Deployable platform systems development

The long range objective is to achieve technology readiness for one or more deployable platform systems by 1986. Engineering plans and approaches to meet this goal are presented in outline form

A preliminary look at control augmented dynamic response of structures

The augmentation of structural characteristics, mass, damping, and stiffness through the use of control theory in lieu of structural redesign or augmentation was reported. The standard single-degree-of-freedom system was followed by a treatment of the same system using control augmentation. The system was extended to elastic structures using single and multisensor approaches and concludes with a brief discussion of potential application to large orbiting space structures

Apparatus for producing high purity silicon carbide crystals Patent

Device for producing high purity silicon carbide on carbon base by hydrogen reduction of silicon tetrachlorid

Method of coating carbonaceous base to prevent oxidation destruction and coated base Patent

Vapor deposited laminated nitride-silicon coating for corrosion prevention of carbonaceous surface

Space Shuttle Main Engine (SSME) Pogo testing and results

To effectively assess the Pogo stability of the space shuttle vehicle, it was necessary to characterize the structural, propellant, and propulsion dynamics subsystems. Extensive analyses and comprehensive testing programs were established early in the project as an implementation of management philosophy of Pogo prevention for space shuttle. The role of the space shuttle main engine (SSMF) in the Pogo prevention plans, the results obtained from engine ground testing with analysis, and measured data from STS-1 flight are discussed

Strategic Institutional Choice: Voters, States, and Congressional Term Limits

This paper demonstrates that states’ decisions on limiting congressional terms are empirically determined by measures of relative political influence in Congress. States’ choices on term limits are quantified as a multiple-categorical variable that reflects variation in the stringency of term limits laws passed. Using 1992 data on the American states, the model controls for unobserved heterogeneity that is introduced by some voters having access to institutions of direct democracy. At 2002 state-level values for congressional tenure and federal spending, the model predicts approximately eight to ten additional states would choose to limit terms of their own congressional delegations, but are prohibited from doing so under a Supreme Court ruling. The results hold implications for institutional federalism and the potential passage of similar political institutions across the states.term limits; political institutions; federalism; political economy

Solventless LARC-160 Polyimide Matrix Resin

The addition polyimide, LARC-160, which was originally synthesized from low cost liquid monomers as a laminating resin in ethanol, was prepared as a solventless, high viscosity, neat liquid resin. The resin was processed by hot-melt coating techniques into graphite prepreg with excellent tack and drape. Comparable data on graphite reinforced laminates made from solvent-coated and various hot-melt coated prepreg were generated. LARC-160, because of its liquid nature, can be easily autoclave processed to produce low void laminates. Liquid chromatographic fingerprints indicate good reaction control on resin scale ups. Minor changes in monomer ratios were also made to improve the thermal aging performance of graphite laminates

Study of a safety margin system for powered-lift STOL aircraft

A study was conducted to explore the feasibility of a safety margin system for powered-lift aircraft which require a backside piloting technique. The objective of the safety margin system was to present multiple safety margin criteria as a single variable which could be tracked manually or automatically and which could be monitored for the purpose of deriving safety margin status. The study involved a pilot-in-the-loop analysis of several safety margin system concepts and a simulation experiment to evaluate those concepts which showed promise of providing a good solution. A system was ultimately configured which offered reasonable compromises in controllability, status information content, and the ability to regulate the safety margin at some expense of the allowable low speed flight path envelope

Computed Responses of Several Aircraft to Atmospheric Turbulence and Discrete Wind Shears

The computed RMS and peak responses due to atmospheric turbulence and discrete wind shears, respectively, are presented for several aircraft in different flight conditions. The responses are presented with and without the effects of a typical second order washout filter. A complete set of dimensional stability derivatives for each aircraft/flight condition combination evaluated is also presented