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991.
In the design of an aircraft at the stage of selecting its geometrical parameters, a method is proposed for evaluating the performance capabilities of manual control to ensure the quality of a given flight stabilization mode. The attainability of the given aircraft-pilot dynamic properties is evaluated by a frequency-domain method for permissible values of the aircraft and the pilot model parameters. The quality of the manual control for the longitudinal motion of the aircraft is evaluated. 相似文献
992.
R. J. Lillis D. A. Brain S. W. Bougher F. Leblanc J. G. Luhmann B. M. Jakosky R. Modolo J. Fox J. Deighan X. Fang Y. C. Wang Y. Lee C. Dong Y. Ma T. Cravens L. Andersson S. M. Curry N. Schneider M. Combi I. Stewart J. Clarke J. Grebowsky D. L. Mitchell R. Yelle A. F. Nagy D. Baker R. P. Lin 《Space Science Reviews》2015,196(1-4):357-358
993.
994.
N. E. Zubov E. A. Mikrin V. N. Ryabchenko A. V. Fomichev 《Russian Aeronautics (Iz VUZ)》2017,60(1):64-73
The problem of lateral motion stabilization is analytically solved for the fourth-order model of aircraft motion using the method of output signal control synthesis that is based on the control object decomposition. Numerical simulation data are presented. 相似文献
995.
Yu. V. Klochkov A. P. Nikolaev O. V. Vakhnina T. A. Kiseleva 《Russian Aeronautics (Iz VUZ)》2016,59(3):316-323
We developed a triangular discretization element of the fuselage fragment in the form of a thin shell compatible with the adjacent elements based on Lagrange multipliers. Solution of several test problems showed a high efficiency of using the modification of a triangular finite element being proposed. 相似文献
996.
C. S. Fish C. M. Swenson G. Crowley A. Barjatya T. Neilsen J. Gunther I. Azeem M. Pilinski R. Wilder D. Allen M. Anderson B. Bingham K. Bradford S. Burr R. Burt B. Byers J. Cook K. Davis C. Frazier S. Grover G. Hansen S. Jensen R. LeBaron J. Martineau J. Miller J. Nelsen W. Nelson P. Patterson E. Stromberg J. Tran S. Wassom C. Weston M. Whiteley Q. Young J. Petersen S. Schaire C. R. Davis M. Bokaie R. Fullmer R. Baktur J. Sojka M. Cousins 《Space Science Reviews》2014,181(1-4):61-120
Funded by the NSF CubeSat and NASA ELaNa programs, the Dynamic Ionosphere CubeSat Experiment (DICE) mission consists of two 1.5U CubeSats which were launched into an eccentric low Earth orbit on October 28, 2011. Each identical spacecraft carries two Langmuir probes to measure ionospheric in-situ plasma densities, electric field probes to measure in-situ DC and AC electric fields, and a science grade magnetometer to measure in-situ DC and AC magnetic fields. Given the tight integration of these multiple sensors with the CubeSat platforms, each of the DICE spacecraft is effectively a “sensor-sat” capable of comprehensive ionospheric diagnostics. The use of two identical sensor-sats at slightly different orbiting velocities in nearly identical orbits permits the de-convolution of spatial and temporal ambiguities in the observations of the ionosphere from a moving platform. In addition to demonstrating nanosat-based constellation science, the DICE mission is advancing a number of groundbreaking CubeSat technologies including miniaturized mechanisms and high-speed downlink communications. 相似文献
997.
A. A. Davydov 《Cosmic Research》2011,49(4):335-344
A communication satellite (small spacecraft) injected into a geosynchronous orbit is considered. Flywheel engines are used
to control the rotational spacecraft motion. The spacecraft after the emergency situation has passed into a state of uncontrolled
rotation. In this case, no direct telemetric information about parameters of its rotational motion was accessible. As a result,
the problem arose to determine the rotational satellite motion according to the available indirect information: current taken
from the solar panels. Telemetric measurements of solar panel current obtained on the time interval of a few hours were simultaneously
processed by the least squares method integrating the equations of rotational satellite motion. We present the results of
processing 10 intervals of the measurement data allowing one to determine the real rotational spacecraft motion and to estimate
the total angular momentum of flywheel engines. 相似文献
998.
999.
K. A. Alekseev 《Russian Aeronautics (Iz VUZ)》2011,54(1):84-88
Some general problems on simulation of folded cores are considered. The application potential of the present-day parametrical
CAD systems for designing constructions based on the regular and irregular structures is shown. 相似文献
1000.
The results of analyzing the reliability of six turbulence models are presented as applied to calculations of flows in the
asymmetric plane diffuser. The influence of grid parameters upon the calculation results is studied and the accuracy of flow
separation and reattachment points prediction is determined. Also carried out is the comparison of processor time spent for
calculations with the aid of each model. 相似文献