The HEST facility utilizes the principle of unsteady shock heating and compression to generate precisely-known high-temperature and high-pressure test conditions to further the basic understanding of gas dynamics, radiative heat transfer, and chemistry at high enthalpies. An optically-accessible test section allows for the integration of laser diagnostics to measure time-resolved profiles of species and temperature.

Key Elements:
-10 cm inner diameter, electropolished stainless steel
-Modular design with driver extension to maximize test times (up to 30 ms)
-Custom low-profile double groove-locking weldless flanges
-Hydrostatically pressure tested to 265 atm
-Post-reflected shock temperature range of 600-12,000 K
-Quick diaphragm loading mechanism
-Optical access ~2 cm from endwall

The multi-phase shock tube facility enables studying of heterogenous chemistry via injection of a uniform aerosol cloud of solid particles. Heating jackets on the tube also allow for materials with low vapor pressures to be studied. The MPST facility can also be equipped with an acrylic test section that permits high-speed imaging of the shock heating process. The MPST was donated by The Aerospace Corp and adapted to our laboratory.

Key Elements:

-52 instrumentation ports
-16 cm inner diameter, electropolished steel
-Solid particle injection system

The detonation tube facility initiates near 1D detonation waves in premixed reactant mixtures at precisely-controlled initial pressures. A Shchelkin spiral assists the transition from deflagration to detonation. Optical access ports along the tube allow for high-speed optical measurements of post-combustion thermodynamics behind detonation waves via laser-based diagnostics.

Key Elements:

-1.5 inch inner diameter stainless steel
-5 piezoelectric sensors to measure detonation wave speeds
-Vacuum surge tank to fully contain and cool detonated mixtures
-Hydrostatically pressure tested to 200 atm

A custom controlled atmosphere cone calorimeter (CACC) facility has been developed to advance the labs fire science and toxicity research. The CACC allows for controlled burns of natural and synthetic materials under varying heat fluxes and atmospheric oxygen content. This allows for the effect of ventilation on fire behavior and toxicity to be better understood. Various instrumentation ports allow for measurements of gas species, gas temperature, and exhaust flow.

Key Elements:

-Controlled radiative heating element
-Variable atmosphere control
-Load cell for mass loss measurement
-In-situ and ex-situ spectroscopic measurement capabilities

The solid fuel combustion facility is capable of testing small hybrid and solid rocket fuels at atmospheric pressure (left) as well as at elevated pressures up to 20 bar (right) with a post-combustion chamber. The facility is setup in a high-flow fume hood with a maximum exhaust rate of 1150 CFM. Load cells are integrated into the test stand for time-resolved thrust/burn profile measurements. Adjacent optical breadboards allow for integration of laser diagnostics for more detailed thermochemistry measurements. A modular thrust plate design accomodates fuel grains between 1/2-2" diameter and up to 10" in length.

Key Elements:
-High-speed data acquisition
-Remote valve control
-Electrical ignition
-Choked orifice for mass flow rate control
-8 ft. x 2 ft. enclosed work surface for auxilary equipment

Our lab is equipped with multiple flow reactors for investigating chemical kinetics and fluid dynamics.

McKenna Burner Key Elements:

-Steady quasi-1D flames at controlled pressures and extended test times
-3 ft. long heated optical gas cell for studying combustion exhaust gases
-Flame visualization via 6" viewport windows

Coaxial Burner Key Elements:

-Interchangeable injector apparatus to test novel injector designs
-Translating optical stage to facilitate laser absorption tomography
-Precision flow control that allows for variable fuel/oxidizer ratios and mixing

Optically-accessible gas cells provide precisely controlled environments for fundamental spectroscopy studies over a wide range of temperature and pressure. These gas cells often represent a starting point in spectroscopic sensor development. Pictured here are two cells, each capable of static or flow operation. A room-temperature cell provides for maximum flexibility in window materials for studies ranging from the ultra-violet to the THz at moderate pressures (less than 5 atm). A second custom high-pressure cell is integrated into a tube furnace for uniform heating of the test gas up to 1400 K and pressurizing up to 200 atm.

Key Elements:

-High-pressure, stainless-steel plumbing throughout system
-Mixing tank for generating custom gas mixtures
-Water-cooled window flanges for high-temperature cell

The Propulsion Test Platform (PTP) is a liquid bi-propellant mobile test facility used for static hot-fire testing of liquid rocket combustion devices. The PTP is mounted to a 8' x 21' trailer for easy transportation to and from UCLA and the Mojave Test Facility. The system uses a pressure blow-down configuration with propellant tank pressure rating of 1500 psi. It is capable of remote valve control, automated sequencing, and data acquisition, all controlled and monitored through a LabVIEW graphical user interface. The PTP is compatible with hypergolic propellants and can be used for egine testing up to 1,000 lbf thrust.

Key Elements:

-16-channel relay box for manual and remote valve control
-Expandable DAQ system for real-time system monitoring (P, T, etc.)
-Venturi flow meter manifolds for mass-flow-rate measurements over a range of testing conditions

The Mojave propulsion test facility provides unique high-energy test and launch infrastructure for research and educational activities. The facility primarily consists of a dedicated control blockhouse and three test pads, along with storage and work areas. Underground data, power, and water transmission infrastructure provide for remote operations. The facility is located near Cantil, CA in the Mojave desert approximately 2 hours north of UCLA main campus.

Key Elements:

-Test articles up to 10,000 lbf thrust can be accommodated
-Wide range of propellants can be tested
-Operated in partnership with Polaris, Inc.