Q flight inspection division
This presentation is the property of its rightful owner.
Sponsored Links
1 / 23

Q Flight Inspection Division PowerPoint PPT Presentation


  • 82 Views
  • Uploaded on
  • Presentation posted in: General

Q Flight Inspection Division. Flight inspection of ground aviation facilities Q experience with GPS. Karel Kučera, Flight Checking Engineer Marek Dobrozemský, Flight Checking Engineer. FID - Supervision of. ILS, VOR, DME, NDB, VDF, COM RADAR SYSTEMS PAPI, VASIS ALS, RLS

Download Presentation

Q Flight Inspection Division

An Image/Link below is provided (as is) to download presentation

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.


- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -

Presentation Transcript


Q flight inspection division

Q

Flight Inspection Division


Flight inspection of ground aviation facilities q experience with gps

Flight inspection of ground aviation facilitiesQexperience with GPS

Karel Kučera, Flight Checking Engineer

Marek Dobrozemský, Flight Checking Engineer


Fid supervision of

FID - Supervision of

  • ILS, VOR, DME, NDB, VDF, COM

  • RADAR SYSTEMS

  • PAPI, VASIS

  • ALS, RLS

  • Flight Procedures

  • FM interference


Fid fleet

Beechjet 400

Business Category jet with an advanced dual Flight management and autopilot systems

150 to 320 KTS IAS, GND to FL 450, 3hrs duration

Let 410 UVP

Commuter aircraft equipped with latest avionics, autopilot and GPS

80 to 200 KTS IAS, unpressurised, 3hrs duration, unpaved runways operation (600m)

FID - Fleet


Method

error curve

track flown

sensor indication

Method

Comparing position indicated to reference one.


Rs evolution

RS Evolution

  • Ground reference points

  • Optical instruments

    • Standard Theodolite

    • Radio Telemetry Theodolite (RTT)

    • Digital Radio Telemetry Theodolite (DRTT)

  • GPS (DGPS, RTK)


Steps utilising gps

Steps utilising GPS

  • 1992 new equipment NM 3625B on BE40

  • 1993 - 1995 Testing period

  • since 1994(1995) Operational use

  • 1995 backup aeroplane L4T equipped NM 3625 B

  • 1998 NM 3625 B - CR2 modified to RTK method

  • 1999 NM 3625 B - CR3 modified to RTK method

  • 2002 Omnistar corrections included


Ils cat iii critical application

ILS cat. III- critical application

ILS points configuration

Runway

Approach direction


Critical requirements

Critical requirements

  • ILS parameters

*at point B

  • Positioning system accuracy


Q flight inspection division

Testing

  • Gradual, following technology implemented

  • APRS (DGPS solution)

    • Static tests

    • Dynamic tests

  • RTK

    • Static tests

    • Dynamic comparisions

    • Theorethical evaluation


Q flight inspection division

APRS (history)

  • DGPS, INS, LRF

    • declared accuracy: 1m horizontal, 1.5m vertical

    • required:

      • PDOP < 2.4,

      • HDOP < 1.5,

      • >6 SATs in view,

      • <100 km from reference station

    • LRF & postprocessing made possible vertical accuracy 0.14m


Q flight inspection division

APRS Testing

  • First: comparing flight test results of both DRTT and APRS (same datalink used)

  • Second frequency added to data link -> REFERENCE CHECK procedure

  • 91 approaches in horizontal plane

  • 80 approaches in vertical plane

  • Declared accuracy confirmed

  • Scenarios: static and dynamic both in horizontal and vertical plane


Q flight inspection division

APRS Testing scenarios (1)

  • Static test in horizontal plane

WPT 1


Q flight inspection division

APRS Testing scenarios (2)

  • Static test in vertical plane


Q flight inspection division

APRS Testing scenarios (3)

  • Dynamic tests

    • approaches to two points (vertical, horizontal)

    • Reference check (APRS, DRTT)

    • DRTT placed to standard points for LLZ respective GP flight testing.

      • Horizontal: until E point

      • Vertical: until B point


Q flight inspection division

Sensor positions

antenna vectors


Q flight inspection division

Test Results

  • Static tests

  • Dynamic tests


Q flight inspection division

RTK

  • Static tests performed - very optimistic results

  • Flight tests (RTK-DRTT comparison) confirms high degree of accuracy

  • High accuracy ensured only if RTK „fixed“.

  • Problem to find „the ruler“ to verify dynamic measurements

  • Theoretical error assessment put in place


Rtk accuracy considerations

Type, Critical Point

Annex 10 Requirements

Reference System Requirements

Estimated RTK Accuracy

LLZ Alignment - Point T

+/-3.0m

+/- 1.00m

+/-0.32m

LLZ Structure - Point D

+/- 2.5m

+/- 0.32m

+/-0.32m

GP Alignment - Point B

+/- 2.8m

+/- 0.21m

+/-0.16m

GP Structure - Point T

+/- 0.5m

+/- 0.17m

+/-0.16m

RTK – accuracy considerations


Technology today

Technology Today

  • Calibration Position Reference: GPS, DGPS, RTK

  • up to dm accuracy in position

  • up to ILS cat III flight checking

  • DRTT as a backup

  • long experience


Q flight inspection division

Measuring Accuracy

  • Standard deviation typically < 5 cm(on GPS antenna)

    • 32 cm horizontal transformed to aircraft measuring antenna position

    • 16 cm vertical transformed to aircraft measuring antenna position


Ground support

Ground support

  • Mobile DGPS reference station

  • DGPS reference station network

    • Major aerodromes (LKPR, LKTB, LKMT, LKKV)

    • Providing coverage over all CR

  • Database of coordinates (WGS-84)

    • Surveyed by Czech Army Topographical Institute

    • Verified by independent agency

  • Special WPT database

    • Computed points

  • GPS surveyor

    • Geodetic (D)GPS, OMNISTAR corrections, ± 0.8m , ± 0.02m relative


Conclusions

Conclusions

  • RTK successfully used for Flight test up to ILS cat III

  • Independence of ground assistance - effectivity

  • Human factor influence reduction.

  • Visibility independence - better serviceability

  • Experience with these technologies in ACFT guidance.

  • Knowledge for future coming satellite technologies

    • EGNOS

    • GALILEO


  • Login