Brownout Situational Awareness Upgrade (BSAU) For CH-47D & UH-60 A/L

Briefing Agenda BSAU Background BSAU Symbology Development & Hardware Details BSAU Testing BSAU Lessons Learned

BSAU Background Brownout History In FY 2002 and 2003 alone 3 Fatal Injuries, 29 Non-Fatal Injuries, and $59,114,234 in loss/damage attributed to Brownout Brownout Solution for CH-47 & UH-60 Moved to Army Aviation’s #3 Priority (of 200+) 02 Sep 03 – PEO AVN directed CH-47/UH-60 to develop immediate Brownout solution. Dec 03 – $8M GWOT for CH/UH Block One NRE

BSAU Background Brownout Objectives The objective of this is to evaluate and demonstrate the functionality of an Interim Brownout Solution system as installed on the CH-47D and UH-60 A/L helicopter by providing a system which: Allowed successful degraded visual environment DVE take-offs and landings Minimized lateral drift and descent rate at touchdown to prevent aircraft damage Prevented spatial disorientation by eliminating pilot induced oscillations (PIO) Allowed controlled approach angle to selected touchdown point

BSAU Background Army’s BSAU Solution Joint BSAU Chinook & Blackhawk Team AATD’s Rapid Prototyping Inclusion of OEM in design process Combined Test Team (AATD, ATTC, RTTC) AATD’s inclusion of DES and User Assessment of Block I system Joint CH/UH Crew Station Working Groups throughout design and development Improved Training (AATD’s XPs & DES IPs develop training package)

BSAU Symbology Development Detect Aircraft Attitude/Movement During Loss of Visual References Cockpit and Heads Up Displays Exploits Existing Equipment (MH-47/60, CH-47F,& UH-60M) Common B-Kit Components for CH-47D & UH-60A/L CH-47F/UH-60M EGI (one each) MH-47/60 MFD (2 each) Compatible w/ ANVIS-7 Night HUD New HMD (2 each Flat Day HUD)

BSAU Symbology Development - Cockpit Modification CH-47D Legacy Cockpit CH-47D BSAU Cockpit Legacy HSI MFD UH-60 A/L Legacy Cockpit UH-60 A/L BSAU Cockpit

4 to 1 GPS Antenna Splitter BSAU Architecture EGI EGI On/Off Switch 4 to 1 GPS Antenna Splitter ASN-128B Doppler Zeroize Switch Circuit Breaker PDP 28VDC, 3 A ARINC 575 Circuit Breaker PDP 28VDC, 1 A ARINC 429 MFD-255M MFD-255M Circuit Breaker PDP No. 2 28VDC, 7.5 A PDP No. 1 ARINC 429 ARINC 429 ARINC 429 CH-47D - New 5 position HUD Switch on Copilot's Thrust Control CH-47D - New 5 position HUD Switch on Copilot's Thrust Control HSI Mode Select HSI Mode Select UH-60 Dual Function Go-Around Button HUD SDC APN-209 RADALT UH-60 Dual Function Go-Around Button Day HMD VOR ADF ASN-43 COMPASS

BSAU Symbology Development Symbology Definition DGNS Waypoint Hover ACP Vertical Speed Indicator Scale Acceleration Cue Radar Altitude Scale Velocity Range Ring Horizon Line Ground Speed Readout Velocity Vector Roll Pointer Waypoint Fly-To Distance Mode of Flight Velocity Range Ring Label Compass Arc Heading Bug Heading Select

BSAU Symbology Development Symbology Set Evolution Reluctance to include user community in proposed symbology Doppler SNAFU Phase II – Level III handling qualities  Symbology redefine

BSAU Symbology Development

BSAU Symbology Development HSI Symbology Definition 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Lubber Line & Heading Readout 2. Distance 3. Compass 4. Compass Benchmark 5. Course Pointer 6. Lateral Deviation Bar 7. Lateral Deviation Scale 8. Soft Key Legend 12. Bearing Pointer #1 13. Vertical deviation pointer 14. Vertical deviation scale 15. Aircraft Symbol 16. To / From Indicator 17. Heading Bug 18. Selected Course 9. Selected Heading 10. Ground Speed 11. Bearing Pointer #2

BSAU Symbology Testing Phase I – Quantitative Flight Test on Hover Page Symbology and Flat Day HUD (FDH) Phase II – Qualitative Flight Test (Includes “Bagged Cockpit”) on Hover Page Symbology and FDH Phase III – Actual Brownout Landings (YPG) Phase IV – User Assessment with Hover Page Symbology and FDH HSI Certification HSI Page Functionality, Accuracy, & Sensitivity Legacy HSI Backwards Compatibility w/ A-kit RTTC EMC Testing

BSAU Phase I Quantitative Testing Instrumentation Advanced Range Data System (ARDS) Synchronized Video System ARINC Data Recorder Engineering Maneuvers Step Inputs (Longitudinal and Lateral) Low Airspeed (Longitudinal and Lateral) Climbs and Descents Hovering Turns

BSAU Phase I Iterative Symbology Development Engineering Page Declutter Page

BSAU Phase II HQR Results MFD With Full EGI – 32,650 LBS GWT Pilot Hover Landing Turn Vertical Maneuv Slope Normal Takeoff ITO Appch & Landing Go-Around Lateral Recover 1 5 6 4 2 3 3.5 AVG 4.1 3.6 4.6 4.3 MFD/INU Only - Degraded EGI 1 5 4 6 2 4.5 MFD With Full EGI – 40,000 LBS GWT (Medium Weight) 2 4 5 6 MFD With Full EGI – 48,000 LBS GW (Heavy Weight) 2 5 4 4.5 HUD With Full EGI – 32,650 LBS GWT Pilot Hover Landing Turn Vertical Maneuv Slope Normal Takeoff ITO Appch & Landing Go-Around Lateral Recover 1 5 6 4 2 3 3.5 AVG 4.2 5.2 5.8 5.5 4.3 4.8 4.6

BSAU Phase III Testing at Yuma Proving Ground CH-47D Brownout Landing

BSAU Phase III Testing at Yuma Proving Ground CH-47D Brownout Take-Off

BSAU Phase III Testing at Yuma Proving Ground UH-60L Brownout Landing

BSAU Phase III Testing at Yuma Proving Ground UH-60L Brownout Take-Off

Lessons Learned Doppler Delays – Not adequate to drive acceleration cue Use of peripheral vision contaminated results Qualitative Testing before Quantitative Testing “Ruggedness” of Data Recording Equipment Simulation may have saved money versus fly-fix-fly iterations One size does not fit all – symbol set ended up being aircraft dependent Must consider training with high tech solutions

Questions?