WE'VE BEEN TO MARS. MORE THAN ONCE - SPACE, SATELLITE, LAUNCH Advanced Composite Materials Selector Guide
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SPACE, SATELLITE, LAUNCH
Advanced Composite Materials Selector Guide
WE’ V E B EEN TO MA RS.
MO RE TH A N O N CE.
SPACE, SATELLITE, LAUNCH
Introduction
SPACE FLIGHT HERITAGE
With our more than 25 years of space flight heritage, TenCate Advanced Composites, part of the Toray Group, is the undisputed
leader in developing and manufacturing cutting-edge, high-reliability materials for the space market. Our products are found
on most satellites, spacecraft, and planetary rovers launched from the Western world. No other materials company offers the
pedigree, experience, or breadth of product knowledge to meet the demanding needs of the space, launch, and satellite industry.
In partnership with our customers and with a close eye to unlock the secrets of the universe. Tomorrow’s spacecraft will
evolving market needs, we have developed a comprehensive journey to more aggressive, hotter, and colder environments,
product portfolio of industry-leading resin systems for use and with greater numbers of planetary rovers and landers.
on high-modulus PAN and pitch carbon fiber and specialty TenCate’s materials are even playing a key role in sending
fabrics, as well as standard reinforcements. humans to Mars.
COMMERCIAL SATELLITES AND LAUNCH VEHICLES NEW SPACE
We continue to develop and serve our long-standing Today’s rapidly emerging New Space market is bringing new
customers, who are building ever larger telecommunications opportunities to meet material demands of mass-produced
satellites to accommodate more powerful and sophisticated satellite constellations, small launch-on-demand vehicles, and
payloads - offering higher resolution, more deployable swarms of high-flying pseudo-satellite drones. New Space
structures, and larger, more accurate reflectors. will bring internet connectivity, new science, and big data to
billions more people.
TenCate also offers a full range of products to meet the
demands of today’s heavy-lift commercial launch vehicles For more product information refer to our app,
being utilized today to send high-value missions reliably
into space. (Search for TenCate Product Selector)
our website www.tencatecomposites.com, and our online
SCIENCE AND EXPLORATION resource center for case studies and technical papers,
Our next generation materials support science missions and for our complete product portfolio, our aerospace
from ESA and NASA, going further than ever before to composite materials selector guide.
OUR OBJECTIVES
ace
Sp
and
Connecting the Furthering Reducing High reliability
To confine our attention to terrestrial matters
ce
fen
planet scientific weight
would be to limit the human spirit.
De
understanding
bus
Air
dit:
Cre
Stephen Hawking
2 | Space, Satellite, Launch Selector Guide Advanced Thermoset and Thermoplastic Composite Products for Space, Satellite, and Launch | 3
SATELLITE
Product Applications
REFLECTORS AND ANTENNAS TenCate’s space
flight-approved cyanate ester and epoxy systems
utilize high-modulus carbon fiber and specialized
weaves. These materials are designed to deliver
HEAT SINKS Composite plates and tubes are manufactured low CTE on reflectors, antennas, and deployable
with TenCate’s highly conductive pitch-based carbon fiber structures over space temperature extremes.
prepregs. These unique materials provide superior thermal
conductivity to reduce heat from electrical components.
TenCate’s prepreg systems for these applications are
designed to withstand high temperatures while providing
exceptional resistance to the effects of thermocycling. LIGHTWEIGHT HIGH TEMPERATURE THERMOCYCLE
RESISTANT STABILITY
SOLAR ARRAY, BOOMS, AND TRUSSES These satellite
applications utilize TenCate’s high-modulus carbon fibers
HIGH TEMPERATURE THERMOCYCLE
RESISTANT STABILITY that deliver low coefficients of thermal expansion (CTE), low
coefficients of moisture expansion (CME), low outgassing,
and strong radiation resistance.
LIGHTWEIGHT RIGID
PRECISION STRUCTURES TenCate materials protect the
payload during launch and resist moisture to prevent
outgassing in orbit. TenCate high-modulus PAN or pitch
based carbon fiber prepregs are utilized for strength,
stiffness, and light weight. Structures made from TenCate
products, including benches for optics and instrumentation,
withstand extreme conditions in space, including thermal
cycling, atomic oxygen, and radiation.
LOW MOISTURE THERMOCYCLE
ABSORPTION STABILITY
4 | Space, Satellite, Launch Selector Guide Advanced Thermoset and Thermoplastic Composite Products for Space, Satellite, and Launch | 5
LAUNCH VEHICLE SPACE, SATELLITE, LAUNCH
Product Applications Product Overview
BARREL ASSEMBLIES, PAYLOAD SHROUDS, AND FAIRINGS THERMOSET PREPREGS EPOXY
LOW MOSITURE
ABSORPTION
The latest generation of launch vehicles utilize TenCate’s
TOUGHENED
SATELLITE
OOA/VBO
LAUNCH
out-of-autoclave (OOA) processable prepreg systems for OUTGASSING, CTE/
SPACE/
RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS CME OR HOT/WET
cost-competitive vehicle barrel assemblies, inner and MATRIX TEMPERATURE
DATA
outer stages, payload shrouds, and fairings for weight
EX-1522 Epoxy 180°C (356°F) 2 hours at >>Excellent mechanical properties TML 0.28 %
and cost savings. 177°C (350°F) >>Good balance of properties CVCM 0.01 %
between cyanate ester and epoxy WVR 0.16 %
TML-WVR 0.12 %
TC250 Epoxy 140°C (285°F) 60 minutes at >>NCAMP qualified Wet Tg
or 180°C 88°C (190°F), >>Long out life of 60 days and the 125°C (257°F)
(356°F) with followed by ability to post cure makes it ideal
OUT-OF-AUTOCLAVE LIGHTWEIGHT
PROCESSABLE post cure 2 hours at for large structures
130°C (265°F)
RS-36 / Epoxy 181°C (358°F) 90 minutes at >>ESA qualified for solar array TML 0.4 %
RS-36-1 190°C (374°F) 177°C (350°F) >>High toughness CVCM 0.01 %
>>Low moisture absorption WVR 0.17 %
TML-WVR 0.12 %
CRYOTANKS Launch vehicle cryotanks utilize TenCate’s
TC275-1 Epoxy 164°C (327°F) 6 hours at >>Ideal for large structure Wet Tg
toughened epoxies for overwrap, resulting in high or 183°C 135°C (275°F) fabrication 136°C (277°F)
reinforcement strength. (362°F) with Optional >>Low density
177°C (350°F) post cure of >>Excellent toughness for impact
post cure 2 hours at resistance
177°C (350°F)
TC275- Epoxy 168°C (334°F) 6 hours at >>Long out time version of TC275-1
1E 135°C (275°F) >>Allows construction of thick or
STRONG
NEW Optional larger composites structures
post cure of >>OOA/VBO processable
2 hours at
STRUTS AND TUBES TenCate’s exceptionally durable and 177°C (350°F
microcrack-resistant thermosets deliver a lightweight, high- TC350-1 Epoxy 191°C (376°F) 2 hours at >>OOA/VBO processable Wet Tg
strength structure for landing leg assemblies, secondary 177°C (350°F) >>Good hot/wet properties 160°C (320°F)
tubes, and struts and conduits.
THERMOSET PREPREGS BMI
LOW MOSITURE
ABSORPTION
TOUGHENED
SATELLITE
OOA/VBO
LAUNCH
SPACE/
RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE
MICROCRACK LIGHTWEIGHT HIGH TEMPERATURE
RESISTANT RESISTANT
RS-8HT BMI 310°C (590°F) 2 hours at 177°C >>Excellent elevated temperature
(350°F) followed performance
THERMOCYCLE
STABILITY
LIGHTWEIGHT HIGH TEMPERATURE
RESISTANT
by 6 hours at >>Good toughness and moisture resistance
232°C (482°F)
HEATSHIELDS TenCate’s high-temperature cyanate ester
prepregs create lightweight, thermally stable structures.
The high char yield of these materials acts as an ablative,
protecting the structure from excessive heat.
For more product information, please refer to our app, our website www.tencatecomposites.com,
and our online resource center for case studies and technical papers.
6 | Space, Satellite, Launch Selector Guide Advanced Thermoset and Thermoplastic Composite Products for Space, Satellite, and Launch | 7
SPACE, SATELLITE, LAUNCH
Product Overview
THERMOSET PREPREGS CYANATE ESTER TENCATE MICROPLY FILM ADHESIVES EPOXY
LOW MOSITURE
LOW MOSITURE
ABSORPTION
ABSORPTION
TOUGHENED
TOUGHENED
SATELLITE
SATELLITE
OOA/VBO
OOA/VBO
LAUNCH
LAUNCH
OUTGASSING, CTE/
SPACE/
SPACE/
RESIN CURE TIME AND RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS CME OR HOT/WET DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE MATRIX TEMPERATURE
DATA
EX-1515 Cyanate 121°C (249°F) 3 hours at >>Low density TML 0.179 % RS-15H Epoxy 99°C (211°F) 6 hours at 93°C >>Low-temperature curing adhesive
Ester or 174°C 121°C (250°F) >>Resistant to microcracking CVCM 0.007 % (200°F) Alternate
(345°F) with Optional >>Low residual stress with CTE 61 ppm/°C cures are available
post cure post cure of 121°C (250°F) TC263 Epoxy 110°C (230°F) 2 hours at >>High peel strength
2 hours at 121°C (250°F) >>Ideal for metal or composite bonding
177°C (350°F)
TC310 Epoxy 157°C (315°F) 2 hours at >>Ideal composite bonding film adhesive
TC410 Cyanate 112°C (234°F) 3 hours at >>Low CTE 58.4 μm/m/°C TML 0.29 % 177°C (350°F)
Ester or 181°C 121°C (250°F) >>Extremely low CME 1205 CVCM >Ideal system for stable TML-WVR 0.12 %
FILM ADHESIVES CYANATE ESTER
LOW MOSITURE
177°C (350°F) structures
ABSORPTION
TOUGHENED
SATELLITE
OOA/VBO
BTCy-1A Cyanate 185°C (365°F) 2 hours at >>Tough CTE 77 ppm/°C
LAUNCH
SPACE/
RESIN CURE TIME AND
Ester or 207°C 177°C (350°F) >>High Tg DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE
(405°F) with Optional post
post cure cure of 60 EX-1516 Cyanate 126°C (258°F) 5 hours at >>Compatible with TenCate EX-1515 prepreg
minutes at Ester 121°C (250°F)
204°C (400°F) RS-4A Cyanate 195°C (383°F) 2 hours at >>Moisture resistant
RS-3/ Cyanate 191°C (375°F) 2 hours at >>Extensive qualification portfolio TML 0.22 % Ester or 238°C 177°C (350°F)
RS-3C Ester or 254°C 177°C (350°F) >>Low CTE, CME CVCM 0.01 % (460°F) with Optional post cure
(490°F) with Optional post >>High stability post cure of 1.5-2 hours at
post cure cure of 60 >>RS-3C is controlled flow 232°C (450°F)
minutes at version EX-1543 Cyanate 207°C (405°F) 2 hours at >>Compatible with 177°C (350°F) curing
232°C(450°F) Ester 177°C (350°F) cyanate ester prepregs
TC420 Cyanate 176°C (349°F) 3 hours at >>Good resistance to TML 0.41 % Optional post cure of >>Low shrinkage
Ester or 348°C 177°C (350°F) microcracking CVCM >Low outgassing
(658°F) with Optional post >>Capable of high-temperature WVR 0.28% 204°C (400°F)
post cure cure at service CTE 55 ppm/°C TC4015 Cyanate 176°C (349°F) 2 hours at 177°C >>Excellent high-temperature properties
260°C (500°F) >>Ideal for heat shield and Ester or 321°C (350°F) >>Compatible with TC420
ablative applications (610°F) with Optional post cure of
post cure >60 minutes at
232°C (450°F)
RTM RESINS
LOW MOSITURE
ABSORPTION
TOUGHENED
SATELLITE
OOA/VBO
TENCATE MICROPLY SYNTACTICS EPOXY
LAUNCH
LOW MOSITURE
SPACE/
CURE TIME AND
ABSORPTION
RESIN DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
TOUGHENED
TEMPERATURE
SATELLITE
OOA/VBO
LAUNCH
SPACE/
EX-1545 Cyanate 173°C (345°F) 2 hours at >>Toughened resin system with low viscosity RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE
Ester 177°C (350°F) of 140 cPs at 43°C (110°F)
>>Long pot life for complex parts EM-3 Epoxy ~116°C 60 minutes at >>High expansion (8-10 x)
RS-16 Cyanate 167°C (332°F) 2 hours at 135°C >>Low-temperature cure resin system (240°F) 121°C (250°F) >>0.64 g/cc (40 pcf) density
Ester or 231°C (275°F) followed by 2 >>Post curable for higher Tg >>Tg estimated from base resin data
(448°F) with hours at TCF4035 Epoxy 140°C (284°F) 3 hours at >>Low density 0.64 g/cc (40 pcf)
post cure 150°C (300°F) 130°C (265°F) >>Compatible with TC250, may be
EX-1510 Cyanate 193°C (380°F) 2 hours at >>Low room temperature viscosity of 150 cPs post cured for higher Tg
Ester 177°C (350°F) >>Post curable for higher Tg
For more product information, please go to our app,
or go to our product explorer at www.tencatecomposites.com/markets/space
8 | Space, Satellite, Launch Selector Guide Advanced Thermoset and Thermoplastic Composite Products for Space, Satellite, and Launch | 9
SPACE, SATELLITE, LAUNCH
Product Overview
TENCATE MICROPLY SYNTACTICS CYANATE ESTER BMC TENCATE CETEX® THERMOPLASTIC
LOW MOSITURE
LOW MOSITURE
ABSORPTION
ABSORPTION
DURABILITY/
TOUGHENED
TOUGHNESS
SATELLITE
SATELLITE
OOA/VBO
OOA/VBO
LAUNCH
LAUNCH
SPACE/
SPACE/
RESIN CURE TIME AND RESIN PROCESSING
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE MATRIX TEMPERATURE
TCF4001 Cyanate 176°C (349°F) 2 hours at >>Low density 0.38 g/cc (24 pcf) MC1100 PPS 90°C(194°F) 330°C (625°F) >>PPS based BMC
Ester 177°C (350°F) >>Fire retardant
Optional post cure MC1200 PEEK 143°C (290°F) 385°C(725°F) >>PEEK based BMC
of 60-90 minutes at >>Fire retardant
232°C (450°F)
TCF4050 Cyanate 176°C (349°F) 2 hours at >>Expanding syntactic film/core splice
Ester or 232°C 177°C (350°F) >>Density of 0.28-0.55 g/cc (17-35 pcf) For product information, please refer to our app, our website www.tencatecomposites.com,
(450°F) with Optional post cure >>Compatible with TC420 prepreg system
and our online resource center for case studies and technical papers.
post cure of 60-90 minutes at
232°C (450°F)
EM-5A Cyanate 204°C (400°F) 2 hours at >>Expansion ratio of 4 x
Ester 177°C (350°F)
Optional post cure
of 60-90 minutes at ENABLING SMAP MISSION SUCCESS ADVANCED SOLAR ADVANCED RIGID ARRAY (ARA)
232°C (450°F) Learn about Northrop Grumman’s deployable Learn about Airborne’s Advanced Solar ARA designed by
reflection dish, used in this NASA launch at Airbus Defence and Space for use in future ESA missions at
www.tencatecomposites.com/company/news. www.tencatecomposites.com/company/success-stories.
LOW MOSITURE
TENCATE MICROPLY SYNTACTICS OTHER THERMOSET MATRICES
ABSORPTION
TOUGHENED
SATELLITE
OOA/VBO
LAUNCH
SPACE/
RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE
SF-4 BMI 295°C (563°F) 2 hours at >>Low density 0.62 g/cc (39 pcf)
204°C (400°F), then >>Compatible with RS-8HT and other
6 hour post cure at BMI systems
250°C (452°F)
BMC THERMOSET EPOXY
LOW MOSITURE
ABSORPTION
TOUGHENED
SATELLITE
OOA/VBO
LAUNCH
SPACE/
RESIN CURE TIME AND
DRY Tg ONSET KEY PRODUCT CHARACTERISTICS
MATRIX TEMPERATURE
MS-1A Epoxy 164°C (327°F) 15-30 minutes >>Chopped fiber epoxy BMC with
at 138°C (280°F) high-modulus fiber
followed by post Read our case study at: www.tencatecomposites.com
cure of 1-2 hours at
titled “Solar arrays for next generation satellites”
177°C (350°F)
MS-1H Epoxy 191°C (375°F) 15-30 minutes >>Chopped fiber epoxy BMC with
at 138°C (280°F) intermediate-modulus fiber
followed by post Learn more with Composite World’s article at:
cure of 1-2 hours at “Precision design for deployable space structures” at
177°C (350°F) www.tencatecomposites.com/resources/literature
MS-4H Epoxy 191°C (375°F) 15-30 minutes >>Chopped fiber epoxy BMC with high-
at 138°C (280°F) strength (standard-modulus) fiber
followed by post
cure of 1-2 hours at
177°C (350°F)
10 | Space, Satellite, Launch Selector Guide Advanced Thermoset and Thermoplastic Composite Products for Space, Satellite, and Launch | 11LOCATIONS AND CAPABILITIES
SOLUTIONS CERTIFICATIONS
Thermoplastic composites Thermoset composites Parts manufacture ISO 9001:2008
Thermoplastic laminates Carbon free manufacturing Sales office AS9100:2015 Rev.D
Fairfield - California, United States
Morgan Hill - California, United States
Camarillo - California, United States
Nottingham, United Kingdom
Nijverdal, The Netherlands
Toulouse, France
Beijing, China
Guangzhou, China
Taichung, Taiwan
TENCATE ADVANCED COMPOSITES TENCATE ADVANCED COMPOSITES TENCATE ADVANCED COMPOSITES
18255 Sutter Blvd. 2450 Cordelia Road Amber Drive, Langley Mill
Morgan Hill, CA 95037 Fairfield, CA 94534 Nottingham, NG16 4BE UK
Tel: +1 408 465 8500 Tel: +1 707 359 3400 Tel: +44 (0)1773 530899
info@tcac-usa.com info@tcac-usa.com tcacsales@tencate.com
TCAC_SpaceLaunchComposites_V10_2018-08-27
(Search for TenCate Product Selector)
For product information, please refer to our app, our website www.tencatecomposites.com, and our online resource center for
case studies and technical papers.
©2018. All data given is based on representative samples of the materials in question. Since the method and circumstances under which these materials are processed and
tested are key to their performance, and TenCate has no assurance of how its customers will use the material, the corporation cannot guarantee these properties. TenCate®,
(TenCate) AmberTool®, (TenCate) Cetex®, and all other related characters, logos, and trade names are claims and/or registered trademarks of Koninklijke Ten Cate B.V. and/or
its subsidiaries in one or more countries. Use of trademarks, trade names, and other IP rights of Royal TenCate without the express written approval of TenCate is strictly
prohibited.
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