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By NASA
Caption: The Intuitive Machines lunar lander that will deliver NASA science and technology to the Moon as part of the agency’s CLPS (Commercial Lunar Payload Services) initiative and Artemis campaign is encapsulated in the fairing of the SpaceX Falcon 9 rocket. Credit: SpaceX Carrying NASA science and technology to the Moon as part of the agency’s CLPS (Commercial Lunar Payload Services) initiative and Artemis campaign, the Intuitive Machines IM-2 mission is targeted to launch no earlier than Wednesday, Feb. 26. The mission will lift off on a SpaceX Falcon 9 rocket from Launch Complex 39A at the agency’s Kennedy Space Center in Florida.
Live launch coverage will air on NASA+ with prelaunch events starting Tuesday, Feb. 25. Learn how to watch NASA content through a variety of platforms, including social media. Follow all events at:
https://www.nasa.gov/live
After the launch, Intuitive Machines’ lunar lander, Athena, will spend approximately one week in transit to the Moon before landing on the lunar surface no earlier than Thursday, March 6. The lander will carry NASA science investigations and technology demonstrations to further our understanding of the Moon’s environment and help prepare for future human missions to the lunar surface, as part of the agency’s Moon to Mars exploration approach.
Among the items on Intuitive Machines’ lander, the IM-2 mission will be one of the first on-site demonstrations of resource use on the Moon. A drill and mass spectrometer will measure the potential presence of volatiles or gases from lunar soil in Mons Mouton, a lunar plateau in the Moon’s South Pole. In addition, a passive Laser Retroreflector Array (LRA) on the top deck of the lander will bounce laser light back at any orbiting or incoming spacecraft to give future spacecraft a permanent reference point on the lunar surface. Other technology instruments on this delivery will demonstrate a robust surface communications system and deploy a propulsive drone that can hop across the lunar surface.
Launching as a rideshare with the IM-2 delivery, NASA’s Lunar Trailblazer spacecraft also will begin its journey to lunar orbit, where it will map the distribution of the different forms of water on the Moon.
The deadline has passed for media accreditation for in-person coverage of this launch. The agency’s media accreditation policy is available online. More information about media accreditation is available by emailing: ksc-media-accreditat@mail.nasa.gov.
Full coverage of this mission is as follows (all times Eastern):
Tuesday, Feb. 25
11 a.m. – Lunar science and technology media teleconference with the following participants:
Joel Kearns, deputy associate administrator for exploration, Science Mission Directorate, NASA Headquarters Niki Werkheiser, director, technology maturation, Space Technology Mission Directorate, NASA Headquarters Jackie Quinn, Polar Resources Ice Mining Experiment 1 (PRIME-1) project manager, NASA Kennedy Daniel Cremons, LRA deputy principal investigator, NASA’s Goddard Space Flight Center Bethany Ehlmann, Lunar Trailblazer principal investigator, Caltech Trent Martin, senior vice president, space systems, Intuitive Machines Thierry Klein, president, Bell Labs Solution Research, Nokia Audio of the teleconference will stream live on the agency’s website:
https://www.nasa.gov/live/
Media may ask questions via phone only. For the dial-in number and passcode, please contact the Kennedy newsroom no later than 10 a.m. EST Tuesday, Feb. 25, at: ksc-newsroom@mail.nasa.gov.
Wednesday, Feb. 26
11:30 a.m. – Lunar delivery readiness media teleconference with the following participants:
Nicky Fox, associate administrator, Science Mission Directorate, NASA Headquarters Clayton Turner, associate administrator, Space Technology Mission Directorate, NASA Headquarters Trent Martin, senior vice president, space systems, Intuitive Machines William Gerstenmaier, vice president, build and flight reliability, SpaceX Melody Lovin, launch weather officer, Cape Canaveral Space Force Station’s 45th Weather Squadron Audio of the teleconference will stream live on the agency’s website:
https://www.nasa.gov/live/
Media may ask questions via phone only. For the dial-in number and passcode, please contact the Kennedy newsroom no later than 10 a.m. EST Wednesday, Feb. 26, at: ksc-newsroom@mail.nasa.gov.
Launch coverage will begin on NASA+ approximately 45 minutes before liftoff. A specific time will be shared the week of Feb. 24.
NASA Launch Coverage
Audio only of the media teleconferences and launch coverage will be carried on the NASA “V” circuits, which may be accessed by dialing 321-867-1220, -1240, or -7135. On launch day, the full mission broadcast can be heard on -1220 and -1240, while the countdown net only can be heard on -7135 beginning approximately one hour before the mission broadcast begins.
On launch day, a “tech feed” of the launch without NASA TV commentary will be carried on the NASA TV media channel.
NASA Website Launch Coverage
Launch day coverage of the mission will be available on the NASA website. Coverage will include live streaming and blog updates beginning Feb. 26, as the countdown milestones occur. On-demand streaming video and photos of the launch will be available shortly after liftoff. For questions about countdown coverage, contact the Kennedy newsroom at 321-867-2468.
NASA Virtual Guests for Launch
Members of the public can register to attend this launch virtually. Registrants will receive mission updates and activities by email, including curated mission resources, schedule updates, and a virtual guest passport stamp following a successful launch. Print your passport and get ready to add your stamp!
Watch, Engage on Social Media
Let people know you’re following the mission on X, Facebook, and Instagram by using the hashtag #Artemis. You can also stay connected by following and tagging these accounts:
X: @NASA, @NASAKennedy, @NASAArtemis, @NASAMoon
Facebook: NASA, NASAKennedy, NASAArtemis
Instagram: @NASA, @NASAKennedy, @NASAArtemis
Coverage en Español
Did you know NASA has a Spanish section called NASA en español? Check out NASA en español on X, Instagram, Facebook, and YouTube for additional mission coverage.
Para obtener información sobre cobertura en español en el Centro Espacial Kennedy o si desea solicitar entrevistas en español, comuníquese con Antonia Jaramillo o Messod Bendayan a: antonia.jaramillobotero@nasa.gov o messod.c.bendayan@nasa.gov.
For more information about the agency’s CLPS initiative, see:
https://www.nasa.gov/clps
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Karen Fox / Jasmine Hopkins
Headquarters, Washington
301-286-6284 / 321-432-4624
karen.c.fox@nasa.gov / jasmine.s.hopkins@nasa.gov
Natalia Riusech / Nilufar Ramji
Johnson Space Center, Houston
281-483-5111
nataila.s.riusech@nasa.gov / nilufar.ramji@nasa.gov
Antonia Jaramillo
Kennedy Space Center, Florida
321-501-8425
antonia.jaramillobotero@nasa.gov
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Last Updated Feb 21, 2025 Related Terms
Missions Artemis Commercial Lunar Payload Services (CLPS) Science Mission Directorate Space Technology Mission Directorate View the full article
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By NASA
Firefly’s Blue Ghost lunar lander captured a bright image of the Moon’s South Pole (on the far left) through the cameras on its top deck, while it travels to the Moon as part of NASA’s CLPS (Commercial Lunar Payload Services) initiative and Artemis campaign.Credits: Firefly Aerospace With a suite of NASA science and technology on board, Firefly Aerospace is targeting no earlier than 3:45 a.m. EST on Sunday, March 2, to land the Blue Ghost lunar lander on the Moon. Blue Ghost is slated to touch down near Mare Crisium, a plain in the northeast quadrant on the near side of the Moon, as part of NASA’s CLPS (Commercial Lunar Payload Services) initiative and Artemis campaign to establish a long-term lunar presence.
Live coverage of the landing, jointly hosted by NASA and Firefly, will air on NASA+ starting at 2:30 a.m. EST, approximately 75 minutes before touchdown on the Moon’s surface. Learn how to watch NASA content through a variety of platforms, including social media. The broadcast will also stream on Firefly’s YouTube channel. Coverage will include live streaming and blog updates as the descent milestones occur.
Accredited media interested in attending the in-person landing event hosted by Firefly in the Austin, Texas, area may request media credentials through this form by Monday, Feb. 24.
Following the landing, NASA and Firefly will host a news conference to discuss the mission and science opportunities that lie ahead as they begin lunar surface operations. The time of the briefing will be shared after touchdown.
Blue Ghost launched Jan. 15, at 1:11 a.m. EST on a SpaceX Falcon 9 rocket from Launch Complex 39A at NASA’s Kennedy Space Center in Florida. The lander is carrying a suite of 10 NASA scientific investigations and technology demonstrations, which will provide insights into the Moon’s environment and test technologies to support future astronauts landing safely on the lunar surface, as well as Mars.
NASA continues to work with multiple American companies to deliver science and technology to the lunar surface through the agency’s CLPS initiative. This pool of companies may bid on contracts for end-to-end lunar delivery services, including payload integration and operations, launching from Earth, and landing on the surface of the Moon. NASA’s CLPS contracts are indefinite-delivery/indefinite-quantity contracts with a cumulative maximum value of $2.6 billion through 2028. In February 2021, the agency awarded Firefly this delivery of 10 NASA science investigations and technology demonstrations to the Moon using its American-designed and -manufactured lunar lander for approximately $93.3 million (modified to $101.5 million).
Through the Artemis campaign, commercial robotic deliveries will perform science experiments, test technologies, and demonstrate capabilities on and around the Moon to help NASA explore in advance of Artemis Generation astronaut missions to the lunar surface, and ultimately crewed missions to Mars.
Watch, engage on social media
Let people know you’re following the mission on X, Facebook, and Instagram by using the hashtag #Artemis. You can also stay connected by following and tagging these accounts:
X: @NASA, @NASA_Johnson, @NASAArtemis, @NASAMoon
Facebook: NASA, NASAJohnsonSpaceCenter, NASAArtemis
Instagram: @NASA, @NASAJohnson, @NASAArtemis
For more information about the agency’s Commercial Lunar Payload Services initiative:
https://www.nasa.gov/clps
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Karen Fox / Alise Fisher
Headquarters, Washington
202-358-1600
karen.c.fox@nasa.gov / alise.m.fisher@nasa.gov
Natalia Riusech / Nilufar Ramji
Johnson Space Center, Houston
281-483-5111
natalia.s.riusech@nasa.gov / nilufar.ramji@nasa.gov
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Last Updated Feb 14, 2025 LocationNASA Headquarters Related Terms
Commercial Lunar Payload Services (CLPS) Artemis Earth's Moon View the full article
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By Space Force
Memorandum on Limited Facilities-Based Exemption for Return to In-Person Work in compliance with Secretary of Defense Memorandum Initial Department of Defense Implementation Guidance, Return to In-Person Work.
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By Space Force
The DAF released guidance on defending women from gender ideology extremism and restoring biological truth to the federal government.
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By NASA
9 min read
Preparations for Next Moonwalk Simulations Underway (and Underwater)
Sector Combustor Studies (CE-5B-1)
Combustion studies are conducted in this two-test position facility specifically in support of the NOx-reduction research for the High Speed Research program and the Advanced Subsonic Technology program. CE-5B-1 is large enough to test sector arrangements of injector elements to include interactions of the elements and single larger elements. The facility receives filtered combustion air from the 450-psig system. The air is heated in a 1,100°F non-vitiated heater at flows up to 20 lb/s, which can be valved to either test stand. The airflow passes through the test section, is water spray quenched, and is then discharged to the altitude exhaust system or the atmospheric exhaust system. The facility preheater consists of a heat exchanger fired by four J-47 burner cans using natural gas for a fuel and the 40-psig combustion air. The research hardware uses ASTM Jet-A, JP-5, or JP-8 as a fuel.
CE-5B-1 Special Features
In addition to inlet and exit rakes and standard instrumentation, water-cooled gas sampling rakes are in the downstream section. Particulate measurements are taken at the exit of the combustion section. Optical accessibility of the combustor section allows never-before-possible nonintrusive laser-based diagnostics of the reacting and non-reacting flowfield. These include such techniques as planar laser-induced fluorescence (PLIF) imaging, Planar Mie scattering, Phase/Doppler particle analysis (PDPA), focused Schlieren imaging, and light sheet photography. Both rigs share the gas analysis, particulate analysis, and diagnostics equipment.
CE-5B Facility Capabilities (typical of both rigs)
ParameterOperating ValueInlet Air Supply Pressure450 psigInlet Air Temperature100°F, preheated to 350-1,350°FInlet Airflow Stand 1 Stand 2 20 lb/s (available)
0.5 to 12.0 pps
0.5 to 5.0 ppsExhaustAtm or 20-26 in. HgRig Pressure Without Windows Stand 1 Stand 2275 psig
400 psigRig Pressure With Windows Stand 1 Stand 2250 psig
275 psigRig Fuel (JP-8) Flow7 gpm @ 400-900 psig
(three legs per stand)Window Cooling GN2 (4 legs)0.125 to 0.5 pps (each leg) Cooling Water150 gpm @ 460 psig
250 gpm @ 395 psig
50 gpm @ 350 psig
15 gpm @ 55 psig CE-5B-1 System Instrumentation
SystemNumber and TypeESP96 Ports of + 500 PSID
Barometric RefEscort240 Channels
154 Available to the CustomerThermocouples156 Type K
24 Type B
12 Type W
524 Type RGas AnalyzersHC – 1,000 ppm 1% & 5%
CO – 2,000 ppm 5%
CO2 – 5%, 10%, 20%
O2 – 25%
NO – 100 ppm, 1,000 ppm 1%
NOx –LaserPLIF, Raman Flame Tube Combustor Studies (CE-5B-2)
CE-5B-2 is one of the two test stands in the CE-5B facility. It can be configured to study lean-premixed-prevaporized (LPP) and lean-direct-injection (LDI) concepts for developing a low-NOx combustor for high-speed research and advanced subsonic applications. The non-windowed combustion flame tube can use a 3-inch square cross section or a 3-inch-diameter round section and has six ports available for gas sampling probes. The windowed combustion flame tube takes advantage of the flat walls on a 3-inch square cross section to install optical windows for non-intrusive measurements. Tests are conducted with combustion air inlet pressure ranging from 10 to 15 atmospheres with preheater and exhaust conditions described for CE-5B-1.
CE-5B-2 Special Features
The same laser-based non-intrusive diagnostics of reacting and non-reacting flowfields described for test position CE-5B-1 are available to this test section. A typical data acquisition system is used for both test positions in CE-5B. In addition, most of the optical diagnostic instruments have their own data acquisition systems.
CE-5B Facility Capabilities (typical of both rigs)
ParameterOperating ValueInlet Air Supply Pressure450 psigInlet Air Temperature100°F, preheated to 350-1,350°FInlet Airflow Stand 1 Stand 2 20 lb/s (available)
0.5 to 12.0 pps
0.5 to 5.0 ppsExhaustAtm or 20-26 in. HgRig Pressure Without Windows Stand 1 Stand 2275 psig
400 psigRig Pressure With Windows Stand 1 Stand 2250 psig
275 psigRig Fuel (JP-8) Flow7 gpm @ 400-900 psig
(three legs per stand)Window Cooling GN2 (4 legs)0.125 to 0.5 pps (each leg) Cooling Water150 gpm @ 460 psig
250 gpm @ 395 psig
50 gpm @ 350 psig
15 gpm @ 55 psig CE-5B-2 System Instrumentation
SystemNumber and TypeESP96 Ports of + 500 PSID
Barometric RefEscort240 Channels
154 Available to the CustomerThermocouples148 Type K
24 Type B
48 Type RGas AnalyzersHC – 1,000 ppm 1% & 5%
CO – 2,000 ppm 5%
CO2 – 5%, 10%, 20%
O2 – 25%
NO – 100 ppm, 1,000 ppm 1%
NOx –LaserPLIF, Raman Combustion and Dynamics Facility (CE-13C)
Test Cell CE-13 Combustion and Dynamics Facility (CDF) is used to investigate ways to reduce NOx and particulate emissions from air-breathing aircraft engines. This low-pressure (1-5 atm) facility is used to study fuel-air injection schemes and how they affect fluid mixing, emissions, dynamics, and flame stability. Jet-A fuel is the primary fuel, but candidate alternate jet fuels and their effects are also studied. Standard measurements consist of major species and dynamic pressures. Some optical measurements available are high-speed video, standard and time-resolved 2D PIV, planar laser induced fluorescence (PLIF), and chemiluminescence imaging.
CE-13C test stand. CE-13C Special Features
Research hardware is designed to flow vertically downwards. Preheated air is fed to the inlet air stream conditioner and then to the fuel injector. Fuel at room temperature is fed separately to the injector. The mixed hot air and fuel mixture moves to the combustor where combustion can be observed via customized windows. The products of combustion flow through an emission sampling ring and choke nozzle/straight outlet pipe. The fuel system consists of a 25-gallon fuel tank, a pump, and a GN2 purge. A separate laser room operates various class 3B and 4 lasers (UV, Vis, NIR) to characterize fuel injection, combustor flow, and measure combustion species.
CE-13C Facility Capabilities
ParameterOperating ValueInlet Air PressureAmbient to 75-psiaInlet Air TemperatureAmbient to 1,000°FInlet Airflow0.0 – 1.0 ppsJet Fuel SupplyCKT 1 6.9-140 pph @ 1,000-psig
CKT 2 1 – 13.1 pph @ 1,000-psig ExhaustAtmosphericPeripheral H2O Cooling54-gpm @ 100-pisgQuench Cooling11-gpm @ 500-psig Combustion species window viewport. CE-13C System Instrumentation
SystemNumber and TypeLabview64 voltage/current channels
32 temperature channels
10 voltage/current channels available to the customer
30 temperature channels available to customerOptical and LaserPLIF, Raman, PIV, droplet sizing, chemiluminescence, temperature, time-resolved imagingGas AnalyzersCO – 1,000 ppm, 5,000 ppm
CO2 – 5%, 15%
O2 – 25%
NO – 100 ppm, 1,000 ppm
NOx – 100 ppm, 1,000 ppm
HC – 100 ppm, 1,000 ppm High-Pressure Gaseous Burner (SE-5)
The SE-5 High-Pressure Combustion Diagnostics (HPCD) laboratory is a gas- and liquid-fueled high-pressure flame tube facility with single-element fuel injection burners and emission sampling ports for advanced diagnostics development and national standard calibrations. The facility provides large-aperture optical access to the primary reaction zone (flame holding) through four UV-grade fused silica optical windows (44-mm-thick by 85-mm clear apertures located around the periphery) enabling non-intrusive optical diagnostics such as laser Raman spectroscopy or high-speed imaging to measure chemical species and temperature. The HPCD rig can operate at sustained pressures up to 30 atm (or 60 atm with limited flow rate) with a variety of gaseous fuels, liquid jet fuels, and oxidizers, including hydrogen, methane, oxygen-argon, and pure oxygen. The innovative microtube array burner or micro-radial-entry counter-swirl (MRX) burner is mounted inside the air-cooled high-temperature liner casing within the rig. The burner was designed to provide a uniform combustion product zone downstream of the flame for calibrating the laser diagnostic system. The facility is also used for bench-mark tests of emission gas and particulate matters (PM) sampling. The data from the HPCD rig enables the validation of numerical codes such as powered by advanced CFD that simulate gas turbine combustors. All aspects of the facility operation, including startup, shutdown, and automatic safety shutdowns, are controlled and monitored via an icon-based touch-screen software system and a most-updated programmable logic controller (PLC) in conjunction with a precision DEWETRON data acquisition system. The HPCD rig can also provide a pressure vessel for prototype thermal or combustion hardware of a customer’s choice.
SE-5 Special Features
The facility is unique because it is the only continuous-flow, hydrogen-capable 60-atm rig in the world with optical access. It will provide researchers with new insights into flame conditions that simulate the environment inside the ultra-high pressure-ratio combustion chambers of tomorrow’s advanced aircraft engines.
SE-5 Facility Capabilities
ParameterOperating ValueCooling Capacity4,000,000 BTU/hrEquivalence Ratio Variance0.2 (fuel very lean) – 4 (fuel rich)Fuel Flow RateLimited by cooling capacity, e.g., 2 GPH of n-heptaneOperating Pressure30 atm nominal, 60 atm maxCooling Airflow0.25 lbm/s maxQuenching Airflow0.20 lbm/s max SE-5 System Instrumentation and Diagnostics
SystemNumber and TypePressure Transducers and ThermocouplesCustomDEWETRON DAQCustomEmission Gas Sampling (Exhaust)NO, NOx, SOx, O2, CO, CO2Particulates Sampling (Exhaust)Mass (TSI), counter (TSI), In-line sensor (GRC in-house)Laser Raman Spectroscopy (In Flame)CustomIn-situ Soot DetectionExtinction measurements Particulate Aerosol Laboratory (SE-11)
The Particulate Aerosol Laboratory (PAL) studies aerosols at simulated upper atmospheric conditions with altitudes up to 55,000 feet at -135°F. Altitude chamber environment and burner settings are individually controlled, creating a multitude of test parameters and a dynamic testing environment. The PAL facility is designed around a small-scale jet exhaust nozzle and altitude chamber and takes full advantage of its reduced size for screening of various alternative fuels, additives, and other combustion concepts. This makes PAL the ideal facility for validating the advancement of such research to the next phase.
Combustion fuel operation capabilities include alternative fuel additive mixing in real-time mode with switching between a baseline fuel and an alternative fuel while maintaining a continuous combustion flame. Heated bypass air is available with optional external burner and associated piping heating up to 1,000°F. Additionally, PAL is enhancing its cloud simulation capability with real-time atmospheric water vapor content readings and on-demand direct liquid injector vaporizers for high purity 100% fluid vaporization.
The SE-11 altitude chamber with the burner and alternate fuel HLPC pumps. SE-11 Special Features
Particulate emission sample extraction taking at burner rear section. Chamber equipped with windows and fused silica lenses providing optical access for non-intrusive optical diagnostic Mie scattering and color video imaging. Particulate size and number density measurements are accomplished with absorption measurements and forward, back, and side scattering. Video capability of both burner flame and altitude chamber contrails. Optical measurement plane location relative to the chamber nozzle exit is adjustable.
SE-11 Facility Capabilities
ParameterOperating ValueBurner Fuel Flow Rate.2 – 9.9 ml/min
various liquid fuelsBurner Air-Filtered and dried
-Downstream heated or non-heated bypass air available to ≤1,000°FBurner EGT≤1,000° FParticle Sizing Range2.5-1,000 nmParticle Size Distribution Concentration Range10-107 particles/cm³Aerosol Particle Size Range.75-10 nmGas Composition AnalyzerCO – CO₂ – O₂Optic Light Source300W Xenon LampOptic Video-32-bit Color
-16-bit Monochrome,
-Frame rate: 15fpsOptic DetectorsSelection of Various Spectrometers and Photodiodes Using Our Facilities
NASA’s Glenn Research Center in Cleveland provides ground test facilities to industry, government, and academia. If you are considering testing in one of our facilities or would like further information about a specific facility or capability, please let us know.
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