34 results about "Maximally informative dimensions" patented technology

A method transforms unstructured text into structured data in a domain-specific ontology. The method includes recording an input block of text using an information extraction module (IEM), accessing a domain-specific ontology and supplemental data in a knowledge source(s) via the IEM, processing the input text block, and using the IEM to generate a plurality of nodes in the domain-specific ontology. Each node classifies the unstructured text to corresponding objects of interest, thereby transforming the unstructured text into the structured data. An IEM is also provided having a computer device and an algorithm executable thereby to transform unstructured text into structured data in a domain-specific ontology. The IEM is adapted for recording a text phrase using the computer device, accessing and retrieving the domain-specific ontology and supplemental data from a knowledge source(s), and processing the text block using the computer device to generate a plurality of nodes in the domain-specific ontology.

An information recording method records information to a multilayer recording medium in which a number of record layers are laminated and recording of information to each record layer is possible. When an amount of the information being recorded to the medium does not exceed a maximum amount of information which can be recorded to the medium, the information being recorded to the medium is divided into data blocks by the number of the record layers. The data blocks are recorded to data areas of the respective record layers so that the recording areas of the record layers where the data blocks are recorded are overlapped each other with respect to a thickness direction of the medium.

The invention relates to a three-dimension microscopic observation method of plant leaf stoma in vivo. The method comprises the following steps that: firstly, optical amplifier components are connected with a focusing guide rail and a varifocus lens is connected with a CCD image acquisition sensor; the focusing guide rail is connected with a connection plate and the connection plate is connected with a horizontal fine tuning guide rail; then, a measured plant is placed on a measured-object load-bearing platform and a observation area of a measured leaf is fixed; the CCD image acquisition sensor is connected with an upper computer so as to real-timely collecting and observing leaf stomata through image acquisition software; finally, an image of a leaf surface can be acquired through automatically focusing or manually focusing and a three dimensional image of leaf surface stoma states can be obtained after performing image denosing, curve smoothing and curve fitting on collected data. By using the method of the invention, when the plant leaves are not separated with the plant body, stoma state images can be continuously collected, and normal plant growth state can be two-dimensionally observed or leaf stoma change status under a specific experiment state can be two-dimensionally observed. Therefore, maximum information of the leaf stomata can be guaranteed.

The invention discloses an aircraft modeling method based on a variable measurement number maximum information criterion. The aircraft modeling method is used for solving the technical problems of poor proving correctness of pneumatic models and parameters provided by flight tests due to the maximum information criterion when observation vectors of existing different flight tests are not the same. The technical scheme includes that during aircraft model modeling and model validation, different flight test factor amendment modeling and model validation criteria of an aircraft are acquired by analyzing the influence of different observation vectors to the maximum information content criterion, and scalar model selection and testing discriminant is acquired through U-D decomposition of measurement variance estimation Rj and Rj+1. By the method, aerodynamic force models and moment models of the aircraft can be established directly conveniently according to flight test data, the technical problem that the aerodynamic force models are established and tested incorrectly according to different flight test data due to the fact that influence of different observations to the maximum information criterion is not considered directly.

The invention discloses an aircraft modeling method based on a maximum information-reliability online identification criterion. The technical problems that the proving correctness of aerodynamic models and parameters verified by a flight test is poor caused by a simplified model identification criterion are solved. The technical scheme includes that data lengths are considered and reliable parameters are introduced in a maximum information criterion, an online modeling criterion is corrected, the division of U-D of Rj and Rj+1 is evaluated for the measurement variance, and a scalar online model selection and verified discriminant is obtained. The method has the advantages that aerodynamic models and moment models of an aircraft can be established on line directly in accordance with flight test data, and the technical problems of aircraft high attack angle model establishment and verification according to flight tests caused by a simplified model determination criterion are solved.

The invention discloses a modeling method of an aircraft based on a maximum information quantity-reliability rule, to solve the technical problem that an aerodynamic model and parameters provided from a flight test are low in correctness due to the existing maximum information quantity rule. According to the technical scheme, reliability parameters are introduced into the maximum information quantity rule, and a modeling rule can be corrected according to flight test factors of different aircrafts; and measurement variances Rj and Rj+1 are estimated and subjected to U-D decomposition so as to obtain a scalar model selection discriminant. Aerodynamic and moment models of the aircraft can be directly and conveniently established according to flight test data, and the technical problem that the aerodynamic model and the parameters obtained from the flight test are incorrect due to increment of fixed parameters in the maximum information quantity rule can be solved.

The invention discloses an aircraft modeling method based on an adjustable parameter maximum information criterion. The method is used for solving a technical problem that an aerodynamic model and parameters given by a flight test are poor in correction due to the existing maximum information criterion. The technical scheme of the invention is as follows: introducing an adjustable parameter through a maximum information criterion, and correcting a modeling criterion according to flight test factors of different aircrafts; and carrying out U-D factorization on measurement variance estimations Rj and R(j+1) to acquire a scalar model selection discriminant. The aircraft modeling method is convenient to directly establish aerodynamic and moment models according to the flight test data, thus avoiding a technical problem that the aerodynamic model and parameters acquired by the flight test are incorrect based on the maximum information criterion due to increased fixed parameters.

The invention discloses a method and a system for transmitting information based on graphics encoded data. The method comprises the following steps: obtaining application description information; determining a plurality of applications wishing to transmit information through the graphics encoded data based on the application description information; and determining a plurality of applications wishing to transmit information through the graphics encoded data. According to the information transmission requirements of each application, determining the maximum amount of information needed by eachapplication to transmit information through a single graphic encoded data; parsing a graphical interface of each application for providing graphical encoded data to determine a display range that eachapplication can use to display graphical encoded data; determining an encoding ratio of an image region for graphics encoded data for each application based on a display range and a maximum amount ofinformation; and generating raw graphics encoded data conforming to the encoding scale when a specific application of the plurality of applications desires information transfer, and performing information transfer based on the raw graphics encoded data conforming to the encoding scale.

The invention relates to an associated word extraction method based on proper nouns. The method comprises the steps that 1, a text set of a set field is acquired; 2, the text set is preprocessed to obtain feature texts; 3, an associated word of every two proper nouns is extracted from the feature texts; 4, according to relevant information of each of the associated words, regression analysis or belief network technology is used to find the interdependent relation between each associated word and the feature texts; 5, according to the interdependent relation, a part or all of the associated words are selected. Through the associated word extraction method based on the proper nouns, a maximum amount of information can be acquired with least time.

The invention discloses an aircraft modeling method based on a maximum information amount on-line identification criterion. The aircraft modeling method based on the maximum information amount on-line identification criterion is used for solving the technical problem that an existing simplified model identification criterion enables a pneumatic model and parameter calibration correctness given through flight test to be poor. The technical scheme is that the data length is considered and an on-line modeling criterion is revised according to the maximum information amount criterion; and an on-line model selecting and verifying discriminant is obtained through U-D disintegration of measurement variance estimates Rj and Pj+1. The aircraft modeling method facilitates on-line building of an aerodynamic force model and a force moment model of an aircraft according to flight test data directly, and solves the technical problem existing in building and verifying process of an aircraft high-incidence model according to a flight test.