MIT Rocket Team Hermes 1 Launch

Of note, this was the second largest university built rocket motor and the largest rocket flown by the MIT team!

Video Caption: MIT Rocket Team flew Hermes 1 on July 21, 2018 at the Friends of Amateur Rocketry site in California. Hermes 1 weighed 121 lbs at liftoff, and flew on an student developed O4300 that delivered the vehicle to 32,400 ft above the Mojave Desert. A newly developed piston based recovery system deployed a disk-gap-band parachute we based on the design from the Viking landers. At 2,000 ft above the desert floor the main parachute was extracted by the drogue, allowing for a safe landing 1.8 miles from the launch site. The student build carbon composite fin can fared well during the flight. The rocket flew a payload developed at the University of Victoria as part of an inter-team collaboration to study DNA repair mechanisms in microorganisms.
The team is grateful to our many industry sponsors, the many mentors we’ve had along the way, and our peers at other universities for their insight and friendship during this launch campaign, and we look forward to returning to IREC in 2019.

P-13000 Failure

Big ups to the MIT Rocket Team team for posting this and sharing their experience. We can all learn from this, but most importantly no one was hurt or injured. A testament to having good safety protocols in place.
Looking forward to seeing the issues resolved, and future testing carried out.

Video Caption: At T+ 2.9s a combination of insufficient grease, poor polyurethane application, and inconsistent assembly technique lead to a catastrophic burn through of the thermal liner in the middle of grain 4.

The motor self extinguished at the catastrophic loss of pressure, but the propellant which remained in the motor reignited several seconds later due to residual heat.

This test did not endanger any people. Always use care when testing rockets.

MIT Rocket Team – P19000 Full Video

As reported earlier, this test happened at the end of February, this is the full video of the days activities.

Video Caption: On Feburary 23, 2018 the MIT Rocket Team burned our first P-Motor. The motor delivered full impulse, despite ejecting parts of the thermal liner for the first and second grains, which burned out early as intended.

Higher than expected combustion efficiency yielded a faster burn and higher pressure than expected. Details here: http://rocketry.mit.edu/2018/02/p-190…

MIT Rocket Team P19000 Motor Test

The MIT Rocket Team recently tested their first ‘P’ class rocket motor (Wikipedia has a good table on the class ranges) at the end of February.

… This test produced 65,077 Ns at a peak pressure of 1440 psi and 22,970 N of thrust.

For all my imperial unit readers, that is 5163lbf of thrust, but the test did not go entirely to plan with the motor ejecting several thermal liners during the burn.
The team states,

…As the design pressure and thrust of this motor were greatly exceeded, we think it likely that aluminum combustion (triggered by the increased residency time in a longer motor) lead to the unplanned increase in burn rate, the increase in combustion pressure, and then triggered the cascade of failures.

The motor did well to hold up, of which I look forward to the next test. This size motor will propel the teams Hermes rocket to 80,000ft in June at Spaceport America.

You can read the team’s full update here.

MIT Rocket Team N3000 Static Fire

From Facebook,

Ignition! The teams first monolithic finocyl motor set team records for highest thrust and highest efficiency, peaking at 6800 N of thrust and 224.2 s of isp.

The team is really pushing forward with their work on solid rocket motors, great to see so many frequent tests on variously sized motors.

I expect to see good things at this rate of progress!

MIT Rocket Team 2nd O3800 Static Fire

Motor Stats
Size: O3800
Pc: 816 PSI (5.6 MPa)
ISP: 209s
Impulse: 31703Ns
Thrust (max): 5221 N (1173.7 lbf)

Follow the team here.

MIT Rocket Team Test O-3500 Motor

Updated 17/1/2018 with YouTube video

More team details can be found here.