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August 31, 2010
Ares Development Motor - 2
Ground Test
A premier aerospace and defense company www.atk.com
53 Design Objectives — 764 Instrumentation Channels
Approved for public release, NASA/MSFC, August 16, 2010
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.
Action Time (sec) 125.6
Max Chamber Pressure (psia) 937.4
Chamber Gas Temp (°F) 5,630 Maximum Thrust (vacuum) (lbf) 3,537,000
Total Impulse (vacuum) (lbf-sec) 366,750,000
Loaded Propellant Weight (lbm) 1,380,300
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
T-1 hr Commence Final Countdown T-45 min Secure Test Area and
Commence Arming Sequence T-5 min Verify Test Bay Clear
T-1 min Commit Motor T-0 Motor Ignition
T+2 min CO2 Quench
Cold Conditioning
1
2
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7
2
3 4 Field Joint
PBI-NBR Insulation 5
5 Aft Dome
Nozzle
PBI-NBR Insulation
Cowl
6
Countdown