ET10_PTL Brochure.pdf

Marshall Space Flight Center Propulsion Test Laboratory

National Aeronautics and Space Administration

Marshall’s Propulsion Test Lab The Advanced Engine Test Facility is a two-position, tripropellant stand capable of evaluating and characterizing full-up engine and vehicle stage systems (designed for maximum thrust load of 12 Mlbf).

The Cryostructural Test Facility is ideal for evaluating the structural integrity of tanks and other propulsion components under a variety of conditions using compression, sheer, and tension loads.

The Hydrogen Cold Flow Facility is ideal for low pressure (≤ 50 psig) flow tests of hydrogen engine and subsystem components.

The Solar-Thermal Test Facility is capable providing 1 MW/m2 solar power in a high vacuum environment.

The Environmental Test Facility, TS300, is capable of simulating ascent launch profiles and deep space vacuum for cryogenic fluid management. Testing includes loading cryofuels and managing in-space, full-scale propulsion systems, cryogenic subsystems, superinsulated LH2 tanks, etc.

The Hot Gas Test Facility is a hydrogen/air combustion-driven envi-ronmental test facility capable of generating flow speeds up to Mach 4, convective heating rates from 4 to 50 Btu/ft2-s, and radiant heating rates up to 30 Btu/ft2-s in a 16-in × 16-in × 40-in test section.

The Hyperthermal Test Facility is built around a high-powered gas discharge device that produces a steady high-enthalpy flow for use in a variety of R&D testing applications. The 1.5 MW input power and multiple test sections allow for heating rates of up to 15,000 Btu/ft2-s in a variety of flow environments.

High-pressure gas and liquid propellants and inerts are readily avail-able and include, but are not limited to, hydrogen, methane, oxygen, nitrogen, helium, RP-1, De-Ionized water, and Trielhylaluminum/ Triethylborane (TEA/TEB).

possesses the infrastructure, facilities, and expertise required to conduct component, scale model, and system-level propulsion tests of hardware at any technology readiness level. Each test stand provides unique capabilities, allowing the flexibility to test a wide range of experimental, developmental, and flight-ready hardware with minimal buildup.

Test Stand (TS) 115, TS116, TS500, and multiple Test Cells provide the ability to test injectors, preburners, turbopumps, combustion chambers, igniters, seals, bearings, valves, engine subsystems, and small solids with little facility modification.

The Solid Propulsion Test Facility (SPTF) was designed to sup-port simulation of reuseable solid rocket motor (RSRM) combustion environments and provides the ability to test solids up to 100,000 lbf vertically and 172,000 lbf horizontally.

Solid Rocket Motor Material Test at SPTF.

Space Shuttle Main Engine Test at the Advanced Engine Test Facility.

Space Shuttle Engine Test at the Advanced Engine

Test Facility.

Thermal Protection System Material Test at the Hot

Gas Test Facility.

Aluminum Lithium Test Article (ALTA) Structural Test at the Cryostructural Test Facility.

Space Shuttle Scale Model Acoustic Test at TS116.

LOX/Methane Technology Demonstrator Test at TS115.

Engineering Solutions for Space Science and Exploration

National Aeronautics and Space Administration

George C. Marshall Space Flight Center Huntsville, AL 35812 www.nasa.gov/marshall www.nasa.gov

FL-2012-06-38-MSFC

8–529794d

ET10

For more information, contact philip.s.swofford@nasa.gov

Key Benefits > High speed data acquisition systems can record at up to 200,000 samples per second. High speed visible and thermal imaging can record up to 18,600 frames per second. Capabilities for both low and high speed color infrared video.

> Full life-cycle testing and evaluation capabilities from materials development and proof-of-concept articles up to qualification of integrated systems are available.

> Budget analysis and risk management are available in-house.

> Workforce and facility flexibility meet customer needs.

Propulsion Capabilities Facility Propellant in psig

LH2 LOX RP-1 Methane

CH4

LN2 LHe LHydro-carbons

GH2 GHe GN2 GOX Missile Grade Air

High-Pressure H2O

Test stand 116 6,000–8,500 5,300 2,700 4,000 4,100 4,200 3,300 4,800

10,000 8,000

15,000 10,000

Test stand 115 1,500 3,000 3,000 3,800 4,100 4,200 2,400 3,000

Test stand 500 100 (elevated) /2,000

80 (elevated) /2,000

1,000 4,000 4,100 4,200 3,300

Test stand 300 Off load from trailers

Off load from trailers

4,000 4,200 4,200 3,300

Solid propulsion test area

4,200 3,300

Test cells 2,200* 2,200 4,100 4,200 2,400 3,300

Advanced engine test facility

50 (run tank) 130/150 (run tanks)

130/150 (run tanks)

3,100 4,100 /10,000

4,200 3,300

Cryostructural test facility

50/100 (storage) 3,100 4,100 4,200 3,300

Hydrogen cold flow facility

50 750 3,100 4,100 1,500 2,400 500

Solar Thermal

Hot gas and Hyperthermal

3,100 4,200 3,300

* Available via k-bottles

Pad Abort Demonstrator Test at TS116.