View this post on Instagram
Episode 4 will be out next week on Tuesday, February 5th! Stay tuned for the latest episode of my ‘Day in the Life of an MIT Aerospace Engineering Student’ series where I go out to the desert to see my friend, Sam test fire his liquid oxygen rocket engine! This is my biggest production yet with footage from more than 5 cameras, and I’m really excited to share this one with all of you. Have that notification bell clicked!
Video Caption: In this video, I talk about how my friend and I conducted a static fire testing of his Liquid Oxygen and Kerosene rocket engine. We tested it at the Friends of Amateur Rocketry site in the Mojave Desert in Southern California. I give some insight into the entire AeroAstro program (Course 16) at MIT, talk about Unified Engineering, our flight competitions, as well as dealing with the stresses of college. I talk about how to stay in the proper mental state to navigate college as well. Please share this video if you liked it!
What a way to start the year! MIT Rocket Team have certainly set the mark for others to follow with the test of their new P motor. Yielding a 15 % performance increase from last year’s tests, delivering a peak thrust of 12,632 N, specific impulse of 74,042 Ns over a burn time of 8 seconds. The motor is intended to power the team’s Hermes II rocket to ~86,000 ft, which will serve as the first stage for a space shot attempt in 2020.
Video Caption: This is the team’s third P motor test, and our most successful one to date. Using only 3 grains, the motor’s volume loading increased. The new propellant formula burned slower, and with better specific impulse. All combined, our various improvements yielded 15% higher performance than last year. We are preparing to fly this motor in March.
Video Caption: Mixing over 290 lbs of propellant for 236,380 Ns of Impulse, the MIT Rocket Team has one of the premier student propulsion teams on the planet, and we’d like to recognize the countless hours they’ve put into their work. Producer: Sam A.
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.
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.
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…