spark

New spark igniter

Zach B. and Jack E. have gotton our new spark igniter working, and it looks powerful! The spark will light propane and air in our preburner pilot light, and the preburner flame will in turn light the main propellants. The new spark electronics are much safer, simpler, and lighter than the previous designs.

Components of the Pyralis engine

Pyralis engine redesign

Over the past months, the team has been re-designing the Pyralis engine. The new revision includes a pre-burner which will heat the engine before ignition; we expect this change to resolve engine start-up issues experienced on the first engine design. We have also modified the injector to include better seals and orifices which can be…

Injector Test

We tested the injector of our Pyralis rocket engine by flowing water into it at 1200 psi (8.3 MPa). The test qualitatively shows good mixing and atomization of the propellant streams.

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Hot Fire Test Stand

Connie Liu and Matt Vernacchia have been building the test stand which we will mount the propulsion system to during static firing tests. The stand must support the thrust produced by the engine, and provides mounting points for the propellant tanks, plumbing, valves and sensors used in the tests. The stand is made from Super-Strut…

injector

Injector finished

We have finished machining the injector for the Pyralis rocket engine. The injector is the most mechanically complex part of the engine. Fuel and oxidizer pipes tap into the injector, and channels within the injector route the propellants to a ring of six injector heads. Within each injector head, the propellants are mixed together and…

Injector with Seals

Injector Seals

We machined glands into the injector bottom face which hold copper seals. These seals will prevent hot combustion gases from leaking through the joint between the combustion chamber wall and the bottom face of the injector.

outside the dust room

Dust Room Renovation

We’ve just finished renovating the dust room in our lab. This room contains our power tools and keeps the dust generated by cutting wood, metal and composites from spreading into the rest of the lab.

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…