PROPULSION ENGINEERING & SPACE TECHNOLOGY

ALULA: Liquid Engine Rocket

STATUS

Flown with 6,126 ft Apogee

TEAM

UC Berkeley Space Technologies and Rocketry (STAR)

PropulsionLOX/EthanolCryogenics
ALULA: Liquid Engine Rocket

SYSTEM OVERVIEW

ALULA is a bi-propellant liquid rocket engine using LOX and ethanol, developed for integration into a flight-ready vehicle. The project spans ground support equipment, cryogenic feed systems, structural integration, and thermal management, with iterative hotfire testing driving design decisions.

MY CONTRIBUTIONS

  • 01

    Designed and built portable, modular ground support structures for liquid engine hotfire operations, using perforated sheet metal, wood framing, and off-the-shelf hardware to enable low-cost iteration and rapid reconfiguration

  • 02

    Conceptualized and developed a custom high-pressure LOX exhaust solenoid valve (>450 psi), including mass optimization and CNC-machined components, to reduce cost and improve flow control precision

  • 03

    Led design reviews for the custom valve and supported the transition to a servo-actuated ball valve when system complexity exceeded program maturity, prioritizing test readiness over ideal performance

  • 04

    Redesigned thruster mounts and LOX/ethanol tank mounts, enabling a carbon-rod load-bearing structure to carry tank mass during transport and airframe integration

  • 05

    Supported structural integration and machining planning for tank mounts using 1-inch-thick, 8-inch-diameter 6061 aluminum stock

  • 06

    Integrated cryogenic insulation into engine infrastructure using thermal calculations to mitigate heat leak and ensure safe handling

  • 07

    Developed and tested quick-disconnect fill systems, resolving reliability issues through extensive iteration on connector orientation, angle, and microcontroller interfacing

RESULTS

  • Hit 6,126 ft apogee!

  • Enabled repeatable liquid engine hotfire operations through portable ground infrastructure

  • Delivered structurally integrated tank and thruster mounting concepts suitable for flight hardware

  • Demonstrated pragmatic system decision-making by pivoting from complex custom hardware to robust, testable solutions

  • Identified key reliability sensitivities in cryogenic quick-disconnect systems through hands-on testing

PROJECT GALLERY

ALULA liquid rocket engine firing on test stand with visible exhaust plume against mountain landscape

HOTFIRE STILL

HOTFIRE TEST

CAD model showing internal rocket engine assembly with propellant tanks and plumbing integration

ENGINE CAD ASSEMBLY

Outdoor hotfire test setup with wooden ground support structures and compressed gas cylinders

GROUND SUPPORT EQUIPMENT

Design presentation showing pressurization system storage and transport with modular pegboard carts

SYSTEM STORAGE DESIGN

Close-up of recovered engine component with aluminum foil cryogenic insulation and tooling

RECOVERED HARDWARE

Hand holding cryogenic quick-disconnect component wrapped in aluminum foil insulation

CRYOGENIC PLUMBING