Accession Number:

ADA326810

Title:

Comparison of Separation Shock for Explosive and Nonexplosive Release Actuators on a Small Spacecraft Panel.

Descriptive Note:

Technical memo.,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s):

• Lucy, M. H.
• Buehrle, R. D.
• Woolley, J. P.

Report Date:

1996-12-01

Pagination or Media Count:

53.0

Abstract:

Functional shock, safety, overall system costs, and emergence of new technologies, have raised concerns regarding continued use of pyrotechnics on spacecraft. NASA Headquarters participated with Lockheed Martin Missile and Space Co. in objectively evaluating applicability of some non-explosive actuators NEA mechanisms to reduce small spacecraft and booster separation event shock. Comparative tests were conducted on a structural simulator using five different separation nut mechanisms consisting of three pyrotechnics. Multiple actuations were performed with preloads up to 7000 pounds, 7000 being the comparison standard. All devices except LMAs NEA rotary flywheel nut concept were available units with no added provisions to attenuate shock. Accelerometer measurements were recorded, reviewed, processed into Shock Response Spectra SRS, and comparisons performed.

Descriptors:

• *SHOCK TESTS
• *LAUNCH VEHICLES
• *SPACE PROPULSION
• ACCELEROMETERS
• BOOSTER ROCKET ENGINES
• PYROTECHNICS
• RECOVERABLE SPACECRAFT
• EXPLOSIVE ACTUATORS
• FLYWHEELS
• SHOCK SPECTRA

Subject Categories:

• Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE