You are not logged in.
This topic is offered for NewMars members who might like to contribute to a collection about Carbon structures used in the context of space flight.
Post #3 opens with a summary by Google. The summary includes details of temperature range of Carbon and manufacture;
Vehicle designers have to decide between various materials.
There are advantages and disadvantages to each material.
For humans who like to argue, there is plenty to argue about, when choosing materials for a project.
(th)
Offline
Like button can go here
This post is reserved for an index to posts that may be contributed by NewMars members over time.
Index:
#3 - summary of carbon-carbon by Google on 2025/09/08
(th)
Offline
Like button can go here
This post contains a snapshot prepared by Google on 2025/09/08 ...
Details may change slightly as new advances are reported, but the history should remain consistent.
The term "carbon-carbon" refers to a lightweight, yet incredibly strong and heat-resistant composite material used on the Space Shuttle. The repeated name reflects its composition: it is made of carbon fibers embedded in a matrix of pure carbon (graphite).
This advanced material, known technically as Reinforced Carbon-Carbon (RCC), was crucial for protecting the shuttle's most vulnerable areas from the intense heat of atmospheric reentry.
Why carbon-carbon was used
Exceptional heat resistance
The reentering Space Shuttle experienced temperatures reaching up to 3,000°F (1,650°C) on its nose cap and wing leading edges. RCC was used in these areas because:
Its constituent element, carbon, is the most refractory material known, with a sublimation temperature of 3,825°C.
It has superior mechanical strength even at very high temperatures, unlike metals which would weaken and melt.
Lightweight and durable
Weight is a critical factor in aerospace, and RCC provided excellent thermal protection without a massive weight penalty. It is significantly lighter than the high-temperature metal alloys that would otherwise be required for a heat-sink type of thermal protection system. It was also fatigue-resistant, which was essential for a reusable spacecraft.
Structural and protective functions
RCC was not just an outer coating; it was a structural component itself. It formed the aerodynamic shape of the wing leading edges and nose cap while also functioning as the thermal barrier. This dual role simplified construction compared to other methods.
Oxidation protection
Carbon can oxidize (burn) in high-temperature air. To prevent this, the outermost layers of the RCC were infused with silica and converted into a silicon carbide coating. This coating would form a thin, glassy layer that protected the underlying carbon structure during reentry.How carbon-carbon was made
The material was not a simple molded block, but a composite created through a multi-stage process:
Layering: Carbon fiber fabric was impregnated with a phenolic resin and arranged in alternating layers.
Pyrolysis: The composite was heated to extremely high temperatures, which converted the resin into pure carbon. This left the material with voids and a lower density.
Densification: The voids were filled over several days by forcing a carbon-forming gas through the material at high temperature. This repetitive process was very long and contributed to the material's high cost.
(th)
Offline
Like button can go here