NASA Validates Revolutionary Propulsion Design for Deep Space Missions - NASA

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

307K views · 2.7K reactions | Take a look at the test run at #Tongchuan engine testing facility ! The latest step toward achieving these plans was announced on Monday, China's Space Day, by the Academy of Aerospace Propulsion Technology in Xi'an of Shaanxi province, a subsidiary of China Aerospace Science and Technology Corp and the country's dominant maker of liquid-propellant rocket engines #SpaceDayofChina | Wu Lei | Facebook