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[b]Ares Development Motor-2[/b] [i]The five-segment Ares motor for NASA's next-generation launch vehicle, features a design derived from the four-segment Space Shuttle reusable solid rocket motor.[/i] [b]53 Design Objectives - 764 Instrumentation Channels[/b] [list][*]Development Motor-2 (DM-2) is the second full-scale, full-duration test of an Ares five-segment reusable solid rocket motor [*]Cold condition motor to achieve reduced propellant mean bulk temperature (PMBT) to obtain performance data on the propellant grain design and delivered motor ballistic characteristics at lower bounds of certification limit [*]Obtain performance of field joints at lower bounds of temperature exposure (shrouding) [*]Obtain data on capability of thermal barrier system on forward field joint with intentional flow feature (demonstrate robustness of joint configuration) [*]Obtain performance data on the environmentally friendly insulator in the entire motor, including the aft dome [*]Obtain performance data on the redesigned nozzle cowl and 15-degree aft exit cone for structural and thermal requirements [*]Obtain vibration, acoustic and heat flux data to support definition of motor-generating external loads for the Ares Launch Vehicle[/list] [b]Countdown[/b] T-1 hrCommence Final CountdownT-45 minSecure Test Area and Commence Arming SequenceT-5 minVerify Test Bay ClearT-1 minCommit MotorT-0Motor IgnitionT+2 minCO2 Quench [b]Predicted Performance[/b] Action Time (sec)125.6Max Chamber Pressure (psia)937.4Chamber Gas Temp (°F)5,630Maximum Thrust (vacuum) (lbf)3,537,000Total Impulse (vacuum) (lbf-sec)366,750,000Loaded Propellant Weight (lbm)1,380,300 Click to enlarge or [URL=http://www.collectspace.com/review/dm2_atkfactsheet.pdf]download PDF[/URL]
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