heat-shield for extreme entry environment (heeet) a game ... · compared to that of heritage carbon...
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Presented by: E. Venkatapathy, !Advanced EDL Materials Project Manager / Game Changing Development Program!
Chief Technologist, Entry System and Technologies Division !NASA Ames Research Center!
!HEEET Project Manager: D. Ellerby!
Leads: M. Stackpoole, K. Peterson and P. Gage!Team Members: A. Beerman, M. Blosser, R. Chinnapongse, R.Dillman, !
J. Feldman, M. Gasch, M. Munk, D. Prabhu and C. Poteet !OPAG Meeting, January 13-14, Tuscon, AZ!
Heat-shield for Extreme Entry Environment (HEEET) !A Game Changing Thermal Protection System !
for Saturn and Uranus Probe Missions !
OBJECTIVES!
Ø Enable!q Discovery and New Frontier proposal teams to have a relatively mature TPS
solution that will pass TMCO evaluation !q Development of heat-shield technology (HEEET) by 2016 for infusion into
future robotic in situ-science missions. !
Ø Engage!q The OPAG and potential PIs/proposing organizations so that they are both
stakeholders and partners in the technology maturation phase!
Ø Ensure!q User requirements are balanced by developmental risk and cost!q The user community understands infusion challenges beyond technology
maturation!
Ø Inform!q The community on current accomplishments and future plans of HEEET!
2!
ENABLING OUTER PLANET MISSIONS IN THE COMING DECADES!
Ø Saturn (and Uranus) in situ science mission(s)!q Missions studied prior to and in support of Decadal Survey !
u Probes based on Galileo Design (rigid aeroshell with TPS)!q Revive heritage carbon phenolic, or!q Develop advanced TPS that is superior in performance to HCP and
sustainable in the longer term!
Current ablative TPS State of the Art ! 3!
ENABLING OUTER PLANET MISSIONS IN THE COMING DECADES!
Ø Saturn (and Uranus) in situ science mission(s)!q Missions studied prior to and in support of Decadal Survey !
u Probes based on Galileo Design (rigid aeroshell with TPS)!q Revive heritage carbon phenolic, or!q Develop advanced TPS that is superior in performance to HCP and
sustainable in the longer term!Ø Under 3-D Woven TPS Effort!
q Combining the advance weaving techniques and resin infusion, we were able to create a family of ablative TPS!
q Heat-shield for extreme entry environment technology (HEEET)!
4!
BACKGROUND: WOVEN TPS!
Ø In FY’12, established viability of the 3-‐D Woven TPS. q Explored the “10,000” manufacturing ways of formulaKng a TPS q AblaKve TPS opKons, dry-‐woven as well as resin infused systems, ranged in
density from (0.3 g/cc – 1.4 g/cc) in overall density q Highlighted the Woven TPS potenKal for meeKng the mission needs of Venus,
Saturn and High-‐speed Sample Return Missions (VEXAG 2012 & OPAG 2013)
OPAG (& VEXAG) recommendaKon to SMD-‐PSD & the resulKng advocacy and support by SMD-‐PSD were criKcal in securing 3-‐year project currently funded by STMD/Game Changing Development Program
Ø HEEET - 3-D Woven TPS Family!q Woven TPS: An approach to the design and
manufacturing of abla;ve TPS by the combina;on of 3-‐D weaving that allows precise placement of fibers in an op;mized manner and resin infusion if needed
5!
FYʼ13 ACCOMPLISHMENTS!
Ø Manufactured and Tested a variety of Woven TPS!q Density range from PICA to
heritage CP!
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0.4
0.6
0.8
1.0
1.2
1.4
1.6
AVCOAT 3-D Woven CP
Fully Dense
Carbon Phenolic
Dual Layer Carbon
Phenolic
Fully Dense 3-D Woven
(low phenolic infusion)
Dry Woven Carbon
Phenolic
Den
sity
(g/c
c)
(different resins)
Woven TPS Heritage TPS KEY
PICA
6!
A BRIEF HISTORY WOVEN TPS TECHNOLOGY: WOVEN TPS TECHNOLOGY MATURATION AND MISSION INSERTION!
Apr
il 20
11!
Woven TPS GCT BAA!
Jan.
201
2!
June
, 201
2!
3-D Woven Multifunctional !Ablative TPS (3D-MAT)!
2017!
Heat-shield for Extreme Entry !Environment Technology (HEEET) !
Oct
, 201
3!
2020
- 20
22!
Tech. Maturation to enable Venus, Saturn and outer
planets missions !
Robust Heat-shield for Human Missions !(Future Potential)!20
16+!
Enabling Orion with Lunar !Capable Compression Pad!
2022
+!
Sept
. 201
6!
7!
FYʼ13 ACCOMPLISHMENTS!
Ø Manufactured and Tested a variety of Woven TPS!
Ø Down-selected a single architecture.!q Based on testing, analysis,
performance characteristics, developmental risk and cost!
Recession Resistant Layer!
Insulating, Lower !Density Layer!
Bonded Structure!
8!
FYʼ13 ACCOMPLISHMENTS!
Ø Manufactured and Tested a variety of Woven TPS!
Ø Down-selected a single architecture.!
Ø Defining TRL 5/6 with community/user input and buy-in!q Held a workshop ( 95+
participants)!q Common capability to meet
Venus, Saturn and other destinations defined with the help of and understanding of the participants!
q Capability requirements verification defines the TRL maturity!
!
Venus!
Saturn!
High-speed !Sample Return!
Ground Test !Capability!Woven TPS !
Technology!
Human !Missions!
9!
FYʼ13 ACCOMPLISHMENTS!
Ø Manufactured and Tested a variety of Woven TPS!
Ø Down-selected a single architecture.!
Ø Defining TRL 5/6 with community/user input!
Ø Developed 3-year technology maturation project plan!
Ø Secured funding and approval from STMD for the technology maturation efforts ( FYʼ14 – FYʼ16)!
Ø User Agreement under development!
Goal: Deliver a TRL 5/6 !Heat-shield Technology in 3 years!
10!
SATURN Probe Design Space!Entry Corridor : Equatorial and a 600 N/S !
Entry Flight Path Angles: -80 and -190!
Mass = 250 kg; Probe Dia. = 1 m!
Equatorial!
600 N/S!
Stag
. Hea
t Flu
x, k
W/c
m2!
Pressure, atm.!
Steeper Entry (-19°) !Shallower Entry ( -8°)!
600 N/S Equat.!
IHF - 6 inch Nozzle!
SATURN Probe Design Space & Ground Test Facility Conditions !Entry Corridor : Equatorial and a 600 N/S !
Entry Flight Path Angles: -80 and -190!
Mass = 250 kg; Probe Dia. = 1 m!St
ag. H
eat F
lux,
kW
/cm
2!
Pressure, atm.!
AEDC (Wedge)!
Pressure, !atm.!IHF – 3” Nozzle!
1” Iso-Q Test Article!Steeper Entry (-19°) !Shallower Entry ( -8°)!
600 N/S Equat.!
FYʼ13 Arc Jet Testing !
IHF 3” Nozzle!1” Flat Face Article!
ARC JET TEST RESULTS – TWO LAYER SYSTEM!
• Both acreage and preliminary seam concepts tested at three relevant conditions.!• No failure observed in these or other relevant arc jet tests to-date. !• HEEET appears to be very robust compared to carbon phenolic. !
13!
SATURN PROBE AREAL MASS COMPARISONS !
• Areal mass of the 2-layer system has the potenital for ~ 40% mass savings compared to that of heritage Carbon Phenolic!
• Un-margined; preliminary estimate with very limited property data!
• Carbon Phenolic heat-shield mass estimates ~ 50% of the entry mass!• Performance combined with anticipated robustness makes HEEET an
exceptional TPS!
Equatorial @ -90! Equatorial @ -190! Lat. 600 @ -190!Lat. 600 @ -90!
14!
SATURN PROBE THICKNESS COMPARISONS !
• Un-margined HEEET thickness ( 0.80” – 1.4”)!• ~20% thicker compared to heritage carbon phenolic!
• Thickness impacts cost, schedule and is a risk drivers for technology maturation. !• Question to the Saturn Community: !
• Equatorial and steeper entry will result in lowest thickness and areal mass!
• Are there scientific rationale for high latitude? How high? !• Are there Con Ops requirements that dictate entry angle? Steeper or shallower? !
0.00!
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0.40!
0.60!
0.80!
1.00!
1.20!
1.40!
1.60!
Weave #1!
Weave #3!
Carbon Phenolic!
Weave #1!
Weave #3!
Carbon Phenolic!
Weave #1!
Weave #3!
Carbon Phenolic!
Weave #1!
Weave #3!
Carbon Phenolic!
G8H90! G19H90! G8H30! G19H30!
Thic
knes
s, in!
Recession Layer!
Insulative Layer!
Equatorial @ -190!Equatorial @ -90! 600 Lat. @ -90! 600 Lat. @ -190!
15!
URANUS MISSION DESIGN COMPARISONSAREAL DENSITY COMPARISONS!
• 2-layer system can result in potential ~ 50% mass savings compared to Carbon Phenolic for the range of entry configurations considered for Uranus small probe(s)!
• Un-margined and based on very limited property data!• Simulation on a flank location comparison is very similar in that the zero-margin areal
density is ~ 50% as that of Carbon Phenolic 16!
URANUS MISSION DESIGN COMPARISONSTHICKNESS COMPARISONS – STAGNATION POINT!
• HEEET thickness is comparable to that of Carbon Phenolic for the range of entry configurations considered for Uranus small probe(s)
• Simulation on a flank location comparison is very similar in that the zero-margin thickness is comparable to that of Carbon Phenolic
• Comparing Saturn and Uranus Probes, Saturn is the driver for thickness • Are there Uranus specific drivers for a technology maturation effort – TBD ?
• We need to engage with the Science and mission design communities as the opportunity is here and now for the TPS technology
0
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1
1.2
HEEET #1 HEEET #3 Carbon Phenolic
HEEET #1 HEEET #3 Carbon Phenolic
HEEET #1 HEEET #3 Carbon Phenolic
Entry Angle: 68 deg Entry Angle: 42 deg Entry Angle: 24 deg
Th
ick
nes
s, i
n
Recession Layer
Insulative Layer
TECHNOLOGY MATURATION CHALLENGES!
Ø System/Manufacturing q Molding flat panels
q Seams q Resin Infusion at scale
Ø IntegraKon q Aeroshell sub-‐structure and with backshell
Ø Flight System design tools development and verificaKon q Thermal response model is an example of design tool needed q Engineering Test Unit – ~(1.0m – 1.5m) Base Diameter, 45° Sphere Cone
– Design will be proven at a smaller scale that is applicable for larger scale – Smaller likely compared to Venus lander missions such as VITaL
– Integrated “Kled” design
Successful ETU design, build and testing = TRL 5/6 (for full scale Venus, Saturn and higher speed sample return missions)
18!
CONCLUDING REMARKS!Ø FYʼ13 has been a great year!
q Successful testing, analysis and planning along with community advocacy resulted in HEEET project becoming a funded, 3-year tech. mat. effort!
Ø Current project plan is aggressive!q Numerous tech maturation challenges need to be overcome!q Dialogue between STMD and SMD-PSD!q NASA (STMD) developed technology infusion in a SMD competed mission !
Ø HEEET is a game changer and applicable to a wide range of missions !q Critical for near, mid and longer term Science missions as well as longer term Human
missions !u Saturn and Venus for the next New Frontier!u Uranus – we need to work with the Uranus community!
Ø Continued community engagement is a must: !
q Through OPAG-VEXAG-other Ags. – Plan to report progress (annual basis) !q Workshop, targeted towards near proposal community (Discovery and New
Frontier), on an annual basis is planned (at a minimum)!q Dialogue between HEEET and proposing organizations/proposal teams on
an on-going and as needed basis is underway!19!
ACKNOWLEDGEMENTS!
!Ø Support and commitment of STMD, GCDP within STMD and SMD-
PSD allowed us to mature our plans in FYʼ13. We are very grateful.!
Ø We are grateful to OPAG and look forward to continued advocacy for HEEET!
Ø Bally Ribbon Mills, our partner in this effort, has shown extraordinary commitment and willingness to explore the myriad of possibilities.!
20!