The combustion chamber is test-fitted to a half finished injector. The rocket's propellants will mix and spray out of the six orifices in the injector.

Injector and Combustion Chamber

We’ve begun to make components for the next iteration of the Pyralis engine. As this version will burn ethanol and nitrous oxide at high temperatures, we need to make the components from materials which can take the heat. The picture below shows the combustion chamber wall being fitted to a half-finished injector. Both are made…

The new spike, made of 6061 Aluminum

New Spike!

We made a new nozzle for the cold-flow rocket engine. By comparing the results of cold-flow tests performed on the two spike versions, the team is gaining valuable insights about aerospike nozzle design.

Looking up the nozzle of the Pyralis Cold Flow prototype

Cold Flow Test!

Today the MIT Rocket Team conducted a successful cold flow test of the Pyralis rocket engine prototype. We flowed compressed nitrogen gas at 4.1 MPa (600 psi) pressure through the engine’s nozzle and combustion chamber, generating about 220 N (50 lbs) of thrust force. Over the next weeks,we will continue to test the Cold-Flow prototype…

James and Ryan setting up the Test Stand in the Gas Turbine Lab

Cold Flow Test Setup

We’ve spent the past week putting the finishing touches on the Cold Flow test stand and engine. Yesterday, we moved the test stand into a blast chamber in MIT’s Gas Turbine Lab where we will conduct several Cold Flow tests of the Pyralis prototype next week. Thanks to Jimmy Letendre and Prof. Spakovszky for letting…

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Test Stand & Cold-Flow Prototypes

The test stand is finished and ready to be used for the upcoming cold-flow test.                               Connie L, James L, Eric R, and Matt V finished machining and assembling the injector plate and the cage that will enclose the Pyralis engine…

Level 1 Rocket

Level 1 Launch From On-Rocket Camera

Sorry for the long wait, but here is a video clip from Connie’s level 1 rocket launch from November in Amesbury, MA as seen from a camera on-board the rocket. Unfortunately, the parachute deployment knocked the camera out of position, so there’s only good footage of the launch on the way up. Enjoy! Click here…

temp scale

Pyralis Thermal Simulation

During firing of the Pyralis engine, heat from the combustion process will flow though the walls of the combustion chamber. The wall consists of of an insulating liner which absorbs heat, surrounded by a structural wall which contains the pressure load of the engine and is protected from intense heat by the insulating liner. The…

Meeting Minutes (2013 Nov 18)

Rocket Team Meeting November 18, 2013   Level 1 Certification Launch went well! Version 2 fins worked a lot better; version 1 fins still wobbled We got a Level 2 certified!   Orbital Sciences Sponsorship Interested in advising/mentoring sponsorship role During IAP, offered to send group of senior engineers to talk through design with us…