66results about How to "Strong engineering achievability" patented technology

The invention discloses a passive sensor networking detection multi-target method. A passive sensor networking system carries out intersection positioning by using a direction-finding intersection method according to angle information provided by a sensor; a ghost point is eliminated by using information redundancy static between multiple platforms; subsequently the ghost point is dynamically eliminated by using a virtual flight path tracking technique, so as to realize the accurate positioning and tracking on multiple targets. The method for eliminating the ghost point comprises the steps of: calculating each flight path tracking door; carrying out association processing on point targets (obtained from the intersection positioning) with each grade of flight path files in sequence in accordance with the flight path grades from high grade to low grade; and starting, combining, cutting, branching and deleting the flight path according to the association situation. The passive sensor networking detection multi-target method has the following advantages that target movement characteristics are sufficiently utilized, the ghost point is dynamically eliminated in the target tracking process, the engineering is strong in realizability, and the ghost point can be effectively eliminated under the condition that the targets are dense or measuring noise exists.

The invention discloses an optical imaging method integrating three-dimensional mapping and broad width imaging. According to the invention, two or three line-scan digital cameras are installed on a satellite within certain interaction angles; each line-scan digital camera is provided with a first imaging detector for three-dimensional mapping and a second imaging detector for broad width imaging, and the conversion between the two imaging detectors are realized by cutting in a reflecting mirror; when the three-dimensional mapping is performed, the satellite flies in a normal attitude, and the imaging detection is realized through the first imaging detector of each line-scan digital camera; and when the broad width monitoring is performed, the satellite flies by yawing a certain angles and converts light paths by cutting in the reflecting mirror, adjacent air strips on the ground are sequentially imaged through the second imaging detector of each line-scan digital camera, and equivalently a wide air strip on the ground is imaged in a segmentation spliced manner, and accordingly the imaging width is remarkably increased. The optical imaging method integrating three-dimensional mapping and broad width imaging realizes multiplexing of the single-satellite function and improves the utilization ratio of on-orbit resources.

The invention discloses a method for calibrating a satellite navigation digital multi-beam launching array antenna phase center. Aiming at the effect of the launching array antenna phase center on satellite navigation high-precision ranging property, the invention provides a method for measuring and marking the array antenna phase center by adopting spread spectrum pseudo code ranging technology. The method for calibrating the satellite navigation digital multi-beam launching array antenna phase center can amend the high-precision ranging application of the satellite navigation field array antenna. The method for calibrating the satellite navigation digital multi-beam launching array antenna phase center has the advantages of being novel, creative, simple and practical.

The invention provides a high-precision ranging positioning method based on channel state information (CSI). The positioning method is mainly divided into an offline phase and an online phase. In theoffline phase, firstly multiple calibration points are selected in a positioning area, then an access point (AP) extracts the CSI from the data from the calibration points and filters the CSI, an environmental factor and a path loss coefficient are obtained by using CSI before and after filtering, the environmental factor and the path loss coefficient are linearly fitted to obtain an adaptive pathloss coefficient, and an adaptive signal propagation model is obtained. In the online phase, the received CSI is filtered, filtered CSI energy is brought into the adaptive propagation model for distance estimation, and an obtained distance is brought into a positioning algorithm for positioning. Compared to the conventional positioning technology, the positioning technology of the invention has the advantage that CSI phase correction compensation and AP synchronization are not needed. In addition, the method has high engineering achievability and high positioning accuracy and is suitable formultiple positioning scenes such as a single station and multiple stations.

The invention relates to a frequency-domain migration-based de-chirping inverse synthetic aperture radar (ISAR) envelope alignment method. According to the method, based on the alignment of a conventional envelope correlation method, the accuracy of envelope alignment is improved by using the frequency-domain migration property of Fourier transform; and the maximum constraint condition of the accuracy of traditional envelope alignment is that the error of migration alignment cannot break through the limitation of half of a range resolution cell when migration alignment is carried out under a condition that time-domain signal sampling is completed, and the solidification of range units is completed, wherein one range unit is one complex data representation. Since FFT operation is required to be carried out before the formation of range units in de-chirping signal processing, echo signals are multiplied by a frequency shift factor before the FFT operation, and accurate migration of data which have been subjected to FFT can be realized.

The invention discloses an under-actuated control method suitable for damping the angular velocity of a satellite attitude. The method includes firstly determining a satellite control failure shaft and two normally working shafts, and determining the angular velocity offset value of the two normally working shafts according to the size relation between main inertias of the two normally working shafts and the actual attitude angular velocity of the failure shaft; then determining the angular velocity deviation according to the actual attitude angular velocity of the angular velocity offset value of the two normally working shafts, and obtaining control moments of the two normally working shafts according to the angular velocity deviation; and controlling the angular velocities of the three shafts through the control moments until all angular velocity deviations of the three shafts are smaller than an angular velocity deviation expectation amplitude. The control method is simple in algorithm, good in dynamic behavior and high in project operability.

The invention relates to an in-orbit fuel consumption balancing method of a formation satellite system. The method comprises the following steps that 1) after kth formation control, the fuel consumption Ek of the formation control is calculated; 2) after the kth formation control, a formation control parameter [delta]lk of two satellite orbit periods is determined; 3) the sum SEk of cumulative fuel consumption of formation control and a residual error [delta]lk of present formation control are substituted into a formula SEk>=k1&&[delta]lk>=k2 for determination; and 4) if the formula is valid, marks of main and auxiliary satellites are switched autonomous on the satellites, main and auxiliary satellite switching control is carried out via a ground annotation instruction or on satellites autonomously so that a new main satellite operates in a reference orbit, parameters are set as initial values, a new auxiliary satellite executes a formation control task, and the steps 1) to 3) are repeated; or if the formula is invalid, the original auxiliary satellite continues to carry out formation control. The method is high in engineering realization performance, can be used to save fuels, requirements of formation satellite tasks are taken into consideration, and the autonomous level of the satellites can be improved.

The invention discloses an on-track motor plume data acquiring method based on momentum wheel data. The on-track motor plume data acquiring method based on the momentum wheel data includes the following steps: constructing a normal three-axis stabilization gesture of a spacecraft, adopting a momentum wheel to be as an executing mechanism of three-axis control, disassembling a magnetic torquer, and confirming gestures of a top and an infrared or star sensor and the like; confirming a start and control position and a time span of air injection of a motor involved in a test, carrying out preparations before the motor works (such as starting of a heater, open of a latching valve); recording data output by the momentum wheel; analyzing a testing result and analyzing disturbing force and moment of force generated by the air injection of the motor according to the momentum wheel data and quality characteristics of the spacecraft. The on-track motor plume data acquiring method based on the momentum wheel data is capable of achieving acquisition of the on-track motor plume data under the condition of high vacuum real environment.

The invention provides a Beidou RDSS micro base station information framing transmission method facing multiple services and multiple users, and satisfies technical requirements for multi-user access and information distribution and transmission. The information is ordered according to the priorities by combining information including priorities of access users, the types of equipment and the types of services; adaptive information compressing and information framing are carried out according to types of the service information, information framing and queuing problems in multi-user information transmission are solved, and optimized transmission of the multi-user information is realized.

The invention discloses a discretized region scanning subarray-level sparse optimization method and system, and belongs to the technical field of array antenna design, and the method comprises the following steps: S1, discretizing an initial population; s2, carrying out region scanning processing; and s3, optimization processing. When the method and the system are applied to sub-array-level sparseoptimization of a large-scale circular aperture antenna, under the condition that the sub-array spacing meets the spacing requirement, the optimization time is greatly reduced, the sidelobe level isreduced, a new way is provided for rapidly solving effective position arrangement of array elements under the specific array element spacing limitation condition, the diversity of a solution set in the optimization process is improved, the probability of finding the optimal solution is improved, and local convergence of the optimization algorithm is effectively avoided; and when the designed arrayantenna is applied to a large-scale radar system, the radar has the advantages of long operating distance, high resolution, low cost, light weight, high engineering realizability and the like, and isworthy of popularization and application.

The invention discloses an on-board autonomic fault diagnosis method controlled based on a control moment gyro group, comprising step 1 of checking a communication state of an on-board computer with acontrol moment gyro; step 2 of diagnosing a working state according to control moment gyro return; and step 3 of diagnosing data according to control moment gyro return. The control moment gyro is output of two degrees of freedom. According to a control manner of the control moment gyro, data of an internal frame and data of an external frame are respectively diagnosed, wherein diagnosis of a rotational speed is performed for the internal frame and diagnosis of a rotational speed and a position is performed for the external frame. The invention has the advantages of timely and effectively diagnosing a potential data abnormality, and, by designing a system fault value threshold and a fault cumulative frequency threshold, timely disposing a fault reflector, to avoid introduction of abnormal data into system control and also facilitate rapid response of the system to a fault, such that its engineering application is relatively simple and it is also convenient to be implemented.

The invention discloses a military benefit-based GSO frequency track resource efficiency evaluation method. The method comprises the following steps of calculating a military coverage area satisfaction degree A1 of to-be-evaluated data; calculating military frequency coverage A2; calculating a service support degree A3; calculating the support degree A4 of the earth station; calculating the effective coverage A5 of the military application; calculating the cooperation degree A6 with the existing military system; taking the to-be-evaluated indexes A1-A6 as first-level indexes, and giving a judgment matrix of the first-level indexes; calculating weights based on the judgment matrix, obtaining weight vectors of the first-level indexes, and calculating the fuzzy satisfaction degree of each first-level index; calculating ambiguity vectors for the obtained first-level index values, and generating an evaluation matrix R; and selecting the maximum value in the matrix C as an efficiency evaluation value based on the weight vector of the first-level index. According to the method, the quality of the stored military frequency orbit resources can be improved, all indexes are clear, and the method has high engineering realizability.

The invention relates to the technical field of unmanned aerial vehicle group control, in particular to a control method for an unmanned aerial vehicle group to cooperatively exit from a circular trajectory. The method comprises the following steps: (1) establishing a common exit point and a common transitional route of an unmanned aerial vehicle group; (2) judging the timing when each unmanned aerial vehicle exits from the circular trajectory; and (3) setting the flight altitude of each unmanned aerial vehicle while exiting from the circular trajectory. According to the control method for theunmanned aerial vehicle group to cooperatively exit from the circular trajectory disclosed by the invention, the common transitional route is set according to the flight circular trajectory area of the unmanned aerial vehicle group to make each unmanned aerial vehicle in the unmanned aerial vehicle group orderly exit from the circular trajectory through the common transitional route, and changesown flight altitude in a flight exit process to form an altitude difference, thereby effectively avoiding collision between the unmanned aerial vehicles, and greatly simplifying the design of a system. The control method is simple and easy to operate, and has relatively high engineering realizability and relatively high practical value.

The invention provides an accurate modeling method for metal material welding spots, and belongs to the technical field of vehicle simulation analysis. The method comprises the steps: by comparing theforce and displacement curve of the actual welding spot sample piece with the force and displacement curve of the CAE analogue simulation, adjusting the parameters of the analogue simulation, so thecurve output by the analogue simulation is unified with the corresponding test curve, the welding spot material parameter model is obtained and used in the whole vehicle analogue analysis model, and the accuracy and precision of the analogue analysis result are improved.

The invention aims to solve the long distance based GPS common view time comparison technical demands, and discloses an embedded long distance real time GPS common view time comparison method; based on a FPGA prototype board card, the method can embed a GPS common view time comparison algorithm into a DSP, thus realizing time comparison in real time; the main task contains GPS common view and single machine synergy; the method can ensure to stably output a clock error result without increasing operation complexity and space complexity, thus realizing inter-station time synchronization within thousands of kilometers.

The invention discloses fluorine-containing polymer coated high-purity boron powder. The fluorine-containing polymer is used for coating the high-purity boron powder, not only can the free energy of the specific surface of boron powder particles be reduced and the agglomeration phenomenon be reduced, but also the combustion efficiency of the boron powder can be remarkably improved. The invention further provides a preparation method of the fluorine-containing polymer coated high-purity boron powder. The fluorine-containing polymer coated high-purity boron powder obtained by the method can well solve the problems that the combustion efficiency of amorphous boron powder in a solid propellant is low, and the heat value of the boron powder cannot be effectively exerted. The coating preparation technology is simple, the engineering implementability of the coating process is high, and the economic added value is high.

The invention provides a design method of a distribution typetrusted radio navigation system architecture for situations where current radio navigation systems are susceptible to fraudulent interference. The method designs navigation system compositions and navigation signal generation and transmission and reception methods, achieves effective resisting on the navigation spoofing means and the like through improving the system architecture and the signal broadcasting mode of the radio navigation system, thereby greatly improving the safety of the radio navigation system including satellite navigation.

The invention discloses an in-orbit engine plume data acquisition method based on gyroscope data. The method comprises the steps of building normal three-axis stabilization attitudes of a spacecraft, adopting a momentum wheel to be an actuator for controlling three axes and a magnetic torquer for unloading, adopting attitude sensors such as a gyroscope and an infrared or star sensor for determining attitude, identifying a starting control point and air injection time of an engine involved in a test, preparing before work of the engine, such as starting a heater and starting a latching valve, recording data output by the gyroscope, analyzing test results, and analyzing disturbing force and moment generated during air injection of the engine according to the gyroscope data and quality characteristics of the spacecraft. According to the in-orbit engine plume data acquisition method based on the gyroscope data, plume data acquisition of the in-orbit engine under high vacuum and real environment is achieved.

The invention discloses a target real-time tracking and early warning method and a target real-time tracking and early warning system based on intelligent equipment, which belong to a novel target behavior identifying technique. A principle is that peripheral information of a geographical position in which a target is positioned is determined by utilizing a positioning technique and location based service (LBS), then the target behavior probability is calculated according to database records, and when a certain behavior probability of the target is greater than a set threshold, early warning is given to the target or the receiving end of the target. According to the method and the system, on the basis that all possible behaviors of the target are analyzed, the target motion diversity problem (which is solved in a user position module) and the target behavior diversity problem (which is solved in a user behavior prediction module and an early warning judgment module) are respectively solved by utilizing the three modules.

The invention discloses a drill rod straightness detection device and method. The device comprises a first supporting mechanism, a second supporting mechanism and a detection mechanism; wherein the second supporting mechanism is connected with the first supporting mechanism, is supported by the first supporting mechanism and is used for supporting a drill rod to be tested; the detection mechanism comprises a driving unit and a spatial position information acquisition unit; the driving unit drives the spatial position information acquisition unit to rotate; the spatial position information acquisition unit is used for being in contact with a to-be-detected drill rod and acquiring spatial position information of the to-be-detected drill rod in real time. According to the invention, the straightness of the drill rod with the key bar can be conveniently, accurately and quickly detected in the production process, so that the device and method has important significance for improving the processing quality and the process of the drill rod.

The invention discloses a compact wide-field white light sighting telescope optical system, which adopts a Kepler telescope system and comprises an objective lens group, an image rotation group, a reticle and an eyepiece group, the objective lens group adopts two groups of three-piece spherical lenses, the image rotation group adopts three groups of five-piece spherical lenses, and the image rotation group is arranged behind an image plane of the objective lens group; the reticle is arranged behind the image rotation group, and the eyepiece group adopts three groups of five spherical lenses and comprises a first eyepiece lens group, a second eyepiece lens group and a third eyepiece lens group. The white light sighting telescope optical system is good in imaging quality, free of sensitive size, good in lens processing technology, reasonable in optical element arrangement, compact in structure, small in size and high in engineering realizability, and has practical application value.

The invention relates to an autonomous diagnosis method for a formation configuration control strategy, and the method comprises the specific steps: step 1, carrying out state inspection related to astrategy before a satellite calculates the formation control strategy; step 2, enabling the satellite to carry out correctness autonomous diagnosis on the control strategy delta vi according to the current formation configuration parameter; if the diagnosis is passed, entering the next step; otherwise, setting an alarm mark; step 3, after the control speed increment sequence delta vi passes the diagnosis, converting delta vi into a control instruction sequence (Tpi, Lti) according to the current on-board time, the actual thrust of the thruster and the satellite mass, and carrying out autonomous diagnosis on the correctness of a control instruction; if the diagnosis is passed, executing the instruction; otherwise, setting an alarm mark.