height and attitude angles pitch roll and heading of an aircraft The system outputs 50Hz rate navigation data to the Panasonic CF 19 computer where it is processed and displayed The GARMIN GPS 35 is a GPS receiver with built in antenna GPS35 tracks up to 12 satellites at a time provides fast time to first fix and 1Hz navigation updates It is housed into water resistant case and designed to withstand rugged operating conditions All settings of GARMIN GPS35 are made by the manufacturer The receiver does not require service or maintenance through its life cycle 2 3 Commutation unit The commutation unit provides PGC A system units data and power interconnection To provide system power supply it is connected to onboard power circuit The unit also incorporates built in accumulator battery and guarantees 2 5 hours of PGC A autonomous work The LED indicators in front panel indicate the battery charge and system state Portable Glass Cockpit System Overview Rev 122008
11. riefing and post mission flight data analysis The system is capable to playback the flight data with different time scales 6 6 Warnings In flight the PGC A software analyses the aircraft motion parameters and compares it with operating limitations set for the aircraft In case flight parameters are close to the limitations or are violating the set values visual and audible warning signals are provided The visual warnings are displayed in the panel of warnings in the upper corner of the program screen Figure 9 TAWS ALT ROLL g load V km h GPS off 60 m 30 0 1 8 0 250 8 Figure 9 Panel of warnings To provide visual warning the appropriate button in the panel is coloured red If the danger occurs the button is coloured red Portable Glass Cockpit System Overview Rev 12 2008 Page18 7 Advanced Configuration E LJ e LJ LJ LJ LJ LJ m LJ LJ LJ in n al LJ U m LI m a LJ a LI L E LJ LI LI oa s amp E LI LJ E LI LJ LJ L L LJ LJ LJ LJ Li LJ LJ LJ LJ LJ LJ LJ a U Li LJ U a m U m LJ LI LI E gt RS 232 z12 27 V lt Ethernet 27 V board Inertial System Panasonic CF 19 GPS Garmin 35 Commutation unit Flight Data Recorder Optional Air Data System Optional The advanced configuration includes 2 tablet computers one for pilot and one for
12. rplane Portable Glass Cockpit System Overview Rev 12 2008 Page 24 Sigma 4 light airplane Portable Glass Cockpit System Overview Rev 12 2008 Page25
13. se includes the approach and taxing charts runway numbers glideslope courses radio link and frequency response data MESIME 807 U 0027 00 2200 8 791 748 MEDILISESE 587 15 002424 2200 11248 386 MED STE 530 16 002728 2200 11346 328 oi amp 120001E s Eos 200 7 083 343 8 Z 5007m 4701175YN O15 14 010E M LOJ fps 3175 NATED S bi Figure 7 Flight planning Portable Glass Cockpit System Overview Rev 12 2008 1 Page15 Figure 8 Aerodrome chart Portable Glass Cockpit System Overview Rev 12 2008 Page16 6 3 In flight operations The PGC A tablet PC communicates with INS unit via a high speed RS 232 interface 50Hz standard data update rate provides uninterrupted flight parameters indication under any flight conditions By processing the navigation data from inertial navigation system and air data computer optionally the PGC software calculates and displays terrain proximity line current motion trajectory and motion forecast vectors motion director and deviations from the desired flight plan etc Along with standard instrumentation PGC A significantly increases pilot s situation awareness by displaying the circle of operational limitations and the integral force which is the primary cause of aircraft motion The PGS A offers a wide range of extended performance allowing a pilot to operate and navigate the aircraft with maximum convenience and safety using advantages of modern computer and database technologies Th
14. stems It includes navigation and flight data source and accumulator battery thus being fully autonomous PGC A can be easily mounted on any type of light aircraft or helicopter and is officially approved for use on Mi8 and Mi17 type of helicopters see Approbation and Approvals section of this document PGC A implements intuitive indication and advanced data processing and display functions to increase flight safety and situational awareness PGC A provides the whole range of flight preparation inflight and post mission operations to enhance the functionality of an aircraft without cockpit modernization PGC A functionality N Flight preparation and simulation Data bases routes maps digital terrain approaches obstacles navigation points Primary flight display PFD with 3D obstacles and flight trajectory indication Navigation display ND and moving map Standard instruments display Forward looking 3D views of terrain TAWS Terrain color change according to the flight altitude Predictive flight guidance Quick charts and digital terrain maps upload Quick enroute marking of obstacles and navigation points Hovering mode for helicopters AS SI measurement systems Approach and landing pattern programming Visual and audible warnings about dangerous flight or aircraft limitations override Portable Glass Cockpit System Overview Rev 12 2008 Page 4 2 System Description The PGC A standard architecture i
15. viate from the programmed route Desired speed and height values are marked at the scales to the right and to the left Portable Glass Cockpit System Overview Rev 12 2008 oo Page 10 TAWS ALT ROLL ALT ROLL gioad Vkmih GPS SYNCH TR RCV Twpt Tfly Sec Lna p DFT gt 9 1 8 0 250 plese ey Suit Her PMTH 78 00 00 00 05 12 29 utc Over off V gps Flight Envelope Forecast vector Of Acceleration y A mese n rum LL RangetoWPT 85138 A T 00 05 LL Time to WPT W165 XTK 0 004 aros mas pad MS 3D SET Rout R Nee Pau lenin REC Go ToAnalysi Figure 2 Primary Flight Display The digital terrain data is overlaid as colored three dimensional image on both PFD display and Navigation Display The PGC A software applies color coding of the terrain data The above flight level terrain is coloured red while the below flight level terrain is green According to terrain data the terrain proximity line is calculated and displayed in 3D PFD view Terrain proximity line along with 3D terrain display function and warnings about aircraft operating limitations increase pilot situation awareness thus TAWS function is implemented Portable Glass Cockpit System Overview Rev 12 2008 Pagell 6 1 2 Navigation Display The Navigation Display shows planned trajectory predicted path and turn limitation The aircraft shape is displayed as a cross with the arrow pointing in the dire
16. vionics instruments and systems including TAWS EFIS and Electronic Flight Bag The PGC A is capable to perform the whole range of flight operations including flight preparation flight planning route map airfield data base creation inflight operations flight director approaches obstacles marking etc post mission flight data analysis 6 1 Data display The navigation data motion parameters and trajectory can be displayed in one of the following ways in 3D image with digital terrain as background Primary Flight Display PFD in 2D image Navigation Display with digital terrain map approach pattern or aerial image as background in standard gauges instrumental panel in combined image 3D 2D 3D map 3D instrumental panel instrumental panel map The type of data indication is selected by the button in the lower corner of the PGC window 6 1 1 Primary Flight Display The default indication mode is PFD It displays all standard flight instrumentation as graphical objects aircraft symbol rulers vectors etc Figure 2 shows PGC A PFD Attitude heading ground speed rate of climb altitude G load are displayed The aircraft symbol depicts the actual attitude of the aircraft with respect to horizon While flying flight director cross marks the flight direction according to the desired flight plan When circle of the forecast vector of acceleration see Figure 2 matches the flight director cross the aircraft won t de
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