KT.← Selected work

SLO Propulsion Technologies / September 2024 to present

NILE
Test Stand.

A modular liquid-engine test stand redesigned to support testing of an eventual ~1,000 lbf N2O / isopropyl-alcohol engine.

Structures leadTechnical directorChief safety officer~7 s design burn

01 / Project brief

From a 100 lbf concept
to a real test capability.

NILE began with students who wanted to apply propulsion concepts from the classroom to real liquid-engine hardware and who saw a need for an R&D-style test capability where students could explore different bipropellant-engine configurations.

That ambition included concepts such as thrust vectoring, engine throttling, and regenerative cooling. The existing Cal Poly propulsion facility could not support that level of flexibility or scale, so the university provided access to an off-campus test site. I helped develop the stand and its deployment approach around the structural, operational, and safety requirements that site and test program demanded. I inherited a stand concept for a much smaller engine and redesigned essentially the entire structural and mechanical architecture as NILE grew toward a ~1,000 lbf design target.

NILE stand during on-site integration
Modular NILE stand deployed for on-site integration at the test location.

02 / Structural architecture

A clear load path
to the ground.

Engine interface→S-load cells→2 thrust members→Welded side frames→Chain restraints→Concrete anchors

The final stand used two symmetric welded L-shaped side frames with ~45° diagonal braces, bolted cross-members for modularity, and extended “paws” to enlarge the support footprint. I owned the SolidWorks structural design, engine mounting, thrust members, blast shield, brackets, manufacturing drawings, and mechanical integration.

CAD isometric view of the NILE test-stand welded and bolted structural frame
Structural CAD view showing the modular welded side frames, bolted cross-members, and mobile base geometry.
CAD isometric view of the NILE test-stand diagonal-brace architecture
Alternate CAD view highlighting the 45-degree bracing and the intended engine-side load path.
~1,000 lbfEngine design target
3,000 lbfInternal yield-case load
2.5 × 2.5 × .25 inSteel-tube section

03 / Analysis drove redesign

The calculation
changed the hardware.

Hand calculations and MATLAB scripts exposed a weakness in an early single-member thrust path.

A simplified 36-inch bending case produced ~49.7 ksi against the 39 ksi conservative yield comparison. That analysis motivated a redesigned engine interface with two structural thrust members and three radially spaced axial S-load cells. It improved the load path and thrust-measurement integration; it was not a claim of a perfectly equal load split or a final FEA validation.

Early conceptSingle member→Final interfaceDual members + 3 load cells

04 / Build and integrate

Designing for
the hardware that exists.

The structure had to work with manufacturing constraints, fluid routing, maintenance access, and an evolving test program.

I coordinated welding, machining, waterjet work, procurement, assembly, and manufacturing schedules. As the fluids geometry matured, I worked with the fluids team to relocate and remake brackets that would otherwise have forced poor tubing bends or limited valve access.

Kanan checking NILE valve motion through test camera view
Checking valve motion through the remote camera system before a test operation.

05 / Test operations

Cold flow first.
Then fire.

I remained involved through hydrostatic testing, cold-flow testing, hot-fire operations, post-test inspection, and safety planning.

As testing progressed into cold-flow and hot-fire operations, I served as Chief Safety Officer. I helped establish test constraints, support abort procedures, coordinate remote camera coverage and bunker operations, and manage day-of-test safety with the multidisciplinary team.

Cold-flow test of the integrated stand and feed system.
Engine hot-fire attempt documenting ignition-timing troubleshooting.
Off-nominal hard-start event; instrumentation saturated near 4,200 lbf indicated load.

06 / Off-nominal learning

Measure the event.
Inspect the hardware.

~4,200 lbf

Indicated load at instrumentation saturation during a hard-start transient.

The actual transient peak is unknown. The event was not a controlled proof test. Post-event inspection found no visible frame damage, loosened joints, weld cracks, or buckled structural members; the load-cell / engine-interface plate required replacement.

07 / Safety and leadership

Test readiness is
an engineering discipline.

As Chief Safety Officer, I helped establish test constraints and coordinated day-of-test safety during operations involving up to ~15 engineers.

~330 ft exclusion zoneRemote bunker operationsSix camera viewsAbort authority for every engineer

The test plan accounted for high-pressure failures, leaks, invisible alcohol fires, electrical hazards, debris, and structural or propulsion-system failure. The blast shield was integrated to help protect critical feed-system hardware from potential engine fragments.

08 / The team

Design, build,
test, iterate.

NILE brought structures, fluids, electronics, and software into one operating test system. My role evolved from Structures Lead to Technical Director and Chief Safety Officer while coordinating the interfaces between them.

NILE team at the liquid-engine test site
NILE team at the test site during integrated operations.