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Athena 511 Integrated Flight Control System
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Athena 511

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Athena 511 Integrated Flight Control System

Overview

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.

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Contacts

Sales
GS Customer Support
800-321-2223
319-295-5100 Email

Features & Benefits
Specifications
Typical System
Related Documents
Training
Services & Support

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
Make a selection:
> Performance
> Physical Specs
> Power
> Environmental

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/h¹
Maximum Angular Rates ± 200 deg/s

Attitude Heading Accuracy in Degrees (1 Sigma):
PERFORMANCE GYRO
IN-RUN BIAS STABILITY		 PITCH, ROLL
WITH GPS		 PITCH, ROLL
GPS DENIED		 HEADING
WITH GPS		 HEADING,
GPS DENIED		 MAXIMUM G
RANGE (ALL AXES)
1 deg/h 0.057 0.3 0.1* 1** ± 37 gs
3 deg/h¹ 0.1 0.3 0.1* 1** ± 37 gs
*In maneuvering flight
**In steady state, using an adequate external magnetic field measurement
¹3 deg/h is the standard model

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
Electrical Power:
Power input is 18-36 VDC; power consumption is 17 W nominal. 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 μs, 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 μF, 20% between 28 V+ and 28 V RETURN.
Operating Temperature -40 to 70 deg C
Operating Vibration MIL-STD-810
Humidity MIL-STD-810

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/h¹
Maximum Angular Rates ± 200 deg/s

Attitude Heading Accuracy in Degrees (1 Sigma):
PERFORMANCE GYRO
IN-RUN BIAS STABILITY		 PITCH, ROLL
WITH GPS		 PITCH, ROLL
GPS DENIED		 HEADING
WITH GPS		 HEADING,
GPS DENIED		 MAXIMUM G
RANGE (ALL AXES)
1 deg/h 0.057 0.3 0.1* 1** ± 37 gs
3 deg/h¹ 0.1 0.3 0.1* 1** ± 37 gs
*In maneuvering flight
**In steady state, using an adequate external magnetic field measurement
¹3 deg/h is the standard model

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
Electrical Power:
Power input is 18-36 VDC; power consumption is 17 W nominal. 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 μs, 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 μF, 20% between 28 V+ and 28 V RETURN.
Operating Temperature -40 to 70 deg C
Operating Vibration MIL-STD-810
Humidity MIL-STD-810

Type

Part Number

Description

Athena 511

GS511-30X-002

     

GPS antenna

172-00008-000

Lab ready

GPS antenna

172-00007-000

Flight ready

User's Manual 523-0020175-001 is available upon request.

We offer a wide range of training courses suitable for both individuals and groups. These courses can be aimed at varying levels from basic user operation to complex fault finding. Field service engineers can visit your facility to conduct training courses.

Contact a representative

Make a selection:
> Field Support Services
> Tailored Services
> Maintenance & Repair
Dedicated Field Service Engineers are there to respond to your support requirements. If technical assistance is needed, troubleshooting and on-site support are available to meet your needs. Contact a representative

Rockwell Collins is at the industry forefront when it comes to working with customers to develop and employ affordable logistics solutions throughout the product life cycle.  Our established 24/7 global service and support capability, over 80 worldwide locations, and over 3,200 dedicated employees provides original equipment manufacturer (OEM) quality service, logistics and field support. 

Rockwell Collins Performance Based Logistics (PBL) delivers the best combination of commercial best practices with proven logistics expertise to support challenging and ever-changing military operational requirements. PBL solutions ensure guaranteed performance for the warfighter and predictable maintenance costs.

Contact a representative

Rockwell Collins facilities and capabilities allow us to offer a variety of support solutions from time and material repairs to fully integrated performance based logistics via both Contractor Logistics Support (CLS) and Public Private Partnerships (PPP). The end result is increased operational readiness for the warfighter. Contact a representative

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