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.
MIL-STD-704 Compliant 28VDC Power Interface
RS422 Asyncronous Serial Interfaces
Test Port Serial Interface, User Port Serial
MIL-STD–1553B Interfaces, dual redundant
ARINC 429 Interfaces
External GPS Interface
Have Quick and 1PPS Interface
Active and Passive RF Antenna Interface
System Operational Modes
In Flight Alignment (IFA)
Gyro Compass (GC) Alignment
Stored Heading Alignment
Directional Gyro (DG)
Hybrid Navigation (HNAV)
Inertial Navigation (INAV)
Initiated Built In Test (IBIT)
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
Free Inertial Hybrid (INS+GPS)
Horizontal 0.8 nm/hr CEP 10 m (CEP)
Altitude < 45 m(1) 16 (PE)
North, East 0.8 m/s (rms) 0.03 m/s (rms)
Vertical 0.6 m/s (rms) 0.03 m/s (rms)
0.05 deg (rms)
0.02 deg (rms)
Azimuth 0.07 deg(2) (rms) 0.02 deg(3) (rms)
With Baro Aiding. %1.5 (rms) for Altitude>3 km.
With 4 minute ground alignment at 45 degree Latitude. 3- With sufficient aircraft maneuvers.
Ground Alignment Mode GPS In-Flight Alignment Mode Stored Heading Mode
4.0 min 10.0 min 30 sec
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