AVCOAT

AVCOAT 5026-39 is a NASA code for two versions of a specific ablative heat shield material originally created by Avco for the Apollo program.^[1]^[2]^[3] It is composed of silica fibers in an epoxy novolac resin. The original AVCOAT was used for the Apollo Command Module heat shield. A reformulated version was used for the initial Orion heat shield and later for a redesigned Orion heat shield.

History

AVCOAT was used for the heat shield on NASA's Apollo command module.^[4] In its final Apollo form, this material was called AVCOAT 5026–39.

Although AVCOAT was not used for the Space Shuttle orbiters, NASA again used the material for its Orion spacecraft^[5] first for the initial Orion test and then for a different type of heat shield for the later Orions. The Avcoat used on the two types of Orion shield was reformulated to meet environmental legislation that was enacted after the end of Apollo.^[6]^[7]

Specifications

Material: epoxy phenol formaldehyde resin with special additives originally for use in a fiberglass honeycomb matrix.^[8]
Density: 32 pounds per cubic foot (0.51 g/cm³)^[8]
Post-ablation char-layer composition: 6.7 pounds per cubic foot (0.107 g/cm³) of carbon and 8 pounds per cubic foot (0.13 g/cm³) of silica.^[8]

AVCOAT-based heat shields

Apollo Command Module

AVCOAT was first used on the parts of the Apollo spacecraft orbiter and as a unit attached to the crew module. The heat shield is a honeycomb structure filled with the AVCOAT. NASA confirmed that this is made of silica fibers with an epoxy novolac resin filled in a fiberglass-phenolic manufactured directly onto the heat shield.^[9]^[10] The paste-like material was gunned into each cell of the fiberglass honeycomb individually.^[11]

NASA's Apollo Flight Test Analysis, AVCOAT 5026-39/HC-G material was tested on the nose cone of a Pacemaker sounding rocket.^[12] The temperature and ablation measurements were made at four locations on the nose cap. The report noted that the wear of the shield is due to the aerodynamic shear and heating rate. The report also noted that scientists believed that the ablation was done in a controlled manner.

Orion EFT-1 Crew Module

To protect the Crew Module during Earth re-entry, the dish shaped AVCOAT heat shield ablator system was selected. NASA announced that this module will encounter temperature as high as 5,000 degrees Fahrenheit (2760 °C).^[13] Licensed by Textron,^[14] AVCOAT material is produced at New Orleans's Michoud Assembly Facility by Lockheed Martin. This heat shield will be installed at the base of the crew module to provide a controlled erosion moving heat away from the crew module into the atmosphere. This process of erosion is called "ablation" - where materials are removed by vaporization or erosion by continuous contact with the supersonic velocity of gas flow and high temperature; thus the construction of honeycomb structure was made.

John Kowal, Orion's thermal protections systems manager at Johnson Space Center, discussed the biggest challenge with AVCOAT has been reviving the technology for manufacturing with similar performance as demonstrated in the Apollo Missions.^[13] After the Apollo missions, Avcoat variants were produced and studied. Orion Chief Engineer requested the heat shield to be redesigned,^[15] however the final design was not selected.

The Orion Crew Module was first designed for the NASA's Constellation program. The first test of this capsule was the EFT-1 flight. The heat shield was manufactured similarly to the Apollo version as a monolithic fiberglass honeycomb which was then filled with the AVCOAT.

The EFT-1 mission performed two orbits of Earth providing the opportunity for Orion's systems to be tested. It took about four hours with the splash down in the ocean.^[16] This was the only flight with this heat shield.

Orion Artemis Crew Module

After the end of the Constellation program, Orion was adapted for use with the Space Launch System to replace the Space Shuttle program. This spacecraft was planned to take astronauts to the International Space Station (ISS) in 2015 and to the moon in 2024. However, Orion was never used for ISS. Its first flight after EFT-1 was the uncrewed Artemis I, which flew in 2022.

Manufacture of the EFT-1 heat shield was labor-intensive and there were concerns that the monolithic honeycomb design was inappropriate for the large Orion shield. Therefore, the shield was redesigned to use carefully shaped Avcoat blocks instead.

The AVCOAT material heat shield went through several rounds of testing before being chosen for the installation. During the investigation of the thermochemical response of Avcoat TPS (based on first principles for comparison with EFT-1 data), things being tested on the heat-shield included: modeling of gas transport, heat transfer, and TPS material regression.^[17]

Orion's 16.5 feet AVCOAT heat shield was secured onto the Orion Crew Module using 68 bolts by Technicians at NASA's Kennedy Space Center (KSC) in Florida. This heat shield is covered in titanium truss and a composite substitute with an addition skin made of carbon fiber layers. Orion's heat-shield was designed and manufactured by Lockheed Martin. The heat shield is like pieces of a puzzle that all must fit together perfectly and the bolt fittings must be lined up.^[14]

After the heat-shield's installation, access to components of the crew module became difficult or no longer accessible.

Flight use

Uncrewed

Several subscale test flights^[8]^[4]
AS-201^[4]
AS-202^[4]
Apollo 4^[4]
Apollo 6^[4]
EFT-1
Artemis 1

Crewed

Apollo 7, Apollo 8, Apollo 9, Apollo 10
Apollo 11, Apollo 12, Apollo 13, Apollo 14
Apollo 15, Apollo 16, Apollo 17
Skylab 2, Skylab 3, Skylab 4
Apollo–Soyuz Test Project

References

^ Wilson, Jim. "NASA - NASA's Exploration Systems Architecture Study -- Final Report". www.nasa.gov.
^ "Fire-Resistant Reinforcement Makes Steel Structures Sturdier". January 12, 2007. Archived from the original on 2007-01-12.
^ Textron Systems History Archived November 30, 2010, at the Wayback Machine, 1984 History, "Textron acquires Avco, including Lycoming, to become Avco Systems Textron", 2010, accessed 2010-11-27.
^ ^a ^b ^c ^d ^e ^f Apollo Experience Report - Thermal Protection Subsystem (Jan. 1974)
^ "NASA - NASA Selects Material for Orion Spacecraft Heat Shield". www.nasa.gov.
^ "Flightglobal.com - NASA's Orion heat shield decision expected this month (Oct 3, 2009)".
^ "Company Watch - NASA. - Free Online Library". www.thefreelibrary.com.
^ ^a ^b ^c ^d FLIGHT-TEST ANALYSIS OF APOLLO HEAT-SHIELD MATERIAL USING THE PACEMAKER VEHICLE SYSTEM NASA Technical Note D-4713, pp. 8, 1968-08, accessed 2024-10-29. "Avcoat 5026-39/HC-G is an epoxy novolac resin with special additives in a fiberglass honeycomb matrix. In fabrication, the empty honeycomb is bonded to the primary structure and the resin is gunned into each cell individually. ... The overall density of the material is 32 lb/ft³ (512 kg/m³). The char of the material is composed mainly of silica and carbon. It is necessary to know the amounts of each in the char because in the ablation analysis the silica is considered to be inert, but the carbon is considered to enter into exothermic reactions with oxygen. ... At 2160° R (1200° K), 54 percent by weight of the virgin material has volatilized and 46 percent has remained as char. ... In the virgin material, 25 percent by weight is silica, and since the silica is considered to be inert the char-layer composition becomes 6.7 lb/ft³ (107.4 kg/m³) of carbon and 8 lb/ft³ (128.1 kg/m³) of silica."
^ Prucey, Rachel; Clem, Kylie. "NASA Selects Material for Orion Spacecraft Heat Shield". NASA News. NASA. Archived from the original on April 11, 2009. Retrieved 3 April 2019.
^ "Aerothermodynamics HEOMD Projects". Nasa.gov. Retrieved 20 August 2020.
^ [1]
^ Graves, Randolph A.; Witte, William G. (August 1968). "Flight-Test Analysis of Apollo Heat-shield Material Using the Pacemaker Vehicle System" (PDF). NASA Scientific and Technical Information (STI) Program. D (4137): 11–12. Retrieved 3 April 2019.
^ ^a ^b Clem, Kylie; Clem, Rachel (April 7, 2009). "NASA Selects Material for Orion Spacecraft Heat Shield". NASA News Release. NASA. Retrieved 2 April 2019.
^ ^a ^b Herridge, Linda. "Heat shield install brings Orion spacecraft closer to space". SpaceDaily. KSC News. Retrieved 2 April 2019.
^ Hoffpauir, Daniel. "An Alternate Orion Heat Shield Carrier Structural Design". NASA News. NASA. Retrieved 29 April 2019.
^ Kramer, Miriam. "NASA's 1st Orion Spaceship Gets World's Largest Heat Shield (Photos)". Space.com. Retrieved 3 April 2019.
^ Levin, Deborah. "Investigating the Thermochemical Response of Avcoat TPS from First Principles for Comparison with EFT-1 Data". NASA News. University of Illinois, Urbana-Champaign. Retrieved 3 April 2019.

External links

[1] Wilson, Jim. "NASA - NASA's Exploration Systems Architecture Study -- Final Report". www.nasa.gov.

[2] "Fire-Resistant Reinforcement Makes Steel Structures Sturdier". January 12, 2007. Archived from the original on 2007-01-12.

[3] Textron Systems History Archived November 30, 2010, at the Wayback Machine, 1984 History, "Textron acquires Avco, including Lycoming, to become Avco Systems Textron", 2010, accessed 2010-11-27.

[Exp-4] ^ ^a ^b ^c ^d ^e ^f Apollo Experience Report - Thermal Protection Subsystem (Jan. 1974)

[Sel-5] "NASA - NASA Selects Material for Orion Spacecraft Heat Shield". www.nasa.gov.

[6] "Flightglobal.com - NASA's Orion heat shield decision expected this month (Oct 3, 2009)".

[7] "Company Watch - NASA. - Free Online Library". www.thefreelibrary.com.

[nasa196808-8] FLIGHT-TEST ANALYSIS OF APOLLO HEAT-SHIELD MATERIAL USING THE PACEMAKER VEHICLE SYSTEM NASA Technical Note D-4713, pp. 8, 1968-08, accessed 2024-10-29. "Avcoat 5026-39/HC-G is an epoxy novolac resin with special additives in a fiberglass honeycomb matrix. In fabrication, the empty honeycomb is bonded to the primary structure and the resin is gunned into each cell individually. ... The overall density of the material is 32 lb/ft³ (512 kg/m³). The char of the material is composed mainly of silica and carbon. It is necessary to know the amounts of each in the char because in the ablation analysis the silica is considered to be inert, but the carbon is considered to enter into exothermic reactions with oxygen. ... At 2160° R (1200° K), 54 percent by weight of the virgin material has volatilized and 46 percent has remained as char. ... In the virgin material, 25 percent by weight is silica, and since the silica is considered to be inert the char-layer composition becomes 6.7 lb/ft³ (107.4 kg/m³) of carbon and 8 lb/ft³ (128.1 kg/m³) of silica."

[9] Prucey, Rachel; Clem, Kylie. "NASA Selects Material for Orion Spacecraft Heat Shield". NASA News. NASA. Archived from the original on April 11, 2009. Retrieved 3 April 2019.

[10] "Aerothermodynamics HEOMD Projects". Nasa.gov. Retrieved 20 August 2020.

[11] [1]

[12] Graves, Randolph A.; Witte, William G. (August 1968). "Flight-Test Analysis of Apollo Heat-shield Material Using the Pacemaker Vehicle System" (PDF). NASA Scientific and Technical Information (STI) Program. D (4137): 11–12. Retrieved 3 April 2019.

[2009-04-07-13] Clem, Kylie; Clem, Rachel (April 7, 2009). "NASA Selects Material for Orion Spacecraft Heat Shield". NASA News Release. NASA. Retrieved 2 April 2019.

[SpaceDaily-14] Herridge, Linda. "Heat shield install brings Orion spacecraft closer to space". SpaceDaily. KSC News. Retrieved 2 April 2019.

[15] Hoffpauir, Daniel. "An Alternate Orion Heat Shield Carrier Structural Design". NASA News. NASA. Retrieved 29 April 2019.

[16] Kramer, Miriam. "NASA's 1st Orion Spaceship Gets World's Largest Heat Shield (Photos)". Space.com. Retrieved 3 April 2019.

[17] Levin, Deborah. "Investigating the Thermochemical Response of Avcoat TPS from First Principles for Comparison with EFT-1 Data". NASA News. University of Illinois, Urbana-Champaign. Retrieved 3 April 2019.

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