X-38 in Flight during Second Free Flight

NASA Technical Reports Server (NTRS)

1999-01-01

NASA's X-38, a research vehicle developed as part of an effort to build an emergency Crew Return Vehicle (CRV) for the International Space Station, descends toward the desert floor under its steerable parafoil on its second free flight. The X-38 was launched from NASA Dryden's B-52 Mothership on Saturday, February 6, 1999, from an altitude of approximately 23,000 feet. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA

X-38 in Flight during Second Free Flight

NASA Technical Reports Server (NTRS)

1999-01-01

NASA's X-38, a research vehicle developed as part of an effort to build an emergency Crew Return Vehicle (CRV) for the International Space Station, descends toward a desert lakebed under its steerable parafoil on its second free flight. The X-38 was launched from NASA Dryden's B-52 Mothership on Saturday, February 6, 1999, from an altitude of approximately 23,000 feet. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA

X-38 - First Free Flight, March 12, 1998

NASA Technical Reports Server (NTRS)

1998-01-01

The X-38 Crew Return Vehicle descends under its steerable parafoil over the California desert in its first free flight at the Dryden Flight Research Center, Edwards, California. The flight took place March 12, 1998. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed

X-38 - First Free Flight, March 12, 1998

NASA Technical Reports Server (NTRS)

1998-01-01

The X-38 Crew Return Vehicle descends under its steerable parafoil over the California desert during its first free flight in March 1998 at the Dryden Flight Research Center, Edwards, California. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the

Parachute Testing for the NASA X-38 Crew Return Vehicle

NASA Technical Reports Server (NTRS)

Stein, Jenny M.

2005-01-01

NASA's X-38 program was an in-house technology demonstration program to develop a Crew Return Vehicle (CRV) for the International Space Station capable of returning seven crewmembers to Earth when the Space Shuttle was not present at the station. The program, managed out of NASA's Johnson Space Center, was started in 1995 and was cancelled in 2003. Eight flights with a prototype atmospheric vehicle were successfully flown at Edwards Air Force Base, demonstrating the feasibility of a parachute landing system for spacecraft. The intensive testing conducted by the program included testing of large ram-air parafoils. The flight test techniques, instrumentation, and simulation models developed during the parachute test program culminated in the successful demonstration of a guided parafoil system to land a 25,000 Ib spacecraft. The test program utilized parafoils of sizes ranging from 750 to 7500 p. The guidance, navigation, and control system (GN&C) consisted of winches, laser or radar altimeter, global positioning system (GPS), magnetic compass, barometric altimeter, flight computer, and modems for uplink commands and downlink data. The winches were used to steer the parafoil and to perform the dynamic flare maneuver for a soft landing. The laser or radar altimeter was used to initiate the flare. In the event of a GPS failure, the software navigated by dead reckoning using the compass and barometric altimeter data. The GN&C test beds included platforms dropped from cargo aircraft, atmospheric vehicles released from a 8-52, and a Buckeye powered parachute. This paper will describe the test program and significant results.

X-38 Vehicle #132 Landing on First Free Flight

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38, a research vehicle built to help develop technology for an emergency Crew Return Vehicle (CRV), flares for its lakebed landing at the end of a March 1999 test flight at the Dryden Flight Research Center, Edwards, California. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted

X-38: Artist Concept of Re-Entering Earth's Atmosphere

NASA Technical Reports Server (NTRS)

1997-01-01

This is an artist's depiction of NASA's proposed Crew Return Vehicle (CRV) re-entering the earth's atmosphere. A team of NASA researchers began free flight tests of the X-38, a technology demonstrator for the CRV, at NASA's Dryden Flight Research Center, Edwards, California, in 1998. The CRV is being designed as a 'lifeboat' for the International Space Station The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used

X-38 Arrival at NASA Dryden on June 4, 1997

NASA Technical Reports Server (NTRS)

1997-01-01

NASA's first X-38 Advanced Technology Demonstrator for the proposed Crew Return Vehicle (CRV) is transported down a road at NASA's Dryden Flight Research Center, Edwards, California, upon its arrival there in June 1997. The vehicle arrived aboard a USAF C-17 transport aircraft from NASA's Johnson Space Center (JSC). The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more

X-38 - Landing After First Free Flight, March 12, 1998

NASA Technical Reports Server (NTRS)

1998-01-01

The X-38 Crew Return Vehicle touches down amidst the California desert scrubbrush at the end of its first free flight at the Dryden Flight Research Center, Edwards, California, in March 1998. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the

X-38 Drop Model: Testing Parafoil Landing System during Drop Tests

NASA Technical Reports Server (NTRS)

1995-01-01

A 4-foot-long model of NASA's X-38, an experimental crew return vehicle, glides to earth after being dropped from a Cessna aircraft in late 1995. The model was used to test the ram-air parafoil landing system, which could allow for accurate and controlled landings of an emergency Crew Return Vehicle spacecraft returning to Earth. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to

X-38 - On Ground after First Free Flight, March 12, 1998

NASA Technical Reports Server (NTRS)

1998-01-01

Crew members surround the X-38 lifting body research vehicle after a successful test flight and landing in March 1998. The flight was the first free flight for the vehicle and took place at the Dryden Flight Research Center, Edwards, California. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an

X-38 Drop Model: Glides to Earth After Being Dropped from a Cessna

NASA Technical Reports Server (NTRS)

1995-01-01

A 4-foot-long model of NASA's X-38, an experimental crew return vehicle, glides to earth after being dropped from a Cessna aircraft in late 1995. The model was used to test the ram-air parafoil landing system, which could allow for accurate and controlled landings of an emergency Crew Return Vehicle spacecraft returning to Earth. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to

X-38 Drop Model: Used to Test Parafoil Landing System during Drop Tests

NASA Technical Reports Server (NTRS)

1995-01-01

A 4-foot-long model of NASA's X-38, an experimental crew return vehicle, glides to earth after being dropped from a Cessna aircraft in late 1995. The model was used to test the ram-air parafoil landing system, which could allow for accurate and controlled landings of an emergency Crew Return Vehicle spacecraft returning to Earth. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to

X-38 Vehicle #132 in Flight Approaching Landing during First Free Flight

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38, a research vehicle built to help develop technology for an emergency Crew Return Vehicle (CRV), maneuvers toward landing at the end of a March 1999 test flight at the Dryden Flight Research Center, Edwards, California. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting

Dale Reed with X-38 and a Subscale Model Used in Test Program

NASA Technical Reports Server (NTRS)

1997-01-01

Dale Reed, a NASA engineer who worked on the original lifting-body research programs in the 1960s and 1970s, stands with a scale-model X-38 that was used in 1995 research flights, with a full-scale X-38 (80 percent of the size of a potential Crew Return Vehicle) behind him. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space

X-38 Vehicle #132 in Flight with Deployed Parafoil during First Free Flight

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38, a research vehicle built to help develop technology for an emergency Crew Return Vehicle (CRV), descends under its steerable parafoil on a March 1999 test flight at the Dryden Flight Research Center, Edwards, California. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting

Two X-38 Ship Demonstrators in Development at NASA Johnson Space Flight Center

NASA Technical Reports Server (NTRS)

1999-01-01

This photo shows two X-38 Crew Return Vehicle technology demonstrators under development at NASA's Johnson Space Flight Center, Houston, Texas. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the size of a projected emergency crew return vehicle

The world's largest parafoil slowly deflates after carrying the X-38, V-131R, to a safe landing

NASA Technical Reports Server (NTRS)

2000-01-01

Looking like a giant air mattress, the world's largest parafoil slowly deflates seconds after it carried the latest version of the X-38, V-131R, to a landing on Rogers Dry Lake adjacent to NASA's Dryden Flight Research Center at Edwards, California, at the end of its first free flight, November 2, 2000. The X-38 prototypes are intended to perfect technology for a planned Crew Return Vehicle (CRV) 'lifeboat' to carry a crew to safety in the event of an emergency on the International Space Station. Free-flight tests of X-38 V-131R are evaluating upgraded avionics and control systems and the aerodynamics of the modified upper body, which is more representative of the final design of the CRV than the two earlier X-38 test craft, including a simulated hatch atop the body. The huge 7,500 square-foot parafoil will enable the CRV to land in the length of a football field after returning from space. The first three X-38's are air-launched from NASA's venerable NB-52B mother ship, while the last version, V-201, will be carried into space by a Space Shuttle and make a fully autonomous re-entry and landing.

The world's largest parafoil slowly deflates after carrying the X-38, V-131R, to a safe landing

NASA Image and Video Library

2000-11-02

Looking like a giant air mattress, the world's largest parafoil slowly deflates seconds after it carried the latest version of the X-38, V-131R, to a landing on Rogers Dry Lake adjacent to NASAÕs Dryden Flight Research Center at Edwards, California, at the end of its first free flight, November 2, 2000. The X-38 prototypes are intended to perfect technology for a planned Crew Return Vehicle (CRV) "lifeboat" to carry a crew to safety in the event of an emergency on the International Space Station. Free-flight tests of X-38 V-131R are evaluating upgraded avionics and control systems and the aerodynamics of the modified upper body, which is more representative of the final design of the CRV than the two earlier X-38 test craft, including a simulated hatch atop the body. The huge 7,500 square-foot parafoil will enable the CRV to land in the length of a football field after returning from space. The first three X-38's are air-launched from NASA's venerable NB-52B mother ship, while the last version, V-201, will be carried into space by a Space Shuttle and make a fully autonomous re-entry and landing.

X-38 V201 Avionics Architecture

NASA Technical Reports Server (NTRS)

Bedos, Thierry; Anderson, Brian L.

1999-01-01

The X-38 is an experimental NASA project developing a core human capable spacecraft at a fraction of the cost of any previous human rated vehicle. The first operational derivative developed from the X-38 program will be the International Space Station (ISS) Crew Return Vehicle (CRV). Although the current X-38 vehicles are designed as re-entry vehicles only, the option exists to modify the vehicle for uses as an upward vehicle launched from an expendable launch vehicle or from the X-33 operational derivative. The Operational CRV, that will be derived from the X-38 spaceflight vehicle, will provide an emergency return capability from the International Space Station (ISS). The spacecraft can hold a crew of up to seven inside a pressurized cabin. The CRV is passively delivered to ISS, stays up to three year on-orbit attached to ISS in a passive mode with periodic functional checkout, before separation from ISS, de-orbit, entry and landing. The X-38 Vehicle 201 (V201) is being developed at NASA/JSC to demonstrate key technologies associated with the development of the CRV design. The X-38 flight test will validate the low cost development concept by demonstrating the entire station departure, re-entry, guidance and landing portions of the CRV mission. All new technologies and subsystems proposed for CRV will be validated during either the on orbit checkout or flight phases of the X-38 space flight test. The X-38 subsystems are required to be similar to those subsystems required for the CRV to the greatest extent possible. In many cases, the subsystems are identical to those that will be utilized on the Operational CRV.

X-38 Experimental Aerothermodynamics

NASA Technical Reports Server (NTRS)

Horvath, Thomas J.; Berry, Scott A.; Merski, N. Ronald; Fitzgerald, Steve M.

2000-01-01

The X-38 program seeks to demonstrate an autonomously returned orbital test flight vehicle to support the development of an operational Crew Return Vehicle for the International Space Station. The test flight, anticipated in 2002, is intended to demonstrate the entire mission profile of returning Space Station crew members safely back to earth in the event of medical or mechanical emergency. Integral to the formulation of the X-38 flight data book and the design of the thermal protection system, the aerothermodynamic environment is being defined through a synergistic combination of ground based testing and computational fluid dynamics. This report provides an overview of the hypersonic aerothermodynamic wind tunnel program conducted at the NASA Langley Research Center in support of the X-38 development. Global and discrete surface heat transfer force and moment, surface streamline patterns, and shock shapes were measured on scaled models of the proposed X-38 configuration in different test gases at Mach 6, 10 and 20. The test parametrics include angle of attack from 0 to 50 degs, unit Reynolds numbers from 0.3 x 10 (exp 6) to 16 x 10 (exp 6)/ ft, rudder deflections of 0, 2, and 5 deg. and body flap deflections from 0 to 30 deg. Results from hypersonic aerodynamic screening studies that were conducted as the configuration evolved to the present shape at, presented. Heavy gas simulation tests have indicated that the primary real gas effects on X-38 aerodynamics at trim conditions are expected to favorably influence flap effectiveness. Comparisons of the experimental heating and force and moment data to prediction and the current aerodynamic data book are highlighted. The effects of discrete roughness elements on boundary layer transition were investigated at Mach 6 and the development of a transition correlation for the X-38 vehicle is described. Extrapolation of ground based heating measurements to flight radiation equilibrium wall temperatures at Mach 6 and 10 were

Battery Systems for X-38 Crew Return Vehicle (CRV) and Deorbit Propulsion Stage (DPS)

NASA Technical Reports Server (NTRS)

Darcy, Eric

1998-01-01

A 28V 32 Ah cell Li/MnO2 and a 28V NiMH battery systems for the Deorbit Propulsion Stage (DPS) and the X-38 Crew Return Vehicle (CRV) are developed in Friwo-Silforkraft, Germany with the following objectives and approach: Provide safe battery designs for lowest volume and cost, and within schedule; Take advantage of less complex requests for V201 vs OPS CRV to simplify design and reduce cost; Use only existing commercial cell designs as building blocks for larger battery; Derive battery designs from the ASTRO-SPAS design which is the largest lithium battery design with Shuttle flight experience; Place maximum amount of battery energy on DPS; DPS battery is non rechargeable; and CRV batteries are rechargeable. This paper contains the following sections: a brief introduction on CRV requirements, CRV advantages over Soyuz, and X-38 programs; Battery objectives and approach; Battery requirements and groundrules (performance, on-orbit operation, etc); Design trades, solutions, redundancy plan, and margins; Envelope, size, and mass; Interfaces (structural, electrical & thermal); and Deviation from OPS CRV.

X-38 Ship #2 Landing on Lakebed, Completing the Program's 4th Flight

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38, a research vehicle built to help develop technology for an emergency Crew Return Vehicle (CRV), makes a gentle lakebed landing at the end of a July 1999 test flight at the Dryden Flight Research Center, Edwards, California. It was the fourth free flight of the test vehicles in the X-38 program, and the second free flight test of Vehicle 132 or Ship 2. The goal of this flight was to release the vehicle from a higher altitude -- 31,500 feet -- and to fly the vehicle longer -- 31 seconds -- than any previous X-38 vehicle had yet flown. The project team also conducted aerodynamic verification maneuvers and checked improvements made to the drogue parachute. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational

X-38: Parachute Canister Fired from Plywood Mockup during Flight Termination System Test

NASA Technical Reports Server (NTRS)

1996-01-01

The canister containing a seven-foot-diameter X-38 Flight Termination System (FTS) parachute is launched safely away from a plywood mockup of the X-38 by a pyrotechnic firing system on December 19, 1996, at NASA Dryden Flight Research Center, Edwards, California. The test was economically accomplished by mounting the mockup of the X-38's aft end, minus vertical stabilizers, on a truck prior to installation in the X-38. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally

X-38: Plywood Mockup of Aft End Used for Flight Termination System Parachute Test

NASA Technical Reports Server (NTRS)

1996-01-01

This photo shows a plywood mockup of the X-38's aft end, minus vertical stabilizers, mounted on a truck for an economical test of the X-38's Flight Termination System (FTS) on December 19, 1996, at NASA Dryden Flight Research Center, Edwards, California. The FTS seven-foot diameter parachute was launched safely away from the mockup by a pyrotechnic firing system. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be

X-38 Vehicle 131R Free Flights 1 and 2

NASA Technical Reports Server (NTRS)

Munday, Steve

2000-01-01

The X-38 program is using a modern flight control system (FCS) architecture originally developed by Honeywell called MACH. During last year's SAE G&C subcommittee meeting, we outlined the design, implementation and testing of MACH in X-38 Vehicles 132, 131R & 201. During this year's SAE meeting, I'll focus upon the first two free flights of V131R, describing what caused the roll-over in FF1 and how we fixed it for FF2. I only have 30 minutes, so it will be a quick summary including VHS video. X-38 is a NASA JSC/DFRC experimental flight test program developing a series of prototypes for an International Space Station (ISS) Crew Return Vehicle (CRV), often described as an ISS "lifeboat." X-38 Vehicle 132 Free Flight 3 was the first flight test of a modern FCS architecture called Multi-Application ControlH (MACH), developed by the Honeywell Technology Center in Minneapolis and Honeywell's Houston Engineering Center. MACH wraps classical Proportional+integral (P+I) outer attitude loops around modern dynamic inversion attitude rate loops. The presentation at last year's SAE Aerospace Meeting No. 85 focused upon the design and testing of the FCS algorithm and Vehicle 132 Free Flight 3. This presentation will summarize flight control and aerodynamics lessons learned during Free Flights 1 and 2 of Vehicle 131R, a subsonic test vehicle laying the groundwork for the orbital/entry test of Vehicle 201 in 2003.

X-38 in Flight during Second Free Flight

NASA Image and Video Library

1999-02-06

NASA's X-38, a research vehicle developed as part of an effort to build an emergency Crew Return Vehicle (CRV) for the International Space Station, descends toward a desert lakebed under its steerable parafoil on its second free flight. The X-38 was launched from NASA Dryden's B-52 Mothership on Saturday, February 6, 1999, from an altitude of approximately 23,000 feet.

X-38 in Flight during Second Free Flight

NASA Image and Video Library

1999-02-06

NASA's X-38, a research vehicle developed as part of an effort to build an emergency Crew Return Vehicle (CRV) for the International Space Station, descends toward the desert floor under its steerable parafoil on its second free flight. The X-38 was launched from NASA Dryden's B-52 Mothership on Saturday, February 6, 1999, from an altitude of approximately 23,000 feet.

The First X-38 Technology Demonstrator (V-131) Shown with Modifications to the Rear to Conform More

NASA Technical Reports Server (NTRS)

1999-01-01

The first X-38 technology demonstrator (V-131) is seen here undergoing modifications to the rear to conform more to the shape of the future Crew Return Vehicle (CRV) The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the size of a projected emergency

X-38: Close-up of Pyrotechnic Firing during Test of Flight Termination System Parachute Deployment

NASA Technical Reports Server (NTRS)

1996-01-01

In these close-ups, the canister containing the seven-foot-diameter X-38 Flight Termination System (FTS) parachute can be seen launching safely away from an aft-end mockup of the X-38 by a pyrotechnic firing system in December 19, 1996, at NASA Dryden Flight Research Center, Edwards, California. The test was economically accomplished by mounting the mockup of the X-38's aft-end, minus vertical stabilizers, on a truck prior to installation in the X-38. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research

Low Velocity Airdrop Tests of an X-38 Backup Parachute Design

NASA Technical Reports Server (NTRS)

Stein, Jenny M.; Machin, Ricardo A.; Wolf, Dean F.; Hillebrandt, F. David

2007-01-01

The NASA Johnson Space Center's X-38 program designed a new backup parachute system to recover the 25,000 lb X-38 prototype for the Crew Return Vehicle spacecraft. Due to weight and cost constraints, the main backup parachute design incorporated rapid and low cost fabrication techniques using off-the-shelf materials. Near the vent, the canopy was constructed of continuous ribbons, to provide more damage tolerance. The remainder of the canopy was a constructed with a continuous ringslot design. After cancellation of the X-38 program, the parachute design was resized, built, and drop tested for Natick Soldiers Center's Low Velocity Air Drop (LVAD) program to deliver cargo loads up to 22,000 lbs from altitudes as low as 500 feet above the ground. Drop tests results showed that the 500-foot LVAD parachute deployment conditions cause severe skirt inversion and inflation problems for large parachutes. The bag strip occurred at a high angle of attack, causing skirt inversion before the parachute could inflate. The addition of a short reefing line prevented the skirt inversion. Using a lower porosity in the vent area, than is normally used in large parachutes, improved inflation. The drop testing demonstrated that the parachute design could be refined to meet the requirements for the 500-foot LVAD mission.

Evaluation of X-38 Crew Return Vehicle Input Control Devices in a Microgravity Environment

NASA Technical Reports Server (NTRS)

Welge, Kirsten; Moore, Alicia; Pope, Ruth Ann; Shivers, Suzette; Fox, Jeffrey

2000-01-01

This report was created by students from Longview High School, Longview, Texas. Longview High School was selected from a group of Texas high schools to participate in the 1999 Texas Fly High Program. This program gives Texas high school students a chance to work with NASA engineers to design and fly a real-world experiment aboard the KC-135 during zero-g parabolas. Jeffrey Fox's role was to provide a concept for the experiment and to mentor the students in its design and testing. The students were responsible for executing all phases of the project. The X-38 Project Office at the Lyndon B. Johnson Space Center Johnson Space is designing a crew return vehicle (CRV) to be docked at the International Space Station for crew rescue in an emergency. Vehicle controls will be almost completely automated, but a few functions will be manually controlled. Four crew input control devices were selected for evaluation by Longview High School students as part of the 1999 Texas Fly High program. These were (1) Logitech Trackman Marble (optical trackball), (2) Smart Cat Touchpad. (3) Microsoft SideWinder 3D-Pro Joystick, and (4) Microsoft SideWinder Gamepad. In two flight tests in the KC-135 aircraft and a series of ground tests, the devices were evaluated for ability to maneuver an on-screen cursor, level of accuracy, ease of handling blind operations, and level of user comfort in microgravity. The tests results led to recommendation of further tests with the Joystick and the Trackman by astronauts and actual space station residents.

The X-38 vehicle #131R arrives at NASA Dryden Flight Research Center

NASA Image and Video Library

2000-07-11

The X-38 Vehicle 131R, intended to prove the utility of a "lifeboat" crew return vehicle to bring crews home from the International Space Station in the event of an emergency, was unloaded from NASA's Super Guppy transport aircraft on July 11, 2000. The newest X-38 version arrived at Dryden for drop tests from NASA's venerable B-52 mother ship. The tests will evaluate a 7,500 square-foot parafoil intended to permit the crew return vehicle to return from space and land in the length of a football field.

The X-38 vehicle #131R arrives at NASA Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

2000-01-01

The X-38 Vehicle 131R, intended to prove the utility of a 'lifeboat' crew return vehicle to bring crews home from the International Space Station in the event of an emergency, was unloaded from NASA's Super Guppy transport aircraft on July 11, 2000. The newest X-38 version arrived at Dryden for drop tests from NASA's venerable B-52 mother ship. The tests will evaluate a 7,500 square-foot parafoil intended to permit the crew return vehicle to return from space and land in the length of a football field.

X-38 Ship #2 in Free Flight

NASA Image and Video Library

1999-07-09

The X-38, a research vehicle built to help develop technology for an emergency Crew Return Vehicle (CRV), descends under its steerable parachute during a July 1999 test flight at the Dryden Flight Research Center, Edwards, California. It was the fourth free flight of the test vehicles in the X-38 program, and the second free flight test of Vehicle 132 or Ship 2. The goal of this flight was to release the vehicle from a higher altitude -- 31,500 feet -- and to fly the vehicle longer -- 31 seconds -- than any previous X-38 vehicle had yet flown. The project team also conducted aerodynamic verification maneuvers and checked improvements made to the drogue parachute.

The X-38 Vehicle 131R drops away from its launch pylon on the wing of NASA's NB-52B mothership as it begins its eighth free flight on Thursday, December 13, 2001

NASA Image and Video Library

2001-12-13

The X-38 prototype of the Crew Return Vehicle for the International Space Station drops away from its launch pylon on the wing of NASA's NB-52B mothership as it begins its eighth free flight on Thursday, Dec. 13, 2001. The 13-minute test flight of X-38 vehicle 131R was the longest and fastest and was launched from the highest altitude to date in the X-38's atmospheric flight test program. A portion of the descent was flown under remote control by a NASA astronaut from a ground vehicle configured like the CRV's interior before the X-38 made an autonomous landing on Rogers Dry Lake.

X-38 Mounted on Pylon of B-52 Mothership

NASA Image and Video Library

1997-07-06

A close-up view of the X-38 research vehicle mounted under the wing of the B-52 mothership prior to a 1997 test flight. The X-38, which was designed to help develop technology for an emergency crew return vehicle (CRV) for the International Space Station, is one of many research vehicles the B-52 has carried aloft over the past 40 years.

X-38 - First Free Flight, March 12, 1998

NASA Image and Video Library

1998-03-12

The X-38 Crew Return Vehicle descends under its steerable parafoil over the California desert in its first free flight at the Dryden Flight Research Center, Edwards, California. The flight took place March 12, 1998.

The X-38 lifting body research vehicle, seen here wrapped in a protective material, lowered onto a t

NASA Technical Reports Server (NTRS)

2000-01-01

The X-38 lifting body research vehicle, seen here wrapped in a protective material, is lowered onto a truck for shipping from the Dryden Flight Research Center in May 2000. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the size of a projected

Commerical Crew Program - SpaceX

NASA Image and Video Library

2016-04-25

The interior structure of the SpaceX Crew Dragon spacecraft at the company's facility in Hawthorne, California. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

Commerical Crew Program - SpaceX

NASA Image and Video Library

2016-04-25

A technician works on the interior structure of the SpaceX Crew Dragon spacecraft at the company's facility in Hawthorne, California. SpaceX is developing its Crew Dragon in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

The Three Main Rings of the X-38 Vehicle 201 Shown under Construction at NASA Johnson Space Flight C

NASA Technical Reports Server (NTRS)

1999-01-01

This photo shows the X-38 Vehicle 201, intended for spaceflight testing, under construction at NASA Johnson Space Flight Center, Houston, Texas. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the size of a projected emergency crew return vehicle

International Space Station Crew Return Vehicle: X-38. Educational Brief.

ERIC Educational Resources Information Center

National Aeronautics and Space Administration, Washington, DC.

The International Space Station (ISS) will provide the world with an orbiting laboratory that will have long-duration micro-gravity experimentation capability. The crew size for this facility will depend upon the crew return capability. The first crews will consist of three astronauts from Russia and the United States. The crew is limited to three…

The X-38 vehicle #131R arrives at NASA Dryden Flight Research Center

NASA Image and Video Library

2000-07-11

The X-38 Vehicle 131R, intended to prove the utility of a "lifeboat" crew return vehicle to bring crews home from the International Space Station in the event of an emergency, was unloaded from NASA's Super Guppy transport aircraft on July 11, 2000. The newest X-38 version arrived at Dryden for drop tests from NASA's venerable B-52 mother ship. The tests will evaluate a 7,500 square-foot parafoil intended to permit the CRV to return from space and land in the length of a football field.

The X-38 vehicle #131R arrives at NASA Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

2000-01-01

The X-38 Vehicle 131R, intended to prove the utility of a 'lifeboat' crew return vehicle to bring crews home from the International Space Station in the event of an emergency, was unloaded from NASA's Super Guppy transport aircraft on July 11, 2000. The newest X-38 version arrived at Dryden for drop tests from NASA's venerable B-52 mother ship. The tests will evaluate a 7,500 square-foot parafoil intended to permit the CRV to return from space and land in the length of a football field.

Commerical Crew Program - SpaceX

NASA Image and Video Library

2016-06-28

The inter-stage of a SpaceX Falcon 9 rocket inside the company's manufacturing facility. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA's Commercial Crew Program to carry astronauts to and from the International Space Station.

Commerical Crew Program - SpaceX

NASA Image and Video Library

2014-05-21

A SpaceX SuperDraco engine is hot-fired at the company's test facility in McGregor, Texas. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

Commerical Crew Program - SpaceX

NASA Image and Video Library

2018-01-02

A SpaceX Merlin engine is on a test stand at the company's facility in McGregor, Texas. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

The X-38 Spacecraft Fault-Tolerant Avionics System

NASA Technical Reports Server (NTRS)

Kouba,Coy; Buscher, Deborah; Busa, Joseph

2003-01-01

In 1995 NASA began an experimental program to develop a reusable crew return vehicle (CRV) for the International Space Station. The purpose of the CRV was threefold: (i) to bring home an injured or ill crewmember; (ii) to bring home the entire crew if the Shuttle fleet was grounded; and (iii) to evacuate the crew in the case of an imminent Station threat (i.e., fire, decompression, etc). Built at the Johnson Space Center, were two approach and landing prototypes and one spacecraft demonstrator (called V201). A series of increasingly complex ground subsystem tests were completed, and eight successful high-altitude drop tests were achieved to prove the design concept. In this program, an unprecedented amount of commercial-off-the-shelf technology was utilized in this first crewed spacecraft NASA has built since the Shuttle program. Unfortunately, in 2002 the program was canceled due to changing Agency priorities. The vehicle was 80% complete and the program was shut down in such a manner as to preserve design, development, test and engineering data. This paper describes the X-38 V201 fault-tolerant avionics system. Based on Draper Laboratory's Byzantine-resilient fault-tolerant parallel processing system and their "network element" hardware, each flight computer exchanges information on a strict timescale to process input data, compare results, and issue voted vehicle output commands. Major accomplishments achieved in this development include: (i) a space qualified two-fault tolerant design using mostly COTS (hardware and operating system); (ii) a single event upset tolerant network element board, (iii) on-the-fly recovery of a failed processor; (iv) use of synched cache; (v) realignment of memory to bring back a failed channel; (vi) flight code automatically generated from the master measurement list; and (vii) built in-house by a team of civil servants and support contractors. This paper will present an overview of the avionics system and the hardware

The US - European Cooperation in the X-38 and CRV Programs

NASA Astrophysics Data System (ADS)

Sygulla, D.; Sabath, D.; Püttmann, N.; Schmid, V.; Caporicci, M.; Anderson, B.

2002-01-01

The European participation in the US X-38 program was initiated in 1997 and is realized by contributions from two European programs, by ESA's "Applied Reentry Technology Program", (ARTP) and the German/DLR "Technologies for Future Space Transportation Systems" (TETRA) program. The space agencies of USA, Europe and Germany have established two Memoranda of Understanding - NASA-ESA and NASA-DLR - for the European participation in the X-38 Program to deliver flight hard- and software in exchange to a re-entry flight opportunity with Vehicle 201 (V201). By October 2002 all European contributions to V201 of the X-38 program will be delivered to NASA JSC. Vehicle 201 represents the orbital test vehicle of the experimental vehicle family, developed and built from 1996 onwards by NASA at Johnson Space Center, JSC in Houston. The X-38 Program was initiated by NASA to prepare and develop the Crew Return Vehicle (CRV) with Vehicle 201 as prototype. NASA conducts the overall X-38 vehicle system engineering and integration, intended to provide the launch of the vehicle 201 with the Space Shuttle and will deliver flight data for post-flight analysis and assessment to DLR and ESA. The German national project TETRA (Technologies for future Space Transportation Systems) and the European ARTP (Applied Re-entry Technology Programme) are providing engineering support for design, analysis, system engineering and layout as well as delivering essential flight hard- and software: CMC Body flaps and CMC nose assembly from TETRA; rudders, CMC leading edges, landing gears and major elements of the V201 primary structure from ARTP. Since both programmes contribute in cooperation the major part of the aerodynamic database is generated, the flexible external insulation is developed and manufactured, and advanced sensors and data acquisition systems are built. The parts for V201 have been developed, fulfill the requirements, are qualified for flight and they are in the process of being

X-38 Application of Dynamic Inversion Flight Control

NASA Technical Reports Server (NTRS)

Wacker, Roger; Munday, Steve; Merkle, Scott

2001-01-01

This paper summarizes the application of a nonlinear dynamic inversion (DI) flight control system (FCS) to an autonomous flight test vehicle in NASA's X-38 Project, a predecessor to the International Space Station (ISS) Crew Return Vehicle (CRV). Honeywell's Multi-Application Control-H (MACH) is a parameterized FCS design architecture including both model-based DI rate-compensation and classical P+I command-tracking. MACH was adopted by X-38 in order to shorten the design cycle time for different vehicle shapes and flight envelopes and evolving aerodynamic databases. Specific design issues and analysis results are presented for the application of MACH to the 3rd free flight (FF3) of X-38 Vehicle 132 (V132). This B-52 drop test, occurring on March 30, 2000, represents the first flight test of MACH and one of the first few known applications of DI in the primary FCS of an autonomous flight test vehicle.

T-38 Primary Flight Display Prototyping and HIVE Support Abstract & Summary

NASA Technical Reports Server (NTRS)

Boniface, Andrew

2015-01-01

This fall I worked in EV3 within NASA's Johnson Space Center in The HIVE (Human Integrated Vehicles & Environments). The HIVE is responsible for human in the loop testing, getting new technologies in front of astronauts, operators, and users early in the development cycle to make the interfaces more human friendly. Some projects the HIVE is working on includes user interfaces for future spacecraft, wearables to alert astronauts about important information, and test beds to simulate mock missions. During my internship I created a prototype for T-38 aircraft displays using LabVIEW, learned how to use microcontrollers, and helped out with other small tasks in the HIVE. The purpose of developing a prototype for T-38 Displays in LabVIEW is to analyze functions of the display such as navigation in a cost and time effective manner. The LabVIEW prototypes allow Ellington Field AOD to easily make adjustments to the display before hardcoding the final product. LabVIEW was used to create a user interface for simulation almost identical to the real aircraft display. Goals to begin the T-38 PFD (Primary Flight Display) prototype included creating a T-38 PFD hardware display in a software environment, designing navigation for the menu's, incorporating vertical and horizontal navigation bars, and to add a heading bug for compass controls connected to the HSI (Horizontal Situation Indicator). To get started with the project, measurements of the entire display were taken. This enabled an accurate model of the hardware display to be created. Navigation of menu's required some exploration of different buttons on the display. The T-38 simulator and aircraft were used for examining the display. After one piece of the prototype was finished, another trip of to the simulator took place. This was done until all goals for the prototype were complete. Some possible integration ideas for displays in the near future are autopilot selection, touch screen displays, and crew member preferences

Adaptive Guidance and Control Algorithms applied to the X-38 Reentry Mission

NASA Astrophysics Data System (ADS)

Graesslin, M.; Wallner, E.; Burkhardt, J.; Schoettle, U.; Well, K. H.

International Space Station's Crew Return/Rescue Vehicle (CRV) is planned to autonomously return the complete crew of 7 astronauts back to earth in case of an emergency. As prototype of such a vehicle, the X-38, is being developed and built by NASA with European participation. The X-38 is a lifting body with a hyper- sonic lift to drag ratio of about 0.9. In comparison to the Space Shuttle Orbiter, the X-38 has less aerodynamic manoeuvring capability and less actuators. Within the German technology programme TETRA (TEchnologies for future space TRAnsportation systems) contributing to the X-38 program, guidance and control algorithms have been developed and applied to the X-38 reentry mission. The adaptive guidance concept conceived combines an on-board closed-loop predictive guidance algorithm with flight load control that temporarily overrides the attitude commands of the predictive component if the corre- sponding load constraints are violated. The predictive guidance scheme combines an optimization step and a sequence of constraint restoration cycles. In order to satisfy on-board computation limitations the complete scheme is performed only during the exo-atmospheric flight coast phase. During the controlled atmospheric flight segment the task is reduced to a repeatedly solved targeting problem based on the initial optimal solution, thus omitting in-flight constraints. To keep the flight loads - especially the heat flux, which is in fact a major concern of the X-38 reentry flight - below their maximum admissible values, a flight path controller based on quadratic minimization techniques may override the predictive guidance command for a flight along the con- straint boundary. The attitude control algorithms developed are based on dynamic inversion. This methodology enables the designer to straightforwardly devise a controller structure from the system dynamics. The main ad- vantage of this approach with regard to reentry control design lies in the fact that

A prototype Crew Medical Restraint System (CMRS) for Space Station Freedom

NASA Technical Reports Server (NTRS)

Johnston, S. L.; Eichstadt, F. T.; Billica, R. D.

1992-01-01

The Crew Medical Restrain System (CMRS) is a prototype system designed and developed for use as a universally deployable medical restraint/workstation on Space Station Freedom (SSF), the Shuttle Transportation System (STS), and the Assured Crew Rescue Vehicle (ACRV) for support of an ill or injured crewmember requiring stabilization and transportation to Earth. The CMRS will support all medical capabilities of the Health Maintenance Facility (HMF) by providing a restraint/interface system for all equipment (advance life support packs, defibrillator, ventilator, portable oxygen supply, IV pump, transport monitor, transport aspirator, and intervenous fluids delivery system) and personnel (patient and crew medical officers). It must be functional within the STS, ACRV, and all SSF habitable volumes. The CMRS will allow for medical capabilities within CPR, ACLS and ATLS standards of care. This must all be accomplished for a worst case transport time scenario of 24 hours from SSF to a definitive medical care facility on Earth. A presentation of the above design prototype with its subsequent one year SSF/HMF and STS/ACRV high fidelity mock-up ground based simulation testing will be given. Also, parabolic flight and underwater Weightless Test Facility evaluations will be demonstrated for various medical contingencies. The final design configuration to date will be discussed with future space program impact considerations.

Overview of X-38 Hypersonic Wind Tunnel Data and Comparison with Numerical Results

NASA Technical Reports Server (NTRS)

Campbell, Charles H.; Caram, Jose; Berry, Scott; DiFulvio, Michael; Horvath, Tom

1997-01-01

A NASA team of engineers has been organized to design a crew return vehicle for returning International Space Station crew members from orbit. The hypersonic characteristics of this X-23/X-2&4 derived crew return vehicle (designated X-38) are being evaluated in various wind tunnels in support of this effort. Aerodynamic data has been acquired in three NASA hypersonic facilities at Mach 20, and Mach 6. Computational Fluid Dynamics tools have been applied at the appropriate wind tunnel conditions to make comparisons with portions of this data. Experimental data from the Mach 6 Air and CF4 facilities illustrate a net positive pitching moment increment due to density ratio, as well as increased elevon effectiveness. Chemical nonequilibrium computational fluid dynamics solutions at flight conditions reinforce this conclusion.

Ares I-X Ground Diagnostic Prototype

NASA Technical Reports Server (NTRS)

Schwabacher, Mark; Martin, Rodney; Waterman, Robert; Oostdyk, Rebecca; Ossenfort, John; Matthews, Bryan

2010-01-01

Automating prelaunch diagnostics for launch vehicles offers three potential benefits. First, it potentially improves safety by detecting faults that might otherwise have been missed so that they can be corrected before launch. Second, it potentially reduces launch delays by more quickly diagnosing the cause of anomalies that occur during prelaunch processing. Reducing launch delays will be critical to the success of NASA's planned future missions that require in-orbit rendezvous. Third, it potentially reduces costs by reducing both launch delays and the number of people needed to monitor the prelaunch process. NASA is currently developing the Ares I launch vehicle to bring the Orion capsule and its crew of four astronauts to low-earth orbit on their way to the moon. Ares I-X will be the first unmanned test flight of Ares I. It is scheduled to launch on October 27, 2009. The Ares I-X Ground Diagnostic Prototype is a prototype ground diagnostic system that will provide anomaly detection, fault detection, fault isolation, and diagnostics for the Ares I-X first-stage thrust vector control (TVC) and for the associated ground hydraulics while it is in the Vehicle Assembly Building (VAB) at John F. Kennedy Space Center (KSC) and on the launch pad. It will serve as a prototype for a future operational ground diagnostic system for Ares I. The prototype combines three existing diagnostic tools. The first tool, TEAMS (Testability Engineering and Maintenance System), is a model-based tool that is commercially produced by Qualtech Systems, Inc. It uses a qualitative model of failure propagation to perform fault isolation and diagnostics. We adapted an existing TEAMS model of the TVC to use for diagnostics and developed a TEAMS model of the ground hydraulics. The second tool, Spacecraft Health Inference Engine (SHINE), is a rule-based expert system developed at the NASA Jet Propulsion Laboratory. We developed SHINE rules for fault detection and mode identification. The prototype

SpaceX Crew Dragon Ship

NASA Image and Video Library

2018-05-20

The SpaceX Crew Dragon spacecraft is in the anechoic chamber for electromagnetic interference testing on May 20, 2018, at NASA's Kennedy Space Center in Florida. The Crew Dragon will be shipped to the agency's Plum Brook Station test facility at Glenn Research City in Cleveland, Ohio, for testing in the Reverberant Acoustic Test Facility, the world's most powerful acoustic test chamber. Crew Dragon is being prepared for its first uncrewed test flight, targeted for August 2018.

German Contribution to the X-38 CRV Demonstrator in the Field of Guidance, Navigation and Control (GNC)

NASA Astrophysics Data System (ADS)

Soppa, Uwe; Görlach, Thomas; Roenneke, Axel Justus

2002-01-01

As a solution to meet a safety requirement to the future full scale space station infrastructure, the Crew Return/Rescue Vehicle (CRV) was supposed to supply the return capability for the complete ISS crew of 7 astronauts back to earth in case of an emergency. A prototype of such a vehicle named X-38 has been developed and built by NASA with European partnership (ESA, DLR). An series of aerial demonstrators (V13x) for tests of the subsonic TAEM phase and the parafoil descent and landing system has been flown by NASA from 1998 to 2001. A full scale unmanned space flight demonstrator (V201) has been built at JSC Houston and although the project has been stopped for budgetary reasons in 2002, it will hopefully still be flown in near future. The X-38 is a lifting body with hypersonic lift to drag ratio about 0.9. In comparison to the Space Shuttle Orbiter, this design provides less aerodynamic maneuvrability and a different actuator layout (divided body flap and winglet rudders instead as combined aileron and elevon in addition to thrust- ers for the early re-entry phase). Hence, the guidance and control concepts used onboard the shuttle orbiter had to be adapted and further developed for the application on the new vehicle. In the frame of the European share of the X-38 project and also of the German TETRA (TEchnol- ogy for future space TRAnsportation) project different GNC related contributions have been made: First, the primary flight control software for the autonomous guidance and control of the X-38 para- foil descent and landing phase has been developed, integrated and successfully flown on multiple vehicles and missions during the aerial drop test campaign conducted by NASA. Second, a real time X-38 vehicle simulator was provided to NASA which has also been used for the validation of a European re-entry guidance and control software (see below). According to the NASA verification and validation plan this simulator is supposed to be used as an independent vali

X-38 flies free from NASA's B-52 mothership, July 10, 2001

NASA Technical Reports Server (NTRS)

2001-01-01

The second free-flight test of an evolving series of X-38 prototypes took place July 10, 2001 when the X-38 was released from NASA's B-52 mothership over the Edwards Air Force Base range in California's Mojave Desert. Shortly after the photo was taken, a sequenced deployment of a drogue parachute followed by a large parafoil fabric wing slowed the X-38 to enable it to land safely on Rogers Dry Lake at Edwards. NASA engineers from the Dryden Flight Research Center at Edwards, and the Johnson Space Center, Houston, Texas, are developing a 'lifeboat' for the International Space Station based on X-38 research.

X-38 flies free from NASA's B-52 mothership, July 10, 2001

NASA Image and Video Library

2001-07-10

The second free-flight test of an evolving series of X-38 prototypes took place July 10, 2001 when the X-38 was released from NASA's B-52 mothership over the Edwards Air Force Base range in California's Mojave Desert. Shortly after the photo was taken, a sequenced deployment of a drogue parachute followed by a large parafoil fabric wing slowed the X-38 to enable it to land safely on Rogers Dry Lake at Edwards. NASA engineers from the Dryden Flight Research Center at Edwards, and the Johnson Space Center, Houston, Texas, are developing a "lifeboat" for the International Space Station based on X-38 research.

Overview of X-38 Hypersonic Aerothermodynamic Wind Tunnel Data and Comparison with Numerical Results

NASA Technical Reports Server (NTRS)

Campbell, C.; Caram, J.; Berry, S.; Horvath, T.; Merski, N.; Loomis, M.; Venkatapathy, E.

2004-01-01

A NASA team of engineers has been organized to design a crew return vehicle for returning International Space Station crew members from orbit. The hypersonic aerothermodynamic characteristics of the X-23/X-24A derived X-38 crew return vehicle are being evaluated in various wind tunnels in support of this effort. Aerothermodynamic data from two NASA hypersonic tunnels at Mach 6 and Mach 10 has been obtained with cast ceramic models and a thermographic phosphorus digital imaging system. General windward surface heating features are described based on experimental surface heating images and surface oil flow patterns for the nominal hypersonic aerodynamic orientation. Body flap reattachment heating levels are examined. Computational Fluid Dynamics tools have been applied at the appropriate wind tunnel conditions to make comparisons with this data.

Mass Properties Measurement in the X-38 Project

NASA Technical Reports Server (NTRS)

Peterson, Wayne L.

2004-01-01

This paper details the techniques used in measuring the mass properties for the X-38 family of test vehicles. The X-38 Project was a NASA internal venture in which a series of test vehicles were built in order to develop a Crew Return Vehicle (CRV) for the International Space Station. Three atmospheric test vehicles and one spaceflight vehicle were built to develop the technologies required for a CRV. The three atmospheric test vehicles have undergone flight-testing by a combined team from the NASA Johnson Space Center and the NASA Dryden Flight Research Center. The flight-testing was performed at Edward's Air Force Base in California. The X-38 test vehicles are based on the X-24A, which flew in the '60s and '70s. Scaled Composites, Inc. of Mojave, California, built the airframes and the vehicles were outfitted at the NASA Johnson Space Center in Houston, Texas. Mass properties measurements on the atmospheric test vehicles included weight and balance by the three-point suspension method, four-point suspension method, three load cells on jackstands, and on three in-ground platform scales. Inertia measurements were performed as well in which Ixx, Iyy, Izz, and Ixz were obtained. This paper describes each technique and the relative merits of each. The proposed measurement methods for an X-38 spaceflight test vehicle will also be discussed. This vehicle had different measurement challenges, but integrated vehicle measurements were never conducted. The spaceflight test vehicle was also developed by NASA and was scheduled to fly on the Space Shuttle before the project was cancelled.

Testing of the International Space Station and X-38 Crew Return Vehicle GPS Receiver

NASA Technical Reports Server (NTRS)

Simpson, James; Campbell, Chip; Carpenter, Russell; Davis, Ed; Kizhner, Semion; Lightsey, E. Glenn; Davis, George; Jackson, Larry

1999-01-01

This paper discusses the process and results of the performance testing of the GPS receiver planned for use on the International Space Station (ISS) and the X-38 Crew Return Vehicle (CRV). The receiver is a Force-19 unit manufactured by Trimble Navigation and modified in software by the NASA Goddard Space Flight Center (GSFC) to perform navigation and attitude determination in space. The receiver is the primary source of navigation and attitude information for ISS and CRV. Engineers at GSFC have developed and tested the new receiver with a Global Simulation Systems Ltd (GSS) GPS Signal Generator (GPSSG). This paper documents the unique aspects of ground testing a GPS receiver that is designed for use in space. A discussion of the design of tests using the GPSSG, documentation, data capture, data analysis, and lessons learned will precede an overview of the performance of the new receiver. A description of the challenges that were overcome during this testing exercise will be presented. Results from testing show that the receiver will be within or near the specifications for ISS attitude and navigation performance. The process for verifying other requirements such as Time to First Fix, Time to First Attitude, selection/deselection of a specific GPS satellite vehicles (SV), minimum signal strength while still obtaining attitude and navigation, navigation and attitude output coverage, GPS week rollover, and Y2K requirements are also given in this paper.

Testing of the International Space Station and X-38 Crew Return Vehicle GPS Receiver

NASA Technical Reports Server (NTRS)

Simpson, James; Campbell, Chip; Carpenter, Russell; Davis, Ed; Kizhner, Semion; Lightsey, E. Glenn; Davis, George; Jackson, Larry

1999-01-01

This paper discusses the process and results of the performance testing of the GPS receiver planned for use on the International Space Station (ISS) and the X-38 Crew Return Vehicle (CRV). The receiver is a Force-19 unit manufactured by Trimble Navigation and Modified in software by the NASA Goddard Space Flight Center (GSFC) to perform navigation and attitude determination in space. The receiver is the primary source of navigation and attitude information for ISS and CRV. Engineers at GSFC have developed and tested the new receiver with a Global Simulation Systems Ltd (GSS) GPS Signal Generator (GPSSG). This paper documents the unique aspects of ground testing a GPS receiver that is designed for use in space. A discussion of the design and tests using the GPSSG, documentation, data capture, data analysis, and lessons learned will precede an overview of the performance of the new receiver. A description of the challenges of that were overcome during this testing exercise will be presented. Results from testing show that the receiver will be within or near the specifications for ISS attitude and navigation performance. The process for verifying other requirements such as Time to First Fix, Time to First Attitude, selection/deselection of a specific GPS satellite vehicles (SV), minimum signal strength while still obtaining attitude and navigation, navigation and attitude output coverage, GPS week rollover, and Y2K requirements are also given in this paper.

Testing of the International Space Station and X-38 Crew Return Vehicle GPS Receiver

NASA Technical Reports Server (NTRS)

Simpson, James; Lightsey, Glenn; Campbell, Chip; Carpenter, Russell; Davis, George; Jackson, Larry; Davis, Ed; Kizhner, Semion

1999-01-01

This paper discusses the process and results of the performance testing of the GPS receiver planned for use on the International Space Station (ISS) and the X- 38CrewReturnVehicle(CRV). The receiver is a Force-19 unit manufactured by Trimble Navigation and modified in software by NASA:s Goddard Space Flight Center (GSFC) to perform navigation and attitude determination in space. The receiver is the primary source of navigation and attitude information for ISS and CRV. Engineers at GSFC have developed and tested the new receiver with a Global Simulation Systems Ltd (GSS) GPS Signal Generator (GPSSG). This paper documents the unique aspects of ground testing a GPS receiver that is designed for use in space. A discussion of the design of tests using the GPSSG, documentation, data capture, data analysis, and lessons learned will precede an overview of the performance of the new receiver. A description of the challenges that were overcome during this testing exercise will be presented. Results from testing show that the receiver will be within or near the specifications for ISS attitude and navigation performance. The process for verifying other requirements such as Time to First Fix, Time to First Attitude, selection/deselection of a specific GPS satellite vehicles (SV), minimum signal strength while still obtaining attitude and navigation, navigation and attitude output coverage, GPS week rollover, and Y2K requirements are also given in this paper.

X-38 Landing Gear Skid Test Report

NASA Technical Reports Server (NTRS)

Gafka, George K.; Daugherty, Robert H.

2000-01-01

NASA incorporates skid-equipped landing gear on its series of X-38 flight test vehicles. The X-38 test program is the proving ground for the Crew Return Vehicle (CRV) a gliding parafoil-equipped vehicle designed to land at relatively low speeds. The skid-equipped landing gear is designed to attenuate the vertical landing energy of the vehicle at touchdown using crushable materials within the struts themselves. The vehicle then slides out as the vehicle horizontal energy is dissipated through the skids. A series of tests was conducted at Edwards Airforce Base (EAFB) in an attempt to quantify the drag force produced while "dragging" various X-38 landing gear skids across lakebed regions of varying surface properties. These data were then used to calculate coefficients of friction for each condition. Coefficient of friction information is critical for landing analyses as well as for landing gear load and interface load analysis. The skid specimens included full- and sub-scale V201 (space test vehicle) nose and main gear designs, a V131/V 132 (atmospheric flight test vehicles) main gear skid (actual flight hardware), and a newly modified, full-scale V201 nose -ear skid with substantially increased edge curvature as compared to its original design. Results of the testing are discussed along with comments on the relative importance of various parameters that influence skid stability and other dynamic behavior.

X-38 NASA/DLR/ESA-Dassault Aviation Integrated Aerodynamic and Aerothermodynamic Activities

NASA Technical Reports Server (NTRS)

Labbe, Steve G.; Perez, Leo F.; Fitzgerald, Steve; Longo, Jose; Rapuc, Marc; Molina, Rafael; Nicholson, Leonard S. (Technical Monitor)

1999-01-01

The characterization of the aeroshape selected for the X-38 [Crew Return Vehicle (CRV) demonstrator] is presently being performed as a cooperative endeavour between NASA, DLR (through its TETRA Program), and European Space Agency (ESA) with Dassault Aviation integrating the aerodynamic and aerothermodynamic activities. The methodologies selected for characterizing the aerodynamic and aerothermodynamic environment of the X-38 are presented. Also, the implications for related disciplines such as Guidance Navigation and Control (GN&C) with its corresponding Flight Control System (FCS), Structural, and Thermal Protection System (TPS) design are discussed. An attempt is made at defining the additional activities required to support the design of a derived operational CRV.

The Interior of the Crew Return Vehicle (CRV) Shows How Up to Seven Astronauts Can Be Carried

NASA Technical Reports Server (NTRS)

1999-01-01

This photo of the interior of a full-size mock-up of the Crew Return Vehicle (CRV) cabin at NASA's Johnson Space Center, Houston, Texas, shows how up to seven astronauts could be carried aboard the spacecraft. The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80

A Full-Size Mockup of the Cabin for the Crew Return Vehicle (CRV) for the International Space Statio

NASA Technical Reports Server (NTRS)

1999-01-01

This photo, taken at NASA's Johnson Space Center, Houston, Texas, shows a full-size mockup of the cabin for the Crew Return Vehicle (CRV) for the International Space Station The X-38 Crew Return Vehicle (CRV) research project is designed to develop the technology for a prototype emergency crew return vehicle, or lifeboat, for the International Space Station. The project is also intended to develop a crew return vehicle design that could be modified for other uses, such as a joint U.S. and international human spacecraft that could be launched on the French Ariane-5 Booster. The X-38 project is using available technology and off-the-shelf equipment to significantly decrease development costs. Original estimates to develop a capsule-type crew return vehicle were estimated at more than $2 billion. X-38 project officials have estimated that development costs for the X-38 concept will be approximately one quarter of the original estimate. Off-the-shelf technology is not necessarily 'old' technology. Many of the technologies being used in the X-38 project have never before been applied to a human-flight spacecraft. For example, the X-38 flight computer is commercial equipment currently used in aircraft and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment for the X-38 is existing equipment, some of which has already flown on the space shuttle for previous NASA experiments. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters. The X-38 electromechanical actuators come from previous joint NASA, U.S. Air Force, and U.S. Navy research and development projects. Finally, an existing special coating developed by NASA will be used on the X-38 thermal tiles to make them more durable than those used on the space shuttles. The X-38 itself was an unpiloted lifting body designed at 80 percent of the size of a projected

X-38 - First Flight

NASA Technical Reports Server (NTRS)

1997-01-01

Reminiscent of the lifting body research flights conducted more than 30 years earlier, NASA's B-52 mothership lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also

The X-38 V-201 Flap Actuator Mechanism

NASA Technical Reports Server (NTRS)

Hagen, Jeff; Moore, Landon; Estes, Jay; Layer, Chris

2004-01-01

The X-38 Crew Rescue Vehicle V-201 space flight test article was designed to achieve an aerodynamically controlled re-entry from orbit in part through the use of two body mounted flaps on the lower rear side. These flaps are actuated by an electromechanical system that is partially exposed to the re-entry environment. These actuators are of a novel configuration and are unique in their requirement to function while exposed to re-entry conditions. The authors are not aware of any other vehicle in which a major actuator system was required to function throughout the complete re-entry profile while parts of the actuator were directly exposed to the ambient environment.

Thermal stress imposed by prototype bilayer and current ground crew chemical defense ensembles: a limited laboratory comparison. Final report, 30 June 1986-1 January 1987

DOE Office of Scientific and Technical Information (OSTI.GOV)

Krock, L.P.; Navalta, R.; Myhre, L.G.

An open bilayer ground-crew chemical defense ensemble (CDE) was proposed to reduce the thermal burden during vapor-only exposure periods. This study compared the thermal-stress profile of the proposed ensemble to that produced by the currently employed closed CDE. Four subjects, alternating ensembles on separate days, walked on a treadmill in an environmental chamber at 5.3 km/h (3.3 mph) and 2% grade (an energy expenditure of 350 kcal/h) for alternating work/rest to achieve significant recovery. Mean total sweat production was lower (1.38 vs. 2.50 liters) and percent sweat evaporation greater (65.7% vs. 30.0%) in the prototype ensemble than in the CDE.more » The prototype ensemble provided greater heat dissipation and allowed more-efficient sweat evaporation which had the double benefit of reducing heat storage and limiting dehydration.« less

Design and Demonstration of Bolt Retractor Separation System for X-38 Deorbit Propulsion Stage

NASA Technical Reports Server (NTRS)

Ahmed, Raf; Johnston, A. S.; Garrison, J. C.; Gaines, J. L.; Waggoner, J. D.

2003-01-01

A separation system was designed for the X-38 experimental crew return vehicle program to allow the Deorbit Propulsion Stage (DPS) to separate from the X-38 lifting body during reentry operations. The configuration chosen was a spring-loaded plunger, known as the Bolt Retractor Subsystem (BRS), that retracts each of the six DPS-to-lifting body attachment bolts across the interface plane after being triggered by a separation nut mechanism. The system was designed to function on the ground in an atmospheric environment as well as in space. The BRS provides the same functionality as that of a completely pyrotechnic shear separation system that would normally be considered ideal for this application, but at a much lower cost. This system also could potentially be applied to future space station crew return vehicles. The design goal of 40 ms retraction time was successfully met in a series of demonstrations performed at the NASA Marshall Space Flight Center s Pyrotechnic Shock Facility (PSF) and Flight Robotics Laboratory (FRL). It must be emphasized that a full-scale test series was not performed on the BRS due to program schedule and cost constraints.

Game-based versus storyboard-based evaluations of crew support prototypes for long duration missions

NASA Astrophysics Data System (ADS)

Smets, N. J. J. M.; Abbing, M. S.; Neerincx, M. A.; Lindenberg, J.; van Oostendorp, H.

2010-03-01

The Mission Execution Crew Assistant (MECA) is developing a distributed system of electronic partners (ePartners) to support astronauts performing nominal and off- nominal actions in long duration missions. The ePartners' support should adequately deal with the dynamics of the context, operations, team and personal conditions, which will change over time substantially. Such support—with the concerning context effects—should be thoroughly tested in all stages of the development process. A major question is how to address the context effects of in-space operations for evaluations of crew support prototypes. Via game-technology, the prototype can be tested with astronauts or their representatives, immersed in the envisioned, simulated context. We investigated if a game-based evaluation better addresses the context effects by producing a more elaborate, in-depth and realistic user experience than a "classical" storyboard-based evaluation. In the game-based evaluation, the participants showed higher arousal levels where expected, a more intense feeling of spatial presence, better situation awareness, and faster performance where needed. Such an evaluation can be used as an alternative or complement of field or micro-world tests when context dynamics cannot be simulated in these last tests cost-efficiently.

A prototype case-based reasoning human assistant for space crew assessment and mission management

NASA Technical Reports Server (NTRS)

Owen, Robert B.; Holland, Albert W.; Wood, Joanna

1993-01-01

We present a prototype human assistant system for space crew assessment and mission management. Our system is based on case episodes from American and Russian space missions and analog environments such as polar stations and undersea habitats. The general domain of small groups in isolated and confined environments represents a near ideal application area for case-based reasoning (CBR) - there are few reliable rules to follow, and most domain knowledge is in the form of cases. We define the problem domain and outline a unique knowledge representation system driven by conflict and communication triggers. The prototype system is able to represent, index, and retrieve case studies of human performance. We index by social, behavioral, and environmental factors. We present the problem domain, our current implementation, our research approach for an operational system, and prototype performance and results.

X-38 - First Flight

NASA Technical Reports Server (NTRS)

1997-01-01

In a scene reminiscent of the lifting body research flights conducted more than 30 years earlier, this photo shows a close-up view of NASA's B-52 mothership as it lifts off carrying a new generation of lifting body research vehicle--the X-38. The X-38 was designed to help develop an emergency crew return vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the

View forward from bulkhead no. 38 of compartment B126 crew ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

View forward from bulkhead no. 38 of compartment B-126 crew space. Note stop valves on bulkhead at right side of photograph; these steam control valves allowed remote activation of the main, auxiliary and safety valves for the port engine in the event that the engine room valves were disabled or unreachable. (044) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

STS-121 Crew attends the "X Games" in Los Angeles

NASA Image and Video Library

2006-08-03

JSC2006-E-32816 (3 August 2006) --- The crew of STS-121 attended opening day of the 12th "X Games" in Los Angeles Aug. 3, discussing their recent mission to the International Space Station with students and athletes. Astronaut Steven W. Lindsey (with microphone), commander, and his crew take time out of the question and answer session to watch "Rally Car" practice. The crew's visit also included presentations at the Jet Propulsion Laboratory and the California Science Center.

T-38 AT SLF DURING STS-80 CREW ARRIVAL

NASA Technical Reports Server (NTRS)

1996-01-01

A T-38 parked at KSC's Shuttle Landing Facility is profiled against the brilliant twilight sky. The five astronauts assigned to Space Shuttle Mission STS-80 arrived from Houston at around 6:30 p.m.: Mission Commander Kenneth D. Cockrell; Pilot Kent V. Rominger; and Mission Specialists Tamara E. Jernigan, Thomas D. Jones and Story Musgrave headed for the crew quarters in the Operations and Checkout Building. Tomorrow, Nov. 12, the launch countdown will begin at 1 p.m. with the countdown clock set at T- 43 hours. The Space Shuttle Columbia is scheduled for liftoff from Launch Pad 39B at 2:50 p.m. EST, Nov. 15.

Low Speed Aerodynamics of the X-38 CRV

NASA Technical Reports Server (NTRS)

Komerath, N. M.; Funk, R.; Ames, R. G.; Mahalingam, R.; Matos, C.

1998-01-01

This project was performed in support of the engineering development of the NASA X-38 Crew Return Vehicle (CRV)system. Wind tunnel experiments were used to visualize various aerodynamic phenomena encountered by the CRV during the final stages of descent and landing. Scale models of the CRV were used to visualize vortex structures above and below the vehicle, and in its wake, and to quantify their trajectories. The effect of flaperon deflection on these structures was studied. The structure and dynamics of the CRV's wake during the drag parachute deployment stage were measured. Regions of high vorticity were identified using surveys conducted in several planes using a vortex meter. Periodic shedding of the vortex sheets from the sides of the CRV was observed using laser sheet videography as the CRV reached high angles of attack during the quasi-steady pitch-up prior to parafoil deployment. Using spectral analysis of hot-film anemometer data, the Strouhal number of these wake fluctuations was found to be 0.14 based on the model span. Phenomena encountered in flight test during parafoil operation were captured in scale-model tests, and a video photogrammetry technique was implemented to obtain parafoil surface shapes during flight in the tunnel. Forces on the parafoil were resolved using tension gages on individual lines. The temporal evolution of the phenomenon of leading edge collapse was captured. Laser velocimetry was used to demonstrate measurement of the porosity of the parafoil surface. From these measurements, several physical explanations have been developed for phenomena observed at various stages of the X-38 development program. Quantitative measurement capabilities have also been demonstrated for continued refinement of the aerodynamic technologies employed in the X-38 project. Detailed results from these studies are given in an AIAA Paper, two slide presentations, and other material which are given on a Web-based archival resource. This is the Digital

Ares I-X Ground Diagnostic Prototype

NASA Technical Reports Server (NTRS)

Schwabacher, Mark A.; Martin, Rodney Alexander; Waterman, Robert D.; Oostdyk, Rebecca Lynn; Ossenfort, John P.; Matthews, Bryan

2010-01-01

The automation of pre-launch diagnostics for launch vehicles offers three potential benefits: improving safety, reducing cost, and reducing launch delays. The Ares I-X Ground Diagnostic Prototype demonstrated anomaly detection, fault detection, fault isolation, and diagnostics for the Ares I-X first-stage Thrust Vector Control and for the associated ground hydraulics while the vehicle was in the Vehicle Assembly Building at Kennedy Space Center (KSC) and while it was on the launch pad. The prototype combines three existing tools. The first tool, TEAMS (Testability Engineering and Maintenance System), is a model-based tool from Qualtech Systems Inc. for fault isolation and diagnostics. The second tool, SHINE (Spacecraft Health Inference Engine), is a rule-based expert system that was developed at the NASA Jet Propulsion Laboratory. We developed SHINE rules for fault detection and mode identification, and used the outputs of SHINE as inputs to TEAMS. The third tool, IMS (Inductive Monitoring System), is an anomaly detection tool that was developed at NASA Ames Research Center. The three tools were integrated and deployed to KSC, where they were interfaced with live data. This paper describes how the prototype performed during the period of time before the launch, including accuracy and computer resource usage. The paper concludes with some of the lessons that we learned from the experience of developing and deploying the prototype.

STS-121 Crew attends the "X Games" in Los Angeles

NASA Image and Video Library

2006-08-03

JSC2006-E-32814 (3 August 2006) --- The crew of STS-121 attended opening day of the 12th "X Games" in Los Angeles Aug. 3, discussing their recent mission to the International Space Station with students and athletes. Astronaut Mark E. Kelly, pilot, stands at the edge of the signature 80 foot high "Big Air Jump" skateboarding ramp - location for one of the event highlights. The crew's visit also included presentations at the Jet Propulsion Laboratory and the California Science Center.

The X-38 V-201 Fin Fold Actuation Mechanism

NASA Technical Reports Server (NTRS)

Lupo, Christian; Robertson, Brandan; Gafka, George

2004-01-01

The X-38 Vehicle 201 (V-201) is a space flight prototype lifting body vehicle that was designed to launch to orbit in the Space Shuttle orbiter payload bay. Although the project was cancelled in May 2003, many of the systems were nearly complete. This paper will describe the fin folding actuation mechanism flight subsystems and development units as well as lessons learned in the design, assembly, development testing, and qualification testing. The two vertical tail fins must be stowed (folded inboard) to allow the orbiter payload bay doors to close. The fin folding actuation mechanism is a remotely or extravehicular activity (EVA) actuated single fault tolerant system consisting of seven subsystems capable of repeatedly deploying or stowing the fins.

Rudder/Fin Seal Investigations for the X-38 Re-Entry Vehicle

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; Curry, Donald M.

2000-01-01

NASA is currently developing the X-38 vehicle that will be used to demonstrate the technologies required for a crew return vehicle (CRV) for the International Space Station. The X-38 control surfaces require high temperature seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent over-temperature of these structures and possible loss of the vehicle. This paper presents results for thermal analyses and flow and compression tests conducted on as-received and thermally exposed seals for the rudder/fin location of the X-38. A thermal analysis of the rudder/fin dual seal assembly based on representative heating rates on the windward surface of the rudder/fin area predicted a peak seal temperature of 1900 F. The temperature-exposed seals were heated in a compressed state at 1900 F corresponding to the predicted peak temperature. Room temperature compression tests were performed to determine load versus linear compression, preload, contact area, stiffness, and resiliency characteristics for the as-received and temperature-exposed seals. Temperature exposure resulted in permanent set and loss of resiliency in these seals. Unit loads and contact pressures for the seals were below the 5 lb/in. and 10 psi limits set to limit the loads on the Shuttle thermal tiles that the seals seal against in the rudder/fin location. Measured seal flow rates for a double seal were about 4.5 times higher than the preliminary seal flow goal. The seal designs examined in this study are expected to be able to endure the high temperatures that they will be exposed to for a single-use life. Tests performed herein combined with future analyses, arc jet tests, and scrubbing tests will be used to select the final seal design for this application.

Rudder/Fin Seal Investigations for the X-38 Re-Entry Vehicle

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; Curry, Donald M.

2000-01-01

NASA is currently developing the X-38 vehicle that will be used to demonstrate the technologies required for a crew return vehicle (CRV) for the International Space Station. The X-38 control surfaces require high temperature seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent over-temperature of these structures and possible loss of the vehicle. This paper presents results for thermal analyses and flow and compression tests conducted on as-received and thermally exposed seals for the rudder/fin location of the X-38. A thermal analysis of the rudder/fin dual seal assembly based on representative heating rates on the windward surface of the rudder/fin area predicted a peak seal temperature of 1900 F. The temperature-exposed seals were heated in a compressed state at 1900 F corresponding to the predicted peak temperature. Room temperature compression tests were performed to determine load versus linear compression, preload, contact area, stiffness, and resiliency characteristics for the as-received and temperature-exposed seals. Temperature exposure resulted in permanent set and loss of resiliency in these seals. Unit loads and contact pressures for the seals were below the five pounds/inch and ten psi limits set to limit the loads on the Shuttle thermal tiles that the seals seal against in the rudder/fin location. Measured seal flow rates for a double seal were about 4.5 times higher than the preliminary seal flow goal. The seal designs examined in this study are expected to be able to endure the high temperatures that they will be exposed to for a single-use life. Tests performed herein combined with future analyses, arc jet tests, and scrubbing tests will be used to select the final seal design for this application.

156 Mbps Ultrahigh-Speed Wireless LAN Prototype in the 38 GHz Band

NASA Astrophysics Data System (ADS)

Wu, Gang; Inoue, Masugi; Murakami, Homare; Hase, Yoshihiro

2001-12-01

This paper describes a 156 Mbps ultrahigh-speed wireless LAN operating in the 38 GHz millimeter (mm)-wave band. The system is a third prototype developed at the Communications Research Laboratory since 1998. Compared with the previous prototypes, the system is faster (156 Mbps) and smaller (volume of radio transceiver less than 1000 cc), it has a larger service area (two overlapping basic service sets), and a longer transmission distance (the protocol can support a distance of more than two hundred meters). The development is focused on the physical layer and the data link control layer, and thus a GMSK-based mm-wave transceiver and an enhanced RS-ISMA (reservation-based slotted idle signal multiple access) protocol are key development components. This paper describes the prototype system's design, configuration, and implementation.

KENNEDY SPACE CENTER, FLA. - Walking away from the T-38 jet aircraft that brought them to KSC are STS-114 Mission Specialist Wendy Lawrence and Pilot James Kelly. Lawrence is a new addition to the crew. They and other crew members are at KSC to take part in crew equipment and orbiter familiarization.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - Walking away from the T-38 jet aircraft that brought them to KSC are STS-114 Mission Specialist Wendy Lawrence and Pilot James Kelly. Lawrence is a new addition to the crew. They and other crew members are at KSC to take part in crew equipment and orbiter familiarization.

STS-121 Crew attends the "X Games" in Los Angeles

NASA Image and Video Library

2006-08-03

JSC2006-E-32815 (3 Aug. 2006) --- The crew of STS-121 attended opening day of the 12th "X Games" in Los Angeles Aug. 3, discussing their recent mission to the International Space Station with students and athletes. From left to right are astronauts Piers J. Sellers, Stephanie D. Wilson, Steven W. Lindsey, Michael E. Fossum, Lisa M. Nowak and Mark E. Kelly. In the background is the signature 80 foot high "Big Air Jump" skateboarding ramp - one of the event highlights. The crew's visit also included presentations at the Jet Propulsion Laboratory and the California Science Center.

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronaut Bob Behnken, work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

Dynamic and Static High Temperature Resistant Ceramic Seals for X- 38 re-Entry Vehicle

NASA Astrophysics Data System (ADS)

Handrick, Karin E.; Curry, Donald M.

2002-01-01

In a highly successful partnership, NAS A, ESA, DLR (German Space Agency) and European industry are building the X-38, V201 re-entry spacecraft, the prototype of the International Space Station's Crew Return Vehicle (CRV). This vehicle would serve both as an ambulance for medical emergencies and as an evacuation vehicle for the Space Station. The development of essential systems and technologies for a reusable re-entry vehicle is a first for Europe, and sharing the development of an advanced re-entry spacecraft with foreign partners is a first for NASA. NASA, in addition to its subsystem responsibilities, is performing overall X-38 vehicle system engineering and integration, will launch V201 on the Space Shuttle, deliver flight data for post-flight analysis and assessment and is responsible for development and manufacture of structural vehicle components and thermal protection (TPS) tiles. The major European objective for cooperation with NASA on X-38 was to establish a clear path through which key technologies needed for future space transportation systems could be developed and validated at affordable cost and with controlled risk. Europe has taken the responsibility to design and manufacture hot control surfaces like metallic rudders and ceramic matrix composites (CMC) body flaps, thermal protection systems such as CMC leading edges, the CMC nose cap and -skirt, insulation, landing gears and elements of the V201 primary structure. Especially hot control surfaces require extremely high temperature resistant seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent overheating of these structures and possible loss of the vehicle. Complex seal interfaces, which have to fulfill various, tight mission- and vehicle-related requirements exist between the moveable ceramic body flaps and the bottom surface of the vehicle, between the rudder and fin structure and the ceramic leading edge panel and TPS tiles. While NASA

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronauts Eric Boe, right, and Bob Behnken work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

Commerical Crew Astronauts Evaluate Crew Dragon Controls

NASA Image and Video Library

2017-01-10

Astronauts Bob Behnken, left, and Eric Boe work in a mock-up of the SpaceX Crew Dragon flight deck at the company's Hawthorne, California, headquarters as development of the crew systems continues for eventual missions to the International Space Station.

X-ray source characteristics and detection efficiencies of prototype Lixiscopes

NASA Technical Reports Server (NTRS)

Seltzer, S. M.

1978-01-01

The radioactive X-ray sources and scintillator screens used in prototype Lixiscope units are described. Some of those considerations necessary for the optimization of future Lixiscope designs are stressed as well as some semi-quantitative information on the present prototype devices.

Crew Configuration, Ingress/Egress Procedures, and In-Flight Caregiving Capacity in a Space Ambulance Based on the Boeing X-37B

NASA Astrophysics Data System (ADS)

Halberg, Ephriam Etan

This study proposes that a Boeing X-37B space plane, its dimensions and performance characteristics estimated from publicly available documents, diagrams, and photographs, could be internally redesigned as a medical evacuation (ambulance) vehicle for the International Space Station. As of 2017, there is currently no spacecraft designed to accommodate a contingency medical evacuation wherein a crew member aboard the ISS is injured or ailing and must be returned to Earth for immediate medical attention. The X-37B is an unmanned vehicle with a history of success in both sub-orbital testing and all four of its long-duration orbital missions to date. Research conducted at UC Davis suggests that it is possible to retain the outer mold line of the X-37B while expanding the internal payload compartment to a volume sufficient for a crew of three--pilot, crew medical officer, and injured crew member--throughout ISS un-dock and atmospheric entry, descent, and landing. In addition to crew life support systems, this re-purposed X-37B, hereafter referred to as the X-37SA (Space Ambulance), includes medical equipment for stabilization of a patient in-transit. This study suggests an optimal, ergonomic crew configuration and berthing port location, procedures for microgravity ingress and 1G egress, a minimum medical equipment list and location within the crew cabin for the medical care and monitoring equipment. Conceptual crew configuration, ingress/egress procedures, and patient/equipment access are validated via physical simulation in a full-scale mockup of the proposed X-37SA crew cabin.

Development of a universal medical X-ray imaging phantom prototype.

PubMed

Groenewald, Annemari; Groenewald, Willem A

2016-11-08

Diagnostic X-ray imaging depends on the maintenance of image quality that allows for proper diagnosis of medical conditions. Maintenance of image quality requires quality assurance programs on the various X-ray modalities, which consist of pro-jection radiography (including mobile X-ray units), fluoroscopy, mammography, and computed tomography (CT) scanning. Currently a variety of modality-specific phantoms are used to perform quality assurance (QA) tests. These phantoms are not only expensive, but suitably trained personnel are needed to successfully use them and interpret the results. The question arose as to whether a single universal phantom could be designed and applied to all of the X-ray imaging modalities. A universal phantom would reduce initial procurement cost, possibly reduce the time spent on QA procedures and simplify training of staff on the single device. The aim of the study was to design and manufacture a prototype of a universal phantom, suitable for image quality assurance in general X-rays, fluoroscopy, mammography, and CT scanning. The universal phantom should be easy to use and would enable automatic data analysis, pass/fail reporting, and corrective action recommendation. In addition, a universal phantom would especially be of value in low-income countries where finances and human resources are limited. The design process included a thorough investigation of commercially available phantoms. Image quality parameters necessary for image quality assurance in the different X-ray imaging modalities were determined. Based on information obtained from the above-mentioned investigations, a prototype of a universal phantom was developed, keeping ease of use and reduced cost in mind. A variety of possible phantom housing and insert materials were investigated, considering physical properties, machinability, and cost. A three-dimensional computer model of the first phantom prototype was used to manufacture the prototype housing and inserts. Some of the

The FEI-TPS on the Upper Surface of the X-38

NASA Astrophysics Data System (ADS)

Antonenko, Johann; Kowal, John

2002-01-01

The X-38 is being developed by NASA-JSC as a technology demonstrator of a future Crew Rescue Vehicle. The size of the vehicle is limited to fit into the cargo bay of the shuttle. Due to its small size and shuttle-like trajectory all surfaces will receive comparably high heat rates leading to high surface temperatures. Temperatures on the nose are calculated to reach 1750°C, which is significantly higher than on the shuttle. Due to the lifting body shape, large areas of the central fuselage will be exposed to flow of hot gases around the vehicle. Here temperatures of the upper surface are calculated to reach up to 1000°C and the application of a high temperature blanket thermal protection system (TPS) becomes mandatory. Consecutively, the temperature level of the upper surface and the base area will be significantly high. Unlike on the shuttle, where large areas of the surface are covered by flexible reusable surface insulation (FRSI), locations with temperatures below 400°C will be scarce on the X-38. During development of the European shuttle HERMES the Flexible External Insulation (FEI) was developed for the upper surface TPS. This development was continued by ESA and DLR funded programs and currently a product family is available for temperatures ranging from 450°C to 1100°C for re-usable application. For a single re- entry under ultimate conditions temperatures may reach up to 1400°C. Under funding of DLR and ESA, the FEI assembly is one of the European contributions to the X-38. Three subassemblies have been chosen: the FEI-450, FEI-650 and FEI- 1000, capable of limit temperatures of 450°C, 650°C and 1000°C, respectively. The FEI-650 and FEI-1000 were already developed in the HERMES program. The FEI- 450 was developed in the German TETRA program. The qualification for X-38 application was performed for temperatures up to 510°C for the FEI-450 and up to 1130°C for the FEI-1000. Acoustic noise loads of up to 160dB have been endured, far beyond what X

Coral Reef Early Warning System (CREWS) RPC Experiment

NASA Technical Reports Server (NTRS)

Estep, Leland; Spruce, Joseph P.; Hall, Callie

2007-01-01

This viewgraph document reviews the background, objectives, methodology, validation, and present status of the Coral Reef Early Warning System (CREWS) Rapid Prototyping Capability (RPC) experiment. The potential NASA contribution to CREWS Decision Support Tool (DST) centers on remotely sensed imagery products.

NASA engineer Wayne Peterson from the Johnson Space Center reviews postflight checklists following a

NASA Technical Reports Server (NTRS)

2001-01-01

NASA engineer Wayne Peterson from the Johnson Space Center reviews postflight checklists following a spectacular flight of the X-38 prototype for a crew recovery vehicle that may be built for the International Space Station. The X-38 tested atmospheric flight characteristics on December 13, 2001, in a descent from 45,000 feet to Rogers Dry Lake at the NASA Dryden Flight Research Center/Edwards Air Force Base complex in California.

X-38 Mounted on Pylon of B-52 Mothership

NASA Technical Reports Server (NTRS)

1997-01-01

A close-up view of the X-38 research vehicle mounted under the wing of the B-52 mothership prior to a 1997 test flight. The X-38, which was designed to help develop technology for an emergency crew return vehicle (CRV) for the International Space Station, is one of many research vehicles the B-52 has carried aloft over the past 40 years. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space

Ares I-X Flight Test Vehicle Similitude to the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Smith, R. Marshall; Campbell, John R., Jr.; Taylor, Terry L.

2008-01-01

The Ares I-X Flight Test Vehicle is the first in a series of flight test vehicles that will take the Ares I Crew Launch Vehicle design from development to operational capability. The test flight is scheduled for April 2009, relatively early in the Ares I design process so that data obtained from the flight can impact the design of Ares I before its Critical Design Review. Because of the short time frame (relative to new launch vehicle development) before the Ares I-X flight, decisions about the flight test vehicle design had to be made in order to complete analysis and testing in time to manufacture the Ares I-X vehicle hardware elements. This paper describes the similarities and differences between the Ares I-X Flight Test Vehicle and the Ares I Crew Launch Vehicle. Areas of comparison include the outer mold line geometry, aerosciences, trajectory, structural modes, flight control architecture, separation sequence, and relevant element differences. Most of the outer mold line differences present between Ares I and Ares I-X are minor and will not have a significant effect on overall vehicle performance. The most significant impacts are related to the geometric differences in Orion Crew Exploration Vehicle at the forward end of the stack. These physical differences will cause differences in the flow physics in these areas. Even with these differences, the Ares I-X flight test is poised to meet all five primary objectives and six secondary objectives. Knowledge of what the Ares I-X flight test will provide in similitude to Ares I as well as what the test will not provide is important in the continued execution of the Ares I-X mission leading to its flight and the continued design and development of Ares I.

Ares I-X Flight Test Vehicle Similitude to the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Smith, R. Marshall; Campbell, John R.; Taylor, Terry L.

2009-01-01

The Ares I-X Flight Test Vehicle is the first in a series of flight test vehicles that will take the Ares I Crew Launch Vehicle design from development to operational capability. Ares I-X is scheduled for a 2009 flight date, early enough in the Ares I design and development process so that data obtained from the flight can impact the design of Ares I before its Critical Design Review. Decisions on Ares I-X scope, flight test objectives, and FTV fidelity were made prior to the Ares I systems requirements being baselined. This was necessary in order to achieve a development flight test to impact the Ares I design. Differences between the Ares I-X and the Ares I configurations are artifacts of formulating this experimental project at an early stage and the natural maturation of the Ares I design process. This paper describes the similarities and differences between the Ares I-X Flight Test Vehicle and the Ares I Crew Launch Vehicle. Areas of comparison include the outer mold line geometry, aerosciences, trajectory, structural modes, flight control architecture, separation sequence, and relevant element differences. Most of the outer mold line differences present between Ares I and Ares I-X are minor and will not have a significant effect on overall vehicle performance. The most significant impacts are related to the geometric differences in Orion Crew Exploration Vehicle at the forward end of the stack. These physical differences will cause differences in the flow physics in these areas. Even with these differences, the Ares I-X flight test is poised to meet all five primary objectives and six secondary objectives. Knowledge of what the Ares I-X flight test will provide in similitude to Ares I - as well as what the test will not provide - is important in the continued execution of the Ares I-X mission leading to its flight and the continued design and development of Ares I.

Development of a Prototype Nickel Optic for the Constellation-X Hard-X-Ray Telescope

NASA Technical Reports Server (NTRS)

Basso, S.; Bruni, R. J.; Citerio, O.; Engelhaupt, D.; Ghigo, M.; Gorenstien, P.; Mazzoleni, F.; ODell, S. L.; Pareschi, G.; Ramsey, B. D.

2003-01-01

The Constellation-X mission, planned for launch in 2011, will feature an array of hard-x ray telescopes with a total collecting area goal of 1500 square centimeters at 40 keV. Various technologies are currently being investigated for the optics of these telescopes including multilayer-coated Eletroformed-Nickel-Replicated (ENR) shells. The attraction of the ENR process is that the resulting full-shell optics are inherently stable and offer the promise of good angular resolution and enhanced instrument sensitivity. The challenge for this process is to meet a relatively tight weight budget with a relatively dense material (rho nickel = 9 grams per cubic centimeters.) To demonstrate the viability of the ENR process we are fabricating a prototype HXT mirror module to be tested against a competing segmented-glass-shell optic. The ENR prototype will consist of 5 shells of diameters from 150 mm to 280 mm and of 426 mm total length. To meet the stringent weight budget for Con-X, the shells will be only 150 micron thick. The innermost of these will be coated with Iridium, while the remainder will be coated with graded-density multilayers. Mandrels for these shells are currently under fabrication (Jan 03), with the first shells scheduled for production in February 03. A tentative date of late Summer has been set for prototype testing. Issues currently being addressed are the control of stresses in the multiplayer coating and ways of mitigating their effects on the figure of the necessarily thin shells. Also, the fabrication, handling and mounting of these shells without inducing permanent figure distortions. A full status report on the prototype optic will be presented along with test results as available.

X-15 #3 being secured by ground crew after flight

NASA Technical Reports Server (NTRS)

1960-01-01

The X-15-3 (56-6672) research aircraft is secured by ground crew after landing on Rogers Dry Lakebed. The work of the X-15 team did not end with the landing of the aircraft. Once it had stopped on the lakebed, the pilot had to complete an extensive post-landing checklist. This involved recording instrument readings, pressures and temperatures, positioning switches, and shutting down systems. The pilot was then assisted from the aircraft, and a small ground crew depressurized the tanks before the rest of the ground crew finished their work on the aircraft. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

Kathy Lueders, program manager of NASA's Commercial Crew Program, speaks during a news conference where it was announced that Boeing and SpaceX have been selected to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

APOLLO X - CREW

NASA Image and Video Library

1969-06-03

S69-35505 (June 1969) --- The prime crews of the Apollo 10 lunar orbit mission and the Apollo 11 lunar landing mission are photographed during an Apollo 10 postflight de-briefing session. Clockwise, from left foreground, are astronauts Michael Collins, Apollo 11 command module pilot; Edwin E. Aldrin Jr., Apollo 11 lunar module pilot; Eugene A. Cernan, Apollo 10 lunar module pilot; Thomas P. Stafford, Apollo 10 commander; Neil A. Armstrong, Apollo 11 commander; and John W. Young, Apollo 10 command module pilot.

Crew Exploration Vehicle Service Module Ascent Abort Coverage

NASA Technical Reports Server (NTRS)

Tedesco, Mark B.; Evans, Bryan M.; Merritt, Deborah S.; Falck, Robert D.

2007-01-01

The Crew Exploration Vehicle (CEV) is required to maintain continuous abort capability from lift off through destination arrival. This requirement is driven by the desire to provide the capability to safely return the crew to Earth after failure scenarios during the various phases of the mission. This paper addresses abort trajectory design considerations, concept of operations and guidance algorithm prototypes for the portion of the ascent trajectory following nominal jettison of the Launch Abort System (LAS) until safe orbit insertion. Factors such as abort system performance, crew load limits, natural environments, crew recovery, and vehicle element disposal were investigated to determine how to achieve continuous vehicle abort capability.

Advanced Crew Escape Suit.

PubMed

1995-09-01

Design of the S1032 Launch Entry Suit (LES) began following the Challenger loss and NASA's decision to incorporate a Shuttle crew escape system. The LES (see Figure 1) has successfully supported Shuttle missions since NASA's Return to Flight with STS-26 in September 1988. In 1990, engineers began developing the S1035 Advanced Crew Escape Suit (ACES) to serve as a replacement for the LES. The ACES was designed to be a simplified, lightweight, low-bulk pressure suit which aided self donning/doffing, provided improved comfort, and enhanced overall performance to reduce crew member stress and fatigue. Favorable crew member evaluations of a prototype led to full-scale development and qualification of the S1035 ACES between 1990 and 1992. Production of the S1035 ACES began in February 1993, with the first unit delivered to NASA in May 1994. The S1035 ACES first flew aboard STS-68 in August 1994 and will become the primary crew escape suit when the S1032 LES ends its service life in late 1995. The primary goal of the S1035 development program was to provide improved performance over that of the S1032 to minimize the stress and fatigue typically experienced by crew members. To achieve this, five fundamental design objectives were established, resulting in various material/configuration changes.

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 backup crew member Reid Wiseman of NASA is seen in quarantine, behind glass, during the final press conference held a day ahead of the launch of Expedition 38 prime crew members; Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, Soyuz Commander Mikhail Tyurin of Roscosmos, and, Flight Engineer Rick Mastracchio of NASA, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

Further Investigations of Control Surface Seals for the X-38 Re-Entry Vehicle

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; Curry, Donald M.; Newquist, Charles W.; Verzemnieks, Juris

2001-01-01

NASA is currently developing the X-38 vehicle that will be used to demonstrate the technologies required for a potential crew return vehicle (CRV) for the International Space Station. This vehicle would serve both as an ambulance for medical emergencies and as an evacuation vehicle for the Space Station. Control surfaces on the X-38 (body flaps and rudder/fin assemblies) require high temperature seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent over-temperature of these structures and possible loss of the vehicle. NASAs Johnson Space Center (JSC) and Glenn Research Center (GRC) are working together to develop and evaluate seals for these control surfaces. This paper presents results for compression. flow, scrub, and arc jet tests conducted on the baseline X-38 rudder/fin seal design. Room temperature seal compression tests were performed at low compression levels to determine load versus linear compression, preload. contact area, stiffness. and resiliency characteristics under low load conditions. For all compression levels that were tested, unit loads and contact pressures for the seals were below the 5 lb/in. and 10 psi limits required to limit the loads on the adjoining Shuttle thermal tiles that the seals will contact. Flow rates through an unloaded (i.e. 0% compression) double arrangement were twice those of a double seal compressed to the 20% design compression level. The seals survived an ambient temperature 1000 cycle scrub test over relatively rough Shuttle tile surfaces. The seals were able to disengage and re-engage the edges of the rub surface tiles while being scrubbed over them. Arc jet tests were performed to experimentally determine anticipated seal temperatures for representative flow boundary conditions (pressures and temperatures) under simulated vehicle re-entry conditions. Installation of a single seat in the gap of the test fixture caused a large temperature drop (1710 F) across the seal

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 backup crew member Alexander Gerst of the European Space Agency is seen in quarantine, behind glass, during the final press conference held a day ahead of the launch of Expedition 38 prime crew members; Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, Soyuz Commander Mikhail Tyurin of Roscosmos, and, Flight Engineer Rick Mastracchio of NASA, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

NASA Administrator Charles Bolden listens to a reporter’s question after he announced the agency’s selection of Boeing and SpaceX to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

Kathy Lueders, program manager of NASA's Commercial Crew Program, speaks, as Former astronaut Bob Cabana, director of NASA's Kennedy Space Center in Florida, left, and Astronaut Mike Fincke, a former commander of the International Space Station look on during a news conference where it was announced that Boeing and SpaceX have been selected to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Tuning Thermoelectric Properties of Type I Clathrate K 8–x Ba x Al 8+x Si 38–x through Barium Substitution

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sui, Fan; Kauzlarich, Susan M.

2016-05-10

The thermal stability and thermoelectric properties of type I clathrate K8Al8Si38 up to 873 K are reported. K8Al8Si38 possesses a high absolute Seebeck coefficient value and high electrical resistivity in the temperature range of 323 to 873 K, which is consistent with previously reported low temperature thermoelectric properties. Samples with Ba partial substitution at the K guest atom sites were synthesized from metal hydride precursors. The samples with the nominal chemical formula of K8–xBaxAl8+xSi38–x (x = 1, 1.5, 2) possess type I clathrate structure (cubic, Pm3n), confirmed by X-ray diffraction. The guest atom site occupancies and thermal motions were investigatedmore » with Rietveld refinement of synchrotron powder X-ray diffraction. Transport properties of Ba-containing samples were characterized from 2 to 300 K. The K–Ba alloy phases showed low thermal conductivity and improved electrical conductivity compared to K8Al8Si38. Electrical resistivity and Seebeck coefficients were measured over the temperature range of 323 to 873 K. Thermal conductivity from 323 to 873 K was estimated from the Wiedemann–Franz relation and lattice thermal conductivity extrapolation from 300 to 873 K. K8–xBaxAl8+xSi38–x (x = 1, 1.5) synthesized with Al deficiency showed enhanced electrical conductivity, and the absolute Seebeck coefficients decrease with the increased carrier concentration. When x = 2, the Al content increases toward the electron balanced composition, and the electrical resistivity increases with the decreasing charge carrier concentration. Overall, K6.5Ba1.5Al9Si37 achieves an enhanced zT of 0.4 at 873 K.« less

Detector, collimator and real-time reconstructor for a new scanning-beam digital x-ray (SBDX) prototype.

PubMed

Speidel, Michael A; Tomkowiak, Michael T; Raval, Amish N; Dunkerley, David A P; Slagowski, Jordan M; Kahn, Paul; Ku, Jamie; Funk, Tobias

Scanning-beam digital x-ray (SBDX) is an inverse geometry fluoroscopy system for low dose cardiac imaging. The use of a narrow scanned x-ray beam in SBDX reduces detected x-ray scatter and improves dose efficiency, however the tight beam collimation also limits the maximum achievable x-ray fluence. To increase the fluence available for imaging, we have constructed a new SBDX prototype with a wider x-ray beam, larger-area detector, and new real-time image reconstructor. Imaging is performed with a scanning source that generates 40,328 narrow overlapping projections from 71 × 71 focal spot positions for every 1/15 s scan period. A high speed 2-mm thick CdTe photon counting detector was constructed with 320×160 elements and 10.6 cm × 5.3 cm area (full readout every 1.28 μs), providing an 86% increase in area over the previous SBDX prototype. A matching multihole collimator was fabricated from layers of tungsten, brass, and lead, and a multi-GPU reconstructor was assembled to reconstruct the stream of captured detector images into full field-of-view images in real time. Thirty-two tomosynthetic planes spaced by 5 mm plus a multiplane composite image are produced for each scan frame. Noise equivalent quanta on the new SBDX prototype measured 63%-71% higher than the previous prototype. X-ray scatter fraction was 3.9-7.8% when imaging 23.3-32.6 cm acrylic phantoms, versus 2.3-4.2% with the previous prototype. Coronary angiographic imaging at 15 frame/s was successfully performed on the new SBDX prototype, with live display of either a multiplane composite or single plane image.

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

From left, NASA Public Affairs Officer Stephanie Schierholz, NASA Administrator Charles Bolden, Former astronaut Bob Cabana, director of NASA's Kennedy Space Center in Florida, Kathy Lueders, program manager of NASA's Commercial Crew Program, and Astronaut Mike Fincke, a former commander of the International Space Station, are seen during a news conference where it was announced that Boeing and SpaceX have been selected to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Real-Time Stability Margin Measurements for X-38 Robustness Analysis

NASA Technical Reports Server (NTRS)

Bosworth, John T.; Stachowiak, Susan J.

2005-01-01

A method has been developed for real-time stability margin measurement calculations. The method relies on a tailored-forced excitation targeted to a specific frequency range. Computation of the frequency response is matched to the specific frequencies contained in the excitation. A recursive Fourier transformation is used to make the method compatible with real-time calculation. The method was incorporated into the X-38 nonlinear simulation and applied to an X-38 robustness test. X-38 stability margins were calculated for different variations in aerodynamic and mass properties over the vehicle flight trajectory. The new method showed results comparable to more traditional stability analysis techniques, and at the same time, this new method provided coverage that is more complete and increased efficiency.

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

NASA Administrator Charles Bolden, left, announces the agency’s selection of Boeing and SpaceX to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft as Former astronaut Bob Cabana, director of NASA's Kennedy Space Center in Florida looks on at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

Astronaut Mike Fincke, a former commander of the International Space Station, speaks during a news conference where it was announced that Boeing and SpaceX have been selected to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Commercial Crew Transportation Capability

NASA Image and Video Library

2014-09-16

Former astronaut Bob Cabana, director of NASA's Kennedy Space Center in Florida, speaks during a news conference where it was announced that Boeing and SpaceX have been selected to transport U.S. crews to and from the International Space Station using the Boeing CST-100 and the SpaceX Crew Dragon spacecraft, at NASA’s Kennedy Space Center in Cape Canaveral, Fla. on Tuesday, Sept. 16, 2014. These Commercial Crew Transportation Capability (CCtCap) contracts are designed to complete the NASA certification for a human space transportation system capable of carrying people into orbit. Once certification is complete, NASA plans to use these systems to transport astronauts to the space station and return them safely to Earth. Photo Credit: (NASA/Bill Ingalls)

Crew Dragon Demonstration Mission 1

NASA Image and Video Library

2018-06-13

SpaceX’s Crew Dragon is at NASA’s Plum Brook Station in Ohio, ready to undergo testing in the In-Space Propulsion Facility — the world’s only facility capable of testing full-scale upper-stage launch vehicles and rocket engines under simulated high-altitude conditions. The chamber will allow SpaceX and NASA to verify Crew Dragon’s ability to withstand the extreme temperatures and vacuum of space. This is the spacecraft that SpaceX will fly during its Demonstration Mission 1 flight test under NASA’s Commercial Crew Transportation Capability contract with the goal of returning human spaceflight launch capabilities to the U.S.

The STS-93 crew takes part in payload familiarization of the Chandra X-ray Observatory

NASA Technical Reports Server (NTRS)

1999-01-01

A TRW technician joins STS-93 Commander Eileen Collins (center) and Pilot Jeffrey S. Ashby (right) as they observe the Chandra X- ray Observatory on its work stand inside the Vertical Processing Facility. Other members of the STS-93 crew who are at KSC for payload familiarization are Mission Specialists Catherine G. Coleman and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). Collins is the first woman to serve as a shuttle mission commander. She was the first woman pilot of a Space Shuttle, on mission STS-63, and also served as pilot on mission STS-84. The fifth member of the crew is Mission Specialist Steven A. Hawley. Chandra is scheduled for launch July 9 aboard Space Shuttle Columbia, on mission STS-93 . Formerly called the Advanced X-ray Astrophysics Facility, Chandra comprises three major elements: the spacecraft, the science instrument module (SIM), and the world's most powerful X-ray telescope. Chandra will allow scientists from around the world to see previously invisible black holes and high-temperature gas clouds, giving the observatory the potential to rewrite the books on the structure and evolution of our universe.

Prototype high resolution multienergy soft x-ray array for NSTX.

PubMed

Tritz, K; Stutman, D; Delgado-Aparicio, L; Finkenthal, M; Kaita, R; Roquemore, L

2010-10-01

A novel diagnostic design seeks to enhance the capability of multienergy soft x-ray (SXR) detection by using an image intensifier to amplify the signals from a larger set of filtered x-ray profiles. The increased number of profiles and simplified detection system provides a compact diagnostic device for measuring T(e) in addition to contributions from density and impurities. A single-energy prototype system has been implemented on NSTX, comprised of a filtered x-ray pinhole camera, which converts the x-rays to visible light using a CsI:Tl phosphor. SXR profiles have been measured in high performance plasmas at frame rates of up to 10 kHz, and comparisons to the toroidally displaced tangential multi-energy SXR have been made.

Crew Office Evaluation of a Precision Lunar Landing System

NASA Technical Reports Server (NTRS)

Major, Laura M.; Duda, Kevin R.; Hirsh, Robert L.

2011-01-01

A representative Human System Interface for a precision lunar landing system, ALHAT, has been developed as a platform for prototype visualization and interaction concepts. This facilitates analysis of crew interaction with advanced sensors and AGNC systems. Human-in-the-loop evaluations with representatives from the Crew Office (i.e. astronauts) and Mission Operations Directorate (MOD) were performed to refine the crew role and information requirements during the final phases of landing. The results include a number of lessons learned from Shuttle that are applicable to the design of a human supervisory landing system and cockpit. Overall, the results provide a first order analysis of the tasks the crew will perform during lunar landing, an architecture for the Human System Interface based on these tasks, as well as details on the information needs to land safely.

Design/Development of Spacecraft and Module Crew Compartments

NASA Technical Reports Server (NTRS)

Goodman, Jerry R.

2010-01-01

This slide presentation reviews the design and development of crew compartments for spacecraft and for modules. The Crew Compartment or Crew Station is defined as the spacecraft interior and all other areas the crewman interfaces inside the cabin, or may potentially interface.It uses examples from all of the human rated spacecraft. It includes information about the process, significant drivers for the design, habitability, definitions of models, mockups, prototypes and trainers, including pictures of each stage in the development from Apollo, pictures of the space shuttle trainers, and International Space Station trainers. It further reviews the size and shape of the Space Shuttle orbiter crew compartment, and the Apollo command module and the lunar module. It also has a chart which reviews the International Space Station (ISS) internal volume by stage. The placement and use of windows is also discussed. Interestingly according to the table presented, the number 1 rated piece of equipment for recreation was viewing windows. The design of crew positions and restraints, crew translation aids and hardware restraints is shown with views of the restraints and handholds used from the Apollo program through the ISS.

Integrated Measurement of Crew Resource Management and Technical Flying Skills

DOT National Transportation Integrated Search

1993-08-01

This report presents the findings of a study designed with two objectives: to produce a prototype performance : measurement instrument (PMI) that integrates the assessment of Crew Resource Management (CRM) and technical flying : skills and to investi...

Initial results of the FUSION-X-US prototype combining 3D automated breast ultrasound and digital breast tomosynthesis.

PubMed

Schaefgen, Benedikt; Heil, Joerg; Barr, Richard G; Radicke, Marcus; Harcos, Aba; Gomez, Christina; Stieber, Anne; Hennigs, André; von Au, Alexandra; Spratte, Julia; Rauch, Geraldine; Rom, Joachim; Schütz, Florian; Sohn, Christof; Golatta, Michael

2018-06-01

To determine the feasibility of a prototype device combining 3D-automated breast ultrasound (ABVS) and digital breast tomosynthesis in a single device to detect and characterize breast lesions. In this prospective feasibility study, the FUSION-X-US prototype was used to perform digital breast tomosynthesis and ABVS in 23 patients with an indication for tomosynthesis based on current guidelines after clinical examination and standard imaging. The ABVS and tomosynthesis images of the prototype were interpreted separately by two blinded experts. The study compares the detection and BI-RADS® scores of breast lesions using only the tomosynthesis and ABVS data from the FUSION-X-US prototype to the results of the complete diagnostic workup. Image acquisition and processing by the prototype was fast and accurate, with some limitations in ultrasound coverage and image quality. In the diagnostic workup, 29 solid lesions (23 benign, including three cases with microcalcifications, and six malignant lesions) were identified. Using the prototype, all malignant lesions were detected and classified as malignant or suspicious by both investigators. Solid breast lesions can be localized accurately and fast by the Fusion-X-US system. Technical improvements of the ultrasound image quality and ultrasound coverage are needed to further study this new device. The prototype combines tomosynthesis and automated 3D-ultrasound (ABVS) in one device. It allows accurate detection of malignant lesions, directly correlating tomosynthesis and ABVS data. The diagnostic evaluation of the prototype-acquired data was interpreter-independent. The prototype provides a time-efficient and technically reliable diagnostic procedure. The combination of tomosynthesis and ABVS is a promising diagnostic approach.

X-38 Experimental Aeroheating at Mach 10

NASA Technical Reports Server (NTRS)

Berry, Scott A.; Horvath, Thomas J.; Weilmuenster, K. James; Alter, Stephan J.; Merski, N. Ronald

2001-01-01

This report provides an update of the hypersonic aerothermodynamic wind tunnel test program conducted at the NASA Langley Research Center in support of the X-38 program. Global surface heat transfer distributions were measured on 0.0177 and 0.0236 scale models of the proposed X-38 configuration at Mach 10 in air. The parametrics that were investigated primarily include freestream unit Reynolds numbers of 0.6 to 2.2 million per foot and body flap deflections of 15, 20, and 25 deg for an angle-of-attack of 40 deg. The model-scale variance was tested to obtain laminar, transitional, and turbulent heating levels on the defected bodyflaps. In addition, a limited investigation of forced boundary layer transition through the use of discrete roughness elements was performed. Comparisons of the present experimental results to computational predictions and previous experimental data were conducted Laminar, transitional, and turbulent heating levels were observed on the deflected body flap, which compared favorably to the computational results and to the predicted heating based on the flight aerothermodynamic database.

Recovery and Rescue Teams Practice with Full-Size Crew Dragon Tr

NASA Image and Video Library

2017-06-07

Personnel from NASA, SpaceX and the U.S. Air Force have begun practicing recovery operations for the SpaceX Crew Dragon. Using a full-size model of the spacecraft that will take astronauts to the International Space Station, Air Force parajumpers practice helping astronauts out of the SpaceX Crew Dragon following a mission. In certain unusual recovery situations, SpaceX may need to work with Air Force for parajumpers to recover astronauts from the capsule following a water landing. The recovery trainer was recently lowered into the Indian River Lagoon near NASA’s Kennedy Space Center allowing Air Force pararescue and others to refine recovery procedures. SpaceX is developing the Crew Dragon in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the International Space Station.

Prototyping a Global Soft X-ray Imaging Instrument for Heliophysics, Planetary Science, and Astrophysics Science

NASA Technical Reports Server (NTRS)

Collier, Michael R.; Porter, F. Scott; Sibeck, David G.; Carter, Jenny A.; Chiao, Meng P.; Chornay, Dennis J.; Cravens, Thomas; Galeazzi, Massimiliano; Keller, John W.; Koutroumpa, Dimitra;

Prototyping a Global Soft X-Ray Imaging Instrument for Heliophysics, Planetary Science, and Astrophysics Science

NASA Technical Reports Server (NTRS)

Collier, M. R.; Porter, F. S.; Sibeck, D. G.; Carter, J. A.; Chiao, M. P.; Chornay, D. J.; Cravens, T.; Galeazzi, M.; Keller, J. W.; Koutroumpa, D.;

Hard x-ray characterization of a HEFT single-reflection prototype

NASA Astrophysics Data System (ADS)

Christensen, Finn E.; Craig, William W.; Hailey, Charles J.; Jimenez-Garate, Mario A.; Windt, David L.; Harrison, Fiona A.; Mao, Peter H.; Ziegler, Eric; Honkimaki, Veijo; Sanchez del Rio, Manuel; Freund, Andreas K.; Ohler, M.

2000-07-01

We have measured the hard X-ray reflectivity and imaging performance from depth graded W/Si multilayer coated mirror segments mounted in a single reflection cylindrical prototype for the hard X-ray telescopes to be flown on the High Energy Focusing Telescope (HEFT) balloon mission. Data have been obtained in the energy range from 18 - 170 keV at the European Synchrotron Radiation Facility and at the Danish Space Research Institute at 8 keV. The modeling of the reflectivity data demonstrate that the multilayer structure can be well described by the intended power law distribution of the bilayer thicknesses optimized for the telescope performance and we find that all the data is consistent with an interfacial width of 4.5 angstroms. We have also demonstrated that the required 5% uniformity of the coatings is obtained over the mirror surface and we have shown that it is feasible to use similar W/Si coatings for much higher energies than the nominal energy range of HEFT leading the way for designing Gamma-ray telescopes for future astronomical applications. Finally we have demonstrate 35 arcsecond Half Power Diameter imaging performance of the one bounce prototype throughout the energy range of the HEFT telescopes.

Prototype Software for Future Spaceflight Tested at Mars Desert Research Station

NASA Technical Reports Server (NTRS)

Clancey, William J.; Sierhuis, Maaretn; Alena, Rick; Dowding, John; Garry, Brent; Scott, Mike; Tompkins, Paul; vanHoof, Ron; Verma, Vandi

2006-01-01

NASA scientists in MDRS Crew 49 (April 23-May 7, 2006) field tested and significantly extended a prototype monitoring and advising system that integrates power system telemetry with a voice commanding interface. A distributed, wireless network of functionally specialized agents interacted with the crew to provide alerts (e.g., impending shut-down of inverter due to low battery voltage), access md interpret historical data, and display troubleshooting procedures. In practical application during two weeks, the system generated speech over loudspeakers and headsets lo alert the crew about the need to investigate power system problems. The prototype system adapts the Brahms/Mobile Agents toolkit to receive data from the OneMeter (Brand Electronics) electric metering system deployed by Crew 47. A computer on the upper deck was connected to loudspeakers, four others were paired with wireless (Bluetooth) headsets that enabled crew members to interact with their personal agents from anywhere in the hab. Voice commands and inquiries included: 1. What is the {battery | generator} {volts | amps | volts and amps}? 2. What is the status of the {generator | inverter | battery | solar panel}? 3. What is the hab{itat} {power usage | volts | voltage | amps | volts and amps}? 4. What was the average hab{itat} {amps | volts | voltage} since <#> {AM | PM)? 5. When did the {generator | batteries} change status? 6. Tell {me I | everyone} when{ ever} the generator goes offline. 7. Tell {me | | everyone} when the hab{itat} {amps | volts | voltage} {exceeds | drops brelow} <#>. 8. {Send | Take | Record} {a} voice note {(for | to} } {at }. This research demonstrates the principles of design in the context of use, investigating requirements through experimental use of prototype systems in an analog setting, and use of MDRS as a research facility for designing and implementing new systems.

STS-93 crew takes part in a Crew Equipment Interface Test

NASA Technical Reports Server (NTRS)

1998-01-01

In the Orbiter Processing Facility Bay 3, during the Crew Equipment Interface Test (CEIT), Mission Specialist Catherine G. Coleman (left) and Mission Commander Eileen M. Collins (right) check equipment that will fly on mission STS-93. The STS-93 mission will deploy the Advanced X-ray Astrophysics Facility (AXAF) which comprises three major elements: the spacecraft, the telescope, and the science instrument module (SIM). AXAF will allow scientists from around the world to obtain unprecedented X- ray images of a variety of high-energy objects to help understand the structure and evolution of the universe. Collins is the first woman to serve as a shuttle mission commander. The other STS-93 crew members are Pilot Jeffrey S. Ashby, Mission Specialist Steven A. Hawley and Mission Specialist Michel Tognini of France. Targeted date for the launch of STS-93 is March 18, 1999.

Methodology for Prototyping Increased Levels of Automation for Spacecraft Rendezvous Functions

NASA Technical Reports Server (NTRS)

Hart, Jeremy J.; Valasek, John

2007-01-01

The Crew Exploration Vehicle necessitates higher levels of automation than previous NASA vehicles, due to program requirements for automation, including Automated Rendezvous and Docking. Studies of spacecraft development often point to the locus of decision-making authority between humans and computers (i.e. automation) as a prime driver for cost, safety, and mission success. Therefore, a critical component in the Crew Exploration Vehicle development is the determination of the correct level of automation. To identify the appropriate levels of automation and autonomy to design into a human space flight vehicle, NASA has created the Function-specific Level of Autonomy and Automation Tool. This paper develops a methodology for prototyping increased levels of automation for spacecraft rendezvous functions. This methodology is used to evaluate the accuracy of the Function-specific Level of Autonomy and Automation Tool specified levels of automation, via prototyping. Spacecraft rendezvous planning tasks are selected and then prototyped in Matlab using Fuzzy Logic techniques and existing Space Shuttle rendezvous trajectory algorithms.

Microgravity Investigation of Crew Reactions in 0-G (MICR0-G): Ground-Based Development Effort

NASA Technical Reports Server (NTRS)

Newman, Dava J.

2002-01-01

This report describes the technology development of an advanced load sensor ground-based prototype and details the preliminary tests in microgravity during parabolic flights. The research effort is entitled, the Microgravity Investigation and Crew Reactions in 0-G (MICR0-G), a ground-based research effort funded by the National Aeronautics and Space Administration (NASA). The MICR0-G project was a follow-on to the Enhanced Dynamic Load Sensors (EDLS) spaceflight experiment flown on the Russian Space Station Mir. The technology development of the advanced load sensor prototype has been carried out by the Massachusetts Institute of Technology (MIT), with collaboration from Politecnico di Milano University and the Italian Space Agency (ASI). The key hardware of the advanced sensor prototype is a set of two types of load sensors - a hand-hold and foot restraints - similar in appearance to the mobility aids found in the Space Shuttle orbiter to assist the crew in moving inside the spacecraft, but able to measure the applied forces and moments about the x-, y-, and z- axes. The aim of Chapter 1 is to give a brief overview of the report contents. The first section summarizes the previous research efforts on astronaut-induced loads in microgravity. The second section provides information on the MICR0-G research project and the technology development work conducted at MIT. Section 1.3 details the motivation for designing a new generation of load sensors and describes the main enhancements and contributions of the MICR0-G advanced load sensors system compared to the EDLS system. Finally, the last section presents the outline of the report.

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency is seen in quarantine, behind glass, during the final press conference held a day ahead of his launch with fellow crew mates, Expedition 38 Soyuz Commander Mikhail Tyurin of Roscosmos, and, Flight Engineer Rick Mastracchio of NASA, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

NASA astronauts and industry experts check out the crew accommod

NASA Image and Video Library

2012-01-30

HAWTHORNE, Calif. -- NASA astronauts and industry experts check out the crew accommodations in the Dragon spacecraft under development by Space Exploration Technologies SpaceX of Hawthorne, Calif., for the agency's Commercial Crew Program. On top, from left, are NASA Crew Survival Engineering Team Lead Dustin Gohmert, NASA astronauts Tony Antonelli and Lee Archambault, and SpaceX Mission Operations Engineer Laura Crabtree. On bottom, from left, are SpaceX Thermal Engineer Brenda Hernandez and NASA astronauts Rex Walheim and Tim Kopra. In 2011, NASA selected SpaceX during Commercial Crew Development Round 2 CCDev2) activities to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also are maturing launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, The Boeing Co., Excalibur Almaz Inc., Blue Origin, Sierra Nevada, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Space Exploration Technologies

Cold Test and Performance Evaluation of Prototype Cryoline-X

NASA Astrophysics Data System (ADS)

Shah, N.; Choukekar, K.; Kapoor, H.; Muralidhara, S.; Garg, A.; Kumar, U.; Jadon, M.; Dash, B.; Bhattachrya, R.; Badgujar, S.; Billot, V.; Bravais, P.; Cadeau, P.

2017-12-01

The multi-process pipe vacuum jacketed cryolines for the ITER project are probably world’s most complex cryolines in terms of layout, load cases, quality, safety and regulatory requirements. As a risk mitigation plan, design, manufacturing and testing of prototype cryoline (PTCL) was planned before the approval of final design of ITER cryolines. The 29 meter long PTCL consist of 6 process pipes encased by thermal shield inside Outer Vacuum Jacket of DN 600 size and carries cold helium at 4.5 K and 80 K. The global heat load limit was defined as 1.2 W/m at 4.5 K and 4.5 W/m at 80 K. The PTCL-X (PTCL for Group-X cryolines) was specified in detail by ITER-India and designed as well as manufactured by Air Liquide. PTCL-X was installed and tested at cryogenic temperature at ITER-India Cryogenic Laboratory in 2016. The heat load at 4.5 K and 80 K, estimated using enthalpy difference method, was found to be approximately 0.8 W/m at 4.5 K, 4.2 W/m at 80 K, which is well within the defined limits. Thermal shield temperature profile was also found to be satisfactory. Paper summarizes the cold test results of PTCL-X

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

Dryden Experimental Fabrication Shop's Andy Blua and Jeff Doughty make sure the new pylon for the X-38 fits precisely during a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California in 1997. The 1,200-pound steel pylon, fabricated at Dryden, was an 'adapter' to allow the X-38 research vehicle to be carried aloft and launched from the bomber. The X-38 was a designed as a technology demonstrator to help develop an emergency Crew Return Vehicle for the International Space Station. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research

X-38 V-132 Free Flight 2 (This is a video tape)

NASA Technical Reports Server (NTRS)

Bordano, Aldo J.

2000-01-01

Mr. Aldo Bordano will be presenting details of some of the JSC flight mechanics involvement in the X-38 testing program. Focus shall be on the parafoil system with regards its testing, performance analysis, and GN&C. An excellent example of a recent flight test at Dryden Flight Research Center shall be shown which portrays the system characteristics, sequencing, performance, and testing techniques. The intent is to inform the scientific and engineering communities about the developments in the X-38 parafoil program, as well as invite feedback on potential improvements in testing or systems.

Commerical Crew Astronauts Visit Launch Complex 39A

NASA Image and Video Library

2018-03-27

Commercial Crew Program astronauts, from the left, Suni Williams, Eric Boe, Bob Behnken and Doug Hurley take in the view from the top of Launch Complex 39A at Kennedy Space Center. The astronauts toured the pad for an up-close look at modifications that are in work for the SpaceX Crew Dragon flight tests. Tower modifications included l removal of the space shuttle era rotating service structure. Future integration of the crew access arm will allow for safe crew entry for launch and exit from the spacecraft in the unlikely event a pad abort is required.

Commerical Crew Astronauts Visit Launch Complex 39A

NASA Image and Video Library

2018-03-27

Commercial Crew Program astronauts, from the left Doug Hurley, Eric Boe, Bob Behnken and Suni Williams, pose just outside Launch Complex 39A at NASA's Kennedy Space Center in Florida. The astronauts toured the pad for an up-close look at modifications that are in work for the SpaceX Crew Dragon flight tests. The tower modifications included removal of the space shuttle era rotating service structure. Future integration of the crew access arm will allow for safe crew entry for launch and exit from the spacecraft in the unlikely event a pad abort is required.

A preclinical Talbot-Lau prototype for x-ray dark-field imaging of human-sized objects.

PubMed

Hauke, C; Bartl, P; Leghissa, M; Ritschl, L; Sutter, S M; Weber, T; Zeidler, J; Freudenberger, J; Mertelmeier, T; Radicke, M; Michel, T; Anton, G; Meinel, F G; Baehr, A; Auweter, S; Bondesson, D; Gaass, T; Dinkel, J; Reiser, M; Hellbach, K

2018-06-01

Talbot-Lau x-ray interferometry provides information about the scattering and refractive properties of an object - in addition to the object's attenuation features. Until recently, this method was ineligible for imaging human-sized objects as it is challenging to adapt Talbot-Lau interferometers (TLIs) to the relevant x-ray energy ranges. In this work, we present a preclinical Talbot-Lau prototype capable of imaging human-sized objects with proper image quality at clinically acceptable dose levels. The TLI is designed to match a setup of clinical relevance as closely as possible. The system provides a scan range of 120 × 30 cm 2 by using a scanning beam geometry. Its ultimate load is 100 kg. High aspect ratios and fine grid periods of the gratings ensure a reasonable setup length and clinically relevant image quality. The system is installed in a university hospital and is, therefore, exposed to the external influences of a clinical environment. To demonstrate the system's capabilities, a full-body scan of a euthanized pig was performed. In addition, freshly excised porcine lungs with an extrinsically provoked pneumothorax were mounted into a human thorax phantom and examined with the prototype. Both examination sequences resulted in clinically relevant image quality - even in the case of a skin entrance air kerma of only 0.3 mGy which is in the range of human thoracic imaging. The presented case of a pneumothorax and a reader study showed that the prototype's dark-field images provide added value for pulmonary diagnosis. We demonstrated that a dedicated design of a Talbot-Lau interferometer can be applied to medical imaging by constructing a preclinical Talbot-Lau prototype. We experienced that the system is feasible for imaging human-sized objects and the phase-stepping approach is suitable for clinical practice. Hence, we conclude that Talbot-Lau x-ray imaging has potential for clinical use and enhances the diagnostic power of medical x-ray imaging. �

Multipurpose Crew Restraints for Long Duration Space Flights

NASA Technical Reports Server (NTRS)

Whitmore, Mihriban; Baggerman, Susan; Ortiz, M. R.; Hua, L.; Sinnott, P.; Webb, L.

2004-01-01

With permanent human presence onboard the International Space Station (ISS), a crew will be living and working in microgravity, interfacing with their physical environment. Without optimum restraints and mobility aids (R&MA' s), the crewmembers may be handicapped for perfonning some of the on-orbit tasks. In addition to weightlessness, the confined nature of a spacecraft environment results in ergonomic challenges such as limited visibility and access to the activity area and may cause prolonged periods of unnatural postures. Thus, determining the right set of human factors requirements and providing an ergonomically designed environment are crucial to astronauts' well-being and productivity. The purpose of this project is to develop requirements and guidelines, and conceptual designs, for an ergonomically designed multi-purpose crew restraint. In order to achieve this goal, the project would involve development of functional and human factors requirements, design concept prototype development, analytical and computer modeling evaluations of concepts, two sets of micro gravity evaluations and preparation of an implementation plan. It is anticipated that developing functional and design requirements for a multi-purpose restraint would facilitate development of ergonomically designed restraints to accommodate the off-nominal but repetitive tasks, and minimize the performance degradation due to lack of optimum setup for onboard task performance. In addition, development of an ergonomically designed restraint concept prototype would allow verification and validation of the requirements defined. To date, we have identified "unique" tasks and areas of need, determine characteristics of "ideal" restraints, and solicit ideas for restraint and mobility aid concepts. Focus group meetings with representatives from training, safety, crew, human factors, engineering, payload developers, and analog environment representatives were key to assist in the development of a restraint

Expedition 38 Crewmembers during Transfer of Command Ceremony

NASA Image and Video Library

2014-03-09

ISS038-E-068903 (9 March 2014) --- The new commander of the current crew on the International Space Station (Expedition 39) and the Expedition 38/39 flight engineers wave inside the Kibo laboratory. Their waving may very well be a symbolic farewell to the Expedition 38 crew members (out of frame) who are on the eve of their departure day from the orbital outpost. Expedition 39 Commander Koichi Wakata (center) of the Japanese Aerospace Exploration Agency (JAXA) is joined here by Flight Engineers Rick Mastracchio (right) of NASA and cosmonaut Mikhail Tyurin of the Russian Federal Space Agency (Roscosmos).

Kinetics and thermal stability of the Ni62Nb38- x Ta x ( x=5, 10, 15, 20 and 25) bulk metallic glasses

NASA Astrophysics Data System (ADS)

He, MengKe; Zhang, Yi; Xia, Lei; Yu, Peng

2017-07-01

We studied thermal stability and its relationship to the glass-forming ability (GFA) of the Ni62Nb38- x Ta x ( x=5, 10, 15, 20, 25) bulk metallic glasses (BMG) from a kinetic point of view. By fitting the heating-rate dependence of glass transition temperature ( T g onset) and crystallization temperatures ( T x onset and T x peak) of the Ni62Nb38- x Ta x BMG using the Vogel-Fulcher-Tammann (VFT) equation, we obtained the ideal glass transition and crystallization temperatures ( T g 0 and T x 0) and the fragility parameter ( m), and also constructed continuous heating transition (CHT) diagrams for crystallization of the BMG. The CHT diagrams of the BMG indicate enhanced thermal stability by Ta addition; the T g 0 as well as the T x 0 also illustrates this improved stability limit. The compositional dependence of m, which agrees well with that of the reduced glass-transition temperature, indicates a strong correlation between liquid fragility and glass-forming ability in the present alloy system. These results provide new evidence for understanding thermal stability, liquid fragility, and GFA in BMG.

Passive Thrust Oscillation Mitigation for the CEV Crew Pallet System

NASA Technical Reports Server (NTRS)

Sammons, Matthew; Powell, Cory; Pellicciotti, Joseph; Buehrle, Ralph; Johnson, Keith

2012-01-01

The Crew Exploration Vehicle (CEV) was intended to be the next-generation human spacecraft for the Constellation Program. The CEV Isolator Strut mechanism was designed to mitigate loads imparted to the CEV crew caused by the Thrust Oscillation (TO) phenomenon of the proposed Ares I Launch Vehicle (LV). The Isolator Strut was also designed to be compatible with Launch Abort (LA) contingencies and landing scenarios. Prototype struts were designed, built, and tested in component, sub-system, and system-level testing. The design of the strut, the results of the tests, and the conclusions and lessons learned from the program will be explored in this paper.

STS-93 Crew Training

NASA Technical Reports Server (NTRS)

1999-01-01

Live footage of the STS-93 crewmembers shows Commander Eileen M. Collins, Pilot Jeffrey S. Ashby, Mission Specialists Steven A. Hawley, Catherine G. Coleman, and Michel Tognini going through various training activities. These activities include Bail Out Training NBL, Emergency Egress Training, Earth Observations Classroom Training, Simulator Training, T-38 Departure from Ellington Field, Chandra Deploy Training, SAREX Shuttle Amateur Radio Experiment, CCT Bail Out Crew Compartment Training, and Southwest Research Ultraviolet Imaging System (SWUIS) Training.

ISS Expedition 42 / 43 Crew Training Resource Reel (JSC-2641)

NASA Image and Video Library

2014-11-14

Media resource reel of ISS Expedition 42 / 43 Crew training activities. Includes footage of crew photo shots with Samantha Cristoforetti, Anton Shkaplerov and Terry Virts; Routine shots with Virts, ISS Expedition 43 crewmember Scott Kelly, Cristoforetti, ISS Expedition 41 / 42 crewmember Barry Wilmore; and Shklaplerov; T-38 Operations with Virts; Routine operations with Cristoforetti, Shkaplerov and Virts; Neutral Buoyancy Lab (NBL) with Cristoforetti and Kelly; and Emergency Scenatios with Virts, Cristoforetti and Shkaplerov.

Flight crew interface aspects of forward-looking airborne windshear detection systems

NASA Technical Reports Server (NTRS)

Anderson, Charles D.; Carbaugh, David C.

1993-01-01

The goal of this research effort was to conduct analyses and research which could provide guidelines for design of the crew interface of an integrated windshear system. Addressed were HF issues, crew/system requirements, candidate display formats, alerting criteria, and crew procedures. A survey identified five flight management issues as top priority: missed alert acceptability; avoidance distance needed; false alert acceptability; nuisance rate acceptability; and crew procedures. Results of a simulation study indicated that the warning time for a look-ahead alert needs to be between 11 and 36 seconds (target of 23 seconds) before the reactive system triggers in order to be effective. Pilots considered the standard go-around maneuver most appropriate for look-ahead alerts, and the escape maneuvers used did not require lateral turns. Prototype display formats were reviewed or developed for alerting the crew; providing guidance to avoid or escape windshear; and status displays to provide windshear situational awareness. The three alerting levels now in use were considered appropriate, with a fourth (time-critical) level as a possible addition, although many reviewers felt only two levels of alerting were needed. Another survey gathered expert opinion on what crew procedures and alerting criteria should be used for look-ahead, or integrated, windshear systems, with a wide diversity of opinion in these areas.

Design of a prototype tri-electrode ion-chamber for megavoltage X-ray imaging

NASA Astrophysics Data System (ADS)

Samant, Sanjiv S.; Gopal, Arun; Jain, Jinesh; Xia, Junyi; DiBianca, Frank A.

2007-04-01

High-energy (megavoltage) X-ray imaging is widely used in industry (e.g., aerospace, construction, material sciences) as well as in health care (radiation therapy). One of the fundamental problems with megavoltage imaging is poor contrast and spatial resolution in the detected images due to the dominance of Compton scattering at megavoltage X-ray energies. Therefore, although megavoltage X-rays can be used to image highly attenuating objects that cannot be imaged at kilovoltage energies, the former does not provide the high image quality that is associated with the latter. A high contrast and spatial resolution detector for high-energy X-ray fields called the kinestatic charge detector (KCD) is presented here. The KCD is a tri-electrode ion-chamber based on highly pressurized noble gas. The KCD operates in conjunction with a strip-collimated X-ray beam (for high scatter rejection) to scan across the imaging field. Its thick detector design and unique operating principle provides enhanced charge signal integration for high quality imaging (quantum efficiency ˜50%) despite the unfavorable implications of high-energy X-ray interactions on image quality. The proposed design for a large-field prototype KCD includes a cylindrical pressure chamber along with 576 signal-collecting electrodes capable of resolving at 2 mm -1. The collecting electrodes are routed out of the chamber through the flat end-cap, thereby optimizing the mechanical strength of the chamber. This article highlights the simplified design of the chamber using minimal components for simple assembly. In addition, fundamental imaging measurements and estimates of ion recombination that were performed on a proof-of-principle test chamber are presented. The imaging performance of the prototype KCD was found to be an order-of-magnitude greater than commercial phosphor screen based flat-panel systems, demonstrating the potential for high-quality megavoltage imaging for a variety of industrial applications.

Next Generation Spacecraft, Crew Exploration Vehicle

NASA Technical Reports Server (NTRS)

2004-01-01

This special bibliography includes research on reusable launch vehicles, aerospace planes, shuttle replacement, crew/cargo transfer vehicle, related X-craft, orbital space plane, and next generation launch technology.

Oxidation and reduction behaviors of a prototypic MgO-PuO2-x inert matrix fuel

NASA Astrophysics Data System (ADS)

Miwa, Shuhei; Osaka, Masahiko

2017-04-01

Oxidation and reduction behaviors of prototypic MgO-based inert matrix fuels (IMFs) containing PuO2-x were experimentally investigated by means of thermogravimetry. The oxidation and reduction kinetics of the MgO-PuO2-x specimen were determined. The oxidation and reduction rates of the MgO-PuO2-x were found to be low compared with those of PuO2-x. It is note that the changes in O/Pu ratios of MgO-PuO2-x from stoichiometry were smaller than those of PuO2-x at high oxygen partial pressure.

Preliminary testing of a prototype portable X-ray fluorescence spectrometer

NASA Technical Reports Server (NTRS)

Patten, L. L.; Anderson, N. B.; Stevenson, J. J.

1982-01-01

A portable X-ray fluorescence spectrometer for use as an analyzer in mineral resource investigative work was built and tested. The prototype battery powered spectrometer, measuring 11 by 12 by 5 inches and weighing only about 15 pounds, was designed specifically for field use. The spectrometer has two gas proportional counters and two radioactive sources, Cd (10a) and Fe (55). Preliminary field and laboratory tests on rock specimens and rock pulps have demonstrated the capability of the spectrometer to detect 33 elements to date. Characteristics of the system present some limitations, however, and further improvements are recommended.

Expedition 38 Crewmembers during Transfer of Command Ceremony

NASA Image and Video Library

2014-03-09

ISS038-E-068899 (9 March 2014) --- The new commander of the current crew on the International Space Station (Expedition 39) and the Expedition 38/39 flight engineers exchange handshakes inside the Kibo laboratory. Their celebration may very well be a follow-up gesture following the transfer of command ceremony and a symbolic farewell to the Expedition 38 crew members (out of frame) who are on the eve of their departure from the orbital outpost. Expedition 39 Commander Koichi Wakata (center) of the Japanese Aerospace Exploration Agency (JAXA) is joined here by Flight Engineers Rick Mastracchio (right) of NASA and cosmonaut Mikhail Tyurin of the Russian Federal Space Agency (Roscosmos).

Commercial crew astronauts on This Week @NASA – July 10, 2015

NASA Image and Video Library

2015-07-10

NASA has selected four astronauts to work closely with two U.S. commercial companies that will return human spaceflight launches to Florida’s Space Coast. NASA named veteran astronauts and experienced test pilots Robert Behnken, Eric Boe, Douglas Hurley and Sunita Williams to work closely with Boeing and SpaceX. NASA contracted with Boeing and SpaceX to develop crew transportation systems and provide crew transportation services to and from the International Space Station. The agency will select the commercial crew astronauts from this group of four for the first test, which is scheduled for 2017. Also, NASA’s newest astronauts, New Horizons still on track, Benefits for Humanity, Cargo ship arrives at space station, Training continues for next ISS crew and more!

International Space Station USOS Crew Quarters Development

NASA Technical Reports Server (NTRS)

Broyan, James Lee, Jr.; Borrego, Melissa Ann; Bahr, Juergen F.

2008-01-01

The International Space Station (ISS) United States Operational Segment (USOS) currently provides a Temporary Sleep Station (TeSS) as crew quarters for one crewmember in the Laboratory Module. The Russian Segment provides permanent crew quarters (Kayutas) for two crewmembers in the Service Module. The TeSS provides limited electrical, communication, and ventilation functionality. A new permanent rack sized USOS ISS Crew Quarters (CQ) is being developed. Up to four CQs can be installed into the Node 2 element to increase the ISS crewmember size to six. The new CQs will provide private crewmember space with enhanced acoustic noise mitigation, integrated radiation reduction material, controllable airflow, communication equipment, redundant electrical systems, and redundant caution and warning systems. The rack sized CQ is a system with multiple crewmember restraints, adjustable lighting, controllable ventilation, and interfaces that allow each crewmember to personalize their CQ workspace. Providing an acoustically quiet and visually isolated environment, while ensuring crewmember safety, is critical for obtaining crewmember rest and comfort to enable long term crewmember performance. The numerous human factor, engineering, and program considerations during the concept, design, and prototyping are outlined in the paper.

Illuminance and luminance distributions of a prototype ambient illumination system for Space Station Freedom

NASA Technical Reports Server (NTRS)

Mullican, R. C.; Hayes, B. C.

1991-01-01

Preliminary results of research conducted in the late 1970's indicate that perceptual qualities of an enclosure can be influenced by the distribution of illumination within the enclosure. Subjective impressions such as spaciousness, perceptual clarity, and relaxation or tenseness, among others, appear to be related to different combinations of surface luminance. A prototype indirect ambient illumination system was developed which will allow crew members to alter surface luminance distributions within an enclosed module, thus modifying perceptual cues to match crew preferences. A traditional lensed direct lighting system was compared to the prototype utilizing the full-scale mockup of Space Station Freedom developed by Marshall Space Flight Center. The direct lensed system was installed in the habitation module with the indirect prototype deployed in the U.S. laboratory module. Analysis centered on the illuminance and luminance distributions resultant from these systems and the implications of various luminaire spacing options. All test configurations were evaluated for compliance with NASA Standard 3000, Man-System Integration Standards.

Commercial Crew Vehicle Ascent Abort Simulation and Analysis

NASA Technical Reports Server (NTRS)

Gnam, Christopher

2017-01-01

SpaceX and Boeing have been selected to develop and operate crew vehicles to transport astronauts to and from the International Space Station. Their design work is to be analyzed to ensure that they are meeting all of the safety and operational requirements put forth by NASA. Throughout my time here, I worked familiarized myself with the SpaceX Dragon Abort system, as well as the NASA Human-Systems Integration Requirements (HSIR). This included understanding the different abort scenarios, and how each one could potentially impact the astronaut crew. In addition, I familiarized myself with the simulation developed my NASA to test and analyze the Guidance Navigation and Control (GN&C) systems developed by SpaceX and Boeing.

A failure diagnosis and impact assessment prototype for Space Station Freedom

NASA Technical Reports Server (NTRS)

Baker, Carolyn G.; Marsh, Christopher A.

1991-01-01

NASA is investigating the use of advanced automation to enhance crew productivity for Space Station Freedom in numerous areas, one being failure management. A prototype is described that diagnoses failure sources and assesses the future impacts of those failures on other Freedom entities.

Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

NASA Technical Reports Server (NTRS)

1997-01-01

Andy Blua and Jeff Doughty of Dryden's Experimental Fabrication Shop, along with B-52 Crew Chief Dan Bains and assistant Mark Thompson, all eye the new X-38 pylon during a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California. The fit-check was the first time the 1,200-pound steel pylon, which was fabricated at Dryden, was mated to the B-52. The pylon served as an 'adapter' that allowed the X-38 to be attached to the B-52's wing. Earlier flight research vehicles had used the X-15 pylon for attachment to and launch from the B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the Hi

NASA's B-52 takes the X-38 aloft for the seventh free flight of the program, July 10, 2001

NASA Image and Video Library

2001-07-10

The X-38, mounted beneath the right wing of NASA's B-52, climbed from the runway at Edwards Air Force Base for the seventh free flight test of the X-38, July 10, 2001. The X-38 was released at 37,500 feet and completed a thirteen minute glide flight to a landing on Rogers Dry Lake.

NASA's B-52 takes the X-38 aloft for the seventh free flight of the program, July 10, 2001

NASA Technical Reports Server (NTRS)

2001-01-01

The X-38, mounted beneath the right wing of NASA's B-52, climbed from the runway at Edwards Air Force Base for the seventh free flight test of the X-38, July 10, 2001. The X-38 was released at 37,500 feet and completed a thirteen minute glide flight to a landing on Rogers Dry Lake.

Commercial Crew Development Program Overview

NASA Technical Reports Server (NTRS)

Russell, Richard W.

2011-01-01

NASA's Commercial Crew Development Program is designed to stimulate efforts within the private sector that will aid in the development and demonstration of safe, reliable, and cost-effective space transportation capabilities. With the goal of delivery cargo and eventually crew to Low Earth Orbit (LEO) and the International Space Station (ISS) the program is designed to foster the development of new spacecraft and launch vehicles in the commercial sector. Through Space Act Agreements (SAAs) in 2011 NASA provided $50M of funding to four partners; Blue Origin, The Boeing Company, Sierra Nevada Corporation, and SpaceX. Additional, NASA has signed two unfunded SAAs with ATK and United Space Alliance. This paper will give a brief summary of these SAAs. Additionally, a brief overview will be provided of the released version of the Commercial Crew Development Program plans and requirements documents.

SpaceX Spacesuit

NASA Image and Video Library

2017-08-22

The SpaceX spacesuit that will be worn by astronauts aboard its Crew Dragon spacecraft (in the background) during missions to and from the International Space Station. SpaceX is developing its Crew Dragon spacecraft and Falcon 9 rocket in partnership with NASA’s Commercial Crew Program to carry astronauts to and from the space station.

The performance of a prototype device designed to evaluate general quality parameters of X-ray equipment

NASA Astrophysics Data System (ADS)

Murata, C. H.; Fernandes, D. C.; Lavínia, N. C.; Caldas, L. V. E.; Pires, S. R.; Medeiros, R. B.

2014-02-01

The performance of radiological equipment can be assessed using non-invasive methods and portable instruments that can analyze an X-ray beam with just one exposure. These instruments use either an ionization chamber or a state solid detector (SSD) to evaluate X-ray beam parameters. In Brazil, no such instruments are currently being manufactured; consequently, these instruments come at a higher cost to users due to importation taxes. Additionally, quality control tests are time consuming and impose a high workload on the X-ray tubes when evaluating their performance parameters. The assessment of some parameters, such as the half-value layer (HVL), requires several exposures; however, this can be reduced by using a SSD that requires only a single exposure. One such SSD uses photodiodes designed for high X-ray sensitivity without the use of scintillation crystals. This sensitivity allows one electron-hole pair to be created per 3.63 eV of incident energy, resulting in extremely high and stable quantum efficiencies. These silicon photodiodes operate by absorbing photons and generating a flow of current that is proportional to the incident power. The aim of this study was to show the response of the solid sensor PIN RD100A detector in a multifunctional X-ray analysis system that is designed to evaluate the average peak voltage (kVp), exposure time, and HVL of radiological equipment. For this purpose, a prototype board that uses four SSDs was developed to measure kVp, exposure time, and HVL using a single exposure. The reproducibility and accuracy of the results were compared to that of different X-ray beam analysis instruments. The kVp reproducibility and accuracy results were 2% and 3%, respectively; the exposure time reproducibility and accuracy results were 2% and 1%, respectively; and the HVL accuracy was ±2%. The prototype's methodology was able to calculate these parameters with appropriate reproducibility and accuracy. Therefore, the prototype can be considered

Commerical Crew Astronaut Suni Williams in SpaceX's Spacesuit

NASA Image and Video Library

2018-05-17

NASA Astronaut Suni Williams, fully suited in SpaceX’s spacesuit, interfaces with the display inside a mock-up of the Crew Dragon spacecraft in Hawthorne, California, during a testing exercise on Tuesday, April 3, 2018.

Spacecraft crew procedures from paper to computers

NASA Technical Reports Server (NTRS)

Oneal, Michael; Manahan, Meera

1991-01-01

Described here is a research project that uses human factors and computer systems knowledge to explore and help guide the design and creation of an effective Human-Computer Interface (HCI) for spacecraft crew procedures. By having a computer system behind the user interface, it is possible to have increased procedure automation, related system monitoring, and personalized annotation and help facilities. The research project includes the development of computer-based procedure system HCI prototypes and a testbed for experiments that measure the effectiveness of HCI alternatives in order to make design recommendations. The testbed will include a system for procedure authoring, editing, training, and execution. Progress on developing HCI prototypes for a middeck experiment performed on Space Shuttle Mission STS-34 and for upcoming medical experiments are discussed. The status of the experimental testbed is also discussed.

X-38 Bolt Retractor Subsystem Separation Demonstration

NASA Technical Reports Server (NTRS)

Rugless, Fedoria (Editor); Johnston, A. S.; Ahmed, R.; Garrison, J. C.; Gaines, J. L.; Waggoner, J. D.

2002-01-01

The Flight Robotics Laboratory FRL successfully demonstrated the X-38 bolt retractor subsystem (BRS). The BRS design was proven safe by testing in the Pyrotechnic Shock Facility (PSI) before being demonstrated in the FRL. This Technical Memorandum describes the BRS, FRL, PSF, and interface hardware. Bolt retraction time, spacecraft simulator acceleration, and a force analysis are also presented. The purpose of the demonstration was to show the FRL capability for spacecraft separation testing using pyrotechnics. Although a formal test was not performed due to schedule and budget constraints, the data will show that the BRS is a successful design concept and the FRL is suitable for future separation tests.

Comparative Field Tests of Pressurised Rover Prototypes

NASA Astrophysics Data System (ADS)

Mann, G. A.; Wood, N. B.; Clarke, J. D.; Piechochinski, S.; Bamsey, M.; Laing, J. H.

The conceptual designs, interior layouts and operational performances of three pressurised rover prototypes - Aonia, ARES and Everest - were field tested during a recent simulation at the Mars Desert Research Station in Utah. A human factors experiment, in which the same crew of three executed the same simulated science mission in each of the three vehicles, yielded comparative data on the capacity of each vehicle to safely and comfortably carry explorers away from the main base, enter and exit the vehicle in spacesuits, perform science tasks in the field, and manage geological and biological samples. As well as offering recommendations for design improvements for specific vehicles, the results suggest that a conventional Sports Utility Vehicle (SUV) would not be suitable for analog field work; that a pressurised docking tunnel to the main habitat is essential; that better provisions for spacesuit storage are required; and that a crew consisting of one driver/navigator and two field science crew specialists may be optimal. From a field operations viewpoint, a recurring conflict between rover and habitat crews at the time of return to the habitat was observed. An analysis of these incidents leads to proposed refinements of operational protocols, specific crew training for rover returns and again points to the need for a pressurised docking tunnel. Sound field testing, circulating of results, and building the lessons learned into new vehicles is advocated as a way of producing ever higher fidelity rover analogues.

Crew Training - Apollo X (Apollo Mission Simulator [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32788 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

CREW TRAINING - APOLLO X (APOLLO MISSION SIMULATOR [AMS]) - KSC

NASA Image and Video Library

1969-04-05

S69-32789 (3 April 1969) --- Astronaut John W. Young, Apollo 10 prime crew command module pilot, participates in simulation activity in the Apollo Mission Simulator at the Kennedy Space Center during preparations for his scheduled lunar orbit mission.

Prototyping phase of the high heat flux scraper element of Wendelstein 7-X

DOE PAGES

Boscary, Jean; Greuner, Henri; Ehrke, G.; ...

2016-03-24

The water-cooled high heat flux scraper element aims to reduce excessive heat loads on the target element ends of the actively cooled divertor of Wendelstein 7-X. Its purpose is to intercept some of the plasma fluxes both upstream and downstream before they reach the divertor surface. The scraper element has 24 identical plasma facing components (PFCs) divided into 6 modules. One module has 4 PFCs hydraulically connected in series by 2 water boxes. A PFC, 247 mm long and 28 mm wide, has 13 monoblocks made of CFC NB31 bonded by hot isostatic pressing onto a CuCrZr cooling tube equippedmore » with a copper twisted tape. 4 full-scale prototypes of PFCs have been successfully tested in the GLADIS facility up to 20 MW/m 2. The difference observed between measured and calculated surface temperatures is probably due to the inhomogeneity of CFC properties. The design of the water box prototypes has been detailed to allow the junction between the cooling pipe of the PFCs and the water boxes by internal orbital welding. In conclusion, the prototypes are presently under fabrication.« less

Novel Applications of Rapid Prototyping in Gamma-ray and X-ray Imaging

PubMed Central

Miller, Brian W.; Moore, Jared W.; Gehm, Michael E.; Furenlid, Lars R.; Barrett, Harrison H.

2010-01-01

Advances in 3D rapid-prototyping printers, 3D modeling software, and casting techniques allow for the fabrication of cost-effective, custom components in gamma-ray and x-ray imaging systems. Applications extend to new fabrication methods for custom collimators, pinholes, calibration and resolution phantoms, mounting and shielding components, and imaging apertures. Details of the fabrication process for these components are presented, specifically the 3D printing process, cold casting with a tungsten epoxy, and lost-wax casting in platinum. PMID:22984341

Crew Training - Apollo X (Apollo Mission Simulator [AMS])

NASA Image and Video Library

1969-04-05

S69-32787 (3 April 1969) --- Two members of the Apollo 10 prime crew participate in simulation activity at the Kennedy Space Center during preparations for their scheduled lunar orbit mission. Astronaut Thomas P. Stafford, commander, is in the background; and in the foreground is astronaut Eugene A. Cernan, lunar module pilot. The two crewmen are in the Lunar Module Mission Simulator.

STS-26 crew arrives at KSC Shuttle Landing Facility (SLF)

NASA Technical Reports Server (NTRS)

1987-01-01

STS-26 Discovery, Orbiter Vehicle (OV) 103, crew arrives at Kennedy Space Center (KSC) Shuttle Landing Facility (SLF). The recently announced flight crew of the next space shuttle mission STS-26 stands in front of NASA T-38 aircraft. The STS-26 crew is making a motivational visit to KSC in order to talk to and meet the support teams that help launch the shuttle. From left to right are: Mission Specialist (MS) David C. Hilmers who flew on 51J; Pilot Richard O. Covey who flew on 51I; Commander Frederick H. Hauck who flew as commander on 51A and as pilot on STS-7; and MS George D. Nelson who flew on 41C and 61C.

X-38 on B-52 Wing Pylon - View from Observation Window

NASA Image and Video Library

1997-11-19

A unique, close-up view of the X-38 under the wing of NASA's B-52 mothership prior to launch of the lifting-body research vehicle. The photo was taken from the observation window of the B-52 bomber as it banked in flight.

High energy X-ray observations of the 38-second pulsar

NASA Technical Reports Server (NTRS)

Byrne, P. F.; Levine, A. M.; Bautz, M.; Howe, S. K.; Lang, F. L.; Primini, F. A.; Lewin, W. H. G.; Gruber, D. E.; Knight, F. K.; Nolan, P. L.

1981-01-01

The results of observations of the 38-second pulsar obtained at high X-ray energies (13-180 keV) with the UCSD/MIT instrument aboard HEAO 1 are reported. The results include a measurement of the source location, measurement of the pulse profile, and determination of the average intensity and spectrum during each of three time intervals spanning a baseline of 1 year. The total intensity of the pulsar is seen to vary on a 6-month time scale. The spectrum is hard but, like other X-ray pulsars, steepens at energies above 20 keV.

Prototype Conflict Alerting Logic for Free Flight

NASA Technical Reports Server (NTRS)

Yang, Lee C.; Kuchar, James K.

1997-01-01

This paper discusses the development of a prototype alerting system for a conceptual Free Flight environment. The concept assumes that datalink between aircraft is available and that conflicts are primarily resolved on the flight deck. Four alert stages are generated depending on the likelihood of a conflict. If the conflict is not resolved by the flight crews, Air Traffic Control is notified to take over separation authority. The alerting logic is based on probabilistic analysis through modeling of aircraft sensor and trajectory uncertainties. Monte Carlo simulations were used over a range of encounter situations to determine conflict probability. The four alert stages were then defined based on probability of conflict and on the number of avoidance maneuvers available to the flight crew. Preliminary results from numerical evaluations and from a piloted simulator study at NASA Ames Research Center are summarized.

Earth observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-11-24

ISS038-E-007756 (24 Nov. 2013) --- One of the Expedition 38 crew members aboard the Earth-orbiting International Space Station used an 800mm lens to record this nadir image of Key West, Florida on Nov. 24, 2013.

STS-71 Pilot Charles J. Precort arrival in T-38

NASA Technical Reports Server (NTRS)

1995-01-01

STS-71 Pilot Charles J. Precourt arrives at the KSC Shuttle Landing Facility in one of the T-38 aircraft traditionally flown by the astronaut corps. The seven STS-71 crew members flew into KSC from Johnson Space Center as final preparations are under way toward the scheduled liftoff on June 23 of the Space Shuttle Atlantis on the first mission to dock with the Russian Space Station Mir. KSC-95EC-870 - Mir 19 Flight Engineer Nikolai M. Budarin arrives at KSC Mir 19 Flight Engineer Nikolai M. Budarin hitches a ride with STS-71 Pilot Charles J. Precourt in a T-38. Budarin, Precourt and the rest of the STS-71 crew arrived at KSC's Shuttle Landing Facility the same day the countdown clock began ticking toward a scheduled liftoff on Friday, June 23. During the historic flight of the Space Shuttle Atlantis on STS- 71, the crew will perform the first U.S. docking with the Russian Space Station Mir. Budarin and Mir 19 Mission Commander Anatoly Solovyev will transfer to Mir during the flight, and the three crew members currently on Mir will return to Earth in the orbiter.

A failure recovery planning prototype for Space Station Freedom

NASA Technical Reports Server (NTRS)

Hammen, David G.; Kelly, Christine M.

1991-01-01

NASA is investigating the use of advanced automation to enhance crew productivity for Space Station Freedom in numerous areas, including failure management. A prototype is described that uses various advanced automation techniques to generate courses of action whose intents are to recover from a diagnosed failure, and to do so within the constraints levied by the failure and by Freedom's configuration and operating conditions.

Operational Prototype Development of a Global Aircraft Radiation Exposure Nowcast

NASA Astrophysics Data System (ADS)

Mertens, Christopher; Kress, Brian; Wiltberger, Michael; Tobiska, W. Kent; Bouwer, Dave

Galactic cosmic rays (GCR) and solar energetic particles (SEP) are the primary sources of human exposure to high linear energy transfer (LET) radiation in the atmosphere. High-LET radiation is effective at directly breaking DNA strands in biological tissue, or producing chemically active radicals in tissue that alter the cell function, both of which can lead to cancer or other adverse health effects. A prototype operational nowcast model of air-crew radiation exposure is currently under development and funded by NASA. The model predicts air-crew radiation exposure levels from both GCR and SEP that may accompany solar storms. The new air-crew radiation exposure model is called the Nowcast of Atmospheric Ionizing Radiation for Aviation Safety (NAIRAS) model. NAIRAS will provide global, data-driven, real-time exposure predictions of biologically harmful radiation at aviation altitudes. Observations are utilized from the ground (neutron monitors), from the atmosphere (the NCEP Global Forecast System), and from space (NASA/ACE and NOAA/GOES). Atmospheric observations characterize the overhead mass shielding and the ground-and space-based observations provide boundary conditions on the incident GCR and SEP particle flux distributions for transport and dosimetry calculations. Radiation exposure rates are calculated using the NASA physics-based HZETRN (High Charge (Z) and Energy TRaNsport) code. An overview of the NAIRAS model is given: the concept, design, prototype implementation status, data access, and example results. Issues encountered thus far and known and/or anticipated hurdles to research to operations transition are also discussed.

Fast prototyping of high-aspect ratio, high-resolution x-ray masks by gas-assisted focused ion beam

NASA Technical Reports Server (NTRS)

Hartley, F.; Malek, C.; Neogi, J.

2001-01-01

The capacity of chemically-assisted focused ion beam (fib) etching systems to undertake direct and highly anisotropic erosion of thin and thick gold (or other high atomic number [Z])coatings on x-ray mask membranes/substrates provides new levels of precision, flexibility, simplification and rapidity in the manufacture of mask absorber patterns, allowing the fast prototyping of high aspect ratio, high-resolution masks for deep x-ray lithography.

Minority-spin t 2gstates and the degree of spin polarization in ferromagnetic metallic La 2-2xSr 1+2xMn 2O 7 (x = 0.38)

DOE PAGES

Sun, Z.; Wang, Q.; Douglas, J. F.; ...

2013-11-07

In this paper, a half-metal is a material with conductive electrons of one spin orientation. This type of substance has been extensively searched for due to the fascinating physics as well as the potential applications for spintronics. Ferromagnetic manganites are considered to be good candidates, though there is no conclusive evidence for this notion. Here we show that the ferromagnet La 2–2xSr 1+2xMn 2O 7 (x = 0.38) possesses minority-spin states, challenging whether any of the manganites may be true half-metals. However, when electron transport properties are taken into account on the basis of the electronic band structure, we foundmore » that the La 2–2xSr 1+2xMn 2O 7 (x = 0.38) can essentially behave like a complete half metal.« less

The STS-92 crew is ready to leave KSC after CEIT

NASA Technical Reports Server (NTRS)

2000-01-01

STS-92 Commander Brian Duffy climbs into a T-38 jet aircraft at KSC's Shuttle Landing Facility for a flight back to Houston. He and other crew members were at KSC for Crew Equipment Interface Test (CEIT) activities, looking over their mission payload and related equipment. STS-92 is scheduled to launch Oct. 5 on Shuttle Discovery from Launch Pad 39A on the fifth flight to the International Space Station. Discovery will carry the Integrated Truss Structure (ITS) Z1, the PMA-3, Ku-band Communications System, and Control Moment Gyros (CMGs).

Rapid prototyping and AI programming environments applied to payload modeling

NASA Technical Reports Server (NTRS)

Carnahan, Richard S., Jr.; Mendler, Andrew P.

1987-01-01

This effort focused on using artificial intelligence (AI) programming environments and rapid prototyping to aid in both space flight manned and unmanned payload simulation and training. Significant problems addressed are the large amount of development time required to design and implement just one of these payload simulations and the relative inflexibility of the resulting model to accepting future modification. Results of this effort have suggested that both rapid prototyping and AI programming environments can significantly reduce development time and cost when applied to the domain of payload modeling for crew training. The techniques employed are applicable to a variety of domains where models or simulations are required.

X-38 Ship #2 Mated to B-52 Mothership in Flight

NASA Image and Video Library

1999-07-09

This photo shows one of the X-38 lifting-body research vehicles mated to NASA's B-52 mothership in flight prior to launch. The B-52 has been a workhorse for the Dryden Flight Research Center for more than 40 years, carrying numerous research vehicles aloft and conducting a variety of other research flight experiments.

Characterizing X-ray detectors for prototype digital breast tomosynthesis systems

NASA Astrophysics Data System (ADS)

Kim, Y.-s.; Park, H.-s.; Park, S.-J.; Choi, S.; Lee, H.; Lee, D.; Choi, Y.-W.; Kim, H.-J.

2016-03-01

The digital breast tomosynthesis (DBT) system is a newly developed 3-D imaging technique that overcomes the tissue superposition problems of conventional mammography. Therefore, it produces fewer false positives. In DBT system, several parameters are involved in image acquisition, including geometric components. A series of projections should be acquired at low exposure. This makes the system strongly dependent on the detector's characteristic performance. This study compares two types of x-ray detectors developed by the Korea Electrotechnology Research Institute (KERI). The first prototype DBT system has a CsI (Tl) scintillator/CMOS based flat panel digital detector (2923 MAM, Dexela Ltd.), with a pixel size of 0.0748 mm. The second uses a-Se based direct conversion full field detector (AXS 2430, analogic) with a pixel size of 0.085 mm. The geometry of both systems is same, with a focal spot 665.8 mm from the detector, and a center of rotation 33 mm above the detector surface. The systems were compared with regard to modulation transfer function (MTF), normalized noise power spectrum (NNPS), detective quantum efficiency (DQE) and a new metric, the relative object detectability (ROD). The ROD quantifies the relative performance of each detector at detecting specified objects. The system response function demonstrated excellent linearity (R2>0.99). The CMOS-based detector had a high sensitivity, while the Anrad detector had a large dynamic range. The higher MTF and noise power spectrum (NPS) values were measured using an Anrad detector. The maximum DQE value of the Dexela detector was higher than that of the Anrad detector with a low exposure level, considering one projection exposure for tomosynthesis. Overall, the Dexela detector performed better than did the Anrad detector with regard to the simulated Al wires, spheres, test objects of ROD with low exposure level. In this study, we compared the newly developed prototype DBT system with two different types of x

Earth observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-11-26

ISS038-E-008471 (26 Nov. 2013) --- One of the Expedition 38 crew members aboard the International Space Station took this photograph showing a part of South Africa's Atlantic Coast. South Africa is the only African nation bordered by both the Indian and Atlantic Oceans.

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 Flight Engineer Rick Mastracchio of NASA talks, while in quarantine behind glass, during the final press conference held a day ahead of his launch with fellow crew mates, Soyuz Commander Mikhail Tyurin of Roscosmos, and, Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 Soyuz Commander Mikhail Tyurin of Roscosmos is seen in quarantine behind glass during the final press conference held a day ahead of his launch with fellow crew mates, Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, and, Flight Engineer Rick Mastracchio of NASA, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

Expedition 38 Press Conference

NASA Image and Video Library

2013-11-06

Expedition 38 Soyuz Commander Mikhail Tyurin of Roscosmos, right, talks as Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, listens, from quarantine behind glass, during the final press conference held a day ahead of their launch with fellow crew mate, Flight Engineer Rick Mastracchio of NASA, to the International Space Station, Wednesday, Nov. 6, 2013 at the Cosmonaut Hotel in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

Views of STS-3 crew during departure activites at Ellington with family

NASA Technical Reports Server (NTRS)

1982-01-01

Views of STS-3 crew, Astronauts Jack R. Lousma, left, and C. Gordon Fullerton prior to their departure in T-38 aircraft from Ellington Air Force Base for the launch of STS-3 (28700); Some of the family members of astronaut crew are greeted by a crowd of spectators on hand for Lousma and Fullerton's departure. Matthew Lousma is standing at the microphone in center of the frame, flanked by Mrs. Gratia Kay Lousma (left) and Mrs. Maria Fullerton. Left to right in front are Mary Lousma, Andrew Fullerton and Molly Fullerton (28701-2); Astronaut Lousma walks away from microphone after greeting news media representatives and public prior to departure for Kennedy (28703); Astronaut Lousma talking to Fullerton, left, and Astronuat Brewster H. Shaw, center before boarding T-38's to leave for KSC (28704); Lousma, left, and Fullerton pause at Ellington prior to their departure in T-38 aircraft for KSC (28705); Lousma, right, and Fullerton greet crowd on hand at Ellington for their departure to KSC

Crew factors in flight operations VII : psychophysiological responses to overnight cargo operations

DOT National Transportation Integrated Search

1996-02-01

To document the psychophysiological effects of flying overnight cargo operations, 41 B-727 crew members (average age 38 yr) were monitored before, during, and after one of two typical 8-day trip patterns. During daytime layovers, the average sleep ep...

X-2 on ramp with B-50 mothership and support crew

NASA Technical Reports Server (NTRS)

1956-01-01

Air Force test pilot Capt. Iven Kincheloe stands in front of the Bell X-2 (46-674) on the ramp at Edwards Air Force Base, California. Behind the X-2 are ground support personnel, the B-50 launch aircraft and crew, chase planes, and support vehicles. Kincheloe had flown nearly 100 combat missions in Korea in an F-86 and was credited with shooting down 10 enemy aircraft. He then graduated from the Empire Test Pilot's School in Great Britain in December 1954, whereupon he was assigned to Edwards Air Force Base. He made four powered flights in the X-2. On September 7, 1956, he reached an altitude of 126,200 feet. After the death of Capt. Mel Apt and the loss of the X-2 #1 on September 27, 1956, in the first Mach 3 flight, Kincheloe was assigned as the Air Force project pilot for the X-15. Before he had a chance to fly that rocket-powered aircraft, Kincheloe himself lost his life on July 26, 1958, in an F-104 accident. The X-2 was a swept-wing, rocket-powered aircraft designed to fly faster than Mach 3 (three times the speed of sound). It was built for the U.S. Air Force by the Bell Aircraft Company, Buffalo, New York. The X-2 was flown to investigate the problems of aerodynamic heating as well as stability and control effectiveness at high altitudes and high speeds (in excess of Mach 3). Bell aircraft built two X-2 aircraft. These were constructed of K-monel (a copper and nickel alloy) for the fuselage and stainless steel for the swept wings and control surfaces. The aircraft had ejectable nose capsules instead of ejection seats because the development of ejection seats had not reached maturity at the time the X-2 was conceived. The X-2 ejection canopy was successfully tested using a German V-2 rocket. The X-2 used a skid-type landing gear to make room for more fuel. The airplane was air launched from a modified Boeing B-50 Superfortress Bomber. X-2 Number 1 made its first unpowered glide flight on Aug. 5, 1954, and made a total of 17 (4 glide and 13 powered) flights

Commercial Crew Program Crew Safety Strategy

NASA Technical Reports Server (NTRS)

Vassberg, Nathan; Stover, Billy

2015-01-01

The purpose of this presentation is to explain to our international partners (ESA and JAXA) how NASA is implementing crew safety onto our commercial partners under the Commercial Crew Program. It will show them the overall strategy of 1) how crew safety boundaries have been established; 2) how Human Rating requirements have been flown down into programmatic requirements and over into contracts and partner requirements; 3) how CCP SMA has assessed CCP Certification and CoFR strategies against Shuttle baselines; 4) Discuss how Risk Based Assessment (RBA) and Shared Assurance is used to accomplish these strategies.

STS-69 Crew members display 'Dog Crew' patches

NASA Technical Reports Server (NTRS)

1995-01-01

Following their arrival at KSC's Shuttle Landing Facility, the five astronauts assigned to Space Shuttle Mission STS-69 display the unofficial crew patch for their upcoming spaceflight: the Dog Crew II patch. Mission Commander David M. Walker (center) and Payload Commander James S. Voss (second from right) previously flew together on Mission STS-53, the final dedicated Department of Defense flight on the Space Shuttle. A close comradery formed among Walker, Voss and the rest of the crew, and they dubbed themselves the 'dogs of war', with each of the STS-53 'Dog Crew' members assigned a 'dog tag' or nickname. When the STS-69 astronauts also became good buddies, they decided it was time for the Dog Crew II to be named. Walker's dog tag is Red Dog, Voss's is Dogface, Pilot Kenneth D. Cockrell (second from left) is Cujo, space rookie and Mission Specialist Michael L. Gernhardt (left) is Under Dog, and Mission Specialist James H. Newman (right) is Pluato. The Dog Crew II patch features a bulldog peering out from a doghouse shaped like the Space Shuttle and lists the five crew member's dog names. The five astronauts are scheduled to lift off on the fifth Shuttle flight of the year at 11:04 a.m. EDT, August 31, aboard the Space Shuttle Endeavour.

Prototype of the Modular Equipment Transporter (MET)

NASA Technical Reports Server (NTRS)

1970-01-01

A prototype of the Modular Equipment Transporter (MET), nicknamed the 'Rickshaw' after its shape and method of propulsion. This equipment was used by the Apollo 14 astronauts during their geological and lunar surface simulation training in the Pinacate volcanic area of northwestern Sonora, Mexico. The Apollo 14 crew will be the first one to use the MET. It will be a portable workbench with a place for the lunar handtools and their carrier, three cameras, two sample container bags, a Special Environmental Sample Container, spare film magazines, and a Lunar Surface Penetrometer.

Space-to-Ground: Busy Crew: 09/22/2017

NASA Image and Video Library

2017-09-21

The SpaceX Dragon returns to Earth...the crew prepares for three spacewalks...and do you get scared in space? NASA's Space to Ground is your weekly update on what's happening aboard the International Space Station.

Role of Hf on Phase Formation in Ti45Zr(38-x)Hf(x)Ni17 Liquids and Solids

NASA Technical Reports Server (NTRS)

Wessels, V.; Sahu, K. K.; Gangopadhyay, A. K.; Huett, V. T.; Canepari, S.; Goldman, A. I.; Hyers, R. W.; Kramer, M. J.; Rogers, J. R.; Kelton, K. F.;

The Secret Lives of Cepheids: δ Cep—The Prototype of a New Class of Pulsating X-Ray Variable Stars

NASA Astrophysics Data System (ADS)

Engle, Scott G.; Guinan, Edward F.; Harper, Graham M.; Cuntz, Manfred; Remage Evans, Nancy; Neilson, Hilding R.; Fawzy, Diaa E.

2017-03-01

From our Secret Lives of Cepheids program, the prototype Classical Cepheid, δ Cep, is found to be an X-ray source with periodic pulsation-modulated X-ray variations. This finding complements our earlier reported phase-dependent FUV-UV emissions of the star that increase ˜10-20 times with highest fluxes at ˜ 0.90{--}0.95φ , just prior to maximum brightness. Previously δ Cep was found as potentially X-ray variable, using XMM-Newton observations. Additional phase-constrained data were secured with Chandra near X-ray emission peak, to determine if the emission and variability were pulsation-phase-specific to δ Cep and not transient or due to a possible coronally active, cool companion. The Chandra data were combined with prior XMM-Newton observations, and were found to very closely match the previously observed X-ray behavior. From the combined data set, a ˜4 increase in X-ray flux is measured, reaching a peak {L}{{X}} = 1.7 × 1029 erg s-1 near 0.45ϕ. The precise X-ray flux phasing with the star’s pulsation indicates that the emissions arise from the Cepheid and not from a companion. However, it is puzzling that the maximum X-ray flux occurs ˜0.5ϕ (˜3 days) later than the FUV-UV maximum. There are several other potential Cepheid X-ray detections with properties similar to δ Cep, and comparable X-ray variability is indicated for two other Cepheids: β Dor and V473 Lyr. X-ray generating mechanisms in δ Cep and other Cepheids are discussed. If additional Cepheids are confirmed to show phased X-ray variations, then δ Cep will be the prototype of a new class of pulsation-induced X-ray variables.

An Overview of the Guided Parafoil System Derived from X-38 Experience

NASA Technical Reports Server (NTRS)

Stein, Jenny M.; Madsen, Chris M.; Strahan, Alan L.

2005-01-01

The NASA Johnson Space Center built a 4200 sq ft parafoil for the U.S. Army Natick Soldier Center to demonstrate autonomous flight using a guided parafoil system to deliver 10,000 lbs of useable payload. The parafoil's design was based upon that developed during the X-38 program. The drop test payload consisted of a standard 20-foot Type V airdrop platform, a standard 12-foot weight tub, a 60 ft drogue parachute, a 4200 ft2 parafoil, an instrumentation system, and a Guidance, Navigation, and Control (GN&C) system. Instrumentation installed on the load was used to gather data to validate simulation models and preflight loads predictions and to perform post flight trajectory and performance reconstructions. The GN&C system, developed during NASA's X-38 program, consisted of a flight computer, modems for uplink commands and downlink data, a compass, laser altimeter, and two winches. The winches were used to steer the parafoil and to perform the dynamic flare maneuver for a soft landing. The laser was used to initiate the flare. The GN&C software was originally provided to NASA by the European Space Agency. NASA incorporated further software refinements based upon the X-38 flight test results. Three full-scale drop tests were conducted, with the third being performed during the Precision Airdrop Technology Conference and Demonstration (PATCAD) Conference at the U.S. Army Yuma Proving Ground (YPG) in November of 2003. For the PATCAD demonstration, the parafoil and GN&C software and hardware performed well, concluding with a good flare and the smallest miss distance ever experienced in NASA's parafoil drop test program. This paper describes the 4200 sq ft parafoil system, simulation results, and the results of the drop tests.

Development and Demonstration of a Prototype Free Flight Cockpit Display of Traffic Information

NASA Technical Reports Server (NTRS)

Johnson, Walter W.; Battiste, Vernol; Delzell, Susanne; Holland, Sheila; Belcher, Sean; Jordan, Kevin

2003-01-01

Two versions of a prototype Free Flight cockpit situational display (Basic and Enhanced) were examined in a simulation at the NASA Ames Research Center. Both displays presented a display of traffic out to a range of 120 NM, and an alert when the automation detected a substantial danger of losing separation with another aircraft. The task for the crews was to detect and resolve threats to separation posed by intruder aircraft. An Enhanced version of the display was also examined. It incorporated two additional conflict alerting levels and tools to aid in trajectory prediction and path planning. Ten crews from a major airline participated in the study. Performance analyses and pilot debriefings showed that the Enhanced display was preferred, and that minimal separation between the intruder and the ownship was larger with the Enhanced display. In addition, the additional information on the Enhanced display did not lead crews to engage in more maneuvering. Instead an opposite trend was indicated. Finally, crews using the Enhanced display responded more proactively, tending to resolve alerts earlier.

38 CFR 3.370 - Pulmonary tuberculosis shown by X-ray in active service.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 1 2010-07-01 2010-07-01 false Pulmonary tuberculosis... Rating Considerations Relative to Specific Diseases § 3.370 Pulmonary tuberculosis shown by X-ray in... connection for pulmonary tuberculosis. When under consideration, all available service department films and...

38 CFR 3.370 - Pulmonary tuberculosis shown by X-ray in active service.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 1 2012-07-01 2012-07-01 false Pulmonary tuberculosis... Rating Considerations Relative to Specific Diseases § 3.370 Pulmonary tuberculosis shown by X-ray in... connection for pulmonary tuberculosis. When under consideration, all available service department films and...

38 CFR 3.370 - Pulmonary tuberculosis shown by X-ray in active service.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 1 2013-07-01 2013-07-01 false Pulmonary tuberculosis... Rating Considerations Relative to Specific Diseases § 3.370 Pulmonary tuberculosis shown by X-ray in... connection for pulmonary tuberculosis. When under consideration, all available service department films and...

38 CFR 3.370 - Pulmonary tuberculosis shown by X-ray in active service.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 1 2011-07-01 2011-07-01 false Pulmonary tuberculosis... Rating Considerations Relative to Specific Diseases § 3.370 Pulmonary tuberculosis shown by X-ray in... connection for pulmonary tuberculosis. When under consideration, all available service department films and...

38 CFR 3.370 - Pulmonary tuberculosis shown by X-ray in active service.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 38 Pensions, Bonuses, and Veterans' Relief 1 2014-07-01 2014-07-01 false Pulmonary tuberculosis... Rating Considerations Relative to Specific Diseases § 3.370 Pulmonary tuberculosis shown by X-ray in... connection for pulmonary tuberculosis. When under consideration, all available service department films and...

Progress on the J-2X Upper Stage Engine for the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle

NASA Technical Reports Server (NTRS)

Byrd, Thomas D.; Kynard, Michael .

2007-01-01

NASA's Vision for Exploration requires a safe, reliable, affordable upper stage engine to power the Ares I Crew Launch Vehicle (CLV) and the Ares V Cargo Launch Vehicle. The J-2X engine is being developed for that purpose, epitomizing NASA's philosophy of employing legacy knowledge, heritage hardware, and commonality to carry the next generation of explorers into low-Earth orbit and out into the solar system This presentation gives top-level details on accomplishments to date and discusses forward work necessary to bring the J-2X engine to the launch pad.

Expedition 38 Prelaunch

NASA Image and Video Library

2013-11-07

Expedition 38 Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency waves hello to family members gathered to watch him through glass as he and fellow crew mates, Soyuz Commander Mikhail Tyurin of Roscosmos, and, Flight Engineer Rick Mastracchio of NASA, have their Russian Sokol suits pressure checked a few hours ahead of their launch, Thursday, Nov. 7, 2013, in Baikonur, Kazakhstan. Tyurin, Wakata, and, Mastracchio will launch in their Soyuz TMA-11M spacecraft to the International Space Station to begin a six-month mission. Photo Credit (NASA/Bill Ingalls)

Activation of p38 MAPK-regulated Bcl-xL signaling increases survival against zoledronic acid-induced apoptosis in osteoclast precursors.

PubMed

Tai, Ta-Wei; Su, Fong-Chin; Chen, Ching-Yu; Jou, I-Ming; Lin, Chiou-Feng

2014-10-01

The nitrogen-containing bisphosphonate zoledronic acid (ZA) induces apoptosis in osteoclasts and inhibits osteoclast-mediated bone resorption. It is widely used to treat osteoporosis. However, some patients are less responsive to ZA treatment, and the mechanisms of resistance are still unclear. Here, we identified that murine osteoclast precursors may develop resistance to ZA-induced apoptosis. These resistant cells survived the apoptotic effect of ZA following an increase in anti-apoptotic Bcl-xL. Pharmacologically inhibiting Bcl-xL facilitated ZA-induced apoptosis. Treatment with ZA activated p38 MAPK, increasing Bcl-xL expression and cell survival. Nuclear import of β-catenin regulated by p38 MAPK determined Bcl-xL mRNA expression and cell survival in response to ZA. ZA also inactivated glycogen synthase kinase (GSK)-3β, a negative upstream regulator of β-catenin, in a p38 MAPK-mediated manner. Synergistic pharmacological inhibition of p38 MAPK with ZA attenuated receptor activator of nuclear factor kappa-B ligand (RANKL)-induced osteoclast differentiation and facilitated ZA-induced apoptosis. These results demonstrate that elevated Bcl-xL expression mediated by p38 MAPK-regulated GSK-3β/β-catenin signaling is required for cell survival of ZA-induced apoptosis in both osteoclast precursors and osteoclasts. Finally, we demonstrated that inhibiting p38 MAPK-mediated pathway enhanced ZA effect on increasing the bone mineral density of ovariectomized mice. This result suggests that targeting these pathways may represent a potential therapeutic strategy. Copyright © 2014 Elsevier Inc. All rights reserved.

The 'missing man' formation concluded the memorial for the STS 51-L crew

NASA Technical Reports Server (NTRS)

1986-01-01

The 'missing man' formation concluded the memorial services at JSC for the STS 51-L crew. Four NASA T-38 jet aircraft were used for the symbolic flight. A small portion of the crowd is visible in the bottom portion of the frame.

A prototype supervised intelligent robot for helping astronauts

NASA Technical Reports Server (NTRS)

Erickson, J. D.; Grimm, K. A.; Pendleton, T. W.

1994-01-01

The development status is described of a prototype supervised intelligent robot for space application for purposes of (1) helping the crew of a spacecraft such as the Space Station with various tasks such as holding objects and retrieving/replacing tools and other objects from/into storage, and for purposes of (2) retrieving detached objects, such as equipment or crew, that have become separated from their spacecraft. In addition to this set of tasks in this low Earth orbiting spacecraft environment, it is argued that certain aspects of the technology can be viewed as generic in approach, thereby offering insight into intelligent robots for other tasks and environments. Also described are characterization results on the usable reduced gravity environment in an aircraft flying parabolas (to simulate weightlessness) and results on hardware performance there. These results show it is feasible to use that environment for evaluative testing of dexterous grasping based on real-time visual sensing of freely rotating and translating objects.

Flight crew aiding for recovery from subsystem failures

NASA Technical Reports Server (NTRS)

Hudlicka, E.; Corker, K.; Schudy, R.; Baron, Sheldon

1990-01-01

Some of the conceptual issues associated with pilot aiding systems are discussed and an implementation of one component of such an aiding system is described. It is essential that the format and content of the information the aiding system presents to the crew be compatible with the crew's mental models of the task. It is proposed that in order to cooperate effectively, both the aiding system and the flight crew should have consistent information processing models, especially at the point of interface. A general information processing strategy, developed by Rasmussen, was selected to serve as the bridge between the human and aiding system's information processes. The development and implementation of a model-based situation assessment and response generation system for commercial transport aircraft are described. The current implementation is a prototype which concentrates on engine and control surface failure situations and consequent flight emergencies. The aiding system, termed Recovery Recommendation System (RECORS), uses a causal model of the relevant subset of the flight domain to simulate the effects of these failures and to generate appropriate responses, given the current aircraft state and the constraints of the current flight phase. Since detailed information about the aircraft state may not always be available, the model represents the domain at varying levels of abstraction and uses the less detailed abstraction levels to make inferences when exact information is not available. The structure of this model is described in detail.

X-38 on B-52 Wing Pylon - View from Observation Window

NASA Technical Reports Server (NTRS)

1997-01-01

A unique, close-up view of the X-38 under the wing of NASA's B-52 mothership prior to launch of the lifting-body research vehicle. The photo was taken from the observation window of the B-52 bomber as it banked in flight. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket booster casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In

Commercial Crew Astronauts Visit Kennedy on This Week @NASA – August 12, 2016

NASA Image and Video Library

2016-08-12

Two of the NASA astronauts training for the first flight tests for the agency’s Commercial Crew Program visited with employees during an Aug. 11 event at Kennedy Space Center. Astronauts Eric Boe and Suni Williams, alongside Commercial Crew Program Manager Kathy Lueders, responded to questions during a panel discussion, moderated by Kennedy Director Robert Cabana. NASA has contracted with Boeing and SpaceX to develop crew transportation systems and provide crew transportation services to and from the International Space Station. The agency will select the commercial crew astronauts from the group that includes Boe, Williams, Bob Behnken and Doug Hurley The first flight tests are targeted for next year. Also, Air Quality Flight over California Wildfire, CYGNSS Media Day, Putting NASA Earth Science to Work, and more!

Aircrew perceived stress: examining crew performance, crew position and captains personality.

PubMed

Bowles, S; Ursin, H; Picano, J

2000-11-01

This study was conducted at NASA Ames Research Center as a part of a larger research project assessing the impact of captain's personality on crew performance and perceived stress in 24 air transport crews (5). Three different personality types for captains were classified based on a previous cluster analysis (3). Crews were comprised of three crewmembers: captain, first officer, and second officer/flight engineer. A total of 72 pilots completed a 1.5-d full-mission simulation of airline operations including emergency situations in the Ames Manned Vehicle System Research Facility B-727 simulator. Crewmembers were tested for perceived stress on four dimensions of the NASA Task Load Index after each of five flight legs. Crews were divided into three groups based on rankings from combined error and rating scores. High performance crews (who committed the least errors in flight) reported experiencing less stress in simulated flight than either low or medium crews. When comparing crew positions for perceived stress over all the simulated flights no significant differences were found. However, the crews led by the "Right Stuff" (e.g., active, warm, confident, competitive, and preferring excellence and challenges) personality type captains typically reported less stress than crewmembers led by other personality types.

Crew operations

NASA Technical Reports Server (NTRS)

1971-01-01

The requirements for the activities involved, and the procedures used by the crew in the operations of the modular space station are presented. All crew-related characteristics of the station and its operations are indicated. The interior configuration and arrangement of each of the space station modules, the facilities and equipment in the module and their operation are described as related to crew habitability. The crew activities and procedures involved in the operation of the station in the accomplishment of its primary mission are defined. The operations involved in initial station buildup, and the on-orbit operation and maintenance of the station and its subsystems to support the experimental program are included. A general description of experiment operations is also given.

A Human Factors Evaluation of a Methodology for Pressurized Crew Module Acceptability for Zero-Gravity Ingress of Spacecraft

NASA Technical Reports Server (NTRS)

Sanchez, Merri J.

2000-01-01

This project aimed to develop a methodology for evaluating performance and acceptability characteristics of the pressurized crew module volume suitability for zero-gravity (g) ingress of a spacecraft and to evaluate the operational acceptability of the NASA crew return vehicle (CRV) for zero-g ingress of astronaut crew, volume for crew tasks, and general crew module and seat layout. No standard or methodology has been established for evaluating volume acceptability in human spaceflight vehicles. Volume affects astronauts'ability to ingress and egress the vehicle, and to maneuver in and perform critical operational tasks inside the vehicle. Much research has been conducted on aircraft ingress, egress, and rescue in order to establish military and civil aircraft standards. However, due to the extremely limited number of human-rated spacecraft, this topic has been un-addressed. The NASA CRV was used for this study. The prototype vehicle can return a 7-member crew from the International Space Station in an emergency. The vehicle's internal arrangement must be designed to facilitate rapid zero-g ingress, zero-g maneuverability, ease of one-g egress and rescue, and ease of operational tasks in multiple acceleration environments. A full-scale crew module mockup was built and outfitted with representative adjustable seats, crew equipment, and a volumetrically equivalent hatch. Human factors testing was conducted in three acceleration environments using ground-based facilities and the KC-135 aircraft. Performance and acceptability measurements were collected. Data analysis was conducted using analysis of variance and nonparametric techniques.

SU-C-209-05: Monte Carlo Model of a Prototype Backscatter X-Ray (BSX) Imager for Projective and Selective Object-Plane Imaging

DOE Office of Scientific and Technical Information (OSTI.GOV)

Rolison, L; Samant, S; Baciak, J

Purpose: To develop a Monte Carlo N-Particle (MCNP) model for the validation of a prototype backscatter x-ray (BSX) imager, and optimization of BSX technology for medical applications, including selective object-plane imaging. Methods: BSX is an emerging technology that represents an alternative to conventional computed tomography (CT) and projective digital radiography (DR). It employs detectors located on the same side as the incident x-ray source, making use of backscatter and avoiding ring geometry to enclose the imaging object. Current BSX imagers suffer from low spatial resolution. A MCNP model was designed to replicate a BSX prototype used for flaw detection inmore » industrial materials. This prototype consisted of a 1.5mm diameter 60kVp pencil beam surrounded by a ring of four 5.0cm diameter NaI scintillation detectors. The imaging phantom consisted of a 2.9cm thick aluminum plate with five 0.6cm diameter holes drilled halfway. The experimental image was created using a raster scanning motion (in 1.5mm increments). Results: A qualitative comparison between the physical and simulated images showed very good agreement with 1.5mm spatial resolution in plane perpendicular to incident x-ray beam. The MCNP model developed the concept of radiography by selective plane detection (RSPD) for BSX, whereby specific object planes can be imaged by varying kVp. 10keV increments in mean x-ray energy yielded 4mm thick slice resolution in the phantom. Image resolution in the MCNP model can be further increased by increasing the number of detectors, and decreasing raster step size. Conclusion: MCNP modelling was used to validate a prototype BSX imager and introduce the RSPD concept, allowing for selective object-plane imaging. There was very good visual agreement between the experimental and MCNP imaging. Beyond optimizing system parameters for the existing prototype, new geometries can be investigated for volumetric image acquisition in medical applications. This material

Blood lead level and types of aviation fuel in aircraft maintenance crew.

PubMed

Park, Won-Ju; Gu, Hye-Min; Lee, Suk-Ho

2013-10-01

This study inquired into any significant difference in blood lead levels (BLLs) among aircraft maintenance crews at the air-bases, each with a different aviation fuel in use, and confirmed an environmental impact of leaded aviation gasoline (AVGAS). This study included a total of 256 male aircraft maintenance personnel, among whom 105 used only AVGAS as their aviation fuel, while 151 used only jet propellant 8 (JP-8), a kerosene variety. BLLs were measured and the data on related factors were obtained. The arithmetic and geometric means of BLLs of the personnel at the airbases that used only AVGAS were 4.20 microg x dl(-1) and 4.01 microg x dl(-1) and that used only JP-8 were 3.79 microg x dl(-1) and 3.57 microg x dl(-1), respectively. The BLLs of the maintenance crew of the main workspace that was located within a 200-m distance from the runway were higher than those of the main workspace that was located 200 m or farther from the runway. The longer the work hours in the runway or the longer the work duration, the higher the BLLs of the maintenance crew. This investigation exposed the fact that a body's BLL could be increased by AVGAS emissions through the examination of aircraft maintenance crew. This result is in agreement with results of previous studies that suggest proximity to an airport may be associated with elevated BLLs for adults and children. Collectively, the results of the current study and previous research suggest that long-duration inhabitation and/or activities in close proximity to an air facility should be limited given that lead poses known health risks.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2014-02-14

ISS038-E-047324 (13 Feb. 2014) --- This grand panorama of the Southern Patagonia Icefield (center) was imaged by an Expedition 38 crew member on the International Space Station on one of the rare clear days in the southern Andes Mountains. With an area of 13,000 square kilometers, the icefield is the largest temperate ice sheet in the Southern Hemisphere. Storms that swirl into the region from the southern Pacific Ocean (top) bring rain and snow (equivalent to a total of 2-11 meters of rainfall per year) resulting in the buildup of the ice sheet shown here (center). During the ice ages the glaciers were far larger. Geologists now know that ice tongues extended far onto the plains in the foreground, completely filling the great Patagonian lakes on repeated occasions. Similarly, ice tongues extended into the dense network of fjords (arms of the sea) on the Pacific side of the icefield. Ice tongues today appear tiny compared to the view that an "ice age" astronaut would have seen. A study of the surface topography of sixty-three glaciers, based on Shuttle Radar Topography Mission (SRTM) data, compared data from 2000 to data from studies going back about 30 years (1968-1975). Many glacier tongues showed significant annual "retreat" of their ice fronts, a familiar signal of climate change. The study also revealed that the almost invisible loss by glacier thinning is far more significant in explaining ice loss. The researchers concluded that volume loss by frontal collapse is 4-10 times smaller than that caused by thinning. Scaled over the entire icefield, including frontal loss (so-called calving when ice masses collapse into the lakes), it was calculated that 13.5 cubic kilometers of ice was lost each year over the study period. This number becomes more meaningful compared with the rate measured in the last five years of the study (1995-2000), when the rate increased almost threefold, averaging 38.7 cubic kilometers per year. Extrapolating results from the low altitude

STS-101 crew waves to media after arriving at KSC for 4th launch attempt

NASA Technical Reports Server (NTRS)

2000-01-01

Members of the STS-101 crew wave at media and photographers at KSC's Shuttle Landing Facility after their landing the night of May 14. Standing left to right are Mission Specialists Yuri Usachev, James Voss, Mary Ellen Weber and Jeff Williams; Commander James Halsell; and Pilot Scott Horowitz. Not present is Mission Specialist Susan Helms, who arrived later. The crew will be preparing for the launch on May 18. The mission will take the crew of seven to the International Space Station, delivering logistics and supplies, plus preparing the Station for the arrival of the Zvezda Service Module, expected to be launched by Russia in July 2000. Also, the crew will conduct one space walk to perform maintenance on the Space Station. This will be the third assembly flight for the Space Station. STS-101 is targeted for liftoff at 6:38 a.m. EDT from Launch Pad 39A.

STS-38 Pilot Culbertson rolls through CCT side hatch during egress training

NASA Technical Reports Server (NTRS)

1990-01-01

STS-38 Pilot Frank L. Culbertson, wearing launch and entry suit (LES) and launch and entry helmet (LEH), rolls through the side hatch of the crew compartment trainer (CCT) located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. Assisted by technicians, Culbertson practices emergency egress through the side hatch using the crew escape system (CES) pole which extends out the side hatch. The inflated safety cushion breaks Culbertson's fall as he rolls out of the side hatch.

STS-38 Pilot Culbertson rolls through CCT side hatch during egress training

NASA Image and Video Library

1990-03-05

STS-38 Pilot Frank L. Culbertson, wearing launch and entry suit (LES) and launch and entry helmet (LEH), rolls through the side hatch of the crew compartment trainer (CCT) located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. Assisted by technicians, Culbertson practices emergency egress through the side hatch using the crew escape system (CES) pole which extends out the side hatch. The inflated safety cushion breaks Culbertson's fall as he rolls out of the side hatch.

Astronauts Bob Behnken and Eric Boe walk the Crew Access Arm at

NASA Image and Video Library

2017-08-30

Astronauts Bob Behnken, left, and Eric Boe walk down the Crew Access Arm being built by SpaceX for Launch Complex 39A at NASA’s Kennedy Space Center in Florida. The access arm will be installed on the launch pad, providing a bridge between the launch tower it’s the Fixed Service Structure, as noted below, and SpaceX’s Dragon 2 spacecraft for astronauts flying to the International Space Station on the company’s Falcon 9 rocket as part of NASA’s Commercial Crew Program. The access arm is being readied for installation in early 2018. It will be installed 70 feet higher than the former space shuttle access arm on the launch pad’s Fixed Service Structure. SpaceX continues to modify the historic launch site from its former space shuttle days, removing more than 500,000 pounds of steel from the pad structure, including the Rotating Service Structure that was once used for accessing the payload bay of the shuttle. SpaceX also is using the modernized site to launch commercial payloads, as well as cargo resupply missions to and from the International Space Station for NASA. The first SpaceX launch from the historic Apollo and space shuttle site was this past February. NASA’s Commercial Crew Program is working with private companies, Boeing and SpaceX, with a goal of once again flying people to and from the International Space Station, launching from the United States.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-11-11

ISS038-E-000232 (11 Nov. 2013) --- One of the Expedition 38 crew members aboard the International Space Station used a 180mm lens to photograph this oblique image featuring the Galapagos Islands or Islas Galapagos, distributed on either side of the Equator in the eastern Pacific Ocean. An archipelago of volcanic islands, the group?s official name is Archipielago de Colon.

X-15 flight crew - Engle, Rushworth, McKay, Knight, Thompson, and Dana

NASA Technical Reports Server (NTRS)

1966-01-01

The X-15 flight crew, left to right; Air Force Captain Joseph H. Engle, Air Force Major Robert A. Rushworth, NASA pilot John B. 'Jack' McKay, Air Force Major William J. 'Pete' Knight, NASA pilot Milton O. Thompson, and NASA pilot Bill Dana. These six pilots made 125 of the 199 total flights in the X-15. Rushworth made 34 flights (the most of any X-15 pilot); McKay flew 29 times; Engle, Knight, and Dana each flew 16 times; Thompson's total was 14. The X-15 was a rocket-powered aircraft 50 ft long with a wingspan of 22 ft. It was a missile-shaped vehicle with an unusual wedge-shaped vertical tail, thin stubby wings, and unique fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was capable of developing 57,000 lb of rated thrust (actual thrust reportedly climbed to 60,000 lb). North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as a testbed to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and canted horizontal surfaces on the tail to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52

STS-93: Chandra Crew Arrival

NASA Technical Reports Server (NTRS)

1999-01-01

The primary objective of the STS-93 mission was to deploy the Advanced X-ray Astrophysical Facility, which had been renamed the Chandra X-ray Observatory in honor of the late Indian-American Nobel Laureate Subrahmanyan Chandrasekhar. The mission was launched at 12:31 on July 23, 1999 onboard the space shuttle Columbia. The mission was led by Commander Eileen Collins. The crew was Pilot Jeff Ashby and Mission Specialists Cady Coleman, Steve Hawley and Michel Tognini from the Centre National d'Etudes Spatiales (CNES). This videotape shows the astronauts arrival at Kennedy Space Center a week before the launch. Each of the astronauts gives brief remarks, beginning with Eileen Collins, the first woman to command a space mission.

STS-38 MS Springer climbs through CCT side hatch prior to egress training

NASA Image and Video Library

1990-03-05

STS-38 Mission Specialist (MS) Robert C. Springer, wearing launch and entry suit (LES), climbs through the side hatch of the crew compartment trainer (CCT) located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. Springer will practice emergency egress through the side hatch using the crew escape system (CES) pole (at Springer's left). The inflated safety cushion under Springer will break his fall as he rolls out of the side hatch.

STS-38 MS Springer climbs through CCT side hatch prior to egress training

NASA Technical Reports Server (NTRS)

1990-01-01

STS-38 Mission Specialist (MS) Robert C. Springer, wearing launch and entry suit (LES), climbs through the side hatch of the crew compartment trainer (CCT) located in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9A. Springer will practice emergency egress through the side hatch using the crew escape system (CES) pole (at Springer's left). The inflated safety cushion under Springer will break his fall as he rolls out of the side hatch.

Lithiation-induced zinc clustering of Zn 3, Zn 12, and Zn 18 units in Zintl-like Ca ~30Li 3+xZn 60-x (x=0.44-1.38)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lin, Qisheng

2014-11-14

Zinc clusters are not common for binary intermetallics with relatively low zinc content, but this work shows that zinc clustering can be triggered by lithiation, as exemplified by Ca ~30Li 3+xZn 60-x, P6/mmm, Z = 1, which can be directly converted from CaZn 2. Two end members of the solid solution (x = 0.44 and 1.38) were established and structurally characterized by single-crystal X-ray diffraction analyses: Ca 30Li 3.44(6)Zn59.56(6), a = 15.4651(9) Å, c = 9.3898(3) Å; Ca 30.45(2)Li 4.38(6)Zn 58.62(6), a = 15.524(3) Å, c = 9.413(2) Å. The structures of Ca ~30Li 3+xZn 60-x feature a condensed anionicmore » network of Zn3 triangles, lithium-centered Zn12 icosahedra, and arachno-(Zn,Li)18 tubular clusters that are surrounded respectively by Ca 14, Ca 20, and Ca 30 polyhedra. These polyhedra share faces and form a clathrate-like cationic framework. The specific occupation of lithium in the structure is consistent with theoretical “coloring” analyses. Analysis by the linear muffin-tin orbital (LMTO) method within the atomic sphere approximation reveals that Ca ~30Li 3+xZn 60-x is a metallic, Zintl-like phase with an open-shell electronic structure. The contribution of Ca–Zn polar covalent interactions is about 41%.« less

Wireless Crew Communication Feasibility Assessment

NASA Technical Reports Server (NTRS)

Archer, Ronald D.; Romero, Andy; Juge, David

2016-01-01

Ongoing discussions with crew currently onboard the ISS as well as the crew debriefs from completed ISS missions indicate that issues associated with the lack of wireless crew communication results in increased crew task completion times and lower productivity, creates cable management issues, and increases crew frustration.

Crew decision making under stress

NASA Technical Reports Server (NTRS)

Orasanu, J.

1992-01-01

Flight crews must make decisions and take action when systems fail or emergencies arise during flight. These situations may involve high stress. Full-missiion flight simulation studies have shown that crews differ in how effectively they cope in these circumstances, judged by operational errors and crew coordination. The present study analyzed the problem solving and decision making strategies used by crews led by captains fitting three different personality profiles. Our goal was to identify more and less effective strategies that could serve as the basis for crew selection or training. Methods: Twelve 3-member B-727 crews flew a 5-leg mission simulated flight over 1 1/2 days. Two legs included 4 abnormal events that required decisions during high workload periods. Transcripts of videotapes were analyzed to describe decision making strategies. Crew performance (errors and coordination) was judged on-line and from videotapes by check airmen. Results: Based on a median split of crew performance errors, analyses to date indicate a difference in general strategy between crews who make more or less errors. Higher performance crews showed greater situational awareness - they responded quickly to cues and interpreted them appropriately. They requested more decision relevant information and took into account more constraints. Lower performing crews showed poorer situational awareness, planning, constraint sensitivity, and coordination. The major difference between higher and lower performing crews was that poorer crews made quick decisions and then collected information to confirm their decision. Conclusion: Differences in overall crew performance were associated with differences in situational awareness, information management, and decision strategy. Captain personality profiles were associated with these differences, a finding with implications for crew selection and training.

GPS Lessons Learned from the International Space Station, Space Shuttle and X-38

NASA Technical Reports Server (NTRS)

Goodman, John L.

2005-01-01

This document is a collection of writings concerning the application of Global Positioning System (GPS) technology to the International Space Station (ISS), Space Shuttle, and X-38 vehicles. An overview of how GPS technology was applied is given for each vehicle, including rationale behind the integration architecture, and rationale governing the use (or non-use) of GPS data during flight.

Asteroid Redirect Crewed Mission Space Suit and EVA System Maturation

NASA Technical Reports Server (NTRS)

Bowie, Jonathan; Buffington, Jesse; Hood, Drew; Kelly, Cody; Naids, Adam; Watson, Richard

2015-01-01

The Asteroid Redirect Crewed Mission (ARCM) requires a Launch/Entry/Abort (LEA) suit capability and short duration Extra Vehicular Activity (EVA) capability from the Orion spacecraft. For this mission, the pressure garment selected for both functions is the Modified Advanced Crew Escape Suit (MACES) with EVA enhancements and the life support option that was selected is the Exploration Portable Life Support System (PLSS) currently under development for Advanced Exploration Systems (AES). The proposed architecture meets the ARCM constraints, but much more work is required to determine the details of the suit upgrades, the integration with the PLSS, and the tools and equipment necessary to accomplish the mission. This work has continued over the last year to better define the operations and hardware maturation of these systems. EVA simulations were completed in the Neutral Buoyancy Lab (NBL) and interfacing options were prototyped and analyzed with testing planned for late 2014. This paper discusses the work done over the last year on the MACES enhancements, the use of tools while using the suit, and the integration of the PLSS with the MACES.

X-38 Ship #2 Mated to B-52 Mothership in Flight

NASA Technical Reports Server (NTRS)

1999-01-01

This photo shows one of the X-38 lifting-body research vehicles mated to NASA's B-52 mothership in flight prior to launch. The B-52 has been a workhorse for the Dryden Flight Research Center for more than 40 years, carrying numerous research vehicles aloft and conducting a variety of other research flight experiments. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket

Research pilot and former astronaut C. Gordon Fullerton in an F/A-18

NASA Image and Video Library

2002-05-14

Former NASA astronaut C. Gordon Fullerton, seated in the cockpit of an F/A-18, is a research pilot at NASA's Dryden Flight Research Center, Edwards, Calif. Since transferring to Dryden in 1986, his assignments have included a variety of flight research and support activities piloting NASA's B-52 launch aircraft, the 747 Shuttle Carrier Aircraft (SCA), and other multi-engine and high performance aircraft. He flew a series of development air launches of the X-38 prototype Crew Return Vehicle and in the launches for the X-43A Hyper-X project. Fullerton also flies Dryden's DC-8 Airborne Science aircraft in support a variety of atmospheric physics, ground mapping and meteorology studies. Fullerton also was project pilot on the Propulsion Controlled Aircraft program, during which he successfully landed both a modified F-15 and an MD-11 transport with all control surfaces neutralized, using only engine thrust modulation for control. Fullerton also evaluated the flying qualities of the Russian Tu-144 supersonic transport during two flights in 1998, one of only two non-Russian pilots to fly that aircraft. With more than 15,000 hours of flying time, Fullerton has piloted 135 different types of aircraft in his career. As an astronaut, Fullerton served on the support crews for the Apollo 14, 15, 16, and 17 lunar missions. In 1977, Fullerton was on one of the two flight crews that piloted the Space Shuttle prototype Enterprise during the Approach and Landing Test Program at Dryden. Fullerton was the pilot on the STS-3 Space Shuttle orbital flight test mission in 1982, and commanded the STS-51F Spacelab 2 mission in 1985. He has logged 382 hours in space flight. In July 1988, he completed a 30-year career with the U.S. Air Force and retired as a colonel.

Expedition 38 Prelaunch

NASA Image and Video Library

2013-11-07

General Director of the Russian Federal Space Agency, Roscosmos, Oleg Ostapenko, left, and, President of RSC Energia, Designer General V.A.Lapota, right, assist Expedition 38 Soyuz Commander Mikhail Tyurin of Roscosmos, as he and fellow crew members, Flight Engineer Koichi Wakata of the Japan Aerospace Exploration Agency, behind Tyurin, and, Flight Engineer Rick Mastracchio of NASA, far back, walk to the soyuz rocket for their launch to the International Space Station, Thursday, Nov. 7, 2013, in Baikonur, Kazakhstan. Tyurin, Wakata, and, Mastracchio will launch in their Soyuz TMA-11M spacecraft to the International Space Station to begin a six-month mission. Photo Credit: (NASA/Bill Ingalls)

ISS Propulsion Module Crew Systems Interface Analysis in the Intelligent Synthesis Environment

NASA Technical Reports Server (NTRS)

Chen, Di-Wen

1999-01-01

ERGO, a human modeling software for ergonomic assessment and task analysis, was used for the crew systems interface analysis of the International Space Station (ISS) Propulsion Module (PM). The objective of analysis was to alleviate passageway size concerns. Three basic passageway configuration concepts: (1) 45" clear passageway without centerline offset (2) 50" clear passageway, 12" centerline offset, (3) 50" clear passageway, no centerline offset, and were reviewed. 95 percentile male and female models which were provided by the software performed crew system analysis from an anthropometric point of view. Four scenarios in which the crew floats in microgravity through a 50" no-offset passageway as they carry a 16" x 20" x 30" avionics box were simulated in the 10-weeks of intensive study. From the results of the analysis, concept (3) was the preferred option. A full scale, three-dimensional virtual model of the ISS Propulsion Module was created to experience the sense of the Intelligent Synthesis Environment and to evaluate the usability and applicability of the software.

Orion Pad Abort 1 Crew Module Inertia Test Approach and Results

NASA Technical Reports Server (NTRS)

Herrera, Claudia; Harding, Adam

2010-01-01

The Flight Loads Laboratory at the Dryden Flight Research Center conducted tests to measure the inertia properties of the Orion Pad Abort 1 (PA-1) Crew Module. These measurements were taken to validate analytical predictions of the inertia properties of the vehicle and assist in reducing uncertainty for derived aero performance results calculated post launch. The first test conducted was to determine the Ixx of the Crew Module. This test approach used a modified torsion pendulum test step up that allowed the suspended Crew Module to rotate about the x axis. The second test used a different approach to measure both the Iyy and Izz properties. This test used a Knife Edge fixture that allowed small rotation of the Crew Module about the y and z axes. Discussions of the techniques and equations used to accomplish each test are presented. Comparisons with the predicted values used for the final flight calculations are made. Problem areas, with explanations and recommendations where available, are addressed. Finally, an evaluation of the value and success of these techniques to measure the moments of inertia of the Crew Module is provided.

Crew health

NASA Technical Reports Server (NTRS)

Billica, Roger D.

1992-01-01

Crew health concerns for Space Station Freedom are numerous due to medical hazards from isolation and confinement, internal and external environments, zero gravity effects, occupational exposures, and possible endogenous medical events. The operational crew health program will evolve from existing programs and from life sciences investigations aboard Space Station Freedom to include medical monitoring and certification, medical intervention, health maintenance and countermeasures, psychosocial support, and environmental health monitoring. The knowledge and experience gained regarding crew health issues and needs aboard Space Station Freedom will be used not only to verify requirements and programs for long duration space flight, but also in planning and preparation for Lunar and Mars exploration and colonization.

Acceptability of Flight Deck-Based Interval Management Crew Procedures

NASA Technical Reports Server (NTRS)

Murdock, Jennifer L.; Wilson, Sara R.; Hubbs, Clay E.; Smail, James W.

2013-01-01

The Interval Management for Near-term Operations Validation of Acceptability (IM-NOVA) experiment was conducted at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) in support of the NASA Next Generation Air Transportation System (NextGen) Airspace Systems Program's Air Traffic Management Technology Demonstration - 1 (ATD-1). ATD-1 is intended to showcase an integrated set of technologies that provide an efficient arrival solution for managing aircraft using NextGen surveillance, navigation, procedures, and automation for both airborne and ground-based systems. The goal of the IM-NOVA experiment was to assess if procedures outlined by the ATD-1 Concept of Operations, when used with a minimum set of Flight deck-based Interval Management (FIM) equipment and a prototype crew interface, were acceptable to and feasible for use by flight crews in a voice communications environment. To investigate an integrated arrival solution using ground-based air traffic control tools and aircraft automatic dependent surveillance broadcast (ADS-B) tools, the LaRC FIM system and the Traffic Management Advisor with Terminal Metering and Controller Managed Spacing tools developed at the NASA Ames Research Center (ARC) were integrated in LaRC's Air Traffic Operations Laboratory. Data were collected from 10 crews of current, qualified 757/767 pilots asked to fly a high-fidelity, fixed based simulator during scenarios conducted within an airspace environment modeled on the Dallas-Fort Worth (DFW) Terminal Radar Approach Control area. The aircraft simulator was equipped with the Airborne Spacing for Terminal Area Routes algorithm and a FIM crew interface consisting of electronic flight bags and ADS-B guidance displays. Researchers used "pseudo-pilot" stations to control 24 simulated aircraft that provided multiple air traffic flows into DFW, and recently retired DFW air traffic controllers served as confederate Center, Feeder, Final, and Tower

Crew Activity Analyzer

NASA Technical Reports Server (NTRS)

Murray, James; Kirillov, Alexander

2008-01-01

The crew activity analyzer (CAA) is a system of electronic hardware and software for automatically identifying patterns of group activity among crew members working together in an office, cockpit, workshop, laboratory, or other enclosed space. The CAA synchronously records multiple streams of data from digital video cameras, wireless microphones, and position sensors, then plays back and processes the data to identify activity patterns specified by human analysts. The processing greatly reduces the amount of time that the analysts must spend in examining large amounts of data, enabling the analysts to concentrate on subsets of data that represent activities of interest. The CAA has potential for use in a variety of governmental and commercial applications, including planning for crews for future long space flights, designing facilities wherein humans must work in proximity for long times, improving crew training and measuring crew performance in military settings, human-factors and safety assessment, development of team procedures, and behavioral and ethnographic research. The data-acquisition hardware of the CAA (see figure) includes two video cameras: an overhead one aimed upward at a paraboloidal mirror on the ceiling and one mounted on a wall aimed in a downward slant toward the crew area. As many as four wireless microphones can be worn by crew members. The audio signals received from the microphones are digitized, then compressed in preparation for storage. Approximate locations of as many as four crew members are measured by use of a Cricket indoor location system. [The Cricket indoor location system includes ultrasonic/radio beacon and listener units. A Cricket beacon (in this case, worn by a crew member) simultaneously transmits a pulse of ultrasound and a radio signal that contains identifying information. Each Cricket listener unit measures the difference between the times of reception of the ultrasound and radio signals from an identified beacon

Coordination strategies of crew management

NASA Technical Reports Server (NTRS)

Conley, Sharon; Cano, Yvonne; Bryant, Don

1991-01-01

An exploratory study that describes and contrasts two three-person flight crews performing in a B-727 simulator is presented. This study specifically attempts to delineate crew communication patterns accounting for measured differences in performance across routine and nonroutine flight patterns. The communication patterns in the two crews evaluated indicated different modes of coordination, i.e., standardization in the less effective crew and planning/mutual adjustment in the more effective crew.

Low Dose High Energy X-ray In-Line Phase Sensitive Imaging Prototype: Investigation of Optimal Geometric Conditions and Design Parameters

PubMed Central

Ghani, Muhammad. U.; Yan, Aimin; Wong, Molly. D.; Li, Yuhua; Ren, Liqiang; Wu, Xizeng; Liu, Hong

2016-01-01

The objective of this study was to investigate the optimization of a high energy in-line phase sensitive x-ray imaging prototype under different geometric and operating conditions for mammography application. A phase retrieval algorithm based on phase attenuation duality (PAD) was applied to the phase contrast images acquired by the prototype. Imaging performance was investigated at four magnification values of 1.67, 2, 2.5 and 3 using an acrylic edge, an American College of Radiology (ACR) mammography phantom and contrast detail (CD) phantom with tube potentials of 100, 120 and 140 kVp. The ACR and CD images were acquired at the same mean glandular dose (MGD) of 1.29 mGy with a computed radiography (CR) detector of 43.75 µm pixel pitch at a fixed source to image distance (SID) of 170 cm. The x-ray tube focal spot size was kept constant as 7 µm while a 2.5 mm thick aluminum (Al) filter was used for beam hardening. The performance of phase contrast and phase retrieved images were compared with computer simulations based on the relative phase contrast factor (RPF) at high x-ray energies. The imaging results showed that the x-ray tube operated at 100 kVp under the magnification of 2.5 exhibits superior imaging performance which is in accordance to the computer simulations. As compared to the phase contrast images, the phase retrieved images of the ACR and CD phantoms demonstrated improved imaging contrast and target discrimination. We compared the CD phantom images acquired in conventional contact mode with and without the anti-scatter grid using the same prototype at 1.295 mGy and 2.59 mGy using 40 kVp, a 25 µm rhodium (Rh) filter. At the same radiation dose, the phase sensitive images provided improved detection capabilities for both the large and small discs, while compared to the double dose image acquired in conventional mode, the observer study also indicated that the phase sensitive images provided improved detection capabilities for the large discs. This

STS-112 crew leave the crew transport vehicle after landing

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- As the STS-112 crew leaves the crew transport vehicle, they are greeted by mission managers and guests. The crew, from left, are Mission Specialists David Wolf, Fyodor Yurchikhin and Sandra Magnus; Pilot Pamela Melroy; Piers Sellers (talking to Acting Deputy Director JoAnn Morgan) and Commander Jeffrey Ashby (talking to Launch Director Mike Leinbach). Morgan is also Director of External Relations and Business Development. The crew returned to KSC after completing a 4.5-million-mile journey to the International Space Station. Main gear touchdown occurred at 11:43:40 a.m. EDT; nose gear touchdown at 11:43:48 a.m.; and wheel stop at 11:44:35 a.m. Mission elapsed time was 10:19:58:44. Mission STS-112 expanded the size of the Station with the addition of the S1 truss segment. .

Imaging Schwarzschild multilayer X-ray microscope

NASA Technical Reports Server (NTRS)

Hoover, Richard B.; Baker, Phillip C.; Shealy, David L.; Core, David B.; Walker, Arthur B. C., Jr.; Barbee, Troy W., Jr.; Kerstetter, Ted

1993-01-01

We have designed, analyzed, fabricated, and tested Schwarzschild multilayer X-ray microscopes. These instruments use flow-polished Zerodur mirror substrates which have been coated with multilayers optimized for maximum reflectivity at normal incidence at 135 A. They are being developed as prototypes for the Water Window Imaging X-Ray Microscope. Ultrasmooth mirror sets of hemlite grade sapphire have been fabricated and they are now being coated with multilayers to reflect soft X-rays at 38 A, within the biologically important 'water window'. In this paper, we discuss the fabrication of the microscope optics and structural components as well as the mounting of the optics and assembly of the microscopes. We also describe the optical alignment, interferometric and visible light testing of the microscopes, present interferometrically measured performance data, and provide the first results of optical imaging tests.

Asteroid Redirect Crewed Mission Space Suit and EVA System Maturation

NASA Technical Reports Server (NTRS)

Bowie, Jonathan T.; Kelly, Cody; Buffington, Jesse; Watson, Richard D.

2015-01-01

The Asteroid Redirect Crewed Mission (ARCM) requires a Launch/Entry/Abort (LEA) suit capability and short duration Extra Vehicular Activity (EVA) capability from the Orion spacecraft. For this mission, the pressure garment that was selected, for both functions, is the Modified Advanced Crew Escape Suit (MACES) with EVA enhancements and the life support option that was selected is the Exploration Portable Life Support System (PLSS). The proposed architecture was found to meet the mission constraints, but much more work is required to determine the details of the required suit upgrades, the integration with the PLSS, and the rest of the tools and equipment required to accomplish the mission. This work has continued over the last year to better define the operations and hardware maturation of these systems. EVA simulations have been completed in the NBL and interfacing options have been prototyped and analyzed with testing planned for late 2014. For NBL EVA simulations, in 2013, components were procured to allow in-house build up for four new suits with mobility enhancements built into the arms. Boots outfitted with clips that fit into foot restraints have also been added to the suit and analyzed for possible loads. Major suit objectives accomplished this year in testing include: evaluation of mobility enhancements, ingress/egress of foot restraint, use of foot restraint for worksite stability, ingress/egress of Orion hatch with PLSS mockup, and testing with two crew members in the water at one time to evaluate the crew's ability to help one another. Major tool objectives accomplished this year include using various other methods for worksite stability, testing new methods for asteroid geologic sampling and improving the fidelity of the mockups and crew equipment. These tests were completed on a medium fidelity capsule mockup, asteroid vehicle mockup, and asteroid mockups that were more accurate for an asteroid type EVA than previous tests. Another focus was the

NASA Ares I Crew Launch Vehicle Upper Stage Overview

NASA Technical Reports Server (NTRS)

Davis, Daniel J.

2008-01-01

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares 1-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.

NASA Ares I Crew Launch Vehicle Upper Stage Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares I-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.

CCP Astronauts at LC 39A and SpaceX Recovery Ship

NASA Image and Video Library

2018-03-28

At Cape Canaveral Air Force Station's Naval Ordnance Test Unit basin in Florida, Commercial Crew Program astronaut Eric Boe observes operation of the SpaceX recovery ship. During a recent visit to the Kennedy Space Center, the crew members were given an up-close look at preparations for the SpaceX Crew Dragon flight tests.

CCP Astronauts at LC 39A and SpaceX Recovery Ship

NASA Image and Video Library

2018-03-28

At Cape Canaveral Air Force Station's Naval Ordnance Test Unit basin in Florida, Commercial Crew Program astronaut Bob Behnken observes operation of the SpaceX recovery ship. During a recent visit to the Kennedy Space Center, the crew members were given an up-close look at preparations for the SpaceX Crew Dragon flight tests.

CCP Astronauts at LC 39A and SpaceX Recovery Ship

NASA Image and Video Library

2018-03-28

At Cape Canaveral Air Force Station's Naval Ordnance Test Unit basin in Florida, Commercial Crew Program astronaut Suni Williams observes operation of the SpaceX recovery ship. During a recent visit to the Kennedy Space Center, the crew members were given an up-close look at preparations for the SpaceX Crew Dragon flight tests.

CCP Astronauts at LC 39A and SpaceX Recovery Ship

NASA Image and Video Library

2018-03-28

At Cape Canaveral Air Force Station's Naval Ordnance Test Unit basin in Florida, Commercial Crew Program astronaut Doug Hurley observes operation of the SpaceX recovery ship. During a recent visit to the Kennedy Space Center, the crew members were given an up-close look at preparations for the SpaceX Crew Dragon flight tests.

Antenna Measurements: Test & Analysis of the Radiated Emissions/Immunity of the NASA/Orion Spacecraft Dart Parachute Simulator & Prototype Capsule - The Crew Exploration Vehicle

NASA Technical Reports Server (NTRS)

Norgard, John D.

2012-01-01

For future NASA Manned Space Exploration of the Moon and Mars, a blunt body capsule, called the Orion Crew Exploration Vehicle (CEV), composed of a Crew Module (CM) and a Service Module (SM), with a parachute decent assembly is planned for reentry back to Earth. A Capsule Parachute Assembly System (CPAS) is being developed for preliminary prototype parachute drop tests at the Yuma Proving Ground (YPG) to simulate high-speed reentry to Earth from beyond Low-Earth-Orbit (LEO) and to provide measurements of position, velocity, acceleration, attitude, temperature, pressure, humidity, and parachute loads. The primary and secondary (backup) avionics systems on CPAS also provide mission critical firing events to deploy, reef, and release the parachutes in three stages (extraction, drogues, mains) using mortars and pressure cartridge assemblies. In addition, a Mid-Air Delivery System (MDS) is used to separate the capsule from the sled that is used to eject the capsule from the back of the drop plane. Also, high-speed and high-definition cameras in a Video Camera System (VCS) are used to film the drop plane extraction and parachute landing events. Intentional and unintentional radiation emitted from and received by antennas and electronic devices on/in the CEV capsule, the MDS sled, and the VCS system are being tested for radiated emissions/immunity (susceptibility) (RE/RS). To verify Electromagnetic Compatibility (EMC) of the Orion capsule, Electromagnetic Interference (EMI) measurements are being made inside a semi-anechoic chamber at NASA/JSC on the components of the CPAS system. Measurements are made at 1m from the components-under-test (CUT). In addition, EMI measurements of the integrated CEV system are being made inside a hanger at YPG. These measurements are made in a complete circle, at 30? angles or less, around the Orion Capsule, the spacecraft system under-test (SUT). Near-field B-Dot probe measurements on the surface of the Orion capsule are being extrapolated

X-ray mirror prototype based on cold shaping of thin glass foils

NASA Astrophysics Data System (ADS)

Basso, Stefano; Civitani, Marta; Ghigo, Mauro; Hołyszko, Joanna; Pareschi, Giovanni; Salmaso, Bianca; Vecchi, Gabriele; Burwitz, Vadim; Pelliciari, Carlo; Hartner, Gisela D.; Breunig, Elias

2017-08-01

The Slumping Glass Optics technology for the fabrication of astronomical X-ray mirrors has been developed in recent years in USA and Europe. The process has been used for making the mirrors of the Nustar, mission. The process starts with very thin glass foils hot formed to copy the profile of replication moulds. At INAF - Osservatorio Astronomico di Brera a process based on cold shaping is being developed, based on an integration method involving the use of interconnecting ribs for making stacks. Each glass foil in the stack is shaped onto a very precise integration mould and the correct shape is frozen by means of glued ribs that act as spacers between one layer and the next one (the first layers being attached to a thick substrate). Therefore, the increasing availability of flexible glass foils with a thickness of a few tens of microns (driven by electronic market for ultra-thin displays) opens new possibilities for the fabrication of X-ray mirrors. This solution appears interesting especially for the fabrication of mirrors for hard X-rays (with energy > 10 keV) based on multilayer coatings, taking advantage from the intrinsic low roughness of the glass foils that should grant a low scattering level. The stress frozen on the glass due to the cold shaping is not negligible, but it is kept into account in the errors of the X-ray optics design. As an exercise, we have considered the requirements and specs of the FORCE hard Xray mission concept (being studied by JAXA) and we have designed the mirror modules assuming the cold slumping as a fabrication method. In the meantime, a prototype (representative of the FORCE mirror modules) is being design and integrated in order to demonstrate the feasibility and the capacity to reach good angular resolution.

Solid Modeling of Crew Exploration Vehicle Structure Concepts for Mass Optimization

NASA Technical Reports Server (NTRS)

Mukhopadhyay, Vivek

2006-01-01

Parametric solid and surface models of the crew exploration vehicle (CEV) command module (CM) structure concepts are developed for rapid finite element analyses, structural sizing and estimation of optimal structural mass. The effects of the structural configuration and critical design parameters on the stress distribution are visualized, examined to arrive at an efficient design. The CM structural components consisted of the outer heat shield, inner pressurized crew cabin, ring bulkhead and spars. For this study only the internal cabin pressure load case is considered. Component stress, deflection, margins of safety and mass are used as design goodness criteria. The design scenario is explored by changing the component thickness parameters and materials until an acceptable design is achieved. Aluminum alloy, titanium alloy and an advanced composite material properties are considered for the stress analysis and the results are compared as a part of lessons learned and to build up a structural component sizing knowledge base for the future CEV technology support. This independent structural analysis and the design scenario based optimization process may also facilitate better CM structural definition and rapid prototyping.

The "Digital Friend": A knowledge-based decision support system for space crews

NASA Astrophysics Data System (ADS)

Hoermann, Hans-Juergen; Johannes, Bernd; Petrovich Salnitski, Vyacheslav

Space travel of far distances presents exceptional strain on the medical and psychological well-being of the astronauts who undertake such missions. An intelligent knowledge management system has been developed, to assist space crews on long-duration missions as an autonomous decision support system, called the "Digital Friend". This system will become available upon request for the purpose of coaching group processes and individual performance levels as well as aiding in tactical decision processes by taking crew condition parameters into account. In its initial stage, the "Digital Friend" utilizes interconnected layers of knowledge, which encompass relevant models of operational, situational, individual psycho-physiological as well as group processes. An example is the human life science model that contains historic, diagnostic, and prognostic knowledge about the habitual, actual, and anticipated patterns of physiological, cognitive, and group psychology parameters of the crew members. Depending on the available data derived from pre-mission screening, regular check-ups, or non-intrusive onboard monitoring, the "Digital Friend" can generate a situational analysis and diagnose potential problems. When coping with the effects of foreseeable and unforeseen stressors encountered during the mission, the system can provide feedback and support the crew with a recommended course of actions. The first prototype of the "Digital Friend" employs the Neurolab/Healthlab platform developed in a cooperation of DLR and IBMP. The prototype contains psycho-physiological sensors with multiple Heally Satellites that relay data to the intelligent Heally Masters and a telemetric Host station. The analysis of data from a long-term simulation study illustrates how the system can be used to estimate the operators' current level of skill reliability based on Salnitski's model [V. Salnitski, A. Bobrov, A. Dudukin, B. Johannes, Reanalysis of operators reliability in professional skills

CCP Astronauts at LC 39A and SpaceX Recovery Ship

NASA Image and Video Library

2018-03-28

At Cape Canaveral Air Force Station's Naval Ordnance Test Unit basin in Florida, Commercial Crew Program astronaut Doug Hurley, right, observes operation of the SpaceX recovery ship. During a recent visit to the Kennedy Space Center, the crew members were given an up-close look at preparations for the SpaceX Crew Dragon flight tests.

STS-99 crew respond to media at SLF

NASA Technical Reports Server (NTRS)

2000-01-01

After landing at the Shuttle Landing Facility aboard T-38 jet aircraft, the STS-99 crew addresses the media. Standing, left to right, are Mission Specialists Gerhard Thiele of Germany and Mamoru Mohri of Japan, Commander Kevin Kregel (at the microphone), Mission Specialists Janice Voss and Janet Kavandi, and Pilot Dominic Gorie. They are ready to prepare for the second launch attempt of Endeavour Feb. 11 at 12:30 p.m. EST from Launch Pad 39A. The earlier launch scheduled for Jan. 31 was scrubbed due to poor weather and a faulty Enhanced Master Events Controller in the orbiter's aft compartment. Over the next few days, the crew will review mission procedures, conduct test flights in the Shuttle Training Aircraft and undergo routine preflight medical exams. STS-99 is the Shuttle Radar Topography Mission, which will produce unrivaled 3-D images of the Earth's surface. The result of the Shuttle Radar Topography Mission could be close to 1 trillion measurements of the Earth's topography. Landing is expected at KSC on Feb. 22 at 4:36 p.m. EST.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-12-26

ISS038-E-021401 (24 Dec. 2013) --- The Caribbean country of Cuba is pictured in this high oblique image, photographed by one of the Expedition 38 crew members aboard the International Space Station. Andros ISland, part of the Bahamas, is Cuba is an archipelago of islands in the northern Caribbean Sea at the confluence with the Gulf of Mexico and the Atlantic Ocean. A Russian Soyuz spacecraft is docked to the station.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2014-01-05

ISS038-E-025812 (5 Feb. 2014) --- One of the Expedition 38 crew members aboard the International Space Station used a 400mm lens to expose this vertical view of the general area of the 2014 Winter Olympics. Sochi is a city in Krasnodar Krai, Russia, located on the Black Sea coast near the border between Georgia/Abkhazia and Russia. It has an area of 1,353 square miles or 3,505 square kilometers.

STS-111 Crew Training Clip

NASA Technical Reports Server (NTRS)

2002-01-01

The STS-111 Crew is in training for space flight. The crew consists of Commander Ken Cockrell, Pilot Paul Lockhart, Mission Specialists Franklin Chang-Diaz and Philippe Perrin. The crew training begins with Post Insertion Operations with the Full Fuselage Trainer (FFT). Franklin Chang-Diaz, Philippe Perrin and Paul Lockhart are shown in training for airlock and Neutral Buoyancy Lab (NBL) activities. Bailout in Crew Compartment Training (CCT) with Expedition Five is also shown. The crew also gets experience with photography, television, and habitation equipment.

Crew Transportation Plan

NASA Technical Reports Server (NTRS)

Zeitler, Pamela S. (Compiler); Mango, Edward J.

2013-01-01

The National Aeronautics and Space Administration (NASA) Commercial Crew Program (CCP) has been chartered to facilitate the development of a United States (U.S.) commercial crew space transportation capability with the goal of achieving safe, reliable, and cost effective access to and from low Earth orbit (LEO) and the International Space Station (ISS) as soon as possible. Once the capability is matured and is available to the Government and other customers, NASA expects to purchase commercial services to meet its ISS crew rotation and emergency return objectives.

STS 51-L crewmembers at Ellington AFB for training flight in T-38

NASA Image and Video Library

1986-01-08

S86-25199 (September 1985) --- Three members of the STS-51L prime crew and a backup crew member walk away from the flight line at nearby Ellington Field following flights in the T-38 jet trainers seen in the background. Sharon Christa McAuliffe (center right), payload specialist/citizen observer for the Teacher-in-Space Project, and Barbara R. Morgan (center left), her backup, are flanked by astronauts Francis R. (Dick) Scobee (right), mission commander, and Michael J. Smith, pilot. The photo was taken by Keith Meyers of the New York Times. EDITOR?S NOTE: The STS-51L crew members lost their lives in the space shuttle Challenger accident moments after launch on Jan. 28, 1986 from the Kennedy Space Center (KSC). Photo credit: NASA

Orion Pad Abort 1 Crew Module Mass Properties Test Approach and Results

NASA Technical Reports Server (NTRS)

Herrera, Claudia; Harding, Adam

2012-01-01

The Flight Loads Laboratory at the Dryden Flight Research Center conducted tests to measure the inertia properties of the Orion Pad Abort 1 (PA-1) Crew Module (CM). These measurements were taken to validate analytical predictions of the inertia properties of the vehicle and assist in reducing uncertainty for derived aero performance coefficients to be calculated post-launch. The first test conducted was to determine the Ixx of the Crew Module. This test approach used a modified torsion pendulum test setup that allowed the suspended Crew Module to rotate about the x axis. The second test used a different approach to measure both the Iyy and Izz properties. This test used a Knife Edge fixture that allowed small rotation of the Crew Module about the y and z axes. Discussions of the techniques and equations used to accomplish each test are presented. Comparisons with the predicted values used for the final flight calculations are made. Problem areas, with explanations and recommendations where available, are addressed. Finally, an evaluation of the value and success of these techniques to measure the moments of inertia of the Crew Module is provided.

Sharing Data between Mobile Devices, Connected Vehicles and Infrastructure Task 10: D2X Hub Prototype Acceptance Test Plan and Summary Report.

DOT National Transportation Integrated Search

2017-10-27

This Devices to Everything (D2X) Acceptance Test Plan (ATP) and Summary Report provides the plan, test cases, and test procedures that were used to verify Prototype System (version 2.0) system requirements, as well as a summary of results of the test...

Enroute flight-path planning - Cooperative performance of flight crews and knowledge-based systems

NASA Technical Reports Server (NTRS)

Smith, Philip J.; Mccoy, Elaine; Layton, Chuck; Galdes, Deb

1989-01-01

Interface design issues associated with the introduction of knowledge-based systems into the cockpit are discussed. Such issues include not only questions about display and control design, they also include deeper system design issues such as questions about the alternative roles and responsibilities of the flight crew and the computer system. In addition, the feasibility of using enroute flight path planning as a context for exploring such research questions is considered. In particular, the development of a prototyping shell that allows rapid design and study of alternative interfaces and system designs is discussed.

Cancer incidence in professional flight crew and air traffic control officers: disentangling the effect of occupational versus lifestyle exposures.

PubMed

dos Santos Silva, Isabel; De Stavola, Bianca; Pizzi, Costanza; Evans, Anthony D; Evans, Sally A

2013-01-15

Flight crew are occupationally exposed to several potentially carcinogenic hazards; however, previous investigations have been hampered by lack of information on lifestyle exposures. The authors identified, through the United Kingdom Civil Aviation Authority medical records, a cohort of 16,329 flight crew and 3,165 air traffic control officers (ATCOs) and assembled data on their occupational and lifestyle exposures. Standardised incidence ratios (SIRs) were estimated to compare cancer incidence in each occupation to that of the general population; internal analyses were conducted by fitting Cox regression models. All-cancer incidence was 20-29% lower in each occupation than in the general population, mainly due to a lower incidence of smoking-related cancers [SIR (95% CI) = 0.33 (0.27-0.38) and 0.42 (0.28-0.60) for flight crew and ATCOs, respectively], consistent with their much lower prevalence of smoking. Skin melanoma rates were increased in both flight crew (SIR = 1.87; 95% CI = 1.45-2.38) and ATCOs (2.66; 1.55-4.25), with rates among the former increasing with increasing number of flight hours (p-trend = 0.02). However, internal analyses revealed no differences in skin melanoma rates between flight crew and ATCOs (hazard ratio: 0.78, 95% CI = 0.37-1.66) and identified skin that burns easily when exposed to sunlight (p = 0.001) and sunbathing to get a tan (p = 0.07) as the strongest risk predictors of skin melanoma in both occupations. The similar site-specific cancer risks between the two occupational groups argue against risks among flight crew being driven by occupation-specific exposures. The skin melanoma excess reflects sun-related behaviour rather than cosmic radiation exposure. Copyright © 2012 UICC.

Full-Scale Crash Test and Finite Element Simulation of a Composite Prototype Helicopter

NASA Technical Reports Server (NTRS)

Jackson, Karen E.; Fasanella, Edwin L.; Boitnott, Richard L.; Lyle, Karen H.

2003-01-01

A full-scale crash test of a prototype composite helicopter was performed at the Impact Dynamics Research Facility at NASA Langley Research Center in 1999 to obtain data for validation of a finite element crash simulation. The helicopter was the flight test article built by Sikorsky Aircraft during the Advanced Composite Airframe Program (ACAP). The composite helicopter was designed to meet the stringent Military Standard (MIL-STD-1290A) crashworthiness criteria and was outfitted with two crew and two troop seats and four anthropomorphic dummies. The test was performed at 38-ft/s vertical and 32.5-ft/s horizontal velocity onto a rigid surface. An existing modal-vibration model of the Sikorsky ACAP helicopter was converted into a model suitable for crash simulation. A two-stage modeling approach was implemented and an external user-defined subroutine was developed to represent the complex landing gear response. The crash simulation was executed with a nonlinear, explicit transient dynamic finite element code. Predictions of structural deformation and failure, the sequence of events, and the dynamic response of the airframe structure were generated and the numerical results were correlated with the experimental data to validate the simulation. The test results, the model development, and the test-analysis correlation are described.

Orbiter fire rescue and crew escape training for EVA crew systems support

NASA Image and Video Library

1993-01-28

Photos of orbiter fire rescue and crew escape training for extravehicular activity (EVA) crew systems support conducted in Bldg 9A Crew Compartment Trainer (CCT) and Fuel Fuselage Trainer (FFT) include views of CCT interior of middeck starboard fuselage showing middeck forward (MF) locker and COAS assembly filter, artiflex film and camcorder bag (26834); launch/entry suit (LES) helmet assembly, neckring and helmet hold-down assembly (26835-26836); middeck aft (MA) lockers (26837); area of middeck airlock and crew escape pole (26838); connectors of crew escape pole in the middeck (268390); three test subjects in LES in the flight deck (26840); emergency side hatch slide before inflated stowage (26841); area of below adjacent to floor panel MD23R (26842); a test subject in LES in the flight deck (26843); control board and also showing sign of "orbital maneuvering system (OMS) secure and OMS TK" (26844); test subject in the flight deck also showing chart of "ascent/abort summary" (26845).

American X-Vehicles: An Inventory, X-1 to X-45

NASA Technical Reports Server (NTRS)

Miller, Jay; Jenkins, Dennis R.

2000-01-01

For a while, it seemed the series of experimental aircraft sponsored by the Air Force and the National Aeronautics and Space Administration had run its course. Between the late 1940s and the late 1970s, almost thirty designations had been allocated to aircraft meant to explore new flight regimes or untried technologies. Then, largely, it ended. But there was a resurgence in the mid- to late-1990s, and as we enter the year 2000 the designations are up to X-45. Many have a misconception that X-Planes have always explored the high-speed and high-altitude flight regimes, something popularized by Chuck Yeager in the original X-1 and the exploits of the twelve men that flew the X-15. Although these flight regimes have always been in the spotlight, many others have been explored by X-Planes. The little Bensen X-25 never exceeded 85 mph, and others were limited to speeds of several hundred mph. There has been some criticism that the use of X designations has been corrupted somewhat by including what are essentially prototypes of future operational aircraft, especially the two JSF demonstrators. But this is not new-the X-11 and X-12 from the 1950s were going to be prototypes of the Atlas intercontinental ballistic missile, and the still-born Lockheed X-27 was always intended as a prototype of a production aircraft. So although this practice does not represent the best use of X designations it is not without precedent. This document is an inventory of the experimental aircraft starting with the X-1 aircraft and ending with the X-45 aircraft.

STS-96 Crew Training

NASA Technical Reports Server (NTRS)

1999-01-01

The training for the crew members of the STS-96 Discovery Shuttle is presented. Crew members are Kent Rominger, Commander; Rick Husband, Pilot; Mission Specialists, Tamara Jernigan, Ellen Ochoa, and Daniel Barry; Julie Payette, Mission Specialist (CSA); and Valery Ivanovich Tokarev, Mission Specialist (RSA). Scenes show the crew sitting and talking about the Electrical Power System; actively taking part in virtual training in the EVA Training VR (Virtual Reality) Lab; using the Orbit Space Vision Training System; being dropped in water as a part of the Bail-Out Training Program; and taking part in the crew photo session.

Apollo experience report: Crew station integration. Volume 1: Crew station design and development

NASA Technical Reports Server (NTRS)

Allen, L. D.; Nussman, D. A.

1976-01-01

An overview of the evolution of the design and development of the Apollo command module and lunar module crew stations is given, with emphasis placed on the period from 1964 to 1969. The organizational planning, engineering techniques, and documentation involved are described, and a detailed chronology of the meetings, reviews, and exercises is presented. Crew station anomalies for the Apollo 7 to 11 missions are discussed, and recommendations for the solution of recurring problems of crew station acoustics, instrument glass failure, and caution and warning system performance are presented. Photographs of the various crew station configurations are also provided.

Direct hot slumping and accurate integration process to manufacture prototypal x-ray optical units made of glass

NASA Astrophysics Data System (ADS)

Civitani, M.; Ghigo, M.; Basso, S.; Proserpio, L.; Spiga, D.; Salmaso, B.; Pareschi, G.; Tagliaferri, G.; Burwitz, V.; Hartner, G.; Menz, B.; Bavdaz, M.; Wille, E.

2013-09-01

X-ray telescopes with very large collecting area, like the proposed International X-ray Observatory (IXO, with around 3 m2 at 1 keV), need to be composed of a large number high quality mirror segments, aiming at achieving an angular resolution better than 5 arcsec HEW (Half-Energy-Width). A possible technology to manufacture the modular elements that will compose the entire optical module, named X-ray Optical Units (XOUs), consists of stacking in Wolter-I configuration several layers of thin foils of borosilicate glass, previously formed by hot slumping. The XOUs are subsequently assembled to form complete multi-shell optics with Wolter-I geometry. The achievable global angular resolution of the optic relies on the required surface shape accuracy of slumped foils, on the smoothness of the mirror surfaces and on the correct integration and co-alignment of the mirror segments. The Brera Astronomical Observatory (INAF-OAB) is leading a study, supported by ESA, concerning the implementation of the IXO telescopes based on thin slumped glass foils. In addition to the opto-mechanical design, the study foresees the development of a direct hot slumping thin glass foils production technology. Moreover, an innovative assembly concept making use of Wolter-I counter-form moulds and glass reinforcing ribs is under development. The ribs connect pairs of consecutive foils in an XOU stack, playing a structural and a functional role. In fact, as the ribs constrain the foil profile to the correct shape during the bonding, they damp the low-frequency profile errors still present on the foil after slumping. A dedicated semirobotic Integration MAchine (IMA) has been realized to this scope and used to build a few integrated prototypes made of several layers of slumped plates. In this paper we provide an overview of the project, we report the results achieved so far, including full illumination intra-focus X-ray tests of the last integrated prototype that are compliant with a HEW of

Monitoring of Crew Activity with FAMOS

NASA Astrophysics Data System (ADS)

Wolf, L.; Cajochen, C.; Bromundt, V.

2007-10-01

The success of long duration space missions, such as manned missions to Mars, depends on high and sustained levels of vigilance and performance of astronauts and operators working in the technology rich environment of a spacecraft. Experiment 'Monitoring of Crew Activity with FAMOS' was set up to obtain operational experience with complimentary methods / technologies to assess the alertness / sleepiness status of selected AustroMars crewmembers on a daily basis. We applied a neurobehavioral test battery consisting of 1) Karolinska Sleepiness Scale KSS, 2) Karolinska Drowsiness Test KDT, 3) Psychomotor Vigilance Task PVT, combined with 4) left eye video recordings with an early prototype of the FAMOS Fatigue Monitoring System headset currently being developed by Sowoon Technologies (CH), and 5) Actiwatches that were worn continuously. A test battery required approximately 15 minutes and was repeated up to 4 times daily by 2 to 4 subjects. Here we present the data analysis of methods 1, 2, 3, and 5, while data analysis of method 4 is still in progress.

The STS-108 crew look over MPLM during Crew Equipment Interface Test

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The STS-108 crew pause during their checkout of the Multi-Purpose Logistics Module Raffaello. From left are Commander Dominic L. Gorie, Mission Specialist Daniel M. Tani, Pilot Mark E. Kelly and Mission Specialist Linda A. Godwin. The four astronauts are taking part in Crew Equipment Interface Test (CEIT) activities at KSC. The CEIT provides familiarization with the launch vehicle and payload. Mission STS-108 is a Utilization Flight (UF-1), carrying the Expedition Four crew plus Multi-Purpose Logistics Module Raffaello to the International Space Station. The Expedition Four crew comprises Yuri Onufriyenko, commander, Russian Aviation and Space Agency, and astronauts Daniel W. Bursch and Carl E. Walz. Endeavour is scheduled to launch Nov. 29 on mission STS-108.

The STS-108 crew look over MPLM during Crew Equipment Interface Test

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The STS-108 crew look into the hatch of the Multi-Purpose Logistics Module Raffaello. From left are Commander Dominic L. Gorie, Pilot Mark E. Kelly, and Mission Specialists Linda A. Godwin and Daniel M. Tani. The four astronauts are taking part in Crew Equipment Interface Test (CEIT) activities at KSC. The CEIT provides familiarization with the launch vehicle and payload. Mission STS-108 is a Utilization Flight (UF-1), carrying the Expedition Four crew plus Multi-Purpose Logistics Module Raffaello to the International Space Station. The Expedition Four crew comprises Yuri Onufriyenko, commander, Russian Aviation and Space Agency, and astronauts Daniel W. Bursch and Carl E. Walz. Endeavour is scheduled to launch Nov. 29 on mission STS-108.

Virtual environment and computer-aided technologies used for system prototyping and requirements development

NASA Technical Reports Server (NTRS)

Logan, Cory; Maida, James; Goldsby, Michael; Clark, Jim; Wu, Liew; Prenger, Henk

1993-01-01

The Space Station Freedom (SSF) Data Management System (DMS) consists of distributed hardware and software which monitor and control the many onboard systems. Virtual environment and off-the-shelf computer technologies can be used at critical points in project development to aid in objectives and requirements development. Geometric models (images) coupled with off-the-shelf hardware and software technologies were used in The Space Station Mockup and Trainer Facility (SSMTF) Crew Operational Assessment Project. Rapid prototyping is shown to be a valuable tool for operational procedure and system hardware and software requirements development. The project objectives, hardware and software technologies used, data gained, current activities, future development and training objectives shall be discussed. The importance of defining prototyping objectives and staying focused while maintaining schedules are discussed along with project pitfalls.

Asteroid Redirect Crewed Mission Space Suit and EVA System Architecture Trade Study

NASA Technical Reports Server (NTRS)

Bowie, Jonathan; Buffington, Jesse; Hood, Drew; Kelly, Cody; Naids, Adam; Watson, Richard; Blanco, Raul; Sipila, Stephanie

2014-01-01

The Asteroid Redirect Crewed Mission (ARCM) requires a Launch/Entry/Abort (LEA) suit capability and short duration Extra Vehicular Activity (EVA) capability from the Orion spacecraft. For this mission, the pressure garment selected for both functions is the Modified Advanced Crew Escape Suit (MACES) with EVA enhancements and the life support option that was selected is the Exploration Portable Life Support System (PLSS) currently under development for Advanced Exploration Systems (AES). The proposed architecture meets the ARCM constraints, but much more work is required to determine the details of the suit upgrades, the integration with the PLSS, and the tools and equipment necessary to accomplish the mission. This work has continued over the last year to better define the operations and hardware maturation of these systems. EVA simulations were completed in the Neutral Buoyancy Lab (NBL) and interfacing options were prototyped and analyzed with testing planned for late 2014. This paper discusses the work done over the last year on the MACES enhancements, the use of tools while using the suit, and the integration of the PLSS with the MACES.

STS-112 Crew Interviews - Wolf

NASA Technical Reports Server (NTRS)

2002-01-01

STS-112 Mission Specialist David Wolf is seen during this preflight interview, where he first answers questions on his career path and role models. Other questions cover mission goals, ISS (International Space Station) Expedition 5 spacecrew, crew training, the S1 Truss and its radiators, the MBS (Mobile Base Structure), his experience onboard Mir, and his EVAs (extravehicular activities) on the coming mission. The EVAs are the subject of several questions. Wolf discusses his crew members, and elsewhere discusses Pilot Pamela Melroy's role as an IV crew member during EVAs. In addition, Wolf answers questions on transfer operations, the SHIMMER experiment, and his thoughts on multinational crews and crew bonding.

Technology for an intelligent, free-flying robot for crew and equipment retrieval in space

NASA Technical Reports Server (NTRS)

Erickson, J. D.; Reuter, G. J.; Healey, Kathleen J.; Phinney, D. E.

1990-01-01

Crew rescue and equipment retrieval is a Space Station Freedom requirement. During Freedom's lifetime, there is a high probability that a number of objects will accidently become separated. Members of the crew, replacement units, and key tools are examples. Retrieval of these objects within a short time is essential. Systems engineering studies were conducted to identify system requirements and candidate approaches. One such approach, based on a voice-supervised, intelligent, free-flying robot was selected for further analysis. A ground-based technology demonstration, now in its second phase, was designed to provide an integrated robotic hardware and software testbed supporting design of a space-borne system. The ground system, known as the EVA Retriever, is examining the problem of autonomously planning and executing a target rendezvous, grapple, and return to base while avoiding stationary and moving obstacles. The current prototype is an anthropomorphic manipulator unit with dexterous arms and hands attached to a robot body and latched in a manned maneuvering unit. A precision air-bearing floor is used to simulate space. Sensor data include two vision systems and force/proximity/tactile sensors on the hands and arms. Planning for a shuttle file experiment is underway. A set of scenarios and strawman requirements were defined to support conceptual development. Initial design activities are expected to begin in late 1989 with the flight occurring in 1994. The flight hardware and software will be based on lessons learned from both the ground prototype and computer simulations.

A Compact Prototype of an Optical Pattern Recognition System

NASA Technical Reports Server (NTRS)

Jin, Y.; Liu, H. K.; Marzwell, N. I.

1996-01-01

In the Technology 2006 Case Studies/Success Stories presentation, we will describe and demonstrate a prototype of a compact optical pattern recognition system as an example of a successful technology transfer and continuuing development of state-of-the-art know-how by the close collaboration among government, academia, and small business via the NASA SBIR program. The prototype consists of a complete set of optical pattern recognition hardware with multi-channel storage and retrieval capability that is compactly configured inside a portable 1'X 2'X 3' aluminum case.

Integrated Testing Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Taylor, James L.; Cockrell, Charles E.; Tuma, Margaret L.; Askins, Bruce R.; Bland, Jeff D.; Davis, Stephan R.; Patterson, Alan F.; Taylor, Terry L.; Robinson, Kimberly L.

2008-01-01

The Ares I crew launch vehicle is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew and cargo access to the International Space Station (ISS) and, together with the Ares V cargo launch vehicle, serves as a critical component of NASA's future human exploration of the Moon. During the preliminary design phase, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements - including the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine - will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the upper stage Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle ground vibration test (IVGVT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, validate the ability of the upper stage to manage cryogenic propellants to achieve upper stage engine start conditions, and a high-altitude demonstration of the launch abort system (LAS) following stage separation. The Orion 1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Expedition 5 Crew Insignia

NASA Technical Reports Server (NTRS)

2002-01-01

JOHNSON SPACE CENTER, HOUSTON, TEXAS -- EXPEDITION FIVE CREW INSIGNIA (ISS05-S-001) -- The International Space Station (ISS) Expedition Five patch depicts the Station in its completed configuration and represents the vision of mankind's first step as a permanent human presence in space. The United States and Russian flags are joined together in a Roman numeral V to represent both the nationalities of the crew and the fifth crew to live aboard the ISS. Crew members' names are shown in the border of this patch. This increment encompasses a new phase in growth for the Station, with three Shuttle crews delivering critical components and building blocks to the ISS. To signify the participation of each crew member, the Shuttle is docked to the Station beneath a constellation of 17 stars symbolizing all those visiting and living aboard Station during this increment. The NASA insignia design for Shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the forms of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, the change will be publicly announced.

Crew Transportation Technical Management Processes

NASA Technical Reports Server (NTRS)

Mckinnie, John M. (Compiler); Lueders, Kathryn L. (Compiler)

2013-01-01

Under the guidance of processes provided by Crew Transportation Plan (CCT-PLN-1100), this document, with its sister documents, International Space Station (ISS) Crew Transportation and Services Requirements Document (CCT-REQ-1130), Crew Transportation Technical Standards and Design Evaluation Criteria (CCT-STD-1140), Crew Transportation Operations Standards (CCT STD-1150), and ISS to Commercial Orbital Transportation Services Interface Requirements Document (SSP 50808), provides the basis for a National Aeronautics and Space Administration (NASA) certification for services to the ISS for the Commercial Provider. When NASA Crew Transportation System (CTS) certification is achieved for ISS transportation, the Commercial Provider will be eligible to provide services to and from the ISS during the services phase.

International Space Station Crew Restraint Design

NASA Technical Reports Server (NTRS)

Whitmore, M.; Norris, L.; Holden, K.

2005-01-01

With permanent human presence onboard the International Space Station (ISS), crews will be living and working in microgravity, dealing with the challenges of a weightless environment. In addition, the confined nature of the spacecraft environment results in ergonomic challenges such as limited visibility and access to the activity areas, as well as prolonged periods of unnatural postures. Without optimum restraints, crewmembers may be handicapped for performing some of the on-orbit tasks. Currently, many of the tasks on ISS are performed with the crew restrained merely by hooking their arms or toes around handrails to steady themselves. This is adequate for some tasks, but not all. There have been some reports of discomfort/calluses on the top of the toes. In addition, this type of restraint is simply insufficient for tasks that require a large degree of stability. Glovebox design is a good example of a confined workstation concept requiring stability for successful use. They are widely used in industry, university, and government laboratories, as well as in the space environment, and are known to cause postural limitations and visual restrictions. Although there are numerous guidelines pertaining to ventilation, seals, and glove attachment, most of the data have been gathered in a 1-g environment, or are from studies that were conducted prior to the early 1980 s. Little is known about how best to restrain a crewmember using a glovebox in microgravity. In 2004, The Usability Testing and Analysis Facility (UTAF) at the NASA Johnson Space Center completed development/evaluation of several design concepts for crew restraints to meet the various needs outlined above. Restraints were designed for general purpose use, for teleoperation (Robonaut) and for use with the Life Sciences Glovebox. All design efforts followed a human factors engineering design lifecycle, beginning with identification of requirements followed by an iterative prototype/test cycle. Anthropometric

Integrated System Test Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Cockrell, Charles E., Jr.; Askins, Bruce R.; Bland, Jeffrey; Davis, Stephan; Holladay, Jon B.; Taylor, James L.; Taylor, Terry L.; Robinson, Kimberly F.; Roberts, Ryan E.; Tuma, Margaret

2007-01-01

The Ares I Crew Launch Vehicle (CLV) is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew access to the International Space Station (ISS) and, together with the Ares V Cargo Launch Vehicle (CaLV), serves as one component of a future launch capability for human exploration of the Moon. During the system requirements definition process and early design cycles, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements: the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine, will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle dynamic test (IVDT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, and a highaltitude actuation of the launch abort system (LAS) following separation. The Orion-1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-12-23

ISS038-E-019899 (23 Dec. 2013) --- The Caribbean country of Cuba appears at the top of this high oblique image, photographed by one of the Expedition 38 crew members aboard the International Space Station. Andros Island, part of the Bahamas, is in the bottom of the frame. Cuba is an archipelago of islands in the northern Caribbean Sea at the confluence with the Gulf of Mexico and the Atlantic Ocean. A Russian Soyuz spacecraft is docked to the station.

Earth observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-12-12

ISS038-E-015162 (12 Dec. 2013) --- One of the Expedition 38 crew members took this brightly lit night picture featuring much of the Houston metropolitan area. The central business district is in the exact center of the photo, with the Galleria area and uptown being in the lower left with Sugar Land being closer to the lower left corner. The 610 Loop and Beltway 8 encircle the city. The southeast sections extend past Hobby Airport to the NASA/Clear Lake area.

Earth observations taken by Expedition 38 crewmember

NASA Image and Video Library

2013-12-12

ISS038-E-015160 (12 Dec. 2013) --- One of the Expedition 38 crew members took this brightly lit night picture featuring much of the Houston metropolitan area. The central business district is in the exact center of the photo, with the Galleria area and uptown being in the lower left with Sugar Land being closer to the lower left corner. The 610 Loop and Beltway 8 encircle the city. The southeast sections extend past Hobby Airport to the NASA/Clear Lake area.

STS-38 crewmembers participate in photography training and camera briefing

NASA Image and Video Library

1990-03-01

STS-38 crewmembers listen as RSOC-JSC crew trainer M. Judy Alexander explains the camera equipment they will be using on their upcoming Department of Defense (DOD) mission. Left to right are Pilot Frank L. Culbertson, Mission Specialist (MS) Carl J. Meade, and MS Charles D. Gemar. Alexander is holding a training version of the 70mm handheld HASSELBLAD camera.

STS-38 crewmembers participate in photography training and camera briefing

NASA Technical Reports Server (NTRS)

1990-01-01

STS-38 crewmembers listen as RSOC-JSC crew trainer M. Judy Alexander explains the camera equipment they will be using on their upcoming Department of Defense (DOD) mission. Left to right are Pilot Frank L. Culbertson, Mission Specialist (MS) Carl J. Meade, and MS Charles D. Gemar. Alexander is holding a training version of the 70mm handheld HASSELBLAD camera.

History of Chandra X-Ray Observatory

NASA Image and Video Library

1999-07-01

A crew member of the STS-93 mission took this photograph of the Chandra X-Ray Observatory, still attached to the Inertial Upper Stage (IUS), backdropped against the darkness of space not long after its release from Orbiter Columbia. Two firings of an attached IUS rocket placed the Observatory into its working orbit. The primary duty of the crew of this mission was to deploy the 50,162-pound Observatory, the world's most powerful x-ray telescope.

STS-102 Crew Patch

NASA Image and Video Library

2001-04-24

STS102-S-001 (January 2001) --- The central image on the STS-102 crew patch depicts the International Space Station (ISS) in the build configuration that it will have at the time of the arrival and docking of Discovery during the STS-102 mission, the first crew exchange flight to the space station. The station is shown along the direction of the flight as will be seen by the shuttle crew during their final approach and docking, the so-called V-bar approach. The names of the shuttle crew members are depicted in gold around the top of the patch, and surnames of the Expedition crew members being exchanged are shown in the lower banner. The three ribbons swirling up to and around the station signify the rotation of these ISS crew members. The number two is for the Expedition Two crew who fly up to the station, and the number one is for the Expedition One crew who then return down to Earth. In conjunction with the face of the Lab module of the station, these Expedition numbers create the shuttle mission number 102. Shown mated below the ISS is the Italian-built Multi-Purpose Logistics Module, Leonardo, that will fly for the first time on this flight, and which will be attached to the station by the shuttle crew during the docked phase of the mission. The flags of the countries that are the major contributors to this effort, the United States, Russia, and Italy are also shown in the lower part of the patch. The build-sequence number of this flight in the overall station assembly sequence, 5A.1, is captured by the constellations in the background. The NASA insignia design for space shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the forms of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, the change will be publicly announced. Photo credit: NASA

Designing and commissioning of a prototype double Laue monochromator at CHESS

NASA Astrophysics Data System (ADS)

Ko, J. Y. Peter; Oswald, Benjamin B.; Savino, James J.; Pauling, Alan K.; Lyndaker, Aaron; Revesz, Peter; Miller, Matthew P.; Brock, Joel D.

2014-03-01

High-energy X-rays are efficiently focused sagittally by a set of asymmetric Laue (transmission) crystals. We designed, built and commissioned a prototype double Laue monochromator ((111) reflection in Si(100)) optimized for high-energy X-rays (30-60 keV). Here, we report our design of novel prototype sagittal bender and highlight results from recent characterization experiments. The design of the bender combines the tuneable bending control afforded by previous leaf-spring designs with the stability and small size of a four-bar bender. The prototype monochromator focuses a 25 mm-wide white beam incident on the first monochromator crystal to a monochromatized 0.6 mm beam waist in the experimental station. Compared to the flux in the same focal spot with the Bragg crystal (without focusing), the prototype Laue monochromator delivered 85 times more at 30 keV.

STS-59 crew insignia

NASA Image and Video Library

1993-11-01

STS059-S-001 (November 1993) --- Designed by the crew members, the STS-59 insignia is dominated by Earth, reflecting the focus of the first Space Radar Laboratory (SRL-1) mission upon our planet's surface and atmosphere. The golden symbol of the astronaut corps emblem sweeps over Earth's surface from the space shuttle Endeavour, representing the operation of the SIR-C/Synthetic Aperture Radar (X-SAR) and the Measurement of Air Pollution from Space (MAPS) sensors. The astronaut emblem also signals the importance of the human element in space exploration and in the study of our planet. Using the unique vantage point of space, Endeavour and its crew -- along with scientists from around the world -- will study Earth and its environment. The starfield visible below Earth represents the many talents and skills of the international (SRL-1) team in working to make this "Mission to Planet Earth" (MTPE) a scientific and operational success. The NASA insignia design for space shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the forms of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, the change will be publicly announced. Photo credit: NASA

Crew Quarters Modifications

NASA Image and Video Library

2018-03-30

Modifications and upgrades are underway inside the Astronaut Crew Quarters in the Neil Armstrong Operations and Checkout Building at NASA's Kennedy Space Center in Florida. The crew quarters are being prepared for the next generation of space explorers. The historic facility housed Apollo and space shuttle astronauts before and after their missions into space.

Flight Crew Health Stabilization Program

NASA Technical Reports Server (NTRS)

Johnston, Smith L.

2010-01-01

This document establishes the policy and procedures for the HSP and is authorized through the Director, Johnson Space Center (JSC). This document delineates the medical operations requirements for the HSP. The HSP goals are accomplished through an awareness campaign and procedures such as limiting access to flight crewmembers, medical screening, and controlling flight crewmember activities. NASA's Human Space Flight Program uses strategic risk mitigation to achieve mission success while protecting crew health and safety. Infectious diseases can compromise crew health and mission success, especially in the immediate preflight period. The primary purpose of the Flight Crew Health Stabilization Program (HSP) is to mitigate the risk of occurrence of infectious disease among astronaut flight crews in the immediate preflight period. Infectious diseases are contracted through direct person-to-person contact, and through contact with infectious material in the environment. The HSP establishes several controls to minimize crew exposure to infectious agents. The HSP provides a quarantine environment for the crew that minimizes contact with potentially infectious material. The HSP also limits the number of individuals who come in close contact with the crew. The infection-carrying potential of these primary contacts (PCs) is minimized by educating them in ways to avoid infections and avoiding contact with the crew if they are or may be sick. The transmission of some infectious diseases can be greatly curtailed by vaccinations. PCs are strongly encouraged to maintain updated vaccinations.

49 CFR 1242.56 - Engine crews and train crews (accounts XX-51-56 and XX-51-57).

Code of Federal Regulations, 2010 CFR

2010-10-01

... 49 Transportation 9 2010-10-01 2010-10-01 false Engine crews and train crews (accounts XX-51-56 and XX-51-57). 1242.56 Section 1242.56 Transportation Other Regulations Relating to Transportation... RAILROADS 1 Operating Expenses-Transportation § 1242.56 Engine crews and train crews (accounts XX-51-56 and...

STS-113 Crew Training Clip

NASA Technical Reports Server (NTRS)

2002-01-01

The STS-113 crew consists of Commander Jim Weatherbee, Pilot Paul Lockhart, and Mission Specialists Michael Lopez-Alegria and John Herrington. The goal of the STS-113 mission is to deliver the Expedition Six crew to the International Space Station and return the Expedition Five crew to Earth. Also, the P1 Truss will be installed on the International Space Station. The STS-113 crew is shown getting suited for Pre-Launch Ingress and Egress. The Neutral Buoyancy Lab Extravehicular Activity training (NBL) (EVA), CETA Bolt Familiarization, and Photography TV instruction are also presented.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

A heavy-load transport truck carrying the Orion crew access arm makes its way toward the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The crew access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

A heavy-load transport truck carrying the Orion crew access arm nears the mobile launcher (ML) at NASA's Kennedy Space Center in Florida. The crew access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

Development of a Prototype Water Pump for Future Space Suit Applications

NASA Technical Reports Server (NTRS)

Hartman, David; Hodgson, Edward; Dionne, Steven; Gervais, Edward, III; Trevino, Luis

2009-01-01

NASA's next generation of space suit systems will place new demands on the pump used to circulate cooling water through the life support system and the crew's liquid cooling garment. Long duration missions and frequent EVA require increased durability and reliability; limited resupply mass requirements demand compatibility with recycled water, and changing system design concepts demand increased tolerance for dissolved and free gas and the ability to operate over a broader range of flow rates and discharge pressure conditions. This paper describes the development of a positive displacement prototype pump to meet these needs. A gerotor based design has been adapted to meet pump performance, gas tolerance, and durability requirements while providing a small, lightweight pump assembly. This design has been detailed and implemented using materials selected to address anticipated water quality and mission needs as a prototype unit for testing in NASA laboratories. Design requirements, pump technology selection and design, performance testing and test results will be discussed.

Development of a Prototype Water Pump for Future Space Suit Applications

NASA Technical Reports Server (NTRS)

Hartman, David; Hodgson, Edward; Gervais, Edward, III; Trevino, Luis

2008-01-01

NASA s next generation of space suit systems will place new demands on the pump used to circulate cooling water through the life support system and the crew s liquid cooling garment. Long duration missions and frequent EVA require increased durability and reliability; limited resupply mass requirements demand compatibility with recycled water, and changing system design concepts demand increased tolerance for dissolved and free gas and the ability to operate over a broader range of flow rates and discharge pressure conditions. This paper describes the development of a positive displacement prototype pump to meet these needs. A gerotor based design has been adapted to meet pump performance, gas tolerance, and durability requirements while providing a small, lightweight pump assembly. This design has been detailed and implemented using materials selected to address anticipated water quality and mission needs as a prototype unit for testing in NASA laboratories. Design requirements, pump technology selection and design, performance testing and test results will be discussed.

A Prototype Cryogenic Oxygen Storage and Delivery Subsystem for Advanced Spacesuits

NASA Technical Reports Server (NTRS)

Overbeeke, Arend; Hodgson, Edward; Paul, Heather; Geier, Harold; Bradt, Howard

2007-01-01

Future spacesuit systems for the exploration of Mars will need to be much lighter than current designs while at the same time reducing the consumption of water for crew cooling. One of the technology paths NASA has identified to achieve these objectives is the replacement of current high pressure oxygen storage technology in EVA systems with cryogenic technology that can simultaneously reduce the mass of tankage required for oxygen storage and enable the use of the stored oxygen as a means of cooling the EVA astronaut. During the past year NASA has funded Hamilton Sundstrand production of a prototype system demonstrating this capability in a design that will allow the cryogenic oxygen to be used in any attitude and gravity environment. This paper will describe the design and manufacture of the prototype system and present the results of preliminary testing to verify its performance characteristics. The potential significance and application of the system will also be discussed.

STS-112 Crew Training Clip

NASA Astrophysics Data System (ADS)

2002-09-01

Footage shows the crew of STS-112 (Jeffrey Ashby, Commander; Pamela Melroy, Pilot; David Wolf, Piers Sellers, Sandra Magnus, and Fyodor Yurchikhin, Mission Specialists) during several parts of their training. The video is arranged into short segments. In 'Topside Activities at the NBL', Wolf and Sellers are fitted with EVA suits for pool training. 'Pre-Launch Bailout Training in CCT II' shows all six crew members exiting from the hatch on a model of a shuttle orbiter cockpit. 'EVA Training in the VR Lab' shows a crew member training with a virtual reality simulator, interspersed with footage of Magnus, and Wolf with Melroy, at monitors. There is a 'Crew Photo Session', and 'Pam Melroy and Sandy Magnus at the SES Dome' also features a virtual reality simulator. The final two segments of the video involve hands-on training. 'Post Landing Egress at the FFT' shows the crew suiting up into their flight suits, and being raised on a harness, to practice rapelling from the cockpit hatch. 'EVA Prep and Post at the ISS Airlock' shows the crew assembling an empty EVA suit onboard a model of a module. The crew tests oxygen masks, and Sellers is shown on an exercise bicycle with an oxygen mask, with his heart rate monitored (not shown).

STS-112 Crew Training Clip

NASA Technical Reports Server (NTRS)

2002-01-01

Footage shows the crew of STS-112 (Jeffrey Ashby, Commander; Pamela Melroy, Pilot; David Wolf, Piers Sellers, Sandra Magnus, and Fyodor Yurchikhin, Mission Specialists) during several parts of their training. The video is arranged into short segments. In 'Topside Activities at the NBL', Wolf and Sellers are fitted with EVA suits for pool training. 'Pre-Launch Bailout Training in CCT II' shows all six crew members exiting from the hatch on a model of a shuttle orbiter cockpit. 'EVA Training in the VR Lab' shows a crew member training with a virtual reality simulator, interspersed with footage of Magnus, and Wolf with Melroy, at monitors. There is a 'Crew Photo Session', and 'Pam Melroy and Sandy Magnus at the SES Dome' also features a virtual reality simulator. The final two segments of the video involve hands-on training. 'Post Landing Egress at the FFT' shows the crew suiting up into their flight suits, and being raised on a harness, to practice rapelling from the cockpit hatch. 'EVA Prep and Post at the ISS Airlock' shows the crew assembling an empty EVA suit onboard a model of a module. The crew tests oxygen masks, and Sellers is shown on an exercise bicycle with an oxygen mask, with his heart rate monitored (not shown).

STS-109 Crew Training

NASA Technical Reports Server (NTRS)

2002-01-01

Footage shows the crew of STS-109 (Commander Scott Altman, Pilot Duane Carey, Payload Commander John Grunsfeld, and Mission Specialists Nancy Currie, James Newman, Richard Linnehan, and Michael Massimino) during various parts of their training. Scenes show the crew's photo session, Post Landing Egress practice, training in Dome Simulator, Extravehicular Activity Training in the Neutral Buoyancy Laboratory (NBL), and using the Virtual Reality Laboratory Robotic Arm. The crew is also seen tasting food as they choose their menus for on-orbit meals.

A Prototype Silicon Compiler in Prolog

DTIC Science & Technology

1988-12-01

A Prototype Silicon Compiler in Prolog 04 William Bush Gino Cheng Partrick C. McGeer Alvin M. Despain DTIC ELECTV JUL 281989 B Report No. UCB/CSD 88...the same register to variables in the same positions in invo- cation and head. Thus in ... g(A, B ),.. and g(X, Y) A and X share one register, and B ...example for a one-bit adder is given below. x = compl(or(and(c,or(a, b )),and(a, b ))). y = compl(or(and(x,or(a, b ,c)),and(a2b,c))). sum = compl(y). carry

Crew Earth Observations

NASA Technical Reports Server (NTRS)

Runco, Susan

2009-01-01

Crew Earth Observations (CEO) takes advantage of the crew in space to observe and photograph natural and human-made changes on Earth. The photographs record the Earth's surface changes over time, along with dynamic events such as storms, floods, fires and volcanic eruptions. These images provide researchers on Earth with key data to better understand the planet.

Wireless Monitoring of Changes in Crew Relations during Long-Duration Mission Simulation.

PubMed

Johannes, Bernd; Sitev, Alexej S; Vinokhodova, Alla G; Salnitski, Vyacheslav P; Savchenko, Eduard G; Artyukhova, Anna E; Bubeev, Yuri A; Morukov, Boris V; Tafforin, Carole; Basner, Mathias; Dinges, David F; Rittweger, Jörn

2015-01-01

Group structure and cohesion along with their changes over time play an important role in the success of missions where crew members spend prolonged periods of time under conditions of isolation and confinement. Therefore, an objective system for unobtrusive monitoring of crew cohesion and possible individual stress reactions is of high interest. For this purpose, an experimental wireless group structure (WLGS) monitoring system integrated into a mobile psychophysiological system was developed. In the presented study the WLGS module was evaluated separately in six male subjects (27-38 years old) participating in a 520-day simulated mission to Mars. Two days per week, each crew member wore a small sensor that registered the presence and distance of the sensors either worn by the other subjects or strategically placed throughout the isolation facility. The registration between two sensors was on average 91.0% in accordance. A correspondence of 95.7% with the survey video on day 475 confirmed external reliability. An integrated score of the "crew relation time index" was calculated and analyzed over time. Correlation analyses of a sociometric questionnaire (r = .35-.55, p< .05) and an ethological group approach (r = .45-.66, p < 05) provided initial evidence of the method's validity as a measure of cohesion when taking behavioral and activity patterns into account (e.g. only including activity phases in the afternoon). This confirms our assumption that the registered amount of time spent together during free time is associated with the intensity of personal relationships.

X-38 Ship #2 in Free Flight after Release from B-52 Mothership

NASA Technical Reports Server (NTRS)

1999-01-01

The X-38 research vehicle drops away from NASA's B-52 mothership immediately after being released from the B-52's wing pylon. More than 30 years earlier, this same B-52 launched the original lifting-body vehicles flight tested by NASA and the Air Force at what is now called the Dryden Flight Research Center and the Air Force Flight Test Center. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the

Science-based HRA: experimental comparison of operator performance to IDAC (Information-Decision-Action Crew) simulations

DOE Office of Scientific and Technical Information (OSTI.GOV)

Shirley, Rachel; Smidts, Carol; Boring, Ronald

Information-Decision-Action Crew (IDAC) operator model simulations of a Steam Generator Tube Rupture are compared to student operator performance in studies conducted in the Ohio State University’s Nuclear Power Plant Simulator Facility. This study is presented as a prototype for conducting simulator studies to validate key aspects of Human Reliability Analysis (HRA) methods. Seven student operator crews are compared to simulation results for crews designed to demonstrate three different decision-making strategies. The IDAC model used in the simulations is modified slightly to capture novice behavior rather that expert operators. Operator actions and scenario pacing are compared. A preliminary review of availablemore » performance shaping factors (PSFs) is presented. After the scenario in the NPP Simulator Facility, student operators review a video of the scenario and evaluate six PSFs at pre-determined points in the scenario. This provides a dynamic record of the PSFs experienced by the OSU student operators. In this preliminary analysis, Time Constraint Load (TCL) calculated in the IDAC simulations is compared to TCL reported by student operators. We identify potential modifications to the IDAC model to develop an “IDAC Student Operator Model.” This analysis provides insights into how similar experiments could be conducted using expert operators to improve the fidelity of IDAC simulations.« less

STS-114 Crew Training Clip

NASA Technical Reports Server (NTRS)

2003-01-01

The crew of Space Shuttle Atlantis on STS-114 is seen conducting several training exercises in preparation for their mission. The crew consists of Commander Eileen Collins, Pilot James Kelly, and Mission Specialists Soichi Noguchi and Stephen Robinson. With them are Yuri Malenchenko, Sergei Moschenko, and Edward Lu, the intended Expedition 7 crew of the International Space Station (ISS). During extravehicular activity (EVA) training in the virtual reality (VR) laboratory, crew members explore the exterior of the ISS, seen on a monitor. Suiting up with VR equipment is also shown. More EVA training takes place in the Neutral Buoyancy Laboratory (NBL). Here the astronauts are suited up for the NBL pool, and lowered into the water on a platform. After a crew photo session, the astronauts are seated in the Motion Base Simulator in their flight suits. The simulator is shown rocking side-to-side. The crew also hears a hands-on explanation of EVA preparations in the ISS airlock, and practices emergency egress from the CCT, a simulator shaped like an orbiter.

A prototype PET/SPECT/X-rays scanner dedicated for whole body small animal studies.

PubMed

Rouchota, Maritina; Georgiou, Maria; Fysikopoulos, Eleftherios; Fragogeorgi, Eirini; Mikropoulos, Konstantinos; Papadimitroulas, Panagiotis; Kagadis, George; Loudos, George

2017-01-01

To present a prototype tri-modal imaging system, consisting of a single photon emission computed tomography (SPET), a positron emission tomography (PET), and a computed tomography (CT) subsystem, evaluated in planar mode. The subsystems are mounted on a rotating gantry, so as to be able to allow tomographic imaging in the future. The system, designed and constructed by our group, allows whole body mouse imaging of competent performance and is currently, to the best of our knowledge, unequaled in a national and regional level. The SPET camera is based on two Position Sensitive Photomultiplier Tubes (PSPMT), coupled to a pixilated Sodium Iodide activated with Thallium (NaI(Tl)) scintillator, having an active area of 5x10cm 2 . The dual head PET camera is also based on two pairs of PSPMT, coupled to pixelated berillium germanium oxide (BGO) scintillators, having an active area of 5x10cm 2 . The X-rays system consists of a micro focus X-rays tube and a complementary metal-oxide-semiconductor (CMOS) detector, having an active area of 12x12cm 2 . The scintigraphic mode has a spatial resolution of 1.88mm full width at half maximum (FWHM) and a sensitivity of 107.5cpm/0.037MBq at the collimator surface. The coincidence PET mode has an average spatial resolution of 3.5mm (FWHM) and a peak sensitivity of 29.9cpm/0.037MBq. The X-rays spatial resolution is 3.5lp/mm and the contrast discrimination function value is lower than 2%. A compact tri-modal system was successfully built and evaluated for planar mode operation. The system has an efficient performance, allowing accurate and informative anatomical and functional imaging, as well as semi-quantitative results. Compared to other available systems, it provides a moderate but comparable performance, at a fraction of the cost and complexity. It is fully open, scalable and its main purpose is to support groups on a national and regional level and provide an open technological platform to study different detector components and

Getting a Crew into Orbit

ERIC Educational Resources Information Center

Riddle, Bob

2011-01-01

Despite the temporary setback in our country's crewed space exploration program, there will continue to be missions requiring crews to orbit Earth and beyond. Under the NASA Authorization Act of 2010, NASA should have its own heavy launch rocket and crew vehicle developed by 2016. Private companies will continue to explore space, as well. At the…

Development Of An 80'-Diameter Ribbon Drogue Parachute For The NASA X-38 Vehicle

NASA Technical Reports Server (NTRS)

Behr, Vance L.; Wolf, Dean F.; Rutledge, Bruce A.; Hillebrandt, F. David

2001-01-01

The NASA X-38 program required a larger, more robust drogue parachute. A multi-organizational team from NASA, Sandia National Laboratories, United Space Alliance, and Pioneer Aerospace Corporation has developed and tested a new 80-ft.-dia., quarter-spherical, ribbon drogue parachute. The design requirements, design specifics, margin analyses, and results of testing are all discussed herein. Some of the weight advantages of switching from Kevlar to Zylon for radial, line and riser materials are presented.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-09

The Orion crew access arm, secured on a stand, is being prepared for its move from a storage location at NASA's Kennedy Space Center in Florida, to the mobile launcher (ML) tower near the Vehicle Assembly Building at the center. The crew access arm will be installed at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-09

The Orion crew access arm is secured in a storage location at NASA's Kennedy Space Center in Florida. The access arm will be prepared for its move to the mobile launcher (ML) tower near the Vehicle Assembly Building at the center. The crew access arm will be installed at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

Airline Crew Training

NASA Technical Reports Server (NTRS)

1989-01-01

The discovery that human error has caused many more airline crashes than mechanical malfunctions led to an increased emphasis on teamwork and coordination in airline flight training programs. Human factors research at Ames Research Center has produced two crew training programs directed toward more effective operations. Cockpit Resource Management (CRM) defines areas like decision making, workload distribution, communication skills, etc. as essential in addressing human error problems. In 1979, a workshop led to the implementation of the CRM program by United Airlines, and later other airlines. In Line Oriented Flight Training (LOFT), crews fly missions in realistic simulators while instructors induce emergency situations requiring crew coordination. This is followed by a self critique. Ames Research Center continues its involvement with these programs.

American X-Vehicles: An Inventory X-1 to X-50 Centennial of Flight Edition

NASA Technical Reports Server (NTRS)

Jenkins, Dennis R.; Landis, Tony; Miller, Jay

2003-01-01

For a while, it seemed the series of experimental aircraft sponsored by the U. S. government had run its course. Between the late 1940s and the late 1970s, almost thirty designations had been allocated to aircraft meant to explore new flight regimes or untried technologies. Then, largely, it ended. But there was a resurgence in the mid- to late- 1990s, and as we enter the fourth year of the new millennia, the designations are up to x-50. Many have a misconception that X-vehicles have always explored the high-speed and high-altitude flight regimes - something popularized by Chuck Yeager in the original X-1 and the exploits of the twelve men that flew the X-15. Although these flight regimes have always been in the spotlight, many others have been explored by X-vehicles. The little Bensen X-25 never exceeded 85 mph, and others were limited to speeds of several hundred mph. There has been some criticism that the use of X designations has been corrupted somewhat by including what are essentially prototypes of future operational aircraft, especially the two JSF demonstrators. But this is not new-the X-11 and X-12 from the 1950s were going to be prototypes of the Atlas intercontinental ballistic missile, and the still-born Lockheed X-27 was always intended as a prototype of a production aircraft. So although this practice does not represent the best use of 'X' designations, it is not without precedent.

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

The Orion crew module for Exploration Mission-1 was moved into the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Docking, synthesis and pharmacological activity of novel urea-derivatives designed as p38 MAPK inhibitors.

PubMed

de Oliveira Lopes, Raquel; Romeiro, Nelilma Correia; de Lima, Cleverton Kleiton F; Louback da Silva, Leandro; de Miranda, Ana Luisa Palhares; Nascimento, Paulo Gustavo B D; Cunha, Fernando Q; Barreiro, Eliezer J; Lima, Lídia Moreira

2012-08-01

p38 mitogen-activated protein kinase (p38 MAPK) is an important signal transducing enzyme involved in many cellular regulations, including signaling pathways, pain and inflammation. Several p38 MAPK inhibitors have been developed as drug candidates to treatment of autoimmune disorders, such as rheumatoid arthritis. In this paper we reported the docking, synthesis and pharmacological activity of novel urea-derivatives (4a-e) designed as p38 MAPK inhibitors. These derivatives presented good theoretical affinity to the target p38 MAPK, standing out compound 4e (LASSBio-998), which showed a better score value compared to the prototype GK-00687. This compound was able to reduce in vitro TNF-α production and was orally active in a hypernociceptive murine model sensible to p38 MAPK inhibitors. Otherwise, compound 4e presented a dose-dependent analgesic effect in a model of antigen (mBSA)-induced arthritis and anti-inflammatory profile in carrageenan induced paw edema, indicating its potential as a new antiarthritis prototype. Copyright © 2012 Elsevier Masson SAS. All rights reserved.

ISS Expedition 43 Crew Departure from Russia

NASA Image and Video Library

2015-03-16

NASA video file of ISS Expedition 43 crew departure from Russia on March 16, 2015 with crewmembers Scott Kelly, Gennady Padalka, and Mikhail Kornienko; and backupcrew Jeff Williams, Sergei Volkov and Alexie Ovchinin. Includes footage of crew and backup crew as the meet outside the Gagarin Cosmonaut Training Center (GCTC); ISS Expedition 42 crewmembers Elena Serova and Alexander Samokutyaev as they exits the GCTC; crew and backup crew with family, friends and officials as they walk to park, pose for photographs and offers short remarks; and finally the crew as they are leaving by bus.

STS-92 crew leave the O&C for Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

The STS-92 crew exits the Operations and Checkout Building on their way to the Astrovan and Launch Pad 39A for a simulated countdown. Walking left to right are (foreground) Mission Specialists Koichi Wakata of Japan, Peter J.K. 'Jeff' Wisoff and Leroy Chiao; and Pilot Pamela Ann Melroy. Behind them are Mission Specialists Michael E. Lopez-Alegria and William S. McArthur Jr.; and Commander Brian Duffy. The crew is taking part in Terminal Countdown Demonstration Test activities that provide emergency egress training, opportunities to inspect the mission payload, and the simulated countdown. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program.

SpaceX Recovery Trainer Egress and Handling Testing

NASA Image and Video Library

2018-04-17

Pararescue specialists from the 304th Rescue Squadron, located in Portland, Oregon and supporting the 45th Operations Group’s Detachment 3, based out of Patrick Air Force Base, prepare equipment during an April astronaut rescue exercise with NASA’s Commercial Crew Program and SpaceX off of Florida’s eastern coast. The pararescue specialists, also known as “Guardian Angels,” jumped from military aircraft and simulated a rescue operation to demonstrate their ability to safely remove crew from the SpaceX Crew Dragon in the unlikely event of an emergency landing. The pararescue specialists are fully qualified paramedics able to perform field surgery, if necessary.

STS-87 crew participates in Crew Equipment Interface Test

NASA Technical Reports Server (NTRS)

1997-01-01

Participating in the Crew Equipment Integration Test (CEIT) at Kennedy Space Center are STS-87 crew members, assisted by Glenda Laws, extravehicular activity (EVA) coordinator, Johnson Space Center. Standing behind Laws are Takao Doi, Ph.D., of the National Space Development Agency of Japan, and Winston Scott, both mission specialists on STS-87. The STS-87 mission will be the fourth United States Microgravity Payload and flight of the Spartan-201 deployable satellite. During the mission, scheduled for a Nov. 19 liftoff from KSC, Dr. Doi and Scott will both perform spacewalks.

Space Station Freedom crew training

NASA Technical Reports Server (NTRS)

Bobko, K. J.; Gibson, E. G.; Maroney, S. A.; Muccio, J. D.

1990-01-01

The nature of the Space Station Freedom Program presents an array of new and enhanced challenges which need to be addressed en route to developing an effective and affordable infrastructure for crew training. Such an infrastructure is essential for the safety and success of the program. The three major challenges that affect crew training are the long lifetime of the program (thirty years), the interdependence of successive increments, and the participation of the three International Partners (Canada, European Space Agency, and Japan) and a myriad of experimenters. This paper addresses these major challenges as they drive the development of a crew training capability and the actual conduct of crew training.

ML Crew Access Arm Move

NASA Image and Video Library

2017-10-16

The Orion crew access arm departs Precision Fabricating and Cleaning in Cocoa, Florida, atop a flatbed truck. The access arm is transported to a storage location at NASA's Kennedy Space Center in Florida. Later this month, the arm will be transported to the mobile launcher (ML) tower at the center. The crew access arm will be located at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

The Orion crew access arm is secured on a flatbed transporter for its move from a storage location at NASA's Kennedy Space Center in Florida to the mobile launcher (ML) tower near the Vehicle Assembly Building at the center. The crew access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

A heavy-load transport truck carries the Orion crew access arm along the NASA Causeway east toward State Road 3 at NASA's Kennedy Space Center in Florida. The access arm will be moved to the mobile launcher (ML) near the Vehicle Assembly Building at the center. The crew access arm will be installed at about the 274-foot level on the tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

Commercial Crew Medical Ops

NASA Technical Reports Server (NTRS)

Heinbaugh, Randall; Cole, Richard

2016-01-01

Provide commercial partners with: center insight into NASA spaceflight medical experience center; information relative to both nominal and emergency care of the astronaut crew at landing site center; a basis for developing and sharing expertise in space medical factors associated with returning crew.

Modeling strength data for CREW CHIEF

NASA Technical Reports Server (NTRS)

Mcdaniel, Joe W.

1990-01-01

The Air Force has developed CREW CHIEF, a computer-aided design (CAD) tool for simulating and evaluating aircraft maintenance to determine if the required activities are feasible. CREW CHIEF gives the designer the ability to simulate maintenance activities with respect to reach, accessibility, strength, hand tool operation, and materials handling. While developing the CREW CHIEF, extensive research was performed to describe workers strength capabilities for using hand tools and manual handling of objects. More than 100,000 strength measures were collected and modeled for CREW CHIEF. These measures involved both male and female subjects in the 12 maintenance postures included in CREW CHIEF. The data collection and modeling effort are described.

Earth Observations taken by the Expedition 39 Crew

NASA Image and Video Library

2014-04-26

ISS039-E-016292 (26 April 2014) --- A wish-bone shaped display of Aurora Australis over the Indian Ocean serves as a very colorful backdrop for the SpaceX Dragon spacecraft which is docked to the International Space Station, 226 miles above Earth. Earth's horizon divides the scene horizontally between the blackness of space and the dark portion of the planet. The photograph was taken by one of the Expedition 39 crew members aboard the orbital outpost.

NASA DFRC Practices for Prototype Qualification

NASA Technical Reports Server (NTRS)

Lokos, William A.

2009-01-01

This slide presentation reviews the practices that Dryden uses for qualification of the prototypes of aircraft. There are many views of aircraft that Dryden has worked with. Included is a discussion of basic considerations for strength, a listing of standards and references, a discussion of typical safety of flight approaches, a discussion of the prototype design, using the X-29A as an example, and requirements for new shapes (i.e., the DAST-ARW1 , F-8 Super Critical Wing, AFTI/F-111 MAW), new control laws (i.e., AAW F-18), new operating envelope (i.e., F-18 HARV), limited sope add-on or substitute structure (i.e., SR-71 LASRE, ECLIPSE, F-16XL SLFC), and extensively modified or replaced structure (i.e., SOFIA, B747SP). There is a listing of causes for the failure of the prototype.

STS-38 Atlantis, OV-104, during safing operations after KSC SLF landing

NASA Image and Video Library

1990-11-20

Spotlights illuminate Atlantis, Orbiter Vehicle (OV) 104, during safing operations at the Kennedy Space Center's (KSC's) Shuttle Landing Facility (SLF). OV-104 parked on runway 33 is serviced by KSC ground crews. STS-38, a Department of Defense (DOD)-devoted mission, came to an end (with complete wheel stop) at 4:43:37 pm (Eastern Standard Time (EST)).

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

Technicians assist as the Orion crew module for Exploration Mission-1 is moved toward the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

A crane is being prepared for use during move operations of the Orion crew module for Exploration Mission-1 to the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

Technicians prepare a crane for use during move operations of the Orion crew module for Exploration Mission-1 to the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Crew Autonomous Scheduling Test (CAST)

NASA Image and Video Library

2017-07-18

iss052e016190 (July 18, 2017) --- Astronaut Peggy Whitson is photographed sitting in front of the Cupola windows during the final Crew Autonomous Scheduling Test (CAST) session. The CAST investigation analyzes whether crews can develop plans in a reasonable period of time with appropriate input, whether proximity of planners to the planned operations increases efficiency, and if crew members are more satisfied when given a role in plan development.

38. Photocopied August 1978. THE POWER CANAL AT THE JUNCTION ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

38. Photocopied August 1978. THE POWER CANAL AT THE JUNCTION BETWEEN SECTIONS I AND II ON AUGUST 1, 1902. THE RECTANGULAR PRISM OF THE ROCK SECTION (I) AND THE TRAPEZOIDAL PRISM OF SECTION II BOTH SHOW UP VERY CLEARLY. COMPANY CREWS ON THE LEFT HAND WALL ARE COMPLETING SOME SMOOTHING-UP WORK ON THE ROCK SECTION WALL. (265) - Michigan Lake Superior Power Company, Portage Street, Sault Ste. Marie, Chippewa County, MI

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

A heavy-load transport truck carries the Orion crew access arm along the NASA Causeway east toward State Road 3 at NASA's Kennedy Space Center in Florida. The access arm will be moved to the mobile launcher (ML) near the Vehicle Assembly Building at the center. The crew access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

John Glenn and rest of STS-95 crew exit Crew Transport Vehicle

NASA Technical Reports Server (NTRS)

1998-01-01

Following touchdown at 12:04 p.m. EST at the Shuttle Landing Facility, the mission STS-95 crew leave the Crew Transport Vehicle. Payload Specialist John H. Glenn Jr. (center), a senator from Ohio, shakes hands with NASA Administrator Daniel S. Goldin. At left is Center Director Roy Bridges. Other crew members shown are Pilot Steven W. Lindsey (far left) and, behind Glenn, Mission Specialists Scott E. Parazynski and Stephen K. Robinson, and Payload Specialist Chiaki Mukai, Ph.D., M.D., with the National Space Development Agency of Japan. Not seen are Mission Commander Curtis L. Brown Jr. and Mission Specialist Pedro Duque of Spain, with the European Space Agency (ESA). The STS-95 crew completed a successful mission, landing at the Shuttle Landing Facility at 12:04 p.m. EST, after 9 days in space, traveling 3.6 million miles. The mission included research payloads such as the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbital Systems Test Platform, the International Extreme Ultraviolet Hitchhiker, as well as the SPACEHAB single module with experiments on space flight and the aging process.

Integrating Human Factors into Crew Exploration Vehicle Design

NASA Technical Reports Server (NTRS)

Whitmore, Mihriban; Baggerman, Susan; Campbell, paul

2007-01-01

With NASA's new Vision for Exploration to send humans beyond Earth orbit, it is critical to consider the human as a system that demands early and continuous user involvement, and an iterative prototype/test/redesign process. Addressing human-system interface issues early on can be very cost effective even cost reducing when performed early in the design and development cycle. To achieve this goal within Crew Exploration Vehicle (CEV) Project Office, human engineering (HE) team is formed. Key tasks are to apply HE requirements and guidelines to hardware/software, and provide HE design, analysis and evaluation of crew interfaces. Initial activities included many practice-orientated evaluations using low-fidelity CEV mock-ups. What follows is a description of such evaluations that focused on a HE requirement regarding Net Habitable Volume (NHV). NHV is defined as the total remaining pressurized volume available to on-orbit crew after accounting for the loss of volume due to deployed hardware and structural inefficiencies which decrease functional volume. The goal of the NHV evaluations was to develop requirements providing sufficient CEV NHV for crewmembers to live and perform tasks in support of mission goals. Efforts included development of a standard NHV calculation method using computer models and physical mockups, and crew/ stakeholder evaluations. Nine stakeholders and ten crewmembers participated in the unsuited evaluations. Six crewmembers also participated in a suited evaluation. The mock-up was outfitted with volumetric representation of sub-systems such as seats, and stowage bags. Thirteen scenarios were developed to represent mission/crew tasks and considered to be primary volume drivers (e.g., suit donning) for the CEV. Unsuited evaluations included a structured walkthrough of these tasks. Suited evaluations included timed donning of the existing launch and entry suit to simulate a contingency scenario followed by doffing/ stowing of the suits. All mockup

Prototype Solid State Induction Modulator for SLAC NLC

NASA Astrophysics Data System (ADS)

Cassel, R. L.; DeLamare, J. E.; Nguyen, M. N.; Pappas, G. C.; Cook, E.

2002-08-01

The Next Linear Collider accelerator proposal at SLAC requires a high efficiency, highly reliable, and low cost pulsed power modulator to drive the X band klystrons. The present NLC envisions a solid-state induction modulator design to drive up to 8 klystrons to 500kV for 3muS at 120 PPS with one modulator (>1,000 megawatt pulse, 500kW average). A prototype modulator is presently under construction, which well power 4 each 5045 SLAC klystron to greater than 380 kV for 3muS (>600 megawatt pulse, >300 kW Ave.). The modulator will be capable of driving the 8 each X band klystrons when they become available. The paper covers the design, construction, fabrication and preliminary testing of the prototype modulator.

Crew Factors in Flight Operations 7: Psychophysiological Responses to Overnight Cargo Operations

NASA Technical Reports Server (NTRS)

Gander, Philippa H.; Gregory, Kevin B.; Connell, Linda J.; Miller, Donna L.; Graeber, R. Curtis; Rosekind, Mark R.

1996-01-01

To document the psychophysiological effects of flying overnight cargo operations, 41 B-727 crew members (average age 38 yr) were monitored before, during, and after one of two typical 8-day trip patterns. During daytime layovers, the average sleep episode was 3 hr (41%) shorter than nighttime sleeps and was rated as lighter, less restorative, and poorer overall. Sleep was frequently split into several episodes and totaled 1.2 hr less per 24 hr than on pretrip days. Each trip pattern included a night off, which was an effective countermeasure against the accumulating sleep debt. The organization of sleep during daytime layovers reflected the interaction of duty timing with circadian physiology. The circadian temperature rhythm did not adapt completely to the inverted wake-rest schedule on duty days, being delayed by about 3 hr. Highest subjective fatigue and lowest activation occurred around the time of the temperature minimum. On duty days, reports of headaches increased by 400%, of congested nose by 200%, and of burning eyes by 900%. Crew members also reported eating more snacks. Compared with daytime short-haul air-transport operations, the overnight cargo trips included fewer duty and flight hours, and had longer layovers. Overnight cargo crews also averaged 5.4 yr younger than their daytime short-haul counterparts. On trips, both groups lost a comparable amount of sleep per 24 hr, but the overnight cargo crews had shorter individual sleep episodes and more broken sleep. These data clearly demonstrate that overnight cargo operations, like other night work, involve physiological disruption not found in comparable daytime operations.

ISS Crew Transportation and Services Requirements Document

NASA Technical Reports Server (NTRS)

Bayt, Robert L. (Compiler); Lueders, Kathryn L. (Compiler)

2016-01-01

The ISS Crew Transportation and Services Requirements Document (CCT-REQ-1130) contains all technical, safety, and crew health medical requirements that are mandatory for achieving a Crew Transportation System Certification that will allow for International Space Station delivery and return of NASA crew and limited cargo. Previously approved on TN23183.

Building a prototype of a Martian base in Poland, an architectural design overview and progress report

NASA Astrophysics Data System (ADS)

Kozicki, Janek

This talk focuses on recent advances in the construction of a prototype 1000 m2 Martian out-post for 8 inhabitants. The architectural design for such a Martian base has been presented previously on COSPAR 2008, the presentation being entitled ,,Architectural design proposal for a Martian base to continue NASA Mars Design Reference Mission". The presentation was welcomed with warm interest by various institutions, some of which offered help in building a prototype such as providing the building site or funding. This year's oral presentation will focus on a progress report and will briefly describe the architectural design. The architectural design is inspired by terrestrial pneumatic architecture. It has small volume, can be easily transported and provides a large habitable space. An architectural solution analo-gous to a terrestrial house with a studio and a workshop was assumed. The spatial placement of the following zones was carefully considered: residential, agricultural and science, as well as garage and workshop. Further attention was paid to transportation routes and a control and communications center. The issues of a life support system, energy, food, water and waste recycling were also discussed. This Martian base was designed to be crewed by a team of eight people to stay on Mars for at least one and a half year. An Open Plan architectural solution was assumed, with a high level of modularity. Walls of standardized sizes with zip-fasteners allow free rearrangement of the interior to adapt to a new situation. The prototype of such a Polish-origin Martian outpost will be used in a manner similar to MDRS or FMARS but to a larger extent. The prototype's design itself will be tested and corrected to achieve a design which can be used on Mars. The procedure of unfolding the pneumatic modules and floor leveling will be tested. The 1000 m2 interior will be used for various simulation exercises: socio-psychological testing, interior arrangement experiments

Dummy left behind by Skylab 3 crew for the Skylab 4 crew

NASA Technical Reports Server (NTRS)

1973-01-01

This photograph is an illustration of the humorous side of the Skylab 3 crew. This dummy was left behind in the Skylab space station by the Skylab 3 crew to be found by the Skylab 4 crew. The dummy is dressed in a flight suit and placed in the Lower Body Negative Pressure Device. The name tag indicates that it represents Gerald P. Carr, Skylab 4 commander. In the background is a partial view of the dummy for William R. Pogue, Skylab 4 pilot, propped upon the bicycle ergometer (1586); This dummy is dressed in a flight suit and propped upon the bicycle ergometer. The name tag indicates that it represents William R. Pogue, Skylab 4 pilot (1587).

Gemini 4 prime crew with Official medical nurse for Astronaut crew members

NASA Technical Reports Server (NTRS)

1965-01-01

Gemini 4 prime crew, Astronauts Edward H. White II, (left), and James A. McDivitt (right) are shown with Lt. Dolores (Dee) O'Hare, US Air Force, Center Medical Office, Flight Medicine Branch, Manned Spaceflight Center (MSC). Lieutenant O'Hare has served during several space flights as Official medical nurse for the astronaut crew members on the missions.

SpaceX Dragon Parachute Test

NASA Image and Video Library

2018-03-04

SpaceX performed its fourteenth overall parachute test supporting Crew Dragon development. This most recent exercise was the first of several planned parachute system qualification tests ahead of the spacecraft’s first crewed flight and resulted in the successful touchdown of Crew Dragon’s parachute system. During this test, a C-130 aircraft transported the parachute test vehicle, designed to achieve the maximum speeds that Crew Dragon could experience on re-entry, over the Mojave Desert in Southern California and dropped the vehicle from an altitude of 25,000 feet. The test demonstrated an off-nominal situation, deploying only one of the two drogue chutes and intentionally skipping a reefing stage on one of the four main parachutes, proving a safe landing in such a contingency scenario.

Expedition Crews Four and Five and STS-111 Crew Aboard the ISS

NASA Technical Reports Server (NTRS)

2002-01-01

Huddled together in the Destiny laboratory of the International Space Station (ISS) are the Expedition Four crew (dark blue shirts), Expedition Five crew (medium blue shirts) and the STS-111 crew (green shirts). The Expedition Four crewmembers are, from front to back, Cosmonaut Ury I. Onufrienko, mission commander; and Astronauts Daniel W. Bursch and Carl E. Waltz, flight engineers. The ISS crewmembers are, from front to back, Astronauts Kerneth D. Cockrell, mission commander; Franklin R. Chang-Diaz, mission specialist; Paul S. Lockhart, pilot; and Philippe Perrin, mission specialist. Expedition Five crewmembers are, from front to back, Cosmonaut Valery G. Korzun, mission commander; Astronaut Peggy A. Whitson and Cosmonaut Sergei Y. Treschev, flight engineers. The ISS recieved a new crew, Expedition Five, replacing Expedition Four after a record-setting 196 days in space, when the Space Shuttle Orbiter Endeavour STS-111 mission visited in June 2002. Three spacewalks enabled the STS-111 crew to accomplish additional mission objectives: the delivery and installation of the Mobile Base System (MBS), which is an important part of the station's Mobile Servicing System allowing the robotic arm to travel the length of the station; the replacement of a wrist roll joint on the Station's robotic arm; and unloading supplies and science experiments from the Leonardo Multi-Purpose Logistics Module, which made its third trip to the orbital outpost. The STS-111 mission, the 14th Shuttle mission to visit the ISS, was launched on June 5, 2002 and landed June 19, 2002.

Ares I-X Flight Test Vehicle: Stack 5 Modal Test

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Danel R.

2010-01-01

Ares I-X was the first flight test vehicle used in the development of NASA's Ares I crew launch vehicle. The Ares I-X used a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Three modal tests were defined to verify the dynamic finite element model of the Ares I-X flight test vehicle. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report focuses on the first modal test that was performed on the top section of the vehicle referred to as Stack 5, which consisted of the spacecraft adapter, service module, crew module and launch abort system simulators. This report describes the test requirements, constraints, pre-test analysis, test operations and data analysis for the Ares I-X Stack 5 modal test.

STS-92 crew leave the O&C for Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

The STS-92 crew exits the Operations and Checkout Building on their way to the Astrovan and Launch Pad 39A for a simulated countdown. On the left, front to back, are Pilot Pamela Ann Melroy and Mission Specialists Leroy Chiao, Peter J.K. '''Jeff''' Wisoff, and Koichi Wakata of Japan. On the right, front to back, are Commander Brian Duffy and Mission Specialists William S. McArthur Jr. and Michael E. Lopez-Alegria. The crew is taking part in Terminal Countdown Demonstration Test activities that provide emergency egress training, opportunities to inspect the mission payload, and the simulated countdown. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program.

STS-121 Crew Portrait

NASA Technical Reports Server (NTRS)

2006-01-01

These seven astronauts take a break from training to pose for the STS-121 crew portrait. From the left are mission specialists Stephanie D. Wilson, and Michael E. Fossum, Commander Steven W. Lindsey, mission specialist Piers J. Sellers, pilot Mark E. Kelly; European Space Agency (ESA) astronaut and mission specialist Thomas Reiter of Germany; and mission specialist Lisa M. Nowak. The crew members are attired in training versions of their shuttle launch and entry suit. The crew, first ever to launch on Independence Day, tested new equipment and procedures to improve shuttle safety, as well as delivered supplies and made repairs to the space station.

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

Technicians check a crane that will be used during move operations of the Orion crew module for Exploration Mission-1 to the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Crewed Space Vehicle Battery Safety Requirements

NASA Technical Reports Server (NTRS)

Jeevarajan, Judith A.; Darcy, Eric C.

2014-01-01

This requirements document is applicable to all batteries on crewed spacecraft, including vehicle, payload, and crew equipment batteries. It defines the specific provisions required to design a battery that is safe for ground personnel and crew members to handle and/or operate during all applicable phases of crewed missions, safe for use in the enclosed environment of a crewed space vehicle, and safe for use in launch vehicles, as well as in unpressurized spaces adjacent to the habitable portion of a space vehicle. The required provisions encompass hazard controls, design evaluation, and verification. The extent of the hazard controls and verification required depends on the applicability and credibility of the hazard to the specific battery design and applicable missions under review. Evaluation of the design and verification program results shall be completed prior to certification for flight and ground operations. This requirements document is geared toward the designers of battery systems to be used in crewed vehicles, crew equipment, crew suits, or batteries to be used in crewed vehicle systems and payloads (or experiments). This requirements document also applies to ground handling and testing of flight batteries. Specific design and verification requirements for a battery are dependent upon the battery chemistry, capacity, complexity, charging, environment, and application. The variety of battery chemistries available, combined with the variety of battery-powered applications, results in each battery application having specific, unique requirements pertinent to the specific battery application. However, there are basic requirements for all battery designs and applications, which are listed in section 4. Section 5 includes a description of hazards and controls and also includes requirements.

ISS Crew Transportation and Services Requirements Document

NASA Technical Reports Server (NTRS)

Lueders, Kathryn L. (Compiler)

2015-01-01

Under the guidance of processes provided by Crew Transportation Plan (CCT-PLN-1100), this document with its sister documents, Crew Transportation Technical Management Processes (CCT-PLN-1120), Crew Transportation Technical Standards and Design Evaluation Criteria (CCT-STD-1140), and Crew Transportation Operations Standards (CCT-STD-1150), and International Space Station (ISS) to Commercial Orbital Transportation Services Interface Requirements Document (SSP 50808), provides the basis for a National Aeronautics and Space Administration (NASA) certification for services to the ISS for the Commercial Provider. When NASA Crew Transportation System (CTS) certification is achieved for ISS transportation, the Commercial Provider will be eligible to provide services to and from the ISS during the services phase of the NASA Commercial Crew Program (CCP).

Commerical Crew Program (CCP) Access Arm Installation

NASA Image and Video Library

2016-08-15

The Crew Access Arm and White Room for Boeing's CST-100 Starliner are attached to the Crew Access Tower at Cape Canaveral Air Force Station’s Space Launch Complex 41. The arm will serve as the connection that astronauts will walk through prior to boarding the Starliner spacecraft when stacked atop a United Launch Alliance Atlas V rocket. This installation completes the major construction of the first new Crew Access Tower to be built at the Cape since the Apollo era. Under a Commercial Crew Transportation Capability contract with NASA, Boeing’s Starliner system will be certified by NASA's Commercial Crew Program to fly crews to and from the International Space Station.

Advanced Propulsion and TPS for a Rapidly-Prototyped CEV

NASA Astrophysics Data System (ADS)

Hudson, Gary C.

2005-02-01

Transformational Space Corporation (t/Space) is developing for NASA the initial designs for the Crew Exploration Vehicle family, focusing on a Launch CEV for transporting NASA and civilian passengers from Earth to orbit. The t/Space methodology is rapid prototyping of major vehicle systems, and deriving detailed specifications from the resulting hardware, avoiding "written-in-advance" specs that can force the costly invention of new capabilities simply to meet such specs. A key technology shared by the CEV family is Vapor Pressurized propulsion (Vapak) for simplicity and reliability, which provides electrical power, life support gas and a heat sink in addition to propulsion. The CEV family also features active transpiration cooling of re-entry surfaces (for reusability) backed up by passive thermal protection.

UWB Two-Cluster AOA Tracking Prototype System Design

NASA Technical Reports Server (NTRS)

Ngo, Phong H.; Arndt, D.; Phan, C.; Gross, J.; Jianjun; Rafford, Melinda

2006-01-01

This presentation discusses a design effort for a prototype ultra-wideband (UWB) tracking system that is currently under development at NASA Johnson Space Center (JSC). The system is being studied for use in tracking of lunar/Mars rovers during early exploration missions when satellite navigation systems are not available. The UWB technology is exploited to implement the tracking system due to its properties such as fine time resolution, low power spectral density and multipath immunity. A two cluster prototype design using commercially available UWB radios is employed to implement the Angle of Arrival (AOA) tracking methodology in this design effort. In order to increase the tracking range, low noise amplifiers (LNA) and high gain horns are used at the receiving sides. Field tests were conducted jointly with the Science and Crew Operation Utility Testbed (SCOUT) vehicle near the Meteor Crater in Arizona to test the tracking capability for a moving target in an operational environment. These tests demonstrate that the UWB tracking system can co-exist with other on-board radio frequency (RF) communication systems (such as Global Positioning System (GPS), video, voice and telemetry systems), and that a tracking resolution less than 1% of the range can be achieved.

Dummy left behind by Skylab 3 crew for the Skylab 4 crew

NASA Image and Video Library

1973-08-16

SL3-113-1587 (July-September 1973) --- This photograph is an illustration of the humorous side of the Skylab 3 crew. This dummy was left behind in the Skylab space station by the Skylab 3 crew to be found by the Skylab 4 crew. The dummy is dressed in a flight suit and propped upon the bicycle ergometer. The name tag indicated that it represents William R. Pogue, Skylab pilot. The dummy for Gerald P. Carr, Skylab 4 commander, was placed in the Lower Body Negative Pressure Device. The dummy representing Edward G. Gibson was left in the waste compartment. Astronauts Alan L. Bean, Owen K. Garriott and Jack R. Lousma were the Skylab 3 crewmen. Gibson is the Skylab 4 science pilot. Photo credit: NASA

46 CFR 122.420 - Crew training.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 4 2011-10-01 2011-10-01 false Crew training. 122.420 Section 122.420 Shipping COAST....420 Crew training. (a) The owner, charterer, master, or managing operator shall instruct each crew... § 122.514. (b) Training conducted on a sister vessel may be considered equivalent to the initial and...

Analysis of Ares Crew Launch Vehicle Transonic Alternating Flow Phenomenon

NASA Technical Reports Server (NTRS)

Sekula, Martin K.; Piatak, David J.; Rausch, Russ D.

2012-01-01

A transonic wind tunnel test of the Ares I-X Rigid Buffet Model (RBM) identified a Mach number regime where unusually large buffet loads are present. A subsequent investigation identified the cause of these loads to be an alternating flow phenomenon at the Crew Module-Service Module junction. The conical design of the Ares I-X Crew Module and the cylindrical design of the Service Module exposes the vehicle to unsteady pressure loads due to the sudden transition between a subsonic separated and a supersonic attached flow about the cone-cylinder junction as the local flow randomly fluctuates back and forth between the two flow states. These fluctuations produce a square-wave like pattern in the pressure time histories resulting in large amplitude, impulsive buffet loads. Subsequent testing of the Ares I RBM found much lower buffet loads since the evolved Ares I design includes an ogive fairing that covers the Crew Module-Service Module junction, thereby making the vehicle less susceptible to the onset of alternating flow. An analysis of the alternating flow separation and attachment phenomenon indicates that the phenomenon is most severe at low angles of attack and exacerbated by the presence of vehicle protuberances. A launch vehicle may experience either a single or, at most, a few impulsive loads since it is constantly accelerating during ascent rather than dwelling at constant flow conditions in a wind tunnel. A comparison of a windtunnel- test-data-derived impulsive load to flight-test-data-derived load indicates a significant over-prediction in the magnitude and duration of the buffet load. I. Introduction One

Orbiter Crew Compartment Integration-Stowage

NASA Technical Reports Server (NTRS)

Morgan, L. Gary

2007-01-01

This viewgraph presentation describes the Orbiter Crew Compartment Integration (CCI) stowage. The evolution of orbiter crew compartment stowage volume is also described, along with photographs presented of the on-orbit volume stowage capacity.

STS-103 Crew Training

NASA Technical Reports Server (NTRS)

1999-01-01

The Hubble Space Telescope (HST) team is preparing for NASA's third scheduled service call to Hubble. This mission, STS-103, will launch from Kennedy Space Center aboard the Space Shuttle Discovery. The seven flight crew members are Commander Curtis L. Brown, Pilot Scott J. Kelly, European Space Agency (ESA) astronaut Jean-Francois Clervoy who will join space walkers Steven L. Smith, C. Michael Foale, John M. Grunsfeld, and ESA astronaut Claude Nicollier. The objectives of the HST Third Servicing Mission (SM3A) are to replace the telescope's six gyroscopes, a Fine-Guidance Sensor, an S-Band Single Access Transmitter, a spare solid-state recorder and a high-voltage/temperature kit for protecting the batteries from overheating. In addition, the crew plans to install an advanced computer that is 20 times faster and has six times the memory of the current Hubble Space Telescope computer. To prepare for these extravehicular activities (EVAs), the SM3A astronauts participated in Crew Familiarization sessions with the actual SM3A flight hardware. During these sessions the crew spent long hours rehearsing their space walks in the Guidance Navigation Simulator and NBL (Neutral Buoyancy Laboratory). Using space gloves, flight Space Support Equipment (SSE), and Crew Aids and Tools (CATs), the astronauts trained with and verified flight orbital replacement unit (ORU) hardware. The crew worked with a number of trainers and simulators, such as the High Fidelity Mechanical Simulator, Guidance Navigation Simulator, System Engineering Simulator, the Aft Shroud Door Trainer, the Forward Shell/Light Shield Simulator, and the Support Systems Module Bay Doors Simulator. They also trained and verified the flight Orbital Replacement Unit Carrier (ORUC) and its ancillary hardware. Discovery's planned 10-day flight is scheduled to end with a night landing at Kennedy.

46 CFR 185.420 - Crew training.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 7 2010-10-01 2010-10-01 false Crew training. 185.420 Section 185.420 Shipping COAST...) OPERATIONS Crew Requirements § 185.420 Crew training. (a) The owner, charterer, master or managing operator... duties listed in the station bill required by § 185.514 of this part. (b) Training conducted on a sister...

46 CFR 185.420 - Crew training.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 7 2011-10-01 2011-10-01 false Crew training. 185.420 Section 185.420 Shipping COAST...) OPERATIONS Crew Requirements § 185.420 Crew training. (a) The owner, charterer, master or managing operator... duties listed in the station bill required by § 185.514 of this part. (b) Training conducted on a sister...

STS-63 crew insignia

NASA Technical Reports Server (NTRS)

1994-01-01

Designed by the crew members, the crew patch depicts the Orbiter maneuving to rendezvous with Russia's Space Station Mir. The name is printed in Cyrillic on the side of the station. Visible in the Orbiter's payload bay are the commercial space laboratory Spacehab and the Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) satellite which are major payloads on the flight. The six points on the rising sun and the three stars are symbolic of the mission's Space Transportation System (STS) numerical designation. Flags of the United States and Russia at the bottom of the patch symbolize the cooperative operations of this mission. The crew will be flying aboard the space shuttle Discovery.

Coordinated crew performance in commercial aircraft operations

NASA Technical Reports Server (NTRS)

Murphy, M. R.

1977-01-01

A specific methodology is proposed for an improved system of coding and analyzing crew member interaction. The complexity and lack of precision of many crew and task variables suggest the usefulness of fuzzy linguistic techniques for modeling and computer simulation of the crew performance process. Other research methodologies and concepts that have promise for increasing the effectiveness of research on crew performance are identified.

STS-92 crew talk to media at Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

At Launch Pad 39A during a question and answer session with the media, STS-92 Commander Brian Duffy talks about the mission. Standing next to him, left to right, are Pilot Pamela Ann Melroy and Mission Specialists Leroy Chiao, William S. McArthur Jr., Peter J.K. 'Jeff' Wisoff, Michael E. Lopez-Alegria and Koichi Wakata of Japan. The crew is at KSC for Terminal Countdown Demonstration Test activities that provide emergency egress training, opportunities to inspect the mission payload, and a simulated countdown. The slidewire basket area is a landing site for the crew if they have to use the slidewire baskets to exit the orbiter on the pad in an emergency. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program.

STS-93 crew practices emergency egress training from Launch Pad 39B

NASA Technical Reports Server (NTRS)

1999-01-01

The STS-93 crew pose in front of an M-113, an armored personnel carrier, before emergency egress training from the launch pad. From left are Mission Specialist Steven A. Hawley (Ph.D.), Pilot Jeffrey S. Ashby, Mission Specialist Michel Tognini of France, Commander Eileen M. Collins and Mission Specialist Catherine G. Coleman. Collins is the first woman to serve as mission commander. Tognini represents the Centre National d'Etudes Spatiales (CNES). TCDT activities familiarize the crew with the mission, provide training in emergency exit from the orbiter and launch pad, and include a launch-day dress rehearsal culminating with a simulated main engine cut-off. The primary mission of STS- 93 is the release of the Chandra X-ray Observatory, which will allow scientists from around the world to obtain unprecedented X- ray images of exotic environments in space to help understand the structure and evolution of the universe. Chandra is expected to provide unique and crucial information on the nature of objects ranging from comets in our solar system to quasars at the edge of the observable universe. Since X-rays are absorbed by the Earth's atmosphere, space-based observatories are necessary to study these phenomena and allow scientists to analyze some of the greatest mysteries of the universe.

Earth Observations taken by Expedition 38 crewmember

NASA Image and Video Library

2014-02-08

ISS038-E-042992 (10 Feb. 2014) --- One of the Expedition 38 crew members aboard the International Space Station downlinked this vertical 600mm night view of Sochi, Russia, which clearly shows the site of the 2014 Winter Olympics while they are just a few days underway. Fisht Stadium where the Opening Ceremonies were held on Feb. 7 is easily recognizable as the bright circular structure. Sochi is a city in Krasnodar Krai, Russia, located on the Black Sea coast near the border between Georgia/Abkhazia and Russia. It has an area of 1,353 square miles or 3,505 square kilometers.

STS-92 crew arrives at KSC for launch

NASA Technical Reports Server (NTRS)

2000-01-01

Still seated in the T-38 jet aircraft that arrived moments before at the Shuttle Landing Facility, STS-92 Mission Specialist Peter J.K. '''Jeff''' Wisoff shows his happiness in being back at KSC for launch. He and other crew members Commander Brian Duffy, Pilot Pamela Ann Melroy and Mission Specialists Koichi Wakata of Japan, Leroy Chiao, Michael E. Lopez-Alegria and William S. McArthur Jr. later talked to a waiting group of media at the Shuttle Landing Facility. The mission is the fifth flight for the construction of the International Space Station. The payload includes the Integrated Truss Structure Z-1 and the third Pressurized Mating Adapter. During the 11-day mission, four extravehicular activities (EVAs), or space walks, are planned.

STS-92 crew arrives at KSC for launch

NASA Technical Reports Server (NTRS)

2000-01-01

Still seated in the T-38 jet aircraft that arrived moments before at the Shuttle Landing Facility, STS-92 Mission Specialist William S. McArthur Jr. shows his happiness in being back at KSC for launch. He and other crew members Commander Brian Duffy, Pilot Pamela Ann Melroy and Mission Specialists Koichi Wakata of Japan, Leroy Chiao, Peter J.K. '''Jeff''' Wisoff and Michael E. Lopez-Alegria later talked to a waiting group of media at the Shuttle Landing Facility. The mission is the fifth flight for the construction of the International Space Station. The payload includes the Integrated Truss Structure Z-1 and the third Pressurized Mating Adapter. During the 11-day mission, four extravehicular activities (EVAs), or space walks, are planned.

Dummy left behind by Skylab 3 crew for the Skylab 4 crew

NASA Image and Video Library

1973-08-16

SL3-113-1586 (July-September 1973) --- This photograph is an illustration of the humorous side of the Skylab 3 crew. This dummy was left behind in the Skylab space station by the Skylab 3 crew to be found by the Skylab 4 crew. The dummy is dressed in a flight suit and placed in the Lower Body Negative Pressure Device. The name tag indicates that it represents Gerald P. Carr, Skylab 4 commander, in the background is a partial view of the dummy for William R. Pogue, Skylab 4 pilot, propped upon the bicycle ergometer. The dummy representing Edward G. Gibson, Skylab science pilot, was left in the waste compartment. Astronauts Alan L. Bean, Owen K. Garriott and Jack R. Lousma were the Skylab 3 crewmen. Photo credit: NASA

STS-93 / Columbia Flight Crew Photo Op & QA at Pad for TCDT

NASA Technical Reports Server (NTRS)

1999-01-01

The primary objective of the STS-93 mission was to deploy the Advanced X-ray Astrophysical Facility, which had been renamed the Chandra X-ray Observatory in honor of the late Indian-American Nobel Laureate Subrahmanyan Chandrasekhar. The mission was launched at 12:31 on July 23, 1999 onboard the space shuttle Columbia. The mission was led by Commander Eileen Collins. The crew was Pilot Jeff Ashby and Mission Specialists Cady Coleman, Steve Hawley and Michel Tognini from the Centre National d'Etudes Spatiales (CNES). This videotape shows a pre-flight press conference. Prior to the astronauts' arrival at the bunker area in front of the launch pad, the narrator discusses some of the training that the astronauts are scheduled to have prior to the launch, particularly the emergency egress procedures. Commander Collins introduces the crew and fields questions from the assembled press. Many questions are asked about the experiences of Commander Collins, and Mission Specialist Coleman as women in NASA. The press conference takes place outside in front of the Shuttle Columbia on the launch pad.

In-Space Crew-Collaborative Task Scheduling

NASA Technical Reports Server (NTRS)

Jaap, John; Meyer, Patrick; Davis, Elizabeth; Richardson, Lea

2007-01-01

For all past and current human space missions, the final scheduling of tasks to be done in space has been devoid of crew control, flexibility, and insight. Ground controllers, with minimal input from the crew, schedule the tasks and uplink the timeline to the crew or uplink the command sequences to the hardware. Prior to the International Space Station (ISS), the crew could make requests about tomorrow s timeline, they could omit a task, or they could request that something in the timeline be delayed. This lack of control over one's own schedule has had negative consequences. There is anecdotal consensus among astronauts that control over their own schedules will mitigate the stresses of long duration missions. On ISS, a modicum of crew control is provided by the job jar. Ground controllers prepare a task list (a.k.a. "job jar") of non-conflicting tasks from which jobs can be chosen by the in space crew. Because there is little free time and few interesting non-conflicting activities, the task-list approach provides little relief from the tedium of being micro-managed by the timeline. Scheduling for space missions is a complex and laborious undertaking which usually requires a large cadre of trained specialists and suites of complex software tools. It is a giant leap from today s ground prepared timeline (with a job jar) to full crew control of the timeline. However, technological advances, currently in-work or proposed, make it reasonable to consider scheduling a collaborative effort by the ground-based teams and the in-space crew. Collaboration would allow the crew to make minor adjustments, add tasks according to their preferences, understand the reasons for the placement of tasks on the timeline, and provide them a sense of control. In foreseeable but extraordinary situations, such as a quick response to anomalies and extended or unexpected loss of signal, the crew should have the autonomous ability to make appropriate modifications to the timeline, extend the

Columbia Crew Survival Investigation Report

NASA Technical Reports Server (NTRS)

2009-01-01

NASA commissioned the Columbia Accident Investigation Board (CAIB) to conduct a thorough review of both the technical and the organizational causes of the loss of the Space Shuttle Columbia and her crew on February 1, 2003. The accident investigation that followed determined that a large piece of insulating foam from Columbia s external tank (ET) had come off during ascent and struck the leading edge of the left wing, causing critical damage. The damage was undetected during the mission. The CAIB's findings and recommendations were published in 2003 and are available on the web at http://caib.nasa.gov/. NASA responded to the CAIB findings and recommendations with the Space Shuttle Return to Flight Implementation Plan. Significant enhancements were made to NASA's organizational structure, technical rigor, and understanding of the flight environment. The ET was redesigned to reduce foam shedding and eliminate critical debris. In 2005, NASA succeeded in returning the space shuttle to flight. In 2010, the space shuttle will complete its mission of assembling the International Space Station and will be retired to make way for the next generation of human space flight vehicles: the Constellation Program. The Space Shuttle Program recognized the importance of capturing the lessons learned from the loss of Columbia and her crew to benefit future human exploration, particularly future vehicle design. The program commissioned the Spacecraft Crew Survival Integrated Investigation Team (SCSIIT). The SCSIIT was asked to perform a comprehensive analysis of the accident, focusing on factors and events affecting crew survival, and to develop recommendations for improving crew survival for all future human space flight vehicles. To do this, the SCSIIT investigated all elements of crew survival, including the design features, equipment, training, and procedures intended to protect the crew. This report documents the SCSIIT findings, conclusions, and recommendations.

Assured crew return capability Crew Emergency Return Vehicle (CERV) avionics

NASA Technical Reports Server (NTRS)

Myers, Harvey Dean

1990-01-01

The Crew Emergency Return Vehicle (CERV) is being defined to provide Assured Crew Return Capability (ACRC) for Space Station Freedom. The CERV, in providing the standby lifeboat capability, would remain in a dormat mode over long periods of time as would a lifeboat on a ship at sea. The vehicle must be simple, reliable, and constantly available to assure the crew's safety. The CERV must also provide this capability in a cost effective and affordable manner. The CERV Project philosophy of a simple vehicle is to maximize its useability by a physically deconditioned crew. The vehicle reliability goes unquestioned since, when needed, it is the vehicle of last resort. Therefore, its systems and subsystems must be simple, proven, state-of-the-art technology with sufficient redundancy to make it available for use as required for the life of the program. The CERV Project Phase 1'/2 Request for Proposal (RFP) is currently scheduled for release on October 2, 1989. The Phase 1'/2 effort will affirm the existing project requirements or amend and modify them based on a thorough evaluation of the contractor(s) recommendations. The system definition phase, Phase 2, will serve to define CERV systems and subsystems. The current CERV Project schedule has Phase 2 scheduled to begin October 1990. Since a firm CERV avionics design is not in place at this time, the treatment of the CERV avionics complement for the reference configuration is not intended to express a preference with regard to a system or subsystem.

ML Crew Access Arm Move

NASA Image and Video Library

2017-11-10

A heavy-load transport truck carrying the Orion crew access arm passes the Vehicle Assembly Building on its way to the mobile launcher at NASA's Kennedy Space Center in Florida. The access arm will be installed at about the 274-foot level on the mobile launcher tower. It will rotate from its retracted position and interface with the Orion crew hatch location to provide entry to the Orion crew module. The Ground Systems Development and Operations Program is overseeing installation of umbilicals and launch accessories on the ML tower to prepare for Exploration Mission-1.

Cockpit and cabin crew coordination

DOT National Transportation Integrated Search

1988-02-01

Cockpit and cabin crew coordination is crucial not only in emergencies, but : also during normal operations. The purposes of this study were to determine the : status of crew coordination in the industry and to identify the implications for : flight ...

STS-100 Crew Training

NASA Technical Reports Server (NTRS)

2001-01-01

Footage shows the crew of STS-100, Commander Kent Rominger, Pilot Jeffrey Ashby, and Mission Specialists Chris Hadfield, Scott Parazynski, John Phillips, Umberto Guidoni, and Yuri Valentinovich Lonchakov, during various parts of their training, including the crew photo session, postlanding egress, extravehicular activity (EVA) large tool training, EVA training in the Neutral Buoyancy Laboratory (NBL), secondary payload training, and during VHF training.

Exploring flight crew behaviour

NASA Technical Reports Server (NTRS)

Helmreich, R. L.

1987-01-01

A programme of research into the determinants of flight crew performance in commercial and military aviation is described, along with limitations and advantages associated with the conduct of research in such settings. Preliminary results indicate significant relationships among personality factors, attitudes regarding flight operations, and crew performance. The potential theoretical and applied utility of the research and directions for further research are discussed.

STS 41-G crew prepares to leave for KSC

NASA Image and Video Library

1984-10-01

41G-90029 / S17-90029 (2 Oct 1984) --- These five astronauts prepare to board T-38 jet aircraft for a trip to Florida where they will begin preparations for a trip into space aboard the Challenger later this week. Astronaut Robert L. Crippen, left, leads the way. The crew commander is followed by (l.-r.) Sally K. Ride (extreme left edge), Kathryn D. Sullivan, David C. Leestma and Jon A. McBride, McBride is pilot and the others are mission specialists. Marc Garneau, representing the National Research Council of Canada and Paul D. Scully-Power, a civilian oceanographer with the U.S. Navy, are the payload specialists who will fly to Florida aboard a Gulfstream aircraft.

Orion Crew Module Move

NASA Image and Video Library

2017-11-17

Technicians in clean-room suits attach a crane to the Orion crew module for Exploration Mission-1 for its move to the thermal chamber in the Neil Armstrong Operations and Checkout Building high bay at NASA's Kennedy Space Center in Florida. Orion will be lifted out of a test stand and lowered onto another stand to for the move. The crew module will undergo a thermal cycle test to assess the workmanship of critical hardware and structural locations. The test also demonstrates crew module subsystem operations in a thermally stressing environment to confirm no damage or anomalous hardware conditions as a result of the test. The Orion spacecraft will launch atop NASA's Space Launch System rocket on its first uncrewed integrated flight.

Cockpit and cabin crew coordination

DOT National Transportation Integrated Search

1988-02-28

Cockpit and cabin crew coordination is crucial not only in emergencies, but also during normal operations. The purposes of this study were to determine the status of crew coordination in the industry and to identify the implications for flight safety...

STS-93 crew members take part in an emergency egress exercise

NASA Technical Reports Server (NTRS)

1999-01-01

During an emergency egress exercise at the launch pad, Pilot Jeffrey S. Ashby (left) and Commander Eileen M. Collins (right) practice getting into the slidewire basket that is part of an emergency escape route for persons in the Shuttle and on the Rotating Service Structure. The STS-93 crew has been taking part in Terminal Countdown Demonstration Test (TCDT) activities that include the emergency exit training and a launch-day dress rehearsal culminating with a simulated main engine cut-off. Other crew members participating are Mission Specialists Catherine G. Coleman (Ph.D.), Steven A. Hawley (Ph.D.), and Michel Tognini of France, who represents the Centre National d'Etudes Spatiales (CNES). Collins is the first woman to serve as a Shuttle commander. The primary mission of STS-93 is the release of the Chandra X-ray Observatory, which will allow scientists from around the world to obtain unprecedented X-ray images of exotic environments in space to help understand the structure and evolution of the universe. The targeted launch date for STS-93 is no earlier than July 20 at 12:36 a.m. EDT from Launch Pad 39B.