- 6 in
- hybrid rocket diameter
- 3
- thermal-response measurements
Chamber-liner application
Ablation, char, and heat penetration
Columbia Space Initiative’s six-inch hybrid rocket requires phenolic chamber liners and a repeatable way to evaluate them. The work connected material preparation and mechanical interfaces to the measurements needed to judge thermal protection.
CSI Rocketry website
Open website ↗The liner and its interfaces
The chamber-liner design includes nozzle-transition bonding, where the material and mechanical interface both affect performance. Fabrication included molds, resin-mixing procedures, and regression-test rigs.
A repeatable process matters because inconsistent specimens make test results hard to compare. The test program established the team’s first reproducible method for evaluating ablation, char formation, and thermal penetration.
Thermocouple instrumentation and data acquisition
Heat-flux tests use thermocouples, MAX31855 interfaces, and Arduino data acquisition. The aim was to connect the observed condition of a specimen with its thermal history, so the next design decision could be based on measurements.
Explore the CSI · Ablative liners geometry in 3D ↗
Illustrative cutaway chamber liner, referencing the documented thermal-protection work.
Context & sources
Project records and published references provide the context below.
3D study: Illustrative cutaway chamber liner, referencing the documented thermal-protection work.