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51.
Chan-oh Min Dae-woo Lee Kyeum-rae Cho Sung-jin Jo Jang-sik Yang Won-boo Lee 《Aerospace Science and Technology》2011,15(4):269-282
The reentry vehicle is affected by various disturbances such as a wind gust, atmospheric condition or aerodynamic problems in the approach and landing phase. Therefore it is necessary to design a robust control scheme. This paper presents a control scheme using Mamdani fuzzy PD controller. In this paper, the reference trajectories are generated using geometric parameters for disturbed circumstances with 4 cases: nominal, headwind and tailwind, drag increased case. Then, a Mamdani fuzzy PD controller was designed in this study. Twenty-five rules were applied in the knowledge-based system. The max–min method for a fuzzy inference system and the center-of-mass method in defuzzification were used. Finally, guidance and control simulations are performed for verification of proposed controller using generated reference trajectories. In addition, the Monte Carlo simulation is performed considering various disturbances. The results show that proposed Mamdani fuzzy PD controller has reliability and robustness for control of reentry vehicle with wind disturbance in the approach and landing phases. 相似文献
52.
Young Chang Choi Kyung-Ho Noh Jae-Woo Lee Yung-Hwan Byun Bong-Kyo Park 《Aerospace Science and Technology》2009,13(7):406-414
Compared with the conventional ground rocket launching, air-launching has many advantages. However, a comprehensive and integrated system design approach is required because the physical geometry of air launch vehicle is quite dependent on the installation limitation of the mother plane. For the selection of the best system alternative, a trade study for the first stage engine type and launching speeds is performed using a sequential optimization technique, confirming the feasibility of the baseline air-launching rocket. Then, a system design has been performed using the multi-disciplinary feasible (MDF) design optimization method. Analysis modules include mission analysis, staging, propulsion analysis, configuration, weight analysis, aerodynamics analysis and trajectory analysis. As a result of multi-disciplinary system optimization, a supersonic air launching rocket with total mass of 1244.9 kg, total length of 6.36 m, outer diameter of 0.60 m has been successfully designed to launch a satellite of 7.5 kg to the 700 km circular orbit. 相似文献
53.
K. Yoshimura K. Abe H. Fuke S. Haino T. Hams M. Hasegawa A. Horikoshi K.C. Kim T. Kumazawa A. Kusumoto M.-H. Lee Y. Makida S. Matsuda Y. Matsukawa J.W. Mitchell A.A. Moiseev J. Nishimura M. Nozaki R. Orito J.F. Ormes K. Sakai M. Sasaki E.S. Seo Y. Shikaze R. Shinoda R.E. Streitmatter J. Suzuki K. Takeuchi N. Thakur K. Tanaka T. Yamagami A. Yamamoto T. Yoshida 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2008
54.
Tae Yoon Um Jang Gyu Lee Seong-Taek Park Chan Gook Park 《IEEE transactions on aerospace and electronic systems》2000,36(1):226-233
This paper presents a new approach to noise covariances estimation for a linear, time-invariant, stochastic system with constant but unknown bias states. The system is supposed to satisfy controllable/observable conditions without bias states. Based on a restructured data representation, the covariance of a new variable that consists of measurement vectors is expressed as a linear combination of unknown parameters. Noise covariances are then estimated by employing a recursive least-squares algorithm. The proposed method requires no a priori estimates of noise covariances, provides consistent estimates, and can also be applied when the relationship between bias states and other states is unknown. The method has been applied to strapdown inertial navigation system initial alignment. Simulation results indicate a satisfactory performance of the proposed method 相似文献
55.
The theory of shock acceleration of energetic particles is briefly discussed and reviewed with an emphasis on clarifying the apparent distinction between the V × B and Fermi mechanisms. Attention is restricted to those situations in which the energetic particles do not themselves influence the given shock structure. In particular, application of the theory to the acceleration of energetic particles in corotating interaction regions (CIR) in the solar wind is presented. Here particles are accelerated at the forward and reverse shocks which bound the CIR by being compressed between the shock fronts and magnetic irregularities upstream from the shocks, or by being compressed between upstream irregularities and those downstream from the shocks. Particles also suffer adiabatic deceleration in the expanding solar wind, an effect not included in previous shock models for acceleration in CIRs. The model is able to account for the observed exponential spectra at Earth, the observed behavior of the spectra with radial distance, the observed radial gradients in the intensity, and the observed differences in the intensity and spectra at the forward and reverse shocks.Calculations and resulting energy spectra are also presented for shock acceleration of energetic particles in large solar flare events. Based on the simplifying assumption that the shock evolves as a spherically symmetric Sedov blast wave, the calculation yields the time-integrated spectrum of particles initially injected at the shock which eventually escape ahead of the shock into interplanetary space. The spectra are similar to those observed at Earth. Finally further applications are suggested.An invited paper presented at STIP Workshop on Shock Waves in the Solar Corona and Interplanetary Space, 15–19 June, 1980, Smolenice, Czechoslovakia. 相似文献
56.
We present a brief introduction to the essential physics of coronal mass ejections as well as a review of theory and models
of CME initiation, solar energetic particle (SEP) acceleration, and shock propagation. A brief review of the history of CME
models demonstrates steady progress toward an understanding of CME initiation, but it is clear that the question of what initiates
CMEs has still not been solved. For illustration, we focus on the flux cancellation model and the breakout model. We contrast
the similarities and differences between these models, and we examine how their essential features compare with observations.
We review the generation of shocks by CMEs. We also outline the theoretical ideas behind the origin of a gradual SEP event
at the evolving CME-driven coronal/interplanetary shock and the origin of “impulsive” SEP events at flare sites of magnetic
reconnection below CMEs. We argue that future developments in models require focused study of “campaign events” to best utilize
the wealth of available CME and SEP observations. 相似文献
57.
58.
The Plasma and Suprathermal Ion Composition (PLASTIC) Investigation on the STEREO Observatories 总被引:1,自引:0,他引:1
A. B. Galvin L. M. Kistler M. A. Popecki C. J. Farrugia K. D. C. Simunac L. Ellis E. Möbius M. A. Lee M. Boehm J. Carroll A. Crawshaw M. Conti P. Demaine S. Ellis J. A. Gaidos J. Googins M. Granoff A. Gustafson D. Heirtzler B. King U. Knauss J. Levasseur S. Longworth K. Singer S. Turco P. Vachon M. Vosbury M. Widholm L. M. Blush R. Karrer P. Bochsler H. Daoudi A. Etter J. Fischer J. Jost A. Opitz M. Sigrist P. Wurz B. Klecker M. Ertl E. Seidenschwang R. F. Wimmer-Schweingruber M. Koeten B. Thompson D. Steinfeld 《Space Science Reviews》2008,136(1-4):437-486
The Plasma and Suprathermal Ion Composition (PLASTIC) investigation provides the in situ solar wind and low energy heliospheric ion measurements for the NASA Solar Terrestrial Relations Observatory Mission, which consists of two spacecraft (STEREO-A, STEREO-B). PLASTIC-A and PLASTIC-B are identical. Each PLASTIC is a time-of-flight/energy mass spectrometer designed to determine the elemental composition, ionic charge states, and bulk flow parameters of major solar wind ions in the mass range from hydrogen to iron. PLASTIC has nearly complete angular coverage in the ecliptic plane and an energy range from ~0.3 to 80 keV/e, from which the distribution functions of suprathermal ions, including those ions created in pick-up and local shock acceleration processes, are also provided. 相似文献
59.
This paper presents an auto-tuning method for a proportion plus integral(PI) controller for permanent magnet synchronous motor(PMSM) drives, which is supposed to be embedded in electro-mechanical actuator(EMA) control module in aircraft. The method, based on a relay feedback with variable delay time, explores different critical points of the system frequency response.The Nyquist points of the plant can then be derived from the delay time and filter time constant.The coefficients of the PI controller can then be obtained by calculation while shifting the Nyquist point to a specific position to obtain the required phase margin. The major advantage of the autotuning method is that it can provide a series of tuning results for different system bandwidths and damping ratios, corresponding to the specification for delay time and phase margin. Simulation and experimental results for the PMSM controller verify the performance of both the current loop and the speed loop auto-tuning. 相似文献
60.
Hartmann Lee Ciesla Fred Gressel Oliver Alexander Richard 《Space Science Reviews》2017,212(1-2):813-834
Space Science Reviews - We review the general theoretical concepts and observational constraints on the distribution and evolution of water vapor and ice in protoplanetary disks, with a focus on... 相似文献