Thermal Protection System of the Gaganyaan Crew Module
Science and Technology / Space · Friday, 21 August 2026
Gaganyaan’s Thermal Protection System is an external shielding layer designed to protect the crew module from extreme aerodynamic heating during hypersonic atmospheric re-entry. Its ablative materials absorb heat, form an insulating char layer and release gases that reduce convective heat transfer.
Quick highlights
- More than 99% of re-entry kinetic energy is converted into intense shock-layer heating.
- Gaganyaan’s TPS is about 30–35 mm thick and is designed to keep structural temperatures below 150°C.
- Ablative materials undergo endothermic decomposition and shed heated mass.
- The char layer insulates the material beneath the exposed surface.
- Outgassing helps push the hot plasma boundary away from the capsule.
- The design draws on technologies validated through SRE and LVM3/CARE.
Context
As ISRO prepared the uncrewed flight-test sequence for Gaganyaan, aerospace experts explained the crew module’s Thermal Protection System and its role during high-speed atmospheric re-entry.
Key Facts
The shield faces temperatures reaching about 1,800°C but is only 30–35 mm thick, keeping the underlying structure below about 150°C. The forward shield uses high-density carbon phenolic tiles, while the side and afterbody panels use medium-density silica phenolic or other ablative tiles.
Significance
TPS protects the crew, habitable environment and aluminum-alloy or CFRP structural frame during rapid deceleration. Its passive and autonomous operation is essential because atmospheric descent cannot be aborted and heating changes too rapidly for manual intervention.
Challenges / Way Forward
The system must tolerate peak heat flux, stagnation pressure, turbulent wake heating and possible impact damage while minimizing mass. Gaganyaan uses a robust single-use ablative composite instead of fragile reusable ceramic radiative tiles.
Exam Angle
Focus on ablative versus radiative thermal protection, pyrolysis, char formation, outgassing, hypersonic re-entry and the technological lineage from the Space Capsule Recovery Experiment and CARE mission.
Remember this
- Peak re-entry temperature cited for Gaganyaan: about 1,800°C.
- TPS thickness: approximately 30–35 mm.
- Target structural temperature: below 150°C.
- The nose shield uses high-density carbon phenolic material.
- Side panels use medium-density silica phenolic or ablative tiles.
- Pyrolysis is an endothermic decomposition process.
- CARE stands for Crew Module Atmospheric Re-entry Experiment.
- CARE was flown with LVM3 in 2014.
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