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Octantis 2 AHRS is a high performance Attitude and Heading Reference System for airborne applications. The model OCT2 AN5300S AHRS has been designed as per the DO-254 standards and qualified as per MIL-STD-461E and MIL-STD-810E/F and G standards. The AHRS software has been tested through a rigorous IV&V process and certified as per DO-178B level B standards. The AHRS system has been accorded the CEMILAC (Indian Airworthiness) certification. The unit meets the performance requirements as per the RTCA-DO-334 minimum operating requirement standards. 

 

The AHRS is an airborne qualified system and can be used as a primary or standby instrument in electronic flight instrumentation systems, cockpit displays in a wide range of fighter, transport and passenger aircrafts. It can be used for autonomous control applications in unmanned aerial vehicles. Check out the exhaustive list of qualification tests cleared by Octantis 2 AHRS to see coverage as per your airborne platform.

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Product Features

High Reliability System

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Airworthiness Certified with Redundant Sensor Configuration.

Software Certification

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Software independently verified and validated in accordance with DO178B Level B with 100% MC-DC coverage.

External True Air Speed (TAS) aiding

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Accepts external TAS data for velocity aiding to deliver unmatched performance in high dynamics of fighter aircraft.

Commination Interface

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Standard isolated Serial RS422, RS232 interfaces and isolated power supply input including lightening protection.

Device Diagnostics

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Complete Continuous Built in Test provides extensive health of the device including sensor and power supply health.

Power Consumption

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Low Power system (<2.5 W) based on MEMS technology ensures no need of external and internal cooling.

External Magnetometer Interface

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Facilitates to choose the external magnetometer data to avoid degradation caused by nearby systems.

TSO Compliant Performance

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Benchmarked performance complying with TSO for flight instrumentation and attitude indication suitable for a wide array of aircraft.

Low Noise Sensors

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Best in class MEMS sensors with excellent bias instability for consistent and accurate attitude and heading data.

Technical Specifications

  • Accelerometer
  • Gyroscope
  • Magnetometer
  • Performance
  • Communication
  • Electrical Specifications
  • Electrical Qualifications
  • Environmental Qualifications
  • Mechanical
  • Electrical Qualifications
Range
±12 g
Bias Instability
10mg
Resolution
1 mg
Range
±450 °/s
Bias Instability
2 °/h
Range
± 4 guass
Bias Instability
10 mguass
Roll Range
±180°
Pitch Range
±90°
Roll/Pitch Accuracy
< ±1° (Static), < ±2.5° (Dynamic),
Heading Range
±180° / 0-360°
Heading Accuracy
< ±1° (Static), < ±2.5° (Dynamic),
Resolution
0.01°
Serial I/O Ports
RS422, RS232
Connector
M24308/3-2F or Equivalent
Update Rate
50 Hz,
Baud Rate
38400 (RS-422), 9600 (RS-232)
Protocol
Binary
External Inputs
True Air Speed (TAS), Magnetic Field, Pressure Altitude
Output Parameters
Euler angles, Body Accelerations, Euler Rates, BIT (Built-In-Tests)
Operating Voltage
12 VDC - 32 VDC
Power Consumption
< 2.5 W
CE102, Conducted Emission
MIL-STD-461E, Basic Curve
RE102, Radiated Emission, Electric Field
MIL-STD-461E
RS103, Radiated Susceptibility, Electric Field
MIL-STD-461E, 60V/m,
CS101, Conducted Susceptibility, Power Leads
MIL-STD-461E, Limit Curve #2
CS114, Conducted Susceptibility, Bulk Cable Injection
MIL-STD-461E, Limit Curve #3
CS115, Conducted Susceptibility, Bulk Cable Injection, Impulse Excitation
MIL-STD-461E
CS116, Conducted Susceptibility, Damped Sinusoidal Transient, Cable and Power Leads
MIL-STD-461E, Imax = 5A
Random Vibration
MIL-STD-810F, Method 514.5C-17, Procedure I, Category 12
High Temperature Ground Survival
MIL-STD-810G, Method 501.5, Procedure I
Ground Operation Short Term
MIL-STD-810G, Method 501.5, Procedure II
Ground Operation Long Term
MIL-STD-810G, Method 501.5, Procedure II
Low Temperature
MIL-STD-810G, Method 502.5, Procedure I
Low Pressure (Altitude)
Clause 3.2.1.4, JSS55555: 2000, Revision No. 2
Humidity
MIL-STD-810F, Method 507.4
Acceleration
Structural, MIL-STD-810G, Method 513.5, Procedure I Operational, MIL-STD-810G, Method 513.5, Procedure II
Shock Survival
MIL-STD-810E, Method 516.4 Procedure I
Transit Drop
MIL-STD-810F, Method 516.5, Procedure IV
Thermal Shock
MIL-STD-810F, Method 503.4
Drip
MIL-STD-810F, Method 506.4, Procedure III
Fungus
MIL-STD-810F, Method 508.5
Fluid Contamination
MIL-STD-810F, Method 504.1
Corrosion Salt Fog
MIL-STD-810E, Method 509.3
Dimensions (mm)
148 (L) x 115 (W) x 63 (H)
Weight, gm
900, ±20
Operating Temperature
-40 °C to +71 °C
Storage Temperature
-55 °C to +90 °C
MTBF
41900 hours at 30°C, 16300 hours at 55°C, As per Part Stress method of MIL-HDBK-217, Notice F
Power Supply
MIL-HBDK-704-8

Applications

Flight Data Recorder (FDR)

High Performance IMU data for Aircraft FDR

Cockpit display

Redundant Attitude information for aircraft

Drone Navigation

Reliable navigation data for drone

Documents & Softwares

Q & A

What interfaces are available on Octantis AHRS?

Octantis AHRS has RS232 and RS422 interfaces for communication.

What standards does the Octantis AHRS comply with?

Octantis AHRS hardware is tested as per MIL standards 461E or F, 810F or G and software is tested in compliance with DO-178B level B

What features does AHRS have for reliability?

Octantis AHRS has redundant sensors for reliability and performance.

What lifecycle support is available for AHRS?

Octantis AHRS is supported for long operational life of 20 years

User Manual