Neptune

Project Neptune | Propulsion Testing Campaign

Propulsion Test Engineer · August 2026–present · Planning

Overview

Two-stage spaceshot rocket project utilizing a sea-based launch platform. Running the propulsion test campaign as the Propulsion Test Engineer under the Test and Integration Lead Nikos Zentefis.

Background

Project Neptune is a joint effort project between the UCF clubs: American Institute of Astronautics and Aeronautics (AIAA) and Students for the Exploration and Development of Space (SEDS), in collaboration with Seagate Space, a startup sea-based launch platform company. The project aims to design, manufacture, and launch a two-stage spaceshot rocket off one of Seagate’s sea-based launch platforms. A spaceshot in amateur/collegiate rocketry is defined as a rocket that crosses the Kármán line, 100km altitude, which is generally recognized as the boundary of space. In the pursuit of a spaceshot we will be designing our own propellent formula and solid rocket motor (SRM).

Propulsion Test Campaign

We will need to run our own testing campaign to characterize and validate our propellant formula and motor designs. The propulsion testing campaign is in development, currently in the planning stage as the scope of the project is defined and testing requirements are outlined. The campaign will be broken into three parts: propellant testing, 54mm motor testing, and full-scale motor testing.

Strand-Burner

For the propellant testing a strand-burner test rig will be designed and manufactured. A strand burner is a pressurized chamber with an integrated pressure sensor that simulates a motor environment and can take out pressure data as a strand of propellant is burned. To simulate motor conditions, inert gas such as nitrogen is used to pressurize the chamber. The pressure chamber will need a high-pressure gas input and a pressure tap with a pressure transducer output. Additionally, the chamber will need to be able to seal against an end wall that holds a propellant strand; this end wall will also need to have an ignition scheme to ignite the propellant. To supply high pressure gas to the chamber, a plumbing scheme will be devised. 

54 mm Static-Fire Test Stand

The planned 54 mm stand will support ground testing of development motors. This stage is intended to connect the propellant-characterization work with evaluation of an assembled motor. The proposed scope includes the stand, its instrumentation, and its interfaces with the motor and test environment. Planning should establish what measurements are needed and how the resulting data will be used to assess the design. This intermediate stage provides a place to develop the testing approach before moving to the full-scale system. Stand design and performance claims will be documented as the work progresses.

Full-Scale Test Stand

The full-scale stand is planned to support ground evaluation of the motor intended for the flight vehicle. Its scope will depend on the final motor configuration and the project's test requirements. The proposed role of this stage is to assess the integrated propulsion system and provide evidence for later vehicle-integration decisions.