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2nd Conference on Computational Methods in Systems and Software (CoMeSySo)

作者： Potapov, Viktor Gushanskiy, Sergei Samoylov, Alexey Polenov, Maxim Southern Fed Univ Dept Comp Engn Taganrog Russia

ISBN: (纸本)9783030002114;9783030002107

Present paper describes the basics of quantum algorithms development and modeling of entangled quantum computations used in quantum algorithms. Since quantum algorithms assume the use of vector and matrix algebras, so the suggested structure of the quantum computer model (QCM) considers this specialty and reflects all functional features of such model. The basic tasks of the proposed model simulation are determined within the quantum algorithms execution taking into account the entanglement property. In accordance with the constructed system for determining the computational complexity of quantum algorithms, the entire set of necessary elements is shown: the time complexity, the number of operations and queries to the quantum oracle, the complexity class of the quantum algorithm.

关键词： Qubit Quantum register Quantum computer model algorithms complexity Quantum circuit

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Structure and Online Self-Repair Mechanisms for Digital Systems Based on System-on-Programmable-Chip

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JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2018年第10期15卷 604-610页

作者： Yao, Rui Du, Junjie Zhu, Ping Wang, Meiqun Nanjing Univ Aeronaut & Astronaut Coll Automat & Engn Nanjing 211106 Jiangsu Peoples R China

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Insight: Operational products validation on ground 15th

Insight: Operational products validation on ground

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15th International Conference on Space Operations, SpaceOps 2018

作者： Gaudin, Emilien Yana, Charles Nonon-Latapie, Michel Vallade, Julien TELESPAZIO 4 Impasse de Candie Toulouse31100 France CNES 18 avenue Edouard Belin Toulouse31400 France THALES Services 290 Allée du Lac Labège31670 France

ISBN: (数字)9781624105623

ISBN: (纸本)9781624105623

In this paper, we will describe the validation process of operational products for SEIS instrument, aboard InSight mission. Starting explaining the instrument commanding concept and the operational needs, we will progressively describe ideas implemented to secure and optimize operations-in agreement with the mission partners-, the different validation means available, and the global workflow orchestrating the operational products qualification. © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Telemetry Earth Structured Programming Flight Software algorithms complexity Feedback Control Regression Testing FIR Filters

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Design Segmented Stiff Skin for a Morphing Wing

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JOURNAL OF AIRCRAFT 2016年第4期53卷 962-970页

作者： Guo Xijuan Qiang, Zhao Xi, Fengfeng Yanshan Univ Dept Comp Sci Qinhuangdao 066004 Hebei Peoples R China Ryerson Univ Dept Aerosp Engn Toronto ON M5B 2K3 Canada

A morphing aircraft adapts to different missions by changing the shape of its wing. With the wingspan change or chord length change, the wing skin will change, which requires the design of the variable wing covering to meet the morphing wing. The core of the variable stiff wing-covering design is splitting the wing surface. By solving the problem, the sliding morphing of the stiff skin is achieved. According to the characteristics of the wing surface, this paper gives two stiff wing-covering segmentation algorithms. First, based on the change of airfoil curve that happened before and after the chord length change, the horizontal noninterference segmentation and morphed method of rigid wing skin is proposed. The airfoil curve is divided into pieces, and the definition of the curve similarity evaluation criterion (that is, K) is presented. The horizontal rigid-surface morphing is achieved, depending on the noninterference folding morphing and the airfoil curve length difference. Second, according to the feature of the column side caused by stretching or shortening of the column, a vertical segmentation method (named "petalized") of the stiff wing covering for the wingspan change is proposed. By means of the segmentation results of the original column side split through the hierarchical structure and the modular concept, the vertical rigid morphing is achieved. In the last step, two experiments validate the horizontal and vertical algorithms of segmentation and morphing, and they make an analysis of the algorithm complexity.

关键词： Aircraft Wings Airfoil Profiles Variable Sweep Wings algorithms complexity MATLAB Morphing Mechanisms Honeycomb Structures Data Storage Trusses

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Convex Solution to a Joint Attitude and Spin-Rate Estimation Problem

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2016年第1期39卷 118-127页

作者： Saunderson, James Parrilo, Pablo A. Willsky, Alan S. MIT Dept Elect Engn & Comp Sci Cambridge MA 02139 USA

This paper considers the problem of jointly estimating the attitude and spin rate of a spinning spacecraft. Psiaki has formulated a family of optimization problems that generalize the classical least-squares attitude-estimation problem, known as Wahba's problem, to the case of a spinning spacecraft. In the special case where the rotation axis and the fundamental sampling period are fixed and known, but the spin rate is unknown (such as for nutation-damped spin-stabilized spacecraft), Psiaki's problem can be reformulated exactly as a type of tractable convex optimization problem called a semidefinite optimization problem. This reformulation allows the problem to be globally solved using standard numerical routines for semidefinite optimization.

关键词： Spinning Spacecraft Convex Optimization Nutation Damping Linear Mapping Attitude Dynamics Extended Kalman Filter Quadratic Programming Magnetometers Gyroscopes algorithms complexity

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High-Accuracy Trajectory Optimization for a Trans-Earth Lunar Mission

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2011年第4期34卷 1219-1227页

作者： Yan, Hui Gong, Qi Park, Chan D. Ross, I. Michael D'Souza, Christopher N. Univ Calif Santa Cruz Dept Appl Math & Stat Santa Cruz CA 95064 USA USN Postgrad Sch Dept Mech & Aerosp Engn Monterey CA 93943 USA NASA Lyndon B Johnson Space Ctr EG6 Aerosci & Flight Mech Div Houston TX 77058 USA

The trajectory optimization of a spacecraft subject to the gravitational effects of the moon, Earth, and sun are considered. The problem is how to achieve Earth-interface conditions from a low lunar orbit. Practical constraints of maximum thrust, fuel budget, and flight time generates a constrained, nonautonomous, nonlinear optimal control problem. Severe constraints on the fuel budget combined with high-accuracy demands on the endpoint conditions necessitate a high-accuracy solution to the trajectory optimization problem. The problem is first solved using the standard Legendre pseudospectral method. The optimality of the solution is verified by an application of the covector mapping principle. It is shown that the thrust structure consists of three finite burns with nearly linear steering-angle time histories. A singular arc is detected and is interpreted as a singular plane change maneuver. The Bellman pseudospectral method is then employed for mesh refinement to improve the accuracy of the solution.

关键词： Covector Mapping Principle Earth Lunar Mission Moon Legendre Pseudospectral Method Fuel Consumption Exhaust Velocity algorithms complexity Periapsis International Space Station

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complexity analysis of a heuristic method for fixed-frequency assignment including adjacent channel interference

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IEEE TRANSACTIONS ON ELECTROMAGNETIC COMPATIBILITY 2008年第1期50卷 203-208页

作者： Chavez-Santiago, Raul Gigi, Eli Lyandres, Vladimir Ben Gurion Univ Negev Dept Elect & Comp Engn IL-84105 Beer Sheva Israel

In this paper, we extend an existing heuristic algorithm for fixed-frequency assignment in cellular communication networks in order to account for the effects of adjacent channel interference (ACI). Our algorithm utilizes estimations of carrier-to-interference ratio instead of binary channel separation constraints. The extended algorithm avoids overoptimistic frequency assignments that do not guarantee interference-free operation environments. Its cost is the increased computational complexity. We estimate the upper bound of the algorithm's complexity when ACI is taken into account. Simulations demonstrate that despite the theoretical high increase in complexity, the algorithm is suitable even for a quasi-dynamic frequency assignment scheme in practical situations. The algorithm enhances the spectrum utilization in cellular networks while reducing harmful interference.

关键词： algorithms complexity cellular communications frequency assignment heuristics interference

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Synchronized rotation of multiple autonomous spacecraft with rule-based controls: Experimental study

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2001年第2期24卷 352-359页

作者： Wang, PKC Yee, J Hadaegh, FY Univ Calif Los Angeles Dept Elect Engn Los Angeles CA 90095 USA CALTECH Jet Prop Lab Pasadena CA 91109 USA

An experimental study is made on the synchronized continuous-rotation of multiple air-levitated autonomous model spacecraft about a fixed axis by means of simple rule-based controls. These controls differ from the conventional ones, which require processing of numerical sensor data. The controls depend solely on the occurrence and timing of certain discrete event sequences. Thus, the controlled model spacecraft is a hybrid continuous-time and discrete-event system. Experimental results show that the proposed rule-based controls are effective in achieving rotational motion with synchronized angular velocity and phase. A description of the experimental setup and a brief discussion of the design of the air-levitated model spacecraft is given. Then, the details on the development of rule-based controls and the derivation of a dynamic model for the resulting hybrid system are presented followed by the presentation and interpretation of the experimental results.

关键词： Air Levitated Autonomous Model Spacecraft Optical Sensor algorithms complexity Tachometer Feedback Control Telemetry System Planetary Surfaces Space Environment Spherical Bearing Lithium Battery

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Multi-pulse-width modulated control of linear systems

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1998年第1期21卷 64-70页

作者： Bernelli-Zazzera, F Mantegazza, P Nurzia, V Politecn Milan Dept Aerosp Engn I-20133 Milan Italy

A method is presented to convert a parent discrete time control into a multi-pulse-width modulated equivalent. Ht is shown that such an equivalence cam be established by matching the system state response at each sampling interval and that, provided a sufficient number of pulses per sampling interval are used, the degree of approximation can be as high as desired even if a relatively slow sampling frequency is adopted A numerical example on a simple fourth-order system provides the basis for understanding the pros and cons of the method, which is then applied to a more complex aerospace problem: the stabilization of coupled thermoelastic vibrations of a space structure.

关键词： Space Structures Single Input Single Output System Shape Control algorithms complexity Nonlinear Actuators Newton Raphson Method Frequency Domain Structural Displacement Structural Damping Nonlinear Control

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Application of two-variable fuzzy-PI control in an aeroengine

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JOURNAL OF PROPULSION AND POWER 1998年第3期14卷 399-402页

作者： Fang, ZX Wu, CH Northwestern Polytech Univ Dept Turbine Engines Xian 710072 Peoples R China

This paper proposes a two-variable fuzzy control algorithm, synthesizes a new two-variable fuzzy-PI controller, and studies the decoupling characteristic and responsibility of a controller in an aeroengine by computer simulation. The results show that the fuzzy-PI controller has it static decoupling characteristic and satisfied responsibility. The rules of a two-variable control system in aeroengines are also probed, and a new method for engine control is provided.

关键词： Aeroengine Gain Scheduling Single Input Single Output System algorithms complexity Engine Control Fuzzy Control System Multivariable Control Mathematical Models

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