This viewgraph presentation gives a general overview of the NASA Langley Research Center's activities including aeronautics, aerospace sciences, and space exploration

DelCorso, Joseph A.

NASA Technical Reports Server

NASA Langley Research Center
https://ntrs.nasa.gov/search.jsp?R=20080034697 2019-08-30T05:22:17+00:00Z
Exploration
MISSE Wing Leading Edge Impact Detection Mission Management Support
Launch Abort SystemFlight Test Articles Ares I Aero Characterization     
Habitat Structures & MaterialsLunar & Mars Architectures Landing Systems
National Aeronautics and Space Administration
Science
Advanced InstrumentsMission Concepts Space based Missions  -  
CALIPSO A Train Algorithm Development-  
Field Missions Applications - Air QualityCERES - Radiation      
National Aeronautics and Space Administration
Aeronautics
Hypersonics Supersonics Fixed Wing Rotary Wing- -
Integrated Resilient 
Aircraft Control
Integrated Intelligent
Flight Deck
Integrated Vehicle 
Health Management
Aircraft Aging and 
Durability    
AirspaceAirportal Test Facilities 
National Aeronautics and Space Administration




Ares I-X Thermal
Ruth Amundsen 2008
Orion Flight Test
Joe Gasbarre, Joe Del Corso 2008
L RC h th l l d f♦ a  as erma  ea  or 
Orion flight tests (PA-1/2, 
AA-1/2/3)
T t t b d t Whit♦ es s o e one a  e 
Sands Missile Range 
(WSMR), NM
PA 1 t t h d l f♦ -  es  sc e u e or 
Spring 2009
♦AA-1 test scheduled for 
Spring 2010
Video of PA-1 Test Article showing 
diurnal shadow contours (6 AM –
7 PM LST)
PICA Thermal Testing
Salvatore Scola 2008
PICA Transient Thermal Test
PICA Vacuum Cycling Test
MEDLI Pressure Port Arc Jet Test
Walt Bruce, Kaitlin Liles 2008
PICA Models Fabricated at Langley
- Quantity = 44
- Four active pressure measurements
- Eight temperature measurements
Tested at Boeing LCAT Facility (St. Louis)
- March 8 – 21, 2008
- Tested 34 models in 13 runs     
- Test conditions match predicted flight conditions
Results
- Pressure port shape change (enlargement) greater than       
anticipated
- Cause identified as material oxidation phenomena
- Use of smaller port diameter being considered to stay under 
a maximum hole growth diameter - Science team evaluating 
t ti l i t ifpo en a  mpac   any
- Hole oxidation barriers (material liners) investigated during 
test with success
MEDLI Thermal Vacuum Testing
Kaitlin Liles, Walt Bruce 2008
Sensor Support Electronics (SSE) Mars Entry Atmospheric Data System 
(MEADS)
Interstage Thermal Protection System Sizing
Joe Gasbarre 2007
Hat-Stiffener Structural Temps, 0.25" TPS 
(with Rohacell Foam within hat section)
175
180
185
190
195
200
Mid-Web Surf
Intersta175
180
185
190
195
200
Mid-Web Surf
Intersta
Mid-cap
200
180 id-Web Surf.
Intersta
Intersta
Mid-Web Surf.
Mid Cap Surf
200
18
125
130
135
140
145
150
155
160
165
170
T
e
m
p
 
(
F
)
Mid-Cap Surf
Mid-Flange Surf
age Jettison
125
130
135
140
145
150
155
160
165
170
T
e
m
p
 
(
F
)
Mid-Cap Surf
Mid-Flange Surf
age Jettison
Mid-web
Mid-flange
Structural Temperature LimitStructural Temperature Limit
16
14
T
e
m
p
 
(
°
F
)
id-Cap Surf.
id-Flange Surf.
age Jettison
age Jettison
-  .
Mid-Flange Surf.16
14
T
e
m
p
 
(
°
F
)
80
85
90
95
100
105
110
115
120
80
85
90
95
100
105
110
115
12012
10
80
12
10
80
0 10 20 30 40 50 60 70 80 90 100 110 120 130 140
Time (sec)
0 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160
Time (sec)
0.75 in TPS Foam-filled Hat-Stiffeners - 0.25 in TPS
0         20       40        60        80     100     120     140     160
Time (sec.)
0           20         40          60         80        100        120       140
Time (sec.)
♦ A thickness of 0.75 in of TPS is required for the DAC-2 thermal loads 
with a heating amplification factor 1.17 for stringers in the flow
♦ Increasing the thickness of the stringer web decreased TPS thickness
♦ Rohacell filled hat sections adds approximately a total of 50 lbm  -        
Interstage RoCS Plume Shielding Sizing Results
Mark Thornblom 2007
BDMs
RoCS ♦ Initial RoCS plume 
shielding analysis was 
f d
Area affected by 
plume heating
per orme
♦Near ‘worst-case’ heating 
requires 1.0 in of P-50 
cork to protect substrate
700
800
Arithmetic 
node
    
from excessive heating
♦Low conductivity 
materials are desired to
400
500
600 Main.T410
Main.T310
Main.T210
Main.T110
Main.T10
    
prevent excessive 
temperature (<120°F) at 
the substrate
m
p
.
 
(
°
F
)
100
200
300T
e
m
0
0 10 20 30 40 50 60 70 80 90 100 110 120 130
Time (sec)
Program to Advance Inflatable-Decelerators for 
Atmospheric Entry (PAIDAE)
Joe Del Corso, Walt Bruce, Kaitlin Liles 2008
Inflatable Reentry Vehicle Experiment (IRVE I & II)
Walt Bruce, Joe Del Corso 2008
Vacuum Deployment Test• Flight test demonstration of inflatable 
ballute concept
• Designed analyzed integrated and, , ,  
tested by NASA Langley
• Aeroshell fabricated by ILC Dover
• Centerbody fabricated by NASA Langley    
RTD/Structures Mechanics Concepts Branch           
Thermal Analysis & Test Highlights
TPS Application: Highly Reliable Reusable Launch Systems (HRRLS)
Hypersonics Project, Fundamental Aeronautics Program
POC: Dr. Kim Bey
CEV TPS ADP Thermal Structures Testing
POC: Dr. Max Blosser
Structurally Integrated TPS Concepts
Flexure
- 4pt bend LaRC Joggle Region Local 3D Model
Entry Thermal Gradients on Shuttle Wing Leading Edge RCC Panel
POC: Dr. Sandra Walker 
Boeing Global Shell Model
Ablator
Aluminum 
Plate
Inner Load Bars
2860F
Outer Load 
BarsThermal Environmental Chamber
– Elevated/Cryogenic
Root Cause Investigation - SiC Coating Liberation in Joggle
8/12/08 LaRC RTD/SMCB Lynn Bowman


NASA Langley Research Center

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