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

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

4. 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

5. 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

6. 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)

7. 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)

8. 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

9. 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

10. 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

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

12. BSAU Symbology Development

13. BSAU Symbology Development HSI Symbology Definition1 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

14. 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

15. 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

16. BSAU Phase I Iterative Symbology Development Engineering Page Declutter Page

17. 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

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

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

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

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

22. 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

23. Questions?