A new type of ultra-high temperature probe at the aero-engine afterburner outlet has been independently developed to address the problem of difficult measurement of high-temperature airflow parameters at the outlet of aircraft engine afterburner combustion chambers. The ultra-high temperature probe solution is composed of a new type of ultra-high temperature resistant CMC-SiC silicon carbide ceramic matrix composite material as the main body，with a tungsten tube as the protective sleeve of embedded platinum rhodium thermocouple. We conducted preliminary verification tests such as airtightness and ablation tests on the main material of the probe，tensile tests on high-temperature bonding adhesive，and fatigue vibration tests on the entire probe. Finally，the ultra-high temperature probe was installed and passed the ground bench test inspection. The experiment results show that the ultra-high temperature probe can work normally under the full boost state of the engine，and the highest temperature measured at the outlet measuring point of the boost combustion chamber under full boost state is 1 680℃，which is comparable to the theoretical calculation value. The successful application of ultra-high temperature probe has improved the level of ultra-high temperature measurement for aviation engines，providing technical support for the improvement of flight test methods and design improvements for subsequent aviation engine afterburner combustion chamber flight tests.