Thermal-Protection Materials for Spacecraft
Glavkosmos
Nonablative thermal-protection silica-fiber-reinforced materials for coating reusable spacecraft and for radio engineering-purpose articles.
Technical specifications
- Purpose
- Provision of normal thermal conditions on passing the dense atmosphere at landing, antenna assembly thermal protection.
- Year of release
- 1977
- Lead time
- Depending on the volume of an order
- Flight qualification of the product
- Yes
- Brief history of flight qualification
- Spacecraft Buran.
- Possibility to adapt the product to customer requirements
- Yes
- Shape
- blocks, shaped molded or custom -made articles
- Operating temperature
- from -60 to +1100 short-time – up to +1250
- Substrate
- Silica fiber
- Thermal conductivity at (25±5) ℃,w/mk
- up to 0.050 (for TZMK-10M and TZMK-14M) up to 0.070 (for TZMK-25M)
- Density, kg/m3
- 135-160 (for TZMK-10M, TZMK-14M) 230-280 (for TZMK-25M)
About
These thermal-protection materials are designed to provide normal thermal conditions for spacecraft, particularly during re-entry through dense atmospheres at landing, and for the thermal protection of antenna assemblies. The materials are nonablative and reinforced with silica fiber. They are available in various forms including blocks, shaped molded articles, or custom-made articles. The product was first released in 1977 and has flight heritage, notably on the Spacecraft Buran. The manufacturer offers the possibility to adapt the product to customer requirements. The materials include types such as TZMK-10(M), TZMK-25(M), and TZMK-14M, with TZMK-14M specifically for radio engineering purposes.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.