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.

Improved signals are developed for use in a wireless system with multiple transmit and multiple receive antennas so that even in the face of some correlation the most open-loop capacity that can be achieved using a substantially open-loop system with a channel of that level of correlation is obtained. In accordance with the principles of the invention, the signals transmitted from the various antennas are processed so as to improve their ability to convey the maximum amount of information. The data to be transmitted is divided into M+1 substreams, where M is the number of transmit antennas. Each transmit antenna is supplied with a combination signal that is made up of a weighted version of a common one of the substreams and a weighted version of a respective one of the substreams that is supplied uniquely for that antenna, so that there are M transmit signals.

In a hierarchical profile, each node represents at least one feature of behavioral data collected (300) about an entity (102) profiled, with the topmost node selected (306) as the "statistically most informative" feature of the data. A profile can cover numerous domains and be predictively very powerful in each domain. A number of observations can be "aggregated" (316) together into a single datapoint. In use, the structure of the profile is compared (402) against current information associated with the entity to produce (406) a recommendation or prediction. If the profile represents at least some data aggregation, then new observations (500) are folded (504a, 504b, 504c) into the profile based on statistical weights of the aggregations. Because of the way the profile is created and updated, its hierarchical structure maps the collected observations. Therefore, as new observations are incorporated, if the new observations change (600a) the profile's structure significantly, then it can be hypothesized (602) that something "interesting" has happened to the entity.

The invention discloses an aircraft modeling method based on a variable data length maximum information amount-credibility criterion. The method is used for solving the technical problems that the existing maximum information amount criterion does not consider data length so that proving correctness of a pneumatic model and parameters of flying tests is poor. The technical scheme is that by considering the data length in the maximum information amount criterion and introducing credibility parameters, and a modeling criterion is revised according to different flying test factors of an aircraft. U-D decomposition of Rj and Rj+1 is estimated on measuring variance, and scalar model selecting and verification discriminant are obtained. The aircraft modeling method is favorable for building aircraft aerodynamic force and moment models according to flying test data directly, and the technical problems that the maximum information amount criterion does not consider data length directly so as to be wrong to establish and verify pneumatic models with different flying test data 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 a maximum information content-credibility criterion of variable metrical data, which is used for solving the technical problem of poor accuracy of parameter calibration of aerodynamic models provided by flight tests caused by the maximum information content criterion when the observation vectors of the conventional different flight tests are different. According to the technical scheme, the method comprises the following steps of: analyzing the influence of the difference of the observation vectors on the maximum information content criterion during modeling and model validation of an aircraft, and introducing a credibility parameter to obtain a criterion on modeling rectification and model verification according to different flight test factors of the aircraft; and decomposing U-D of measured variance estimation Rj and Rj+1 to obtain a scalar model selection and verification discriminant. The method provided by the invention is convenient for directly establishing aerodynamic and moment models of the aircraft according to flight test data, and avoids the technical problem that the aerodynamic model is incorrectly established and verified by different flight test data due to that the different observations are not directly considered in the maximum information content criterion.

The invention discloses an aircraft modeling method based on a variable data length maximum information criterion. The technical problems that the proving correctness of aerodynamic models and parameters verified by a flight test is poor caused by the fact that data lengths are not considered in a prior maximum information criterion are solved. The technical scheme includes that data lengths are considered in the maximum information criterion, a modeling criterion is corrected in accordance with various flight test factors of an aircraft, the division of U-D of Rj and Rj+1 is evaluated for the measurement variance, and a scalar model selection and verified discriminant is obtained. The method has the advantages that aerodynamic models and moment models of the aircraft can be established directly in accordance with flight test data, and the technical problem that aerodynamic models established and verified by different flight test data are not correct caused by the fact that data lengths are not considered in the prior maximum information criterion directly is solved.

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.

A multi-dimensional wireless sensor network capacity calculation method based on node status, which defines the maximum amount of information that can be transmitted within the lifetime of the wireless sensor network as the network capacity, including network channel signal-to-noise ratio model, network node energy consumption model, network Survival time calculation model and graph theory model, establish a multi-dimensional network capacity calculation model based on signal-to-noise ratio and network survival time; use Grover algorithm for optimization control to make the multi-dimensional network capacity calculation model approach the upper limit of network capacity, and obtain the multi-dimensional wireless sensor network capacity. The invention provides a method for measuring and calculating the capacity of a multi-dimensional wireless sensor network based on the node state, which comprehensively considers the two-dimensional information of the signal-to-noise ratio and the network survival time.