One of the original teams founded in November 2018. Currently headed by ICLR founder Will Harradence. Propulsion team is responsible for the design and testing of the hybrid propulsion system (not including any COTS propulsion systems) comprising the ground filling station, nitrous tank, filling system, feed system, throttle control system, and engine itself, as well as any complimentary items, such as fuel casting rigs and testing rigs.
For the original task of designing a throttled hybrid engine for a sounding rocket the team was split into:
See Major Subsystems for a list and descriptions of the subsystems described here.
The first flight engine developed by ICLR. Initial spec was developed at the beginning of 2019, with detailed design work running throughout 2019-2021.
The very first engine developed by ICLR from November 2018-June 2019. This engine was intended as a proof of concept for a throttlable paraffin/nitrous oxide hybrid. Specification was based on current estimates for the thrust needed to fly a low velocity trajectory, as well as the available testing facilities. Pablo was first tested on 24th May, 2019, and the test cell at the University of Hertfordshire. Following unsuccessful attempts to ignite the engine, 1 burn was completed on this date, and data was collected showing a steady state thrust of about 40N.
Propellants were Paraffin wax and Nitrous Oxide.
Specifications:
A conceptual upgrade to Pablo featuring a bell nozzle.
A slightly modified version of Pablo that was successfully test fired at the university of Hertfordshire in June 2019 where a problematic relationship between ignition and injection was highlighted. Equipped with a conical diverging nozzle, however without a converging section
Adds a post-combustion chamber to the Constantine.
Autogenerated on 2022-06-10 using 1337 h4xx0r 5k111z, from ye olde Confluence Wiki
Old Metadata: Created by Sokolowski, Rafal, last modified by Soysal, Alp on May 18, 2021
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