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Trummel, M.

Publications and source records attributed to Trummel, M..

Hybrid vehicle assessment. Phase 1: Petroleum savings analysis

The results of a comprehensive analysis of near term electric hybrid vehicles are presented, with emphasis on their potential to save significant amounts of petroleum on a national scale in the 1990s. Performance requirements and expected annual usage patterns of these vehicles are first modeled. The projected U.S. fleet composition is estimated, and conceptual hybrid vehicle designs are conceived and analyzed for petroleum use when driven in the expected annual patterns. These petroleum consumption estimates are then compared to similar estimates for projected 1990 conventional vehicles having the same performance and driven in the same patterns. Results are presented in the form of three utility functions and comparisons of sevral conceptual designs are made. The Hybrid Vehicle (HV) design and assessment techniques are discussed and a general method is explained for selecting the optimum energy management strategy for any vehicle mission battery combination. Conclusions and recommendations are presented, and development recommendations are identified.

Levin, R.

Specification of pyro shock tests

Specifications of pyro shock tests are treated as the interconnection between raw measurements (or estimates) of the environment and the various test methods available. After a definition of the environment, various aspects of test method specification are discussed including one-sided pulses, test simulation parameters, and the effects of Q. Different test configurations are considered including rigid fixture tests, pseudo-real structure, and real structure.

Trummel, M.

Specification and correlation of the sine vibration environment for Viking '75

Two Viking spacecraft will be individually launched on a new Titan IIIE/Centaur D-1T launch vehicle in August 1975. The method for the establishment of spacecraft sine vibration test levels prior to availability of any Titan IIIE/Centaur D-1T flight data by use of both computer simulations and data from previous Titan and Atlas Centaur vehicles is described. The specification level is compared with actual flight data obtained from a proof flight launch of the Titan IIIE/Centaur D-1T and a Viking dynamic simulator in January 1974. An objective of the proof flight launch was to obtain estimates of the flight loads and environments. The criteria used to minimize the structural weight that would result from an unmodified application of a sine test environment are described.

Snyder, R. E.