[PDF] Top 20 J. Aerosp. Technol. Manag. vol.7 número1

... Brouwer, D., 1959, “Solution of the Problem of Artiicial Satellite Theory without Drag”, Astronomical Journal, Vol. 64, No. 1274, pp. 378396. Coffey, S.L., Neal, H.L., Segerman, A.M. and Travisano, J.J., 1995, “An ... See full document

... he grid is structured and divided in blocks. Figure 5 shows a cut of the grid with a detail of the airfoil. Information is passed from one block to the other in a natural way by means of a simple strategy: the blocks are ... See full document

... excess of incident light, resulting in a contribution of charge to neighboring pixels. CMOS technology presents an independent design, where each photosite delivers digital data separately to avoid blooming efect, while ... See full document

... Connor, J., 2013, “Listening by Design: Teaching Students to Be More Collaborative”, Proceedings of the 9th CDIO Conference, MIT and Harvard University School of Engineering and Applie[r] ... See full document

... he estimated OSPL at 145 dB lit of (GEVS-SE, Rev A, June 1996) is considered. In contrast with the aerodynamic noise during light ascent, the nature of the lit of acoustic pressure loading is close to a difuse ield ... See full document

... DFMA guides the manufacture processes and materials that rule the Fins Module interface to the Microsatellite Launch Vehicle (VLM-1) main structure.. The results of this process are t[r] ... See full document

... Cases (b) and (c), which consider variation in the dynamic matrix of the smart composite structure and Kalman estimator, respectively, demonstrated better results in terms of vibratio[r] ... See full document

... The results show that the ring’s diameter is increased by increasing incident beam power or the distance of the laser beam’s focus for both surfaces.. In addition, increasing the work[r] ... See full document

... he transmission line can be considered lossy when the signal frequency is much below the critical frequency and lossless when the signal frequency is much above the critical frequency. his critical frequency is usually ... See full document

... However, the experimental results showed a considerable diference between the top sample (ibers normal to heat lux) and the lateral and biased sample (ibers inclined to heat lux direc[r] ... See full document

... and CEA are compared. For viscosity, relative errors are lower than 5% and, for thermal conductivity, the errors achieve 15%. he relative errors decrease when temperatures and pressures are reduced. A possible reason for ... See full document

... On the basis of full analysis of aircraft assembly’s feature, this study proposes a forecasting model based on support vector machine (SVM), which is optimized by particle swarm optim[r] ... See full document

... The environmental conditions (meteorological and oceanographic) are crucial for the successful launching of aerospace vehicles such as sounding rockets and satellite launch vehicle (V[r] ... See full document

... Fig. 7 is sustained by back and forth round-trip relections arising from the interfaces at the horn-waveguide junction and at the innermost wire ...and 7 agree with respect to the number of resonance dips, ... See full document

... While conducting the experiments, the observation was made in some EEDs bridge wire breaks (detected from hall sensor) before or at er the ignition (detected from photo detector) at c[r] ... See full document

... Gkikas G, Paipetis AS (2015) Optimisation and analysis of the reinforcement effect of carbon nanotubes in a typical matrix system. Meccanica 50:461-478. doi 10.1007/s11012-014-9915-z Gohardani O, Elola MC, Elizetxea C ... See full document

... Initially, the DSP Setup step conigures the peripherals to work properly. hen, the Calibration step aims at correcting any non-linearity in the generation of Vex(ω,t) before any measurement is performed. Load/Set ... See full document

... ABSTRACT: This paper brings the irst results concerning a new analytic model to evaluate atmospheric dispersion in rocket launch scenarios, namely Generalized Integral Laplace Transf[r] ... See full document

... In addition, this radar cross section model can be directly applied to the radar detection process to calculate the detection probability of a speciic aircraft at any attitude.. Four [r] ... See full document

... (2010) have estimated aircraft stability derivatives from acquired flight data using the Output Error Method (OEM) technique; in this study, longitudinal and lateral dynamics are deco[r] ... See full document