Restored Apollo 11 Moonwalk - Original NASA EVA Mission Video - Walking on the Moon
3:02:31
YouTubeNASA
Restored Apollo 11 Moonwalk - Original NASA EVA Mission Video - Walking on the Moon
Original Mission Video as aired in July 1969 depicting the Apollo 11 astronauts conducting several tasks during extravehicular activity (EVA) operations on the surface of the moon. The EVA lasted approximately 2.5 hours with all scientific activities being completed satisfactorily. The Apollo 11 (EVA) began at 10:39:33 p.m. EDT on July 20, 1969 ...
19.6M viewsJul 17, 2014
Ascent propulsion system Rocket Engine Design
NASA Validates Revolutionary Propulsion Design for Deep Space Missions - NASA
NASA Validates Revolutionary Propulsion Design for Deep Space Missions - NASA
nasa.gov
Jan 25, 2023
This advanced rocket engine design could one day change how future propulsion systems are built! Marshall propulsion engineers designed the Rotating Detonation Rocket Engine (RDRE) to differ from a traditional rocket engine by generating thrust using a supersonic combustion phenomenon known as detonation. This NASA Technology design produces more power while using less fuel than today’s propulsion systems and has the potential to power both human landers and interplanetary vehicles to deep space
0:18
This advanced rocket engine design could one day change how future propulsion systems are built! Marshall propulsion engineers designed the Rotating Detonation Rocket Engine (RDRE) to differ from a traditional rocket engine by generating thrust using a supersonic combustion phenomenon known as detonation. This NASA Technology design produces more power while using less fuel than today’s propulsion systems and has the potential to power both human landers and interplanetary vehicles to deep space
FacebookNASA's Marshall Space Flight
920.2K viewsJan 25, 2023
The following measurements were made in a sea-level test of a solid propellant rocket motor (all cross sections are circular and unchanging);Burn Duration = 50 sInitial Propulsion System Mass = 1300 kgMass of the rocket motor after test = 320 kgSea-level thrust = 63,250 NChamber pressure = 7.00 MPaNozzle exit pressure = 70.0 kPaNozzle throat diameter = 8.66 cmNozzle exit diameter = 27.2 cmDetermine mass flow, V2, c^*, and c at sea-level. Also determine the pressure thrust and the specific impuls
The following measurements were made in a sea-level test of a solid propellant rocket motor (all cross sections are circular and unchanging);Burn Duration = 50 sInitial Propulsion System Mass = 1300 kgMass of the rocket motor after test = 320 kgSea-level thrust = 63,250 NChamber pressure = 7.00 MPaNozzle exit pressure = 70.0 kPaNozzle throat diameter = 8.66 cmNozzle exit diameter = 27.2 cmDetermine mass flow, V2, c^*, and c at sea-level. Also determine the pressure thrust and the specific impuls
numerade.com
May 25, 2023
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