ANS-510 Airborne Inertial Navigation System

ANS-510 is a navigation grade airborne inertial navigation system with embedded GPS receiver which is intended for application to military air vehicles.

ANS-510 has an open architecture and hardware/ software flexible unit which can be adapted to various air platforms including rotary-wing, fixed-wing and unmanned aerial vehicles.

ANS-510 consists of strapdown inertial measurement  unit, system processor unit, power supply unit, Embedded GPS Receiver (EGR) and chassis. EGR is capable of tracking space vehicles simultaneously and transmitting the line-of-sight (LOS), position and velocity information to the system processor. The system processor combines the GPS data with the inertial data from IMU in a tightly coupled mechanization using Kalman filter. ANS-510 is capable of using either SAASM compliant GPS receiver or commercial SPS GPS receiver as embedded GPS receiver. ANS-510 also has capability to operate with an external GPS receiver. In case of external GPS, system processor combines the GPS data with the inertial data in a loosely coupled mechanization.

ANS-510 supplies linear acceleration, linear and angular velocity, position, attitude and heading to the host vehicle systems continuously. ANS-510 provides a hybrid (inertial GPS) navigation solution, inertial only navigation solution and a GPS only navigation solution simultaneously. ANS- 510 is also capable of using external pressure altitude data to complement hybrid and inertial only navigation solutions.

Important Features

System Interfaces

  • MIL-STD-704 Compliant 28VDC Power Interface
  • RS422 Asyncronous Serial Interfaces
    1. Test Port Serial Interface, User Port Serial
  • MIL-STD–1553B Interfaces, dual redundant
  • ARINC 429 Interfaces
  • External GPS Interface
  • Have Quick and 1PPS Interface
  • KYK–13 Interface
  • Active and Passive RF Antenna Interface
  • Discrete Interfaces

System Operational Modes

  • Initialization
  • Alignment

In Flight Alignment (IFA)

Gyro Compass (GC) Alignment

Stored Heading Alignment

  • Directional Gyro (DG)
  • Navigation

Hybrid Navigation (HNAV)

Inertial Navigation (INAV)

  • Initiated Built In Test (IBIT)

System Functions

  • Hybrid, Free Inertial, GPS Only Navigation Solution
  • Magnetic Variation, Wind Speed and Direction Calculation
  • Motion Detection Function
  • Zero Velocity Update, Position Update
  • Vertical Channel Hold
  • Flight Control Filters
  • Alignment Progress Status
  • GPS Lever Arm, Reference Point Lever Arm Correction
  • Start-Up BIT, Periodic BIT, Commanded BIT
  • Field Programmable Software

Navigation Performance

 Free InertialHybrid (INS+GPS)
Position  
Horizontal0.8 nm/hr CEP10 m (CEP)
Altitude< 45 m(1)16 (PE)
Velocity  
North, East0.8 m/s (rms)0.03 m/s  (rms)
Vertical0.6 m/s (rms)0.03 m/s  (rms)
Attitude  

 

Roll, Pitch

0.05 deg (rms)

 

0.02 deg       (rms)

Azimuth0.07 deg(2) (rms)0.02 deg(3)  (rms)
  1. With Baro Aiding. %1.5 (rms) for Altitude>3 km.
  2. With 4 minute ground alignment at 45 degree Latitude. 3- With sufficient aircraft maneuvers.

 Alignment Durations

 

Ground Alignment ModeGPS In-Flight Alignment ModeStored Heading Mode
4.0 min10.0 min30 sec

Environmental Conditions

  • MIL-STD-810 Compliant

Electromagnetic Conditionss

  • MIL-STD-461 / DO-160E Compliant

Dimensions and Weight

  • ~ 26cm x 19cm x 15cm (including connectors)
  • Less than 6.2 kg with GPS receiver installed