CHRONOLOGIE
SPACE SHUTTLE

The A-1 Test Stand is a single-position, vertical firing stand capable of static firing a test article up to 33 ft. in diameter. The A-1 Test Stand was originally designed to test the Apollo Saturn V Second Stage (S-II) - a cluster of five J-2 rocket engines capable of developing a 1.15 M-lb thrust at altitude. The A-1 Test Stand has been re-activated to conduct a Space Shuttle Main Propulsion System Flowliner Hot Fire Test in support of the "return to flight operations" for the Space Shuttle Program.This test stand accommodates full-scale, liquid propellant rocket engine and systems testing. It can be utilized to static fire a test article up to 33 ft. in diameter with a maximum dynamic load of 1.1M-lb vertical (up), 1.7M-lb vertical (rebound), and 0.7M-lb horizontal. The A-1 Test Stand is one of few large, full-scale rocket engine test stands in the country. The test stand resides in a location that has over a 118,000 acres of restrictive easement to provide an acoustic buffer zone around the facility. To preserve the buffer zone, the restrictive easement prohibits construction or maintenance of structures for human habitation. The buffer zone, which is subject to intense sound pressure levels and noise resulting from full power and duration engine firings, guarantees NASA an irreplaceable national rocket test facility.

Single-Position, Vertical Firing Capability LH2 & LO2 Propellants Low-Pressure Run Tanks Barges Re-Supply Run Tanks GHe, GH2, GN2 & HA Support Fluids Purges Pressurant Gases Maximum Dynamic Load - 1.1 M lbf

The A-2 Test Stand is a single-position, vertical-firing stand capable of static firing a test article up to 33 ft. in diameter. It is equipped with an altitude diffuser, which is utilized to simulate altitude conditions during engine testing. The diffuser can simulate altitudes of 54,000 to 70,000 ft. The A-2 Test Stand is equipped with a 200-ton main derrick lifting crane (down rated to 37.5 tons) with a 5 ton jib. The A-2 Test Stand is currently activated to conduct flight certification testing of the Space Shuttle Main Engine. This test stand accommodates full-scale, liquid propellant rocket engine and systems testing. It can be utilized to static fire a test article up to 33 ft. in diameter with a maximum dynamic load of 1.1M-lb vertical (up), 1.7M-lb vertical (rebound), and 0.7M-lb horizontal. The A-2 Test Stand is one of few large, full-scale rocket engine test stands in the country. The test stand resides in a location that has over a 118,000 acres of restrictive easement to provide an acoustic buffer zone around the facility. To preserve the buffer zone, the restrictive easement prohibits construction or maintenance of structures for human habitation. The buffer zone, which is subject to intense sound pressure levels and noise resulting from full power and duration engine firings, guarantees NASA an irreplaceable national rocket test facility.

Single-Position, Vertical Firing Capability Altitude Diffuser Equipped LH2 & LO2 Propellants Low-Pressure Run Tanks Barges Re-Supply Run Tanks GHe, GH2, GN2 & HA Support Fluids Purges Pressurant Gases Maximum Dynamic Load – 1.1 M lbf

The B-1 Test Stand is a single-position, vertical, firing stand capable of static firing a test article up to 33 ft. in diameter. The B-1 Test Stand is 295 feet tall and is equipped with a 200-ton main derrick lifting crane, a 20-ton jib crane, and a 175-ton auxiliary derrick lifting crane. The B-1 Test Stand is currently being leased to Boeing-Rocketdyne to conduct RS-68 Engine Testing. This test stand accommodates full-scale, liquid propellant rocket engine and systems testing. It can be utilized to static fire a test article up to 33 ft. in diameter with a maximum dynamic load of 11M-lb vertical (up), 8.5M-lb vertical (rebound), and 6M-lb horizontal. The B-1 Test Stand is one of few large, full-scale rocket engine test stands in the country.

The B-2 Test Stand is a single-position, vertical, firing stand capable of static firing a test article up to 33 ft. in diameter. The B-1 Test Stand is 295 feet tall and is equipped with a 200-ton main derrick lifting crane, a 20-ton jib crane, and a 175-ton auxiliary derrick lifting crane. The B-2 Test Stand accommodates full-scale, liquid propellant rocket engine and systems testing. It can be utilized to static fire a test article up to 33 ft. in diameter with a maximum dynamic load of 11M-lb vertical (up), 8.5M-lb vertical (rebound), and 6M-lb horizontal. The B-2 Test Stand is the largest, full-scale liquid rocket engine test stand in the country.

The test stand resides in a location that has over a 118,000 acres of restrictive easement to provide an acoustic buffer zone around the facility. To preserve the buffer zone, the restrictive easement prohibits construction or maintenance of structures for human habitation. The buffer zone, which is subject to intense sound pressure levels, shock waves, and noise resulting from full power and duration engine firings, guarantees NASA an irreplaceable national rocket test facility.

Dual-Position Complex with Each Position Similar in Design LH2 & LO2 Propellants Low-Pressure Run Tanks Barges Re-supply Run Tanks GHe, GH2, GN2 & HA Support Fluids Purges Pressurant Gases Maximum Dynamic Load ~ 11M lbf

The E-1 Test Facility, originally designed as a developmental rocket engine component test facility for the National Launch System (NLS) Program, is available for developmental testing projects requiring high pressure and high flow rate cryogenic fluids, hydrogen, oxygen, RP or hydrocarbon (HC), inert gases, and industrial water. E-1 was primarily designed for Pressure-Fed LO2/LH2, LO2/HC, and Hybrid-Based Test Articles. E-1 is the only operational Ultra-high flow, Ultra-high pressure rocket engine component test stand in the world. E-1 has pressure and flowrate capability that exceeds anything in existence today.

E-1 Test Cell 1 is primarily designed to test pressure-fed LOX/LH2, LOX/RP-1, and hybrid combustion devices up to 1 Mlbf of horizontal thrust and 500 Klbf vertical thrust. It can also be used to test individual LH2 and LOX turbopump assemblies.

E-1 Test Cell 2 is primarily designed to test LH2 and LOX turbopump assemblies, either simultaneously or individually. The test article support structure for Cell 2 is designed for test articles weighing up to 3000 lbs and generating up to 60,000 lbf thrust at angles up to 10 degrees above horizontal.

E-1 Test Cell 3 is primarily designed to test turbopump assemblies. The test article support structure for cell 3 is designed for test articles weighing up to 3000 lbs and generating up to 60,000 lbf thrust at angles up to 10 degrees above horizontal.

Multi-Cell (3) Test Facility Horizontal Testing Capabilities Ultra High-Pressure(up to 15 kpsi) Testing Capability for Large-Scale Propulsion Programs High Flow Rate Capability

E1 Cell 1 Primarily Designed for Pressure-Fed LO2/LH2, LO2/HC, and Hybrid-Based Test Articles Thrust Loads up to 1M lbf E1 Cell 2 Designed for LH2 & LO2 Turbopump Assembly Testing Thrust Loads up to 60K lbf E1 Cell 3 Designed for LO2-Rich Turbopump Assembly Testing New installation for LO2/LH2 Engine System High pressure for film cooling and spin start systems Thrust Loads up to 250K lbf

E-2 is available for developmental testing projects involving hot gas, cryogenic fluids, gas impingement, inert gases, industrial gases, specialized gases, hydraulics, deionized and potable water. The E-2 is a highly flexible system that can be easily adapted to alternate open-loop control scenarios and closed-loop schemes with minimal hardware changes.

E-2 Cell 1, formerly known as the High Heat Flux Facility, was originally constructed to support materials development for the National Aerospace Plane (NASP) by subjecting special test articles to extreme temperature conditions. Recent test projects at E-2 have included composite cryogenic tanks, turbopumps, preburners, and thrust chambers in the 75-100 Klbf range. The facility has been modified to support advanced component and engine development projects. Multiple test positions are available. E-2 cell 1 is a versatile, Ultra-High pressure test stand that can be utilized for testing a variety of next generation propulsion cryogenic system components. While the flow rates are not unique, the UHP capability makes it unique in it’s capability. The facility’s two test cells are widely separated and can support multiple test programs at one time.

The E-2 Cell 2 Facility was developed for testing LOX/LH, LOX/RP, and Hydrogen Peroxide/Hydrocarbon full stage systems in the 100 Klbf range. E-2 Cell 2 is capable of supporting tests of complete flight or "flight-like" stages, as well as rocket engines and combustion devices. Cell 2 has the capability to provide low-pressure LOX and RP-1 propellants to a test article, mounted vertically in the test cell. Cell 2 also has an environmentally-approved hydrogen peroxide dilution, safing, and dump system to support H2O2 stage testing. E-2 cell 2 is one of only a few stands in the world built for testing ambient 100 Klbf Class LOX/LH, LOX/RP, and H2O2/HC engine systems and stages in a vertical configuration. E-2 Cell 2 is NASA’s only stand of this kind.

Multi-Cell (2) Test Facility Vertical and Horizontal Testing Capabilities Supports Intermediate Sized Component and Engine Test Programs Originally Designed to Support NASP Materials Testing High Flow Rate Capability High Delivery Pressure Capability E2 Cell 1 Horizontal Test Cell Propellants: LO2, LN2, LH2, RP-1, H2O, GO2, GH2 and GN2 Thrust Loads up to 100K lbf E2 Cell 2 Vertical Test Cell Propellants: LO2, RP-1 and H2O2 Thrust Loads up to 100K lbf

The E-3 Test Stand is a versatile test complex that is available for component development testing of combustion devices, rocket engine components and small/subscale component engines and boosters.

The E-3 Cell 1 was primarily designed to test pressure-fed H2O2/RP, LOX/hydrocarbon fuel, GOX/hydrocarbon fuel, GH2/GOX, and hybrid rocket motor combustion devices. It is a versatile test cell available for component development testing of combustion devices, rocket engine components and small/sub-scale complete engines and boosters. It is a horizontal test cell, which can support horizontal thrust loads up to 60,000 lbf (120,000 lbf impulse load). E-3 Test facility is unique in it’s ability to test Hydrogen Peroxide (H2O2) articles and components in both a horizontal and vertical configuration.

E-3 Cell 2 was primarily designed to test H2O2/JP-8 and rocket motor combustion devices up to 25,000 lbf of vertical thrust (50,000 lbf impulse load). Cell 2 has an additional capacity to test mono-propellant configuration subscale combustion devices, such as catalyst beds and components. It is primarily for vertical testing with provisions for limited horizontal testing. Cell 2 can support vertical thrust loads up to 25,000 lbf thrust (50,000 lbf impulse load) and has a flame bucket below the firing position. E-3 Test facility is unique in it’s ability to test Hydrogen Peroxide (H2O2) articles and components in both a horizontal and vertical configuration.

Multi-Cell (2) Test Facility Vertical and Horizontal Testing Capabilities Primarily Designed for Rocket Engine Component & Sub-Scale Engine Development H2O2 Bulk Storage Tanks H2O2 and JP Catch Tanks Inert Gas Storage (GN2 & GHe) Concrete H2O2 Containment and Dilution Basin

E3 Cell 1 Horizontal Test Cell Propellants: LO2, GO2, H2O2 and JP/RP Thrust Loads up to 60K lbf E3 Cell 2 Vertical Test Cell Propellants: H2O2, HC and JP Thrust Loads up to 25K lb