The Rockwell Collins Athena 511 meets the stringent requirements of today?s unmanned aerial vehicle and military applications with a short time to market and low lifecycle cost. Offering a fully integrated inertial navigation system (INS), GPS, air data/attitude and heading reference system (ADAHRS), the Athena 511 combines inertial sensors and software processing to provide a single-box flight control system.
The unit includes embedded air data transducers, a magnetometer and an analog input for sampling outside air temperature. It gives you a GPS-aided INS to produce inertial attitude, velocity and rates plus air data measurements that comprise a complete state vector of the vehicle.

Our Athena 511 meets MIL-SPEC environmental requirements, including for temperature, shock, vibration, EMI, power and humidity. You can adapt the unit?s software to interface to your specific vehicle systems for control or monitoring using the unit?s I/O capabilities. We also can host our autopilot and 3-D navigation algorithms so you can adapt them to control many different vehicle configurations such as fixed-wing, V-tail, T-tail, propeller- or jet-powered aircraft. An external magnetometer unit, sold separately, can interface with the Athena 511 if required.

Key Features & Benefits
*Tactical grade IMU (1 or 3 degrees per hour)
*Differential ready, WAAS-enabled GPS receiver
*Built-in air data systems pressure transducers including static, airspeed and flow angle measurements
*Full INS and attitude solution
*Accurate roll, pitch and heading in dynamic maneuvers and sustained turns
*Kalman filter INS provides high accuracy navigation and control state vector

Specifications

Performance
INS/GPS Performance:
Update Rate: 100 Hz
Start-up Time: 10 seconds (initial attitude); 1 minute (full alignment)
Heading Range: ? 3.14 rad (? 180 deg)
Attitude Range Pitch: ? 1.57 rad (? 90 deg)
Attitude Range Roll: ? 3.14 rad (? 180 deg)
Altitude Range: -304.8 to 15,240 m (-1,000 ft to 50,000 ft) standard; other custom ranges are available
Baro-inertial Altitude Accuracy: 13.7 m (45 ft) at sea level, 91.4 m (300 ft) at 15,240 m (50,000 ft) altitude
WGS 84 Referenced Altitude Accuracy : GPS receiver accuracy (C/A or alternate GPS)
GPS Range: Worldwide (C/A or alternate GPS)
Lat/Long Position/Velocity Accuracy: GPS receiver accuracy
GPS Antenna Power: 5 V, or 3.3 V, selectable
Airspeed Accuracy: < 2 knots @ 40 knots, < 1 knot @ 60 knots
Max Airspeed: 165 knots standard, 120 and 650 knots available
Angle of Attack Range: ? 0.139 rad (? 8 deg) at max airspeed
Angle of Sideslip Range: ? 0.139 rad (? 8 deg) at max airspeed

Input/Output:
Outside Air Temperature : Input
Program and Maintenance Serial Port: (1) PPP service port (RS-232)
Serial Ports: (1) INS port (RS-422) baud: 230.4 kb/s (3) Spare (RS-422)
Discrete Inputs: (2)
Discrete Outputs : (2)

IMU Performance:
Rate Gyro Bias: 1 or 3 deg/h?
Maximum Angular Rates: ? 200 deg/s

Physical Specs
Size - without mounting bracket :< 15.5 x 15.5 x 15.5 cm (< 6.1 x 6.1 x 6.1 in)
Weight: < 2.7 kg (< 6 lb)
Enclosure: Aluminum
Power: 17 W nominal @ 18-36 VDC

Power
Electrical Power: Power input is 18-36 VDC; power consumption is 17 W nomi
nal. Power characteristic interfaces are designed in accordance with MIL-STD-704F.
CAUTION: INPUT POWER CURRENT LIMITING IS NOT PROVIDED INTERNAL TO THE UNIT. WE RECOMMEND THAT THE INPUT POWER BE CURRENT LIMITED TO 5 AMP RATING.
Input Voltage: The unit operates off 18-36 VDC input power (28 VDC system)
Power Consumption: The power consumption is 17 W nominal.
Inrush Current: When power is applied to the unit, a large inrush current occurs to charge the capacitors in the input power conditioning circuitry. Peak current is 47 A for ~300 ?s, then drops to 20 A for ~1.3 ms. After 1.6 ms, a nominal current of ~470 mA is obtained. Input capacitance is 3300 ?F, 20% between 28 V+ and 28 V RETURN.

Environmental
Operating Temperature: -40 to 70 deg C
Operating Vibration: MIL-STD-810
Humidity: MIL-STD-810