Opening Slide

Report
Brownout Situational Awareness Upgrade
(BSAU) For CH-47D & UH-60 A/L
1
2
Briefing Agenda
• BSAU Background
• BSAU Symbology Development
& Hardware Details
• BSAU Testing
• BSAU Lessons Learned
3
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
4
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:
1. Allowed successful degraded visual
environment DVE take-offs and
landings
2. Minimized lateral drift and descent
rate at touchdown to prevent aircraft
damage
3. Prevented spatial disorientation by
eliminating pilot induced oscillations
(PIO)
4. Allowed controlled approach angle to
selected touchdown point
5
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)
6
BSAU Symbology Development
BSAU Symbology
• Detect Aircraft Attitude/Movement During Loss of Visual
References
• Cockpit and Heads Up Displays
• Exploits Existing Equipment (MH-47/60, CH-47F,& UH60M)
• Common B-Kit Components for CH-47D & UH-60A/L
MFD (2 each)
EGI (one each)
New
HMD
(2 each Flat
Day HUD)
MH-47/60
CH-47F/UH-60M
Compatible w/ ANVIS-7
Night HUD
7
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
8
BSAU
Architecture
EGI
EGI
On/Off
Switch
4 to 1
GPS
Antenna
Splitter
ASN-128B
Doppler
ARINC
575
Circuit
Breaker
Circuit
Breaker
PDP
Zeroize
Switch
28VDC, 3 A
ARINC
429
PDP
28VDC, 1 A
MFD-255M
Circuit
Breaker
PDP No. 1
MFD-255M
Circuit
Breaker
PDP No. 2
ARINC
429
ARINC
429
28VDC, 7.5 A
ARINC
429
28VDC, 7.5 A
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
UH-60 Dual
Function GoAround Button
HSI Mode
Select
HUD SDC
APN-209
RADALT
Day
HMD
VOR
ADF
Day
HMD
UH-60 Dual Function
Go-Around Button
ASN-43
COMPASS
9
BSAU Symbology Development
Symbology Definition
Waypoint Fly-To
Distance
Compass Arc
Heading Bug
Hover ACP
Roll Pointer
Velocity
Range Ring Label
Velocity
Vector
Ground Speed
Readout
Horizon Line
Heading Select
DGNS Waypoint
Acceleration Cue
Vertical Speed
Indicator Scale
Velocity Range
Ring
Radar Altitude
Scale
Mode of Flight
10
BSAU Symbology Development
Symbology Set Evolution
11
BSAU Symbology Development
12
BSAU Symbology Development
HSI Symbology Definition
1
2
3
4
10
11
12
13
14
5
6
15
7
8
16
9
18
1. 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
17
9. Selected Heading
10. Ground Speed
11. Bearing Pointer #2
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
13
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
14
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
15
BSAU Phase I
Iterative Symbology Development
Engineering Page
Declutter Page
16
BSAU Phase II
HQR Results
MFD With Full EGI – 32,650 LBS GWT
Pilot
Hover
Hover
Landing
Hover
Turn
Vertical
Maneuv
Slope
Normal
Takeoff
ITO
Appch &
Landing
GoAround
Lateral
Recover
1
5
5
5
5
6
4
5
5
5
5
2
5
4
5
5
5
3
5
5
4
4
3
5
3.5
5
5
4
4
4
4
3
4
AVG
5
4.1
5
5
5
3.6
4.6
4.6
4
4.3
5
5
5
5
5
5
4.5
5
5
5
4
4
4
5
1
5
4
6
2
5
4
5
MFD/INU Only - Degraded EGI
6
4
5
4.5
4
MFD With Full EGI – 40,000 LBS GWT (Medium Weight)
2
4
4
5
5
6
4
5
MFD With Full EGI – 48,000 LBS GW (Heavy Weight)
4.5
5
5
5
4
HUD With Full EGI – 32,650 LBS GWT
2
5
4
Pilot
Hover
Hover
Landing
Hover
Turn
Vertical
Maneuv
Slope
Normal
Takeoff
ITO
Appch &
Landing
GoAround
Lateral
Recover
1
5
5
5
5
6
4
5
5
5
5
2
5
4
5
5
5
3
5
5
4
4
3
5
3.5
5
5
4
4
4
4
3
4
AVG
5
4.2
5.2
5.8
5.5
4.3
4
4.8
4.3
4.6
17
BSAU Phase III Testing at Yuma Proving Ground
CH-47D Brownout Landing
18
BSAU Phase III Testing at Yuma Proving Ground
CH-47D Brownout Take-Off
19
BSAU Phase III Testing at Yuma Proving Ground
UH-60L Brownout Landing
20
BSAU Phase III Testing at Yuma Proving Ground
UH-60L Brownout Take-Off
21
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
22
Questions?
23

similar documents