CAS-SPACE recently completed a 180-second hot fire test of the Kinecore-1 kerolox engine.

CAS-SPACE aims to conduct a 100km VTVL test flight of the reusable Lihong-2 rocket later this year.

CAS-SPACE is hot-firing the 30-ton thrust Kinecore-1 kerolox engine.

The Lihong-2 rocket is powered by a cluster of three Kinecore-1 engines.

The Kinecore-1 kerolox engine will power the Lihong-2 reusable rocket for suborbital space science experiments and tourism.

The 59th meeting of the Space Development Utilization Committee's Investigation and Safety Subcommittee was held.

The meeting focused on the launch of the H3 rocket's 8th unit.

Distributive materials related to the meeting were published.

The catastrophic failure of the payload attach fitting (PAF) occurred shortly after the fairing pyrotechnics fired.

The failure investigation is focused on the payload attach fitting (PAF).

Telemetry data indicates a catastrophic failure of the payload attach fitting (PAF).

JAXA is certain that the QZS-5 satellite was flung out of the rocket after MECO.

Temperature sensor readings on the PAF went off-scale high.

Rocket camera footage supports the findings from the accelerometer data.

The accelerometers show readings consistent with a loss of signal approximately 2.5 seconds after the MECO signal issuance.

The axial accelerometer shows abnormally low acceleration in the quarter of a second after fairing separation.

At fairing separation, the normal shock from pyros firing is present.

Multiple abnormal peaks were recorded in the yellow zone for the next 2 seconds after fairing separation.

The pitch and yaw accelerometers showed lesser peaks in the yellow zone, indicating axial direction movement.

A physical collision was sensed on the PAF.

The pyro firing signal was followed by movement within 0.1 seconds.

The exterior MLI layer of the satellite was ripped off, exposing its interior panels.

The forward-looking rocket camera captured the satellite leaning at a significant angle after PAF damage.

The flight F8 exhibited a payload leaning to one side in the final 75 seconds of the first stage flight.

The 2nd stage of the rocket had a first burn that was 5% longer than planned.

The engine thrust during the 2nd stage first burn was 20%-35% lower than planned.

The second stage LH2 pressurization pipeline was damaged by the PAF at fairing separation.

Temperature sensors are located on the satellite separation plane and inside the PAF.

Both temperature and gas pressure drop after fairing separation.

The yellow zone temperature and pressure drop is believed to be a result of a collision involving PAF.

The temperature and gas pressure inside the second stage LH2 tank decrease in the yellow zone.

The FTPV is a gas helium regulating valve that pressurizes the LH2 tank before second stage ignition.

The FTPV was constantly open after fairing separation to maintain LH2 pressure.

The FTPV was unable to maintain LH2 pressure after fairing separation.

The voltage acting on the FTPV was shown as a lighter blue line.

The PAF suffered catastrophic failure from the fairing separation shock.

The payload was severely damaged during the failure.

The second stage pressurizing feed line was damaged.

MECO and stage separation occurred approximately 1 minute and 15 seconds after the incident.

The second stage engine failed to restart.

LH2 pressure on the second stage kept decreasing until the engine thrust decayed.

The second stage ignited with nothing left on top after the satellite was detached.

The PAF cracked and caused the satellite to be flung away.

Potential causes of the accident include improper PAF installation, a manufacturing or design flaw of the PAF, and mechanical resonance.

The inner pressure at fairing separation or a fairing collision may have contributed to the accident.

An investigation is ongoing into the failure reason behind a bizarre accident involving the PAF.

The accident may also involve combustion of unknown origin.

JAXA indicates that they might have lost the entire QZS-5 satellite at some point.

JAXA's further analysis indicates that the payload adapter was damaged during fairing separation in the H3-F8/QZS-5 launch.

Initial analysis from JAXA suggests that the failure started at fairing separation with abnormal accelerations measured on the payload adapter.