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Chang, Yale

Publications and source records attributed to Chang, Yale.

4 records
All sourcesNASA NTRSDOE OSTI
DOE OSTI2018

Solid Rocket Propellant Fires Characterization, Final Scientific/Technical Report for 8 May 2014 through 4 October 2017

The Solid Rocket Propellant Fires Characterization Program continued the Johns Hopkins University Applied Physics Laboratory's (JHU/APL's) characterization of solid propellant fires under relevant accident conditions [at 1 atmosphere (atm) ambient pressure, in humid weather], with significant findings that have revolutionized the understanding of these fires and the response and behavior of plutonium dioxide (plutonia) surrogates in the fires. These findings have been disseminated in Department of Energy (DOE) internal working meetings and at technical interchange meetings (TIMs) with DOE, the Interagency Nuclear Safety Review Panel (INSRP), and NASA in support of the Presidential nuclear safety launch approval process for the Mars 2020 mission, as well as via several conference and journal papers.

10 SYNTHETIC FUELS↗
DOE OSTI2014

Final Scientific/Technical Report

JHU/APL conducted solid propellant fire characterization tests in warm, humid, ambient conditions near sea level. Yttria and ceria surrogate materials were placed in the fires. The substrates simulating ground surfaces were concrete from a Kennedy Space Center launch pad, and steel covered with a protective ablative material representing a launch platform. In-situ instrumentation consisted of witness materials, thermocouples, air handlers, filters, and cascade impactors; remote instrumentation consisted of optical cameras and spectrometers. Test and analysis team members included the Naval Air Warfare Center Aircraft Division, Sandia National Laboratories (SNL), Alliant Techsystems, and the Johns Hopkins University. Test data were analyzed, reported, and delivered, including plume rise and transport captured on video. Derivation of the alumina particle size distributions formed the basis for condensing vapor and agglomeration estimates. Assessment of alumina mass in the plume, along with the surrogate fraction from filter forensics, provided an estimate of airborne surrogate mass. Technical interchange meetings were held with SNL and the Jet Propulsion Laboratory. Specifications for the fire environment were developed and delivered. A thermochemistry model that simultaneously provides the maximum temperature and heat flux was developed and delivered. An SPIE paper on 3D pyrometry of the fire was written and presented.

36 MATERIALS SCIENCE↗
NASA NTRS1992

Application of composite materials to impact-insensitive munitions

An approach is outlined for developing bullet-impact-insensitive munitions based on composite materials that provide rapid venting of the rocket-motor case. Impact experiments are conducted with test specimens of hybrid laminates of graphite/epoxy and epoxy reinforcing with woven glass fibers. The dynamic strain response and initial impact force are measured with strain gauges, and perforation damage is examined in the plates. The results show that impact damage can be designed by means of parametric variations of the fiber, matrix, and ply orientations. It is suggested that rocket-motor cases can be designed with composite materials to provide rapid venting during the failure mode. The experimental ballistic testing performed provides data that can be used comparatively with analytical data on composite materials.

Neradka, Vincent F.↗