Still photographs taken over 16 hours on Nov. 13, 2001, on the International Space Station have been condensed into a few seconds to show the de-mixing -- or phase separation -- process studied by the Experiment on Physics of Colloids in Space. Commanded from the ground, dozens of similar tests have been conducted since the experiment arrived on ISS in 2000. The sample is a mix of polymethylmethacrylate (PMMA or acrylic) colloids, polystyrene polymers and solvents. The circular area is 2 cm (0.8 in.) in diameter. The phase separation process occurs spontaneously after the sample is mechanically mixed. The evolving lighter regions are rich in colloid and have the structure of a liquid. The dark regions are poor in colloids and have the structure of a gas. This behavior carnot be observed on Earth because gravity causes the particles to fall out of solution faster than the phase separation can occur. While similar to a gas-liquid phase transition, the growth rate observed in this test is different from any atomic gas-liquid or liquid-liquid phase transition ever measured experimentally. Ultimately, the sample separates into colloid-poor and colloid-rich areas, just as oil and vinegar separate. The fundamental science of de-mixing in this colloid-polymer sample is the same found in the annealing of metal alloys and plastic polymer blends. Improving the understanding of this process may lead to improving processing of these materials on Earth.
An Orion parachute test enters a new phase following separation from a platform.
Two Phase Flow Separator Experiment, TPFSE
The ADvanced SEParation (ADSEP) commercial payload is making use of major advances in separation technology: The Phase Partitioning Experiment (PPE); the Micorencapsulation experiment; and the Hemoglobin Separation Experiment (HSE). Using ADSEP, commercial researchers will attempt to determine the partition coefficients for model particles in a two-phase system. With this information, researchers can develop a higher resolution, more effective cell isolation procedure that can be used for many different types of research and for improved health care. The advanced separation technology is already being made available for use in ground-based laboratories.
The ADvanced SEParation (ADSEP) commercial payload is making use of major advances in separation technology: The Phase Partitioning Experiment (PPE); the Micorencapsulation experiment; and the Hemoglobin Separation Experiment (HSE). Using ADSEP, commercial researchers will attempt to determine the partition coefficients for model particles in a two-phase system. With this information, researchers can develop a higher resolution, more effective cell isolation procedure that can be used for many different types of research and for improved health care. The advanced separation technology is already being made available for use in ground-based laboratories.
HOUSTON – Engineers for Boeing Space Exploration demonstrate that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
S68-51306 (December 1968) --- North American Rockwell artist's concept illustrating a phase of the scheduled Apollo 8 lunar orbit mission. Here, the Apollo 8 spacecraft lunar module adapter (SLA) panels, which have supported the Command and Service Modules, are jettisoned. This is done by astronauts firing the service module reaction control engines. A signal simultaneously deploys and jettisons the panels, separating the spacecraft from the SLA and deploying the high gain (deep space) antenna.
HOUSTON – Engineers for Boeing Space Exploration demonstrate that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
Artist Concepts, Apollo Mission: S66-10983: Ascent Stage Liftoff (S66-05094) S66-10984: Orientation During Ascent Phase (S66-05098) S66-10985: Midcourse Coast (S66-05113) S66-10986: Survey of Landing Site (S66-05117) S66-10987: Lunar Module (LM) Jettison (S66-05089) S66-10988: Trans-Earth Injection (S66-05090) S66-10989: Exploration on Lunar Surface Apollo Surface Lunar Exploration Experiment (ASLEP) S66-10990: Liftoff (S66-05125) S66-10991: Command Module (CM)-Service Module (SM) Separation (S66-05101 N/F) S66-10992: Touchdown on Lunar Surface (S66-05115) S66-10993: Transfer Orbit Insertion (S66-05111) S66-10994: Drogue Parachute Deployment S66-10995: S-IC Stage Separation S-II Stage Thrusting (S66-05099) S66-10996: Jettison Launch Escape System (S66-05114) S66-10997: Main Parachute Deployment (S66-05091) S66-10998: Mid-course correction (S66-05088) S66-10999: Lunar Orbit Insertion (S66-05086) S66-11000: Command Service Module (CSM)-LM Docked in LM Adapter-S-IVB (S66-06526) S66-11001: Docking and Separation of spacecraft from S-IVB (S66-05107) S66-11002: Final Descent (S66-05096) S66-11003: Entry into Earth Atmosphere (S66-05096) S66-11004: Deploy S/C LM Adapter-Separate CSM from LM-S-IVB (S66-06525 & 05105) S66-11005: Turnaround of CSM (S66-05104) S66-11006: S-II Stage Separation S-IVB Stage Thrusting (S66-05102) S66-11007: LM Ascent CSM Docked (S66-05100) S66-11008: Midcourse Correction SPS Mode (S66-05106) S66-11009: Earth Orbit Insertion of S-IVB & S/C (S66-05092) S66-11010: Trans-lunar Injection (S66-05116) S66-11011: LM Descent (S66-05110) S66-11012: S-IVB Stage Operations (S66-05112 N/F) S66-11013: Spacecraft Recovery (S66-05126) S66-11014: Lunar Orbit (S66-05103) S66-11015: CSM-LM Docking (S66-05095) S66-11016: Entry CM (S66-5109) S66-11017: Midcourse Corrections to Lunar Landing (S66-08486) S66-11018: Midcourse Corrections to Lunar Landing w/Overlay (S66-05083) S66-11019: Earth Launch Phase w/Overlay (S66-08485 & 05119) S66-11020: Earth Launch Phase (S66-08487 & S66-05084) S66-11022: Apollo Vehicles (S66-05127) S66-11024: Transfer to LM (S66-05082) S66-11025: Lunar Launch Phase S66-11027: Trans-earth Separation of C/M from S/M-C/M return to Earth (S66-05097) S66-11028: CSM-LM Separation, LM Descent to Moon (S66-05108) MSC, Houston, TX Also available in B&W 12/1965 - 06/1966
NASA Associate Administrator for the Science Mission Directorate Thomas Zurbuchen, center, reacts after hearing confirmation that the James Webb Space Telescope successfully separated from the Ariane 5 rocket, Saturday, Dec. 25, 2021, in the Jupiter Hall of the Guiana Space Centre in Kourou, French Guiana. The James Webb Space Telescope (sometimes called JWST or Webb) is a large infrared telescope with a 21.3 foot (6.5 meter) primary mirror. The observatory will study every phase of cosmic history—from within our solar system to the most distant observable galaxies in the early universe. Photo Credit: (NASA/Bill Ingalls)
HOUSTON – Monitors show Chris Ferguson, a former space shuttle commander who is now director of Crew and Mission Operations for Boeing Space Exploration, at the controls in the inside the company's CST-100 spacecraft simulator. Boeing demonstrated that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
NASA James Webb Space Telescope Program Scientist Eric Smith reacts after hearing confirmation that the James Webb Space Telescope successfully separated from the Ariane 5 rocket, Saturday, Dec. 25, 2021, in the Jupiter Hall of the Guiana Space Centre in Kourou, French Guiana. The James Webb Space Telescope (sometimes called JWST or Webb) is a large infrared telescope with a 21.3 foot (6.5 meter) primary mirror. The observatory will study every phase of cosmic history—from within our solar system to the most distant observable galaxies in the early universe. Photo Credit: (NASA/Bill Ingalls)
HOUSTON – Chris Ferguson, a former space shuttle commander who is now director of Crew and Mission Operations for Boeing Space Exploration, takes the controls inside the company's CST-100 spacecraft simulator. To Ferguson's right, an engineer observes the exercise. Boeing demonstrated that the CST-100's software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
HOUSTON – Chris Ferguson, a former space shuttle commander who is now director of Crew and Mission Operations for Boeing Space Exploration, sits at the controls in the inside the company's CST-100 spacecraft simulator. Boeing demonstrated that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
HOUSTON – Chris Ferguson, a former space shuttle commander who is now director of Crew and Mission Operations for Boeing Space Exploration, talks with an engineer following simulations that showed that the CST-100 software. Boeing demonstrated that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
HOUSTON – An engineer with Boeing Space Exploration explains how to read the cockpit displays inside the company's CST-100 spacecraft simulator to NASA Commercial Crew Program engineers. Boeing demonstrated that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA_Bill Stafford
S75-27288 (April 1975) --- An artist?s concept illustrating the mission profile of the Apollo-Soyuz Test Project. The phases of the mission depicted include launch, rendezvous, docking, separation and splashdown. During the joint U.S.-USSR ASTP flight, scheduled for July 1975, the American and Soviet crews will visit one another?s spacecraft while the Soyuz and Apollo are docked for a maximum period of two days. The mission is designed to test equipment and techniques that will establish international crew rescue capability in space, as well as permit future cooperative scientific missions. This artwork is by Davis Meltzer.
The photograph shows the loading operation of the Saturn I S-IV stage (second stage) into the Pregnant Guppy at the Redstone Airfield, Huntsville, Alabama. The Pregnant Guppy was a Boeing B-377 Stratocruiser modified to transport various stages of Saturn launch vehicles. The modification project called for lengthening the fuselage to accommodate the S-IV stage. After the flight test of that modification, phase two called for the enlargement of the plane's cabin section to approximately double its normal volume. The fuselage separated just aft of the wing's trailing edge to load and unload the S-IV and other cargoes.
HOUSTON - Chris Ferguson, a former space shuttle commander who is now director of Crew and Mission Operations for Boeing Space Exploration, sits at the controls in the inside the company's CST-100 spacecraft simulator. Boeing demonstrated that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford
NASA's Perseverance rover fires up its descent stage engines as it nears the Martian surface in this illustration. This phase of its entry, descent and landing sequence, or EDL, is known as "powered descent." Hundreds of critical events must execute perfectly and exactly on time for the rover to land safely on Feb. 18, 2021. The cruise stage separates about 10 minutes before entering into the atmosphere, leaving the aeroshell, which encloses the rover and descent stage, to make the trip to the surface. At about 6,900 feet (2,100 meters) above the surface, the rover separates from the parachute and backshell. At this point, the rover is joined to the descent stage, which functions as a sort of jetpack for the rover. The descent stage fires up its engines, flies to a reachable self-selected safe landing target, levels out, and slows to its final descent speed of about 1.7 mph (2.7 kph). It then initiates the "skycrane" maneuver: about 12 seconds before touchdown, roughly 66 feet (20 meters) above the surface, the descent stage lowers the rover on a set of cables about 21 feet (6.4 meters) long. The rover unstows its mobility system, locking its legs and wheels into landing position. EDL ends about seven minutes after atmospheric entry, with Perseverance stationary on the Martian surface. https://photojournal.jpl.nasa.gov/catalog/PIA24318
This artist's concept shows a diagram of how the inside of Ceres could be structured, based on data about the dwarf planet's gravity field from NASA's Dawn mission. Using information about Ceres' gravity and topography, scientists found that Ceres is "differentiated," which means that it has compositionally distinct layers at different depths. The densest layer is at the core, which scientists suspect is made of hydrated silicates. Above that is a volatile-rich shell, topped with a crust of mixed materials. This research teaches scientists about what internal processes could have occurred during the early history of Ceres. It appears that, during a heating phase early in the history of Ceres, water and other light materials partially separated from rock. These light materials and water then rose to the outer layer of Ceres. http://photojournal.jpl.nasa.gov/catalog/PIA20867
Arianespace CEO Stéphane Israël, at desk, and NASA Associate Administrator for the Science Mission Directorate Thomas Zurbuchen, right, both gives a thumbs up after receiving confirmation that the Ariane 5 rocket upper stage shut down as planed a few minutes before separation from the James Webb Space Telescope, Saturday, Dec. 25, 2021, in the Jupiter Hall of the Guiana Space Centre in Kourou, French Guiana. The James Webb Space Telescope (sometimes called JWST or Webb) is a large infrared telescope with a 21.3 foot (6.5 meter) primary mirror. The observatory will study every phase of cosmic history—from within our solar system to the most distant observable galaxies in the early universe. Photo Credit: (NASA/Bill Ingalls)
ESA (European Space Agency) Director-General Dr. Josef Aschbacher, 2nd from left, and NASA Associate Administrator for the Science Mission Directorate Thomas Zurbuchen, 3rd from left, celebrate after hearing confirmation that the James Webb Space Telescope successfully separated from the Ariane 5 rocket, Saturday, Dec. 25, 2021, in the Jupiter Hall of the Guiana Space Centre in Kourou, French Guiana. The James Webb Space Telescope (sometimes called JWST or Webb) is a large infrared telescope with a 21.3 foot (6.5 meter) primary mirror. The observatory will study every phase of cosmic history—from within our solar system to the most distant observable galaxies in the early universe. Photo Credit: (NASA/Bill Ingalls)
ISS039-E-014672 (23 April 2014) --- The unpiloted Progress 53 cargo ship undocks from the aft port of the Zvezda service module at 3:58 a.m. (CDT) on April 23 and begins its relative separation from the International Space Station for tests on its upgraded Kurs automated rendezvous system that were delayed from last November. The Russian resupply vehicle will move to a distance of some 300 miles from the complex before it begins to phase back in, testing the Kurs-NA rendezvous hardware and its associated software. The enhanced Kurs system will be incorporated into future Progress vehicles to reduce weight by eliminating several navigational antennas, thus enabling the Progress to carry additional supplies to the station. The Progress is scheduled to redock to Zvezda around 7:15 a.m. (CDT) April 25.
ISS039-E-016869 (23 April 2014) --- The unpiloted Progress 53 cargo ship undocks from the aft port of the Zvezda service module at 3:58 a.m. (CDT) on April 23 and begins its relative separation from the International Space Station for tests on its upgraded Kurs automated rendezvous system that were delayed from last November. The Russian resupply vehicle will move to a distance of some 300 miles from the complex before it begins to phase back in, testing the Kurs-NA rendezvous hardware and its associated software. The enhanced Kurs system will be incorporated into future Progress vehicles to reduce weight by eliminating several navigational antennas, thus enabling the Progress to carry additional supplies to the station. The Progress is scheduled to redock to Zvezda around 7:15 a.m. (CDT) April 25.
It may look as though Saturn's moon Mimas is crashing through the rings in this image taken by NASA's Cassini spacecraft, but Mimas is actually 28,000 miles (45,000 kilometers) away from the rings. There is a strong connection between the icy moon and Saturn's rings, though. Gravity links them together and shapes the way they both move. The gravitational pull of Mimas (246 miles or 396 kilometers across) creates waves in Saturn's rings that are visible in some Cassini images. Mimas' gravity also helps create the Cassini Division (not pictured here), which separates the A and B rings. This view looks toward the anti-Saturn hemisphere of Mimas. North on Mimas is up and rotated 15 degrees to the right. The image was taken in green light with the Cassini spacecraft narrow-angle camera on Oct. 23, 2016. The view was acquired at a distance of approximately 114,000 miles (183,000 kilometers) from Mimas and at a Sun-Mimas-spacecraft, or phase, angle of 29 degrees. Image scale is 3,300 feet (1 kilometer) per pixel. http://photojournal.jpl.nasa.gov/catalog/PIA20510
In response to President Reagan's directive to NASA to develop a permanent marned Space Station within a decade, part of the State of the Union message to Congress on January 25, 1984, NASA and the Administration adopted a phased approach to Station development. This approach provided an initial capability at reduced costs, to be followed by an enhanced Space Station capability in the future. This illustration depicts the baseline configuration, which features a 110-meter-long horizontal boom with four pressurized modules attached in the middle. Located at each end are four photovoltaic arrays generating a total of 75-kW of power. Two attachment points for external payloads are provided along this boom. The four pressurized modules include the following: A laboratory and habitation module provided by the United States; two additional laboratories, one each provided by the European Space Agency (ESA) and Japan; and an ESA-provided Man-Tended Free Flyer, a pressurized module capable of operations both attached to and separate from the Space Station core. Canada was expected to provide the first increment of a Mobile Serving System.
A cutaway illustration of Saturn I launch vehicle characteristics: The Saturn I, first of the Saturn launch vehicles' family, is a two-stage vehicle with a low-earth-orbit payload capability of approximately 25,000 pounds. The research and development program was plarned in two phases or blocks; one for first stage development (Block I) and the second for first and second stage development (Block II). The S-I (first) stage consisted of a cluster of nine propellant tanks and eight H-1 engines built by Rocketdyne, yeilding a total thrust of 1,500,000 pounds. The second stage identified as S-IV, was designed as a single cylinder with a common bulkhead separating the liquid oxygen from the liquid hydrogen. Propulsion was provided by six RL-10 engines built by Pratt Whitney, capable of producing a combined thrust of 90,000 pounds. Of the 10 Saturn I's planned, the first eight were designed and built at the Marshall Space Flight Center. The remaining two were built by the Chrysler Corporation.
This photograph was taken during the final assembly phase of the Space Shuttle light weight external tanks (LWT) 5, 6, and 7 at the Michoud Assembly Facility in New Orleans, Louisiana. The giant cylinder, higher than a 15-story building, with a length of 154-feet (47-meters) and a diameter of 27.5-feet (8.4-meters), is the largest single piece of the Space Shuttle. During launch, the external tank (ET) acts as a backbone for the orbiter and solid rocket boosters. In separate, internal pressurized tank sections, the ET holds the liquid hydrogen fuel and liquid oxygen oxidizer for the Shuttle's three main engines. During launch, the ET feeds the fuel under pressure through 17-inch (43.2-centimeter) ducts which branch off into smaller lines that feed directly into the main engines. Some 64,000 gallons (242,260 liters) of fuel are consumed by the main engines each minute. Machined from aluminum alloys, the Space Shuttle's ET is the only part of the launch vehicle that currently is not reused. After its 526,000 gallons (1,991,071 liters) of propellants are consumed during the first 8.5 minutes of flight, it is jettisoned from the orbiter and breaks up in the upper atmosphere, its pieces falling into remote ocean waters. The Marshall Space Flight Center was responsible for developing the ET
Engineers and technicians examine and test the first of NASA's Europa Clipper's science instruments to be delivered to the agency's Jet Propulsion Laboratory in Southern California. The ultraviolet spectrograph, called Europa-UVS and led by the Southwest Research Institute in San Antonio, Texas, will be integrated into the spacecraft during the phase of the mission called assembly, test, and launch operations. Europa-UVS is part of a payload of nine science instruments aboard Europa Clipper. In this photo, captured in February 2022, the instrument's custom testing equipment is seen at left, with a boxy, red frame. The instrument itself is seen at right. During testing, technicians shined ultraviolet light into the instrument's front aperture. With an internal global ocean under a thick layer of ice, Jupiter's moon Europa may have the potential to harbor existing life. Europa Clipper will swoop around Jupiter in an elliptical orbit, dipping close to the moon on each flyby to collect data. Understanding Europa's habitability will help scientists better understand how life developed on Earth and the potential for finding life beyond our planet. Europa Clipper is set to launch in 2024. Europa-UVS will search above the surface of Europa for signs of potential plumes that may be venting subsurface water into space. The instrument collects ultraviolet light, then separates the wavelengths of that light to help determine the composition of the moon's surface and gases in the atmosphere. https://photojournal.jpl.nasa.gov/catalog/PIA24897
A cutaway illustration of Saturn 1 launch vehicle mission. The Saturn I, first of the Saturn launch vehicles' family, is a two-stage vehicle with a low-earth-orbit payload capability of approximately 25,000 pounds. The research and development program was plarned in two phases or blocks; one for first stage development (Block I) and the second for first and second stage development (Block II). The S-I (first) stage consisted of a cluster of nine propellant tanks and eight H-1 engines built by Rocketdyne, yeilding a total thrust of 1,500,000 pounds. The second stage of Saturn I, identified as S-IV, was designed as a single cylinder with a common bulkhead separating the liquid oxygen from the liquid hydrogen. Propulsion was provided by six RL-10 engines built by Pratt Whitney, capable of producing a combined thrust of 90,000 pounds. Of the 10 Saturn I's planned, the first eight were designed and built at the Marshall Space Flight Center. The remaining two were built by the Chrysler Corporation.
The aeroshell containing NASA's Perseverance rover guides itself towards the Martian surface as it descends through the atmosphere in this illustration. Hundreds of critical events must execute perfectly and exactly on time for the rover to land on Mars safely on Feb. 18, 2021. Entry, Descent, and Landing, or "EDL," begins when the spacecraft reaches the top of the Martian atmosphere, traveling nearly 12,500 mph (20,000 kph). The cruise stage separates about 10 minutes before entering into the atmosphere, leaving the aeroshell, which encloses the rover and descent stage, to make the trip to the surface. The vehicle fires small thrusters on the backshell to reorient itself and make sure the heat shield is facing forward. The spacecraft uses the Martian atmosphere to brake, causing it to heat up dramatically. Peak heating occurs about 80 seconds after atmospheric entry. The rover is safe in the aeroshell, and reaches only about room temperature. Peak deceleration occurs about 10 seconds later (~90 seconds after atmospheric entry). As it descends through the atmosphere, the spacecraft fires thrusters on its backshell to guide itself. This phase of the descent is referred to as "guided entry." https://photojournal.jpl.nasa.gov/catalog/PIA24315
NASA's Cassini spacecraft looks toward the brilliant disk of Saturn, surrounded by the icy lanes of its rings. Faint wisps of cloud are visible in the atmosphere. At bottom, ring shadows trace delicate, curving lines across the planet. Prometheus (53 miles or 86 kilometers across) is just a few pixels wide in this view, barely visible as a dark speck in front of the planet, below the rings and to the left of center. Between April and September 2017, Cassini will plunge repeatedly through the gap that separates the planet from the rings. This view looks toward the sunlit side of the rings from about a degree above the ring plane. The image was taken in green light with the Cassini spacecraft wide-angle camera on July 21, 2016. The view was obtained at a distance of approximately 529,000 miles (852,000 kilometers) from Saturn and at a sun-Saturn-spacecraft, or phase, angle of 37 degrees. Image scale is 30 miles (50 kilometers) per pixel. http://photojournal.jpl.nasa.gov/catalog/PIA20500
In response to President Reagan's directive to NASA to develop a permanent marned Space Station within a decade, part of the State of the Union message to Congress on January 25, 1984, NASA and the Administration adopted a phased approach to Station development. This approach provided an initial capability at reduced costs, to be followed by an enhanced Space Station capability in the future. This illustration depicts the baseline configuration, which features a 110-meter-long horizontal boom with four pressurized modules attached in the middle. Located at each end are four photovoltaic arrays generating a total of 75-kW of power. Two attachment points for external payloads are provided along this boom. The four pressurized modules include the following: A laboratory and habitation module provided by the United States; two additional laboratories, one each provided by the European Space Agency (ESA) and Japan; and an ESA-provided Man-Tended Free Flyer, a pressurized module capable of operations both attached to and separate from the Space Station core. Canada was expected to provide the first increment of a Mobile Serving System.
ISS020-E-028123 (5 Aug. 2009) --- Mount Hood, Oregon is featured in this image photographed by an Expedition 20 crew member on the International Space Station. Mount Hood is located within the Cascade Range of the western United States, and is the highest peak (3,426 m) in Oregon. The Cascade Range is characterized by a line of volcanoes associated with a slab of oceanic crust that is subducting, or descending underneath, the westward moving continental crust of North America. Magma generated by the subduction process rises upward through the crust and feeds a line of active volcanoes that extends from northern California in the United States to southern British Columbia in Canada. While hot springs and steam vents are still active on Mount Hood, the last eruption from the volcano occurred in 1866. The volcano is considered dormant, but still actively monitored. Separate phases of eruptive activity produced pyroclastic flows and lahars ? mudflows ? that carried erupted materials down all of the major rivers draining the volcano. Gray volcanic deposits extend southwards along the banks of the White River (upper right), and form several prominent ridges along the southeast to southwest flanks of the volcano. The deposits contrast sharply with the green vegetated lower flanks of the volcano. The Mount Hood stratovolcano ? a typically cone-shaped volcanic structure formed by interlayered lava flows and explosive eruption deposits ? hosts twelve mapped glaciers along its upper flanks (center). Like other glaciers in the Pacific Northwest, the Hood glaciers have been receding due to global warming, and have lost an estimated 61 percent of their volume over the past century. The predicted loss of glacial meltwater under future warming scenarios will have significant effects on regional hydrology and water supplies.
Shown here in a new image taken with the Advanced Camera for Surveys (ACS) on board the NASA/ESA Hubble Space Telescope, is the globular cluster NGC 1783. This is one of the biggest globular clusters in the Large Magellanic Cloud, a satellite galaxy of our own galaxy, the Milky Way, in the southern hemisphere constellation of Dorado. First observed by John Herschel in 1835, NGC 1783 is nearly 160 000 light-years from Earth, and has a mass around 170 000 times that of the Sun. Globular clusters are dense collections of stars held together by their own gravity, which orbit around galaxies like satellites. The image clearly shows the symmetrical shape of NGC 1783 and the concentration of stars towards the centre, both typical features of globular clusters. By measuring the colour and brightness of individual stars, astronomers can deduce an overall age for a cluster and a picture of its star formation history. NGC 1783 is thought to be under one and a half billion years old — which is very young for globular clusters, which are typically several billion years old. During that time, it is thought to have undergone at least two periods of star formation, separated by 50 to 100 million years. This ebb and flow of star-forming activity is an indicator of how much gas is available for star formation at any one time. When the most massive stars created in the first burst of formation explode as supernovae they blow away the gas needed to form further stars, but the gas reservoir can later be replenished by less massive stars which last longer and shed their gas less violently. After this gas flows to the dense central regions of the star cluster, a second phase of star formation can take place and once again the short-lived massive stars blow away any leftover gas. This cycle can continue a few times, at which time the remaining gas reservoir is thought to be too small to form any new stars. A version of this image was entered into the Hubble's Hidden Treasures image pr
Shown here in a new image taken with the Advanced Camera for Surveys (ACS) on board the NASA/ESA Hubble Space Telescope is the globular cluster NGC 1783. This is one of the biggest globular clusters in the Large Magellanic Cloud, a satellite galaxy of our own galaxy, the Milky Way, in the southern hemisphere constellation of Dorado. First observed by John Herschel in 1835, NGC 1783 is nearly 160,000 light-years from Earth, and has a mass around 170,000 times that of the sun. Globular clusters are dense collections of stars held together by their own gravity, which orbit around galaxies like satellites. The image clearly shows the symmetrical shape of NGC 1783 and the concentration of stars towards the center, both typical features of globular clusters. By measuring the color and brightness of individual stars, astronomers can deduce an overall age for a cluster and a picture of its star formation history. NGC 1783 is thought to be less than one and a half billion years old — which is very young for globular clusters, which are typically several billion years old. During that time, it is thought to have undergone at least two periods of star formation, separated by 50 to 100 million years. This ebb and flow of star-forming activity is an indicator of how much gas is available for star formation at any one time. When the most massive stars created in the first burst of formation explode as supernovae they blow away the gas needed to form further stars, but the gas reservoir can later be replenished by less massive stars which last longer and shed their gas less violently. After this gas flows to the dense central regions of the star cluster, a second phase of star formation can take place and once again the short-lived massive stars blow away any leftover gas. This cycle can continue a few times, at which time the remaining gas reservoir is thought to be too small to form any new stars. Image credit: ESA/Hubble & NASA, Acknowledgement: Judy Schmidt <b><a href="http://www.nasa.gov/audience/formedia/features/MP_Photo_Guidelines.html" rel="nofollow">NASA image use policy.</a></b> <b><a href="http://www.nasa.gov/centers/goddard/home/index.html" rel="nofollow">NASA Goddard Space Flight Center</a></b> enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. <b>Follow us on <a href="http://twitter.com/NASAGoddardPix" rel="nofollow">Twitter</a></b> <b>Like us on <a href="http://www.facebook.com/pages/Greenbelt-MD/NASA-Goddard/395013845897?ref=tsd" rel="nofollow">Facebook</a></b> <b>Find us on <a href="http://instagrid.me/nasagoddard/?vm=grid" rel="nofollow">Instagram</a></b>
The Lunar Gateway Launch, mapped. Gateway's first elements, the Power and Propulsion Element and HALO (Habitation and Logistics Outpost), will launch together to lunar orbit, where they’ll set the stage for Artemis IV: the first Gateway assembly mission. During this milestone mission, the Artemis IV crew will deliver the European Space Agency's Lunar I-Hab, dock it to HALO, and enter the space station for the very first time. NASA is currently targeting a 2027 launch for HALO and the Power and Propulsion Element. This timeline allows for the roughly year-long journey to lunar orbit and ensures everything is in place ahead of Artemis IV.