Marc Katra – CES III COR & Program Manager (G) Dick Dickson – Tri-Service GPS SMO IPT Lead

1. Tri-Service GPS Sustainment Management Office (GPS SMO)Hill Geodetics GPS Receiver (HGGR) Development & Test Activities17th ITEA Test Instrumentation WorkshopMay 2014 Marc Katra – CES III COR & Program Manager (G) Dick Dickson – Tri-Service GPS SMO IPT Lead

2. Background • Hill AFB, AFLCML/HBZC & SMXS/MXDED organizations needed to identify a Form Fit Function Interface (FFFI) replacement for the obsolete Rockwell Collins GNP-10TM GPS Receiver Navigation Unit. • Utilized in the AN/ASQ-T38C P4R1 and AN/ASQ-T27B P4BE airborne instrumentation pods. • Also utilized in the AN/ASQ-T50 P5 airborne instrumentation pod. • Identified Geodetics Incorporated as the vendor to produce this FFFI GNP-10TM replacement. • Developed a comprehensive Performance Work Statement (PWS) • Utilized the Tri-Service GPS Sustainment Management Office (GPS SMO) to execute this development.

3. Background • Utilized an existing Tri-Service GPS SMO subcontract with Geodetics CES III-12-040 • Official start date was February 2013 • Utilized an existing Geodetics GEO-iNAV GPS receiver • Repackage the GEO-iNAV • Decided to utilize the existing DIGS GPS receiver mechanical housing as the primary mechanical form factor • Add Selective Availability Anti-Spoofing Module (SAASM) • Convert GEO-iNAV message format to GNP-10TM message format

4. HGGR Design Concept

5. Background • Hill and the GPS SMO reviewed the current GNP-10TM messages utilized by the P4R1, P4BE, and P5 Advanced Digital Interface Units (ADIU). • Initially identified 10 messages. • 3418: GPS Sensor Measurements • 3434: RAJPO Differential SV Corrections • 3500: System Status • 3502: System Delta Velocity and Delta Theta • 3503: BIT Summary / Software Configuration • 3504: GNP Parameter Control • 3560: Extended Receiver Control and Initialization • 3561: Combined TSPI Output • 3562: Auxiliary TSPI Output • 6000: Battery Voltage

6. Current Status • Decided to put message 3434 RAJPO Differential SV Corrections on hold. • This message is not utilized by the training pods • Only used in the T&E ARDS pods • $50K required to finish implementing this message – Unfunded T&E requirement • Geodetics on contract to deliver 4 first article receivers to Hill AFB and 4 first article receivers to the P5 program office at Eglin AFB for testing and evaluation. • Mechanical/Electrical design is complete. • SAASM integration is complete • Two first article units compete – remainder scheduled for delivery in June 2014.

7. HGGR First Article Units

8. HGGR First Article Units HGGR TSPI Processor HGGR Internal Data Recorder HGGR SAASM GPS Module

9. HGGR First Article Units

10. Current Status • Message format conversion is 95% complete • Minor issues remain with the Control Display Unit (CDU) Receiver BIT pass/fail displays. • The HGGR is working correctly but not providing the correct output to the ADIU on one specific message. • All other message data formats, data output, and TSPI solutions appear to be working correctly. • Initial In-house testing complete. • Two 1st article units delivered for Environmental Stress Screening (ESS)

11. Current Status • ESS and GPS simulator testing conducted at the U.S. Army’s Fort Huachuca, Electronic Proving Ground (EPG) in Sierra Vista, Arizona. • Testing included EMI/EMC, High/Low Temperature, Shake & Vibration, and GPS Simulator Lab testing. • The HGGR passed all tests. • A Spirent GSS8000 GPS Signal Simulator with a 16-Channel L1+L2 C/A & Y-code capability was utilized. • The Spirent also had an inertial measurement simulation capability. • Simulated a Honeywell HG1700 IMU • Simulated a Northrop Grumman LN-200 IMU

12. Current Status • GPS simulations included the following scenarios: • High dynamic flight profile previously recorded on high dynamic accuracy testing conducted in Germany. • Prime Meridian Crossing. • Equator Crossing. • North & South Pole Crossing. • GPS Epoch (Week 1023-0) Transition. • These simulator scenarios were also conducted on a GNP-10TM and a DIGS receiver and compared to the results of the HGGR under the same testing scenarios. • An equator scenario was run on the HGGR during all high/low temperature testing and shake and vibration testing.

13. HGGR ESS – Sim Lab Testing

14. HGGR ESS – Sim Lab Testing

15. HGGR ESS – Sim Lab Testing

16. HGGR ESS – Sim Lab Testing

17. HGGR ESS – Sim Lab Testing

18. HGGR ESS – Sim Lab Testing

19. HGGR ESS – Shake & Vibration

20. HGGR ESS – Shake & Vibration

21. HGGR ESS – Shake & Vibration

22. HGGR ESS – EMI/EMC

23. HGGR ESS – EMI/EMC

24. HGGR ESS – EMI/EMC

25. HGGR ESS – EMI/EMC

26. HGGR ESS – EMI/EMC

27. HGGR ESS – Temperature Testing

28. HGGR ESS – Temperature Testing

29. HGGR ESS – Temperature Testing

30. Current Status • Low and high dynamic flight testing scheduled to be conducted at Nellis AFB in June or July (depending on aircraft availability and test schedule availability) is on hold pending flight clearance approval. • Need to conduct mass properties measurements at China Lake • Documentation due after government acceptance of first article units that is yet to be delivered by Geodetics includes: • Interface Control Document (ICD). • Operations and Maintenance Manuals. • Source code for all message conversion work. • Mechanical/Electrical drawings resulting from the Geo-iNAV repackaging into the DIGS form factor.

31. Summary • The HGGR is being designed as a SAASM based Form Fit Function Interface replacement for the Rockwell Collins GNP-10TM GPS Receiver. • Development, including mechanical and electrical, is complete. • Software is 95-98% complete with minor CDU interface issues remaining. • Initial first article units have passed all required Environmental Stress Screening. • Remaining 6 first article units scheduled for delivery in June 2014. • Government flight testing will be scheduled after flight clearances are received.