BPSN-2 is a device using the signals from GLONASS and GPS global satellite navigation systems, operating as part of on-board equipment of present-day aircraft and helicopters. BPSN-2 equipment complies with the requirements KT-34-01 (version 2) to onboard equipment for satellite navigation, subclass S1, the software complies with requirements of KT-178A.


BPSN-2 provides:

  • continuous determination of aircraft navigation parameters using the signals from GLONASS and GPS global satellite navigation systems and using the information received from the following systems: the set of onboard equipment, ground-based augmentation system (GBAS) via hardware facilities of the set of onboard equipment, space-based augmentation system (SBAS).
  • determination and outputting of navigation parameters in WGS-84, PZ-90.02, SK-42 coordinate systems, with possibility of prompt selection of the coordinate system.
  • integrity check of output parameters.
  • fault detection and elimination of signals from faulty navigation satellites (FDE function).
  • outputting the time stamp pulse pursuant to ARINC 743A requirements.
  • performing the forecast of RAIM function availability at the planned point, at calculated time with deviation ±15 minutes, and outputting the results of forecast of RAIM function availability to the customer (upon request). Determination of RAIM function availability is provided within 24 hours upon reception by BPSN-2 device of the complete almanac, reception from the set of onboard equipment of geodetic coordinates of the planned point and calculated arrival time.
  • outputting of additional parameters: number of each tracked satellite, azimuth, elevation angle, signal-to-noise ratio.
  • outputting of parameters (coordinates, altitude, velocity, true course angle and time) to the consumers at update rate not less than 10 Hz.
  • selection of SNS type for calculation of navigation parameters.
  • setting of threshold for integrity check alarm according to the information related to flight stage and information received from differential data reception device operating with SBAS augmentation system or with GBAS landing station.
  • several automatic modes of checking are provided: on the ground - «Extended ground check» and «Autonomous check», during flight and on the ground - «Run-time check».
  • Operational availability not less than 0, 99975 during 5 h.
  • Continuity of operation not less than (1,0-0,5·10-4) per hour and (1,0-2,1·10-7) during any 15 s.
GPS/GLONASS/SBAS receiver (designed by Navis Inc. using proprietary set of components) - 24 parallel independent channels for signal reception.
Type of received signal:
• GLONASS SNS in L1 range, ST-code
• GPS SNS in L1 range, C/A code
Error of determination in “Autonomous” mode and “Navigation” mode with probability 0,95:
horizontal coordinates/altitude
  • GPS 33/70 m
  • GLONASS 44/66 m
  • GNSS 44/70 m
actual velocity
  • GPS 2,0 m/s
  • GLONASS 0,3 m/s
  • GNSS 0,3 m/s
true course angle during change of actual velocity from 100 to 1200 km/h
  • GPS from 5° to 30´
  • GLONASS from 35´ to 3´
  • GNSS from 35´ to 3´
Error of determination of horizontal coordinates/altitude in SBAS and GBAS modes with probability 0,95
  • by APV-I 16/20 m
  • by APV-II 16/8 m
  • by category 1 16/6 m
Instrumental error of measuring pseudoranges with probability 0,95, not more than 1,5 m
Coordinate systems WGS-84, PZ-90.02, SK-42
Supply voltage +27 V
Input current not more than 0,5 A
Lightning proofness AP-25, AP-29

Exposure factors 

ENLG-S (Unified aircraft airworthiness requirements), NLGV-2 (Helicopter airworthiness requirements)

Operating temperature range





from – 40 to +55°C





from – 55 to +85°C





from – 55 to +55°C

    7 receiving channels
    3 transmitting channels
    1 channel (UTC time stamp)
One-time commands 
  input – 9 (8 ground/1 power supply)
   output – 2 (ground)


Quantity, pcs.
Dimensions, mm
Weight, kg
Receiver-computer unit (BPV)
 Antenna A101P
 Amplifier MSh-RFS
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