Calculation of the incremental stress-strain relation of a polygonal packing

The constitutive relation of the quasi-static deformation on two dimensional packed samples of polygons is calculated using molecular dynamic simulations. The stress values at which the system remains stable are bounded by a failure surface, that shows a power law dependence on the pressure. Below the failure surface, non linear elasticity and plastic deformation are obtained, which are evaluated in the framework of the incremental linear theory. The results shows that the stiffness tensor can be directly related to the micro-contact rearrangements. The plasticity obeys a non-associated flow rule, with a plastic limit surface that does not agree with the failure surface.Comment: 11 pages, 20 figur

Results of the AFRSI Detailed-Environment Test of the 0.035-Scale SSV Pressure-Loads Model 84-0 in the Ames 11X11 Ft. TWT and the Lewis 8X6 Ft. and 10X10 Ft. SWT (OA-310A, B, C), Volume 2

In order to support analysis of the STS-6 advanced flexible reusable surface insulation (AFRSI) anomaly, data were obtained for aerodynamic and aeroacoustic environments in affected areas of the orbiter. Data are presented in tabular form

Design of Cooperative Networks

In this paper we analyse several approaches to the design of Cooperative Algorithms for solving a general problem: That of computing the values of some property over a spatial domain, when these values are constrained (but not uniquely determined) by some observations, and by some a priori knowledge about the nature of the solution (smoothness, for example). Specifically, we discuss the use of: Variational techniques; stochastic approximation methods for global optimization, and linear threshold networks. Finally, we present a new approach, based on the interconnection of Winner-take-all networks, for which it is possible to establish precise convergence results, including bounds on the rate of convergence.MIT Artificial Intelligence Laborator

Results of tests using a 0.030-scale model (45-0) of space shuttle vehicle orbiter in the NASA/ARC 12-foot pressure wind tunnel (OA159)

An experimental investigation (test OA159) was conducted in the NASA/ARC 12-foot Pressure Wind Tunnel from June 23 through July 8, 1975. The objective was to obtain detailed strut tare and interference effects of the support system used in the NASA/ARC 40 x 80-foot wind tunnel during 0.36-scale orbiter testing (OA100). Six-component force and moment data were obtained through an angle-of-attack range from -9 through +18 degrees with 0 deg angle of sideslip and a sideslip angle range from -9 through +18 degrees at 9 deg angle of attack results are presented

Does Culture Impact Academic Anxiety in University Students?

University students may experience academic anxiety when attending an institution of higher education. For this study we recruited a diverse population of college students with different cultural backgrounds to investigate if specific groups are more impacted by these experiences. The purpose of this study is to determine whether cultural factors (cultural inclusion, country of origin, language) influence academic anxiety in college students. A survey was distributed to Eastern Kentucky University students. The results indicated that cultural inclusion had the greatest impact on academic anxiety. Country of origin and language did not influence academic anxiety according to results

Effects of reaction control system jet simulation on the stability and control characteristics of a 0.015-scale space shuttle orbiter model in the Ames Research Center 3.5-foot hypersonic wind tunnel

An experimental investigation was performed in the Ames Research Center 3.5-Foot Hypersonic Wind Tunnel to obtain detailed effects which interactions between the RCS jet flow field and the local orbiter flow field have on orbiter hypersonic stability and control characteristics. Six-component force data were obtained through an angle-of-attack range of 15 to 35 deg with 0 deg angle of sideslip. The test was conducted with yaw, pitch and roll jet simulation at a free-stream Mach number of 10.3. These data simulate two SSV reentry flight conditions at Mach numbers of 28.3 and 10.3. Fuselage base pressures and pressures on the nonmetric RCS pods were obtained in addition to the basic force measurements. Model 42-0 was used for these tests

Results of a M = 5.3 heat transfer test of the integrated vehicle using phase-change paint techniques on the 0.0175-scale model 56-OTS in the NASA/Ames Research Center 3.5-foot hypersonic wind tunnel

An experimental investigation was performed in the NASA/Ames Research Center 3.5-foot Hypersonic Wind Tunnel to obtain supersonic heat-distribution data in areas between the orbiter and external tank using phase-change paint techniques. The tests used Novamide SSV Model 56-OTS in the first and second-stage ascent configurations. Data were obtained at a nominal Mach number of 5.3 and a Reynolds number per foot of 5 x 10 to the 6th power with angles of attack of 0 deg, +/- 5 deg, and sideslip angles of 0 deg and +/- 5 deg

Results of reaction control system on-orbit jet simulation using an 0.0175-scale configuration 3 space shuttle orbiter model (21-0) in the LaRC 60-foot vacuum sphere

An experimental investigation was conducted to obtain detailed effects of the RCS jet flow direct impingement on the orbiter during on-orbit flight of the space shuttle vehicle. RCS flow was simulated by blowing a jet of cold air from nozzles attached to the model sting support system near the fuselage base. Thrust was obtained by setting the nozzle plenum pressure. Three RCS on-orbit flight conditions were simulated. Six component force data were measured on the complete model