Ethanol Cold Flow

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Completed:September 2020

In this test, we ran water pressurized with nitrogen gas through our Ethanol tower in order to verify our system and get readings on pressure and temperature. This cold flow test was our first major checkpoint to our way to Callisto 1 and required a great effort from each subsystem.

Nitrous Cold Flow (Water)

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Completed:December 2020

In this test, we will run water pressurized with nitrogen gas through our nitrogen tower, mirroring that of our preliminary ethanol cold flow test. Our oxidizer, nitrous oxide, is self-pressurizing. This means that in a certain temperature range, liquid nitrous oxide will boil off and create a gas that exerts a pressure on the remaining nitrous oxide liquid. This means that unlike our fuel (ethanol), which requires a nitrogen tank to pressurize, nitrous oxide can pressurize itself and takes out the need for any K-bottle. However, since nitrous is a rather dangerous material, we have decided to first perform this preliminary nitrous oxide test where we replace the nitrous oxide with water and add in a nitrogen tank for pressurization.


Nitrous Cold Flow

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Estimated Completion:November 2023

This is the second part of nitrous cold flow testing. In this test, we run nitrous oxide through our nitrous tower to verify our system, get pressure and temperature readings, and ensure a safe enviornment for testing with nitrous. Nitrous oxide is a rather dangerous chemical, so much safety regarding handling nitrous research needs to be completed in order to progress with our test.

Static Engine Fire

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Estimated Completion:December 2023

In this test, we will run ethanol pressurized with nitrogen gas through our ethanol tower and nitrous oxide through our nitrous tower and feed these into the injector and into the combustion chamber, where they will ignite and go through the nozzle to get a reading on the thrust. This test has particular emphasis on ignition, injector functionality, and hazard prevention since it models what our actual rocket's interior will consist of.


Full Cold Flow

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Estimated Completion:April 2022

In this test, we will run both nitrous oxide through our nitrous tower and water pressurized with nitrogen through our ethanol tower and feed the resulting propellants through the injector and into the combustion chamber. This test requires the integration of both towers and much work will need to be done in terms of combining procedures and hazard prevention.

Callisto I

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Estimated Completion:July 2022

Callisto I will be the first liquid bi-propellant rocket to be flown by Project Caelus. Its primary mission is to test the avionics, software defined radio (SDR), video streaming, passive control systems, recovery systems, launchpad preparations, and launch procedures. As the first of the three Callisto rockets, Callisto I will be a major milestone in our progress to reaching the Karman line.

Callisto II

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Estimated Completion:June 2022

The purpose of Callisto II is to serve as an intermediate testing platform between Callisto I, our first flight, and Callisto III, our projected attempt at a suborbital flight. The possibilities of multi-engine stages, solid strap-on boosters, and a high altitude optimized upper stage are still on the table. Perhaps the greatest innovation in this iteration of the Callisto family is the implementation of a helium dynamic pressure regulation system (DPR) to ensure constant and controlled chamber pressures throughout the entirety of the flight. In addition, due to the projected top speed and high altitudes, the recovery and communication systems may need to be redesigned entirely.

Callisto III

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Estimated Completion:June 2025

Callisto III is the culmination of the immense dedication and passion our team will have put into this project. Our final goal, to reach the Karman line (100 km) and successfully recover the rocket, will be achieved with this massive 9 meter long, ~100 kN liftoff thrust rocket projected to cost over $50,000. The engineering challenges associated with this are evidently difficult — massive combustion instability problems, large cooling circuits, and a more complex ground station communication system. The statistics for this flight are not yet determined at this point.

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