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68results about How to "Save research and development costs" patented technology

Radar signal parallel processing method and system based on heterogeneous multinucleated system

The invention discloses a radar signal parallel processing method and system based on a heterogeneous multinucleated system. The method comprises the following steps: S1, initializing equipment-end parameters, opening up a task execution thread, and dividing thread grids of data processing and the dimensions of a thread block; S2, opening up a video memory space and a memory space which are needed for the signal processing; S3, acquiring data transmission and calculating time needed by signal processing of a single time, and scheduling a genetic task scheduling algorithm to obtain a task scheduling mode; and S4, acquiring laser sampling data for storing in the memory space by means of segments according to a time sequence, sending the data to a CPU and a GPU according to the task scheduling mode, mapping sampling points to each thread and performing concurrent execution according to the thread grids and the dimensions of the thread block, and scheduling a filter coefficient to perform orthogonal phase demodulation, pulse compression, moving object display, moving object detection, pulse accumulation and constant false alarm detection on the sampling data. By applying the method and system provided by the invention, the speed of a general processor in executing the signal processing is improved, and the requirement for real-time performance of radar signal processing is met.
Owner:NAVAL UNIV OF ENG PLA

Satellite-borne software in-orbit maintaining and upgrading method

The invention relates to a satellite-borne software in-orbit maintaining and upgrading method. Satellite-borne software is divided into basic applications and applications; the basic applications are stored in a PROM (Programmable Read Only Memory); the applications are stored in a read-write non-volatile storage medium such as an EEPROM (Electrically Erasable Programmable Read-Only Memory) or an FLASH and the like; a storage logic of the applications comprises an original software storage region, an upgraded software storage region and a module software top inputting region; all the three regions comprise checking information; and in an initial state, storage contents in both the original software storage region and the upgraded software storage region are original applications of the satellite-borne software and the module software top inputting region is empty.. By ground command control and data top inputting, three requirements of the satellite-borne software on integral software upgradation, software module replacement or parameter modification and increase of software modules can be supported and satellite-borne software in-orbit maintaining and upgrading efficiency is improved.
Owner:AEROSPACE DONGFANGHONG SATELLITE

Simple high-temperature testing device and method for flange rubber sealing element

The invention provides a simple high-temperature testing device and method for a flange rubber sealing element. A lower flange is in butt joint with an upper flange; the end face of the lower flange which is contacted with the upper flange is provided with a ring groove which serves a sealing groove for assembling the flange rubber sealing element to be tested; an upper cover is welded on the top of the upper flange; a bottom cover is welded at the bottom of the lower flange; the upper cover is connected to a gas medium charging pipeline; one end of a thermocouple is inserted into the upper flange through a gap, and the other end of the thermocouple is connected with a temperature indicator; and the upper flange and the lower flange which are connected one above the other are arranged in a high-temperature oil bath container. In the invention, a gas source is cut off by pressurizing under the normal-temperature condition, and a pressurizing way for reaching a preset pressure at the high temperature by using a gas expanding principle is adopted, so that the pressure constancy under the high-temperature condition is ensured; and an oil bath heating way is adopted, so that rapid heat transfer of a leakage test tool is realized. Due to the adoption of the device and the method, detection of the high-temperature sealing property of the rubber sealing element at the extreme usage temperature during short-time use is realized, and the development cost is greatly saved.
Owner:AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1

Typical flight action-based aircraft severe load spectrum compilation method

The invention relates to the field of aircraft fatigue, in particular to a typical flight action-based aircraft severe load spectrum compilation method. The severe load spectrum compilation method comprises the steps of determining an aircraft usage mission profile containing a typical flight action according to a predetermined condition; through numerical simulation analysis, expressing the typical flight action as a time function of a predetermined flight parameter; performing equivalent damage calculation on typical flight action data subjected to the numerical simulation analysis; analyzing an equivalent damage distribution law of the typical flight action subjected to the equivalent damage calculation; and compiling a severe load spectrum according to the equivalent damage distribution law of the typical flight action. According to the typical flight action-based aircraft severe load spectrum compilation method, a concept of the severe spectrum is applied to a representative flight method, so that the reliability of the load spectrum can be remarkably improved, the design analysis and test verification cycle can be shortened, and the research and development expenditures can be reduced.
Owner:SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA

Satellite temperature control method allowing rapid responding and multi-orbit adaption

The invention provides a satellite temperature control method allowing rapid responding and multi-orbit adaption, wherein by adopting a heat pipe network, reinforcing contact thermal conduction, and spraying a high-emissivity thermal control coating inside a satellite to reinforce in-cabin thermal conduction and radiation heat exchange, a temperature field is distributed uniformly in a cabin; a whole satellite temperature level is adjusted by a compensative electric heater; a nightside of a side plate of the satellite is taken as a major heat dissipation face, the outer surface of the nightside is sprayed with a white paint, and all the other outer surfaces of the satellite body, except for the major heat dissipation face, are covered by multiple layers of thermal insulation assemblies; and components outside the satellite are sprayed with a white paint thermal control coating. A propelling cabin has independent design, wherein the entire outside of the cabin is covered by the multiple layers of the thermal insulation assemblies, a baseplate inside the cabin is covered by the multiple layers of the thermal insulation assemblies, and the propelling cabin is finally integrated with a platform cabin. By integral design of machinery, heat and electricity, the satellite temperature control method allowing the rapid responding and the multi-orbit adaption provided by the invention realizes thermal control requirements of the whole satellite under conditions of a sun-synchronous orbit and an inclined track by the temperature control method.
Owner:SHANGHAI SATELLITE ENG INST

Method for obtaining control value of temperature behind turbine of aviation engine at high altitude and high speed

The invention relates to a method for obtaining control value of temperature behind a turbine of an aviation engine at high altitude and high speed. The method comprises the following steps of (1) screening several parameters which are mostly related with the engine efficiency from an engine logbook; (2) on the basis of using the known control values of the temperature behind the turbines of morethan hundreds of engines at high altitude and high speed as a training set, establishing a nervous network, using the selected parameters as input nodes, and using the control value of the temperaturebehind the turbine as the target value to train; after training, obtaining a nervous network model for calculating the control value of the temperature behind the turbine of the aviation engine at high altitude and high speed.
Owner:CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD

Ammunition link small-diameter artillery ammunition feeding and recoil and counter-recoil analog device

The invention relates to an ammunition link small-diameter artillery ammunition feeding and recoil and counter-recoil analog device, which consists of an ammunition feeding analog mechanism and a recoil and counter-recoil analog mechanism under the ammunition feeding analog mechanism, wherein the ammunition feeding analog mechanism mainly includes an ammunition feeding guide, a pair of ammunition link brackets, a pair of feed sprockets and a first hydraulic motor driving the pair of feed sprockets; and the recoil and counter-recoil analog mechanism mainly includes a bearing frame body, a curved groove cam mounted on the bearing frame body and a second hydraulic motor driving the curved groove cam. The device achieves the analog of ammunition feeding, link removal, link disposal, ammunition disposal and recoil and counter-recoil functions of the small-diameter artillery, adopts the hydraulic motor as the power source, further realizes the high-power output during the work of the device, and not only meets the requirements for the experiments in the ammunition feeding system laboratory, but also saves the experiment cost as the ammunition feeding speed and the frequency and displacement of recoil and counter-recoil are adjustable.
Owner:中国兵器工业第二0二研究所

Calculation method of internal resistance of engine nacelle

The invention provides a calculation method of the internal resistance of an engine nacelle. The calculation method is characterized by comprising the following steps: 1) carrying out flow field numerical value calculation on a design configuration provided with a ventilation nacelle to obtain the total flow field data of an airplane under a simulation working condition, requiring to define a profile on the exit position of the ventilation nacelle when a numerical value computational grid of the design configuration is constructed, and dividing the interpolation grid of the profile; 2) obtaining flow field information on the interpolation grid, wherein the flow field information comprises density [Rho]i, j, speed Vi, j, and static pressure Pi,j; and 3) calculating the internal resistance of the ventilation nacelle.
Owner:XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA

Calibration method and calibration device for vacuum ultraviolet imaging spectrometer

The invention provides a calibration method for a vacuum ultraviolet imaging spectrometer. The calibration method comprises the following steps of calibrating a wavelength measurement range, wavelength accuracy, spectrum response rate, uniformity and space angle resolution of the vacuum ultraviolet imaging spectrometer. The invention also provides a calibration device for the vacuum ultraviolet imaging spectrometer. The calibration device comprises a light source, a vacuum ultraviolet monochrome beam splitting system, a vacuum ultraviolet integrating sphere, a vacuum ultraviolet target and a vacuum ultraviolet collimating optical system which are arranged in an optical path in sequence, and further comprises a vacuum ultraviolet standard detector which is arranged on the output end of the vacuum ultraviolet collimating optical system together with the vacuum ultraviolet imaging spectrometer needing to be calibrated in a switchable manner, and a vacuum three-dimensional scanning mechanism which is used for implementing transformation of a space angle of the vacuum ultraviolet imaging spectrometer. By adopting the technical scheme of the invention, defects of the vacuum ultravioletimaging spectrometer in a design process can be timely discovered, and meanwhile, accuracy for data acquisition of the vacuum ultraviolet imaging spectrometer can be effectively guaranteed.
Owner:BEIJING ZHENXING METROLOGY & TEST INST

External radiation source radar real-time signal processing method based on multi-CPU processing

The invention relates to the technical field o radar systems, discloses an external radiation source radar real-time signal processing method based on multi-CPU processing, and a multi-CPU computer or server is utilized to realize external radiation source radar real-time signal processing with a general programming language, thereby increasing the flexibility of realization of signal processing of an external radiation source radar. The whole signal processing process of the external radiation source radar is split into a plurality of processing steps of clutter suppression, correlation processing and target detection, each step runs on a different CPU resource, the processing time of each step is smaller than accumulation time of a set of data, i.e., if a signal loss phenomenon does not occur, continuity and real-time performance of signal processing are realized, and through the method provided by the invention, clutter cancellation processing can be completed, the flexibility of signal processing of the external radiation source radar is improved, and real-time performance of signal processing of the external radiation source radar is realized. In addition, the development period of signal processing of the external radiation source radar can also be shortened, and requirements for development technicians by signal processing of the external radiation source radar are lowered.
Owner:STATE KEY LAB OF COMPLEX ELECTROMAGNETIC ENVIRONMENTAL EFFECTS ON ELECTRONICS & INFORMATION SYST

Optical registration method and system for LFOV (large field of view) and small-F-number line-surface combined remote sensing camera

ActiveCN107783270ASolve the accuracy problemSolve the problem of linear array-area array optical registrationTelescopesCamera lensSystem integration
The invention discloses an optical registration method and system for an LFOV (large field of view) and small-F-number line-surface combined remote sensing camera. The method comprises steps as follows: connecting a to-be-registered camera body and a table board of a two-dimensional turntable; step S200: determining the best focal plane position of a linear array channel and a surface array channel of a camera; establishing a light path for registration; making sure that reflecting light can fill a full aperture of a camera lens; drawing an orthogonal reticle cross on a screen of a display, and enabling a reticle cross target to be focused to and imaged in the center of the display; making a pixel of a linear array CCD parallel to the horizontal line of the reticle cross of the display; making a first row of pixels of a surface array CCD parallel to the horizontal line of the reticle cross of the display; aligning the Xth row of pixels of the surface array CCD parallel to the reticle cross of the display; verifying whether the Xth row of pixels of the surface array CCD are aligned to the horizontal line of the reticle cross of the display. The problems about high-accuracy system integration and linear array-surface array optical registration of an LFOV, small-F-number, light and small remote sensing camera are solved once.
Owner:BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH

Remote radar calibration satellite system and calibration method thereof

The invention relates to a remote radar calibration satellite system, which comprises a measurement and control operation control center, a ground application system, a reflective radar calibration satellite and a responsive measurement and control device calibration satellite, wherein the measurement and control operation control center is used for completing satellite launching and early orbitalsection measurement and control tasks, long-term operation section measurement and control management and load data receiving tasks; the ground application system is used for calibration satellite service planning, precision orbit data processing and publishing of a precision satellite orbit for each user; the reflective radar calibration satellite provides an RCS reference and a precise positionreference for calibration of a ground reflection-type radar device; and the responsive measurement and control device calibration satellite provides a precise position reference for calibration of aground response-type measurement and control device. The existing technical resources can be thoroughly used, the calibration requirements of the user can be met to the maximum degree, and the application range of the calibration satellite is expanded actively.
Owner:NO 63921 UNIT OF PLA

Multi-mode filtering method

ActiveCN105738870AAccurate and efficient calculationMeet the requirements of real-time calculationWave based measurement systemsGamma filterComputer science
The invention provides a multi-mode filtering method, and the method comprises the steps: receiving detection data; enabling a filter to carry out point removal judgment: enabling the filter to carry out resetting judgment if there is point removable identification, or else, calculating an output value of alpha-beta filtering and an output value of alpha-beta-gamma filtering; judging whether a mechanical operating identification is true or not through mechanical operation: outputting an output value of alpha-beta-gamma filtering if the mechanical operating identification is true, or else, judging whether the mechanical operating identification at a last observation moment is true or not; outputting the output value of alpha-beta-gamma filtering if the mechanical operating identification at the last observation moment is true, or else, outputting the output value of alpha-beta filtering. The method employs a fundamental structure of alpha-beta filtering and alpha-beta-gamma filtering synchronization parallel calculation, and the observation accumulation windows of two filters are different in size, and are very suitable for non-mechanical operating condition and mechanical operating condition. According to a mechanical recognition result, the method switches the output of the filters in real time, and can calculate the target position accurately and efficiently.
Owner:SHANGHAI INST OF ELECTROMECHANICAL ENG

Temperature control method for satellite propelling module

The invention provides a temperature control method for a satellite propelling module. According to the adopted design method for the independent propelling module installed on the basis of a propelling system, the outer surface of the whole module is coated with multiple thermal insulation components; part of a thruster needs to wrap the thermal insulation components outside the module; a compensating heater is designed to ensure the temperature level of an electromagnetic valve; pipelines and a support which are arranged outside the module wrap the thermal insulation components; no thermal control processing is conducted in the propelling module. By adopting the temperature control method on the basis of novel low-temperature propellant, the temperature control requirements of the satellite propelling module can be met.
Owner:SHANGHAI SATELLITE ENG INST

Method for accurately controlling infrared target interference model

A method for accurately controlling an infrared target interference model comprises the steps: establishing an infrared guidance semi-physical simulation device, wherein a simulation console, a simulation computer and an infrared target simulation system in the infrared guidance semi-physical simulation device are connected with one another to form a simulation closed loop, and a simulation turntable is connected with the simulation computer; after the infrared guidance semi-physical simulation device is powered on and initial setting is completed, enabling the simulation computer to completea dynamics and kinematics model in real time and drives the position and rate of the simulation turntable; meanwhile, enabling an infrared scene simulator in the infrared target simulation system to receive interference control parameters sent by the simulation computer in real time, and setting each module of an infrared interference model generated by the infrared scene simulator according to two control mechanisms of simulation time and missile-target distance of the simulation computer; therefore, the clutter and divergence model of the infrared radiation energy is generated, the infraredinterference model is accurately controlled in real time, and the confidence degree of infrared missile anti-interference performance evaluation is effectively improved.
Owner:JIANGXI HONGDU AVIATION IND GRP

A Compact Field RF Target Simulator

The invention belongs to simulation test technology and relates to a compact field target simulator. The compact field radio frequency target simulator of the present invention includes a reflector, a feed source, and a feed source bracket that supports multi-degree-of-freedom adjustment of the feed source, wherein the reflector is a cut parabolic antenna, and the feed source is a pyramidal horn jacket choke circle, and the feed is located at the focal plane of the reflector. The invention utilizes the principle that the feed source horn is placed on the focus of the rotating parabola, and the reflection surface is irradiated to form a parallel wave to simulate the target echo; by designing a suitable feed source, processing a high-precision reflection surface, and processing the edge of the reflection surface, etc., the static area of ​​the field is controlled to tighten the quiet zone The characteristics of electromagnetic waves make it close to the far-field conditions of the target echo, and the structure is compact, the form is simple, the volume is small, and the cost is low.
Owner:CHINA AIR TO AIR MISSILE INST

Simulation method for oceanic reverberation under any sound velocity gradient

The invention discloses a simulation method for oceanic reverberation under any sound velocity gradient, which comprises the following steps of: (1) calculating the variable sound velocity gradient of sea water; (2) evenly distributing a plurality of reverberation scattering elements on a space; (3) calculating the intrinsic sound ray of each reverberation scattering element according to the variable sound velocity gradient of the sea water, and selecting one reverberation scattering element according to the intrinsic sound ray of each reverberation scattering element; and (4) respectively calculating a sea surface reverberation time sequence generated by a sea surface scattering element in the selected reverberation scattering element, a volume reverberation time sequence generated by a volume scattering element, and a sea bottom reverberation time sequence generated by a seat bottom scattering element, and overlapping the sea surface reverberation time sequence, the volume reverberation time sequence and the sea bottom reverberation time sequence to obtain an oceanic reverberation time sequence. The simulation method not only can work under any sound velocity gradient but also can be used for accurately simulating the oceanic reverberation.
Owner:NAVAL UNIV OF ENG PLA

Synchronous control method of motion of combined supporting mechanism of wind tunnel

The invention discloses a synchronous control method of the motion of a combined supporting mechanism of a wind tunnel. First, a tail supporting mechanism is identified as an active control object, and a stripe hanging supporting mechanism is identified as a follow-up control object; second, the characteristics including dynamic response time difference, motion speed and the like of the two independent supporting mechanisms in the combined supporting mechanism are tested and data of the characteristics are recorded; finally, the effect that the auxiliary supporting mechanism follows the main supporting mechanism in real time is achieved through sequential control of instructions, and corresponding safety strategies are adopted to cope with risks likely to exist in the process of a test, so that the test suffers no risk at all. The synchronous control method has the advantages that through the synchronous control over the two independent supporting mechanisms, combination supporting of an aircraft model is achieved, and a new test technology is provided for an aerodynamic test of the aircraft model in the wind tunnel; the method is good in operability, strong in engineering adaptability and high in safety and can meet special requirements in the technical field of wind tunnel supporting interference tests, greatly save equipment development expenditure and shorten the development period.
Owner:INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT

Spectral radiation luminance responsivity measurement system

The invention relates to the technical field of optical testing equipment and discloses a spectral radiation luminance responsivity measurement system. The system comprises a vacuum ultraviolet lightsource, a vacuum ultraviolet monochrome beam splitter, a vacuum ultraviolet uniformizing device, a reference radiation luminance meter, a switching device, a controller and an oil-free vacuum chamber,wherein the vacuum ultraviolet light source is used for emitting vacuum ultraviolet light radiation; the vacuum ultraviolet monochrome beam splitter is used for carrying out beam-splitting processingon incident vacuum ultraviolet light radiation and then outputting light radiation with a predetermined wavelength; the vacuum ultraviolet uniformizing device is used for carrying out uniform processing on the output light radiation with the predetermined wavelength; the switching device is used for carrying out switching between alignment of the reference radiation luminance meter with the vacuum ultraviolet uniformizing device and alignment of a to-be-calibrated radiometer with the vacuum ultraviolet uniformizing device; the controller is used for calculating spectral radiation luminance responsivity of the to-be-calibrated radiometer according to radiation luminance values measured by the reference radiation luminance meter and the to-be-calibrated radiometer separately; and the oil-free vacuum chamber provides a vacuum environment, thereby accurately obtaining the spectral radiation luminance responsivity of the to-be-calibrated radiometer.
Owner:BEIJING ZHENXING METROLOGY & TEST INST

Flexible support micro-vibration testing device for simulating whole satellite

Provided is a flexible support micro-vibration testing device for simulating a whole satellite. The flexible support micro-vibration testing device comprises a brace supporting structure, a six-component force sensor, an acceleration sensor, a data acquiring and processing system, a rigid platform, and an adaptive support. A whole satellite simulated member is a test object. The top of the brace supporting structure is fixed to the six-component force sensor through an interface. The six-component force sensor is fixed to the whole satellite simulated member through the adaptive support. The acceleration sensor is pasted onto the brace supporting structure. The data acquiring and processing system is connected with the six-component force sensor and the acceleration sensor. The rigid platform is equipped with a plurality of ground racks. The brace supporting structure is fixed to the ground racks on the rigid platform through screws. The flexible support micro-vibration testing device may control and change the rigidity of a whole test system, simulates a transverse fundamental frequency satellite from 5 to 15Hz, has level support structures each of which forms the function of a measuring subsystem in order to simulate the flexible support of a single machine and components to a brace, a single cabin, and a whole satellite.
Owner:BEIJING INST OF SPACECRAFT SYST ENG

VPX computer processing board based on VITA series standard

The invention discloses a VPX computer processing board based on VITA series standards. The VPX computer processing board comprises a COM Express module, a VPX function carrier plate, a panel and a VPX connector, wherein the COM Express module, the panel and the VPX connector are all mounted on the VPX function carrier plate; a VGA signal output from the COM Express module is led to the panel through a VGA interface; the COM Express module is connected with the panel; the COM Express module is connected with the VPX connector through a PCIE bridge; a RaidIO bridge chip is further connected between the COM Express module and the VPX connector; PCIE can be converted into a RapidIO bus through the RapidIO bridge chip; 1 path of PCIE x4 can convert 1 path of RapidIO x4 and is compatible with 1 path of PCIE x1 and converts 1 path of RapidIO x1; conversion of 4 paths of PCIE to 4 paths of RapidIO buss can be achieved at most; 1 path of PCIE3.0 x16 can be converted into 5 paths of PCIE x16 through the PCIE bridge at most; the PCIE bridge is further compatible with PCIE1.0 and PCIE2.0. On the basis of the principle, diverse demands of users can be met, the development period is shortened, and the research expenditure can be lowered.
Owner:CHENGDU PUNUO TECH CO LTD

Method for converting different normal matrix test data

InactiveCN102110185ASolve the problem of poor estimation accuracy or even impossible estimationMeet the requirements of reliability evaluationSpecial data processing applicationsNormal matrixProduct system
The invention discloses a method for converting different normal matrix test data. The method comprises the following steps of: randomizing a function related to test data, obtaining massive simulation test data under each normal matrix by utilizing a Monte-Carlo simulation technology, and then estimating normal environmental factors used for conversion on different normal matrix test data by utilizing the simulation test data to complete conversion between small sample test data among different normal matrixes. The method has the beneficial effect that the normal environmental factor used for conversion on different normal matrix test data is obtained by utilizing the Monte-Carlo simulation technology, on one hand, enough test data can be obtained to achieve the performance parametric reliability evaluation requirement, on the other hand, the number of system tests on a product is increased to obtain enough reliability evaluation data, thus development expenditure and development time are greatly saved.
Owner:713 RES INST OF CHINA SHIPBUILDING IND CORP

Centroid deviation measurement method for conical cylindrical parts

The invention relates to the technical field of centroid deviation measurement methods, in particular to a centroid deviation measurement method for conical cylindrical parts. The centroid deviation measurement method includes the following steps: measuring the axial centroid of a conical cylindrical part: placing the conical cylindrical part horizontally, arranging a first support and a second support at the front and back ends of the conical cylindrical part respectively, and determining the axial centroid of the conical cylindrical part according to the distances between and the weights ofthe conical cylindrical part, the first support and the second support; measuring the radial centroid deviation of the conical cylindrical part; and lifting the conical cylindrical part, measuring theobtained centroid position according to the axial centroid, and calculating the radial centroid deviation of the conical cylindrical part according to the triangular function relationship of the conical cylindrical part after lifting. The centroid deviation measurement method provided by the invention is designed for conical cylindrical parts, has certain universality for mass deviation measurement, does not need to develop special measurement equipment, has the characteristics of short investment time and low development cost, and can be used to complete the centroid deviation measurement ofconical cylindrical parts in an economical and convenient way.
Owner:SHANGHAI SPACE PRECISION MACHINERY RES INST

Synchronous control method of motion of combined supporting mechanism of wind tunnel

The invention discloses a synchronous control method of the motion of a combined supporting mechanism of a wind tunnel. First, a tail supporting mechanism is identified as an active control object, and a stripe hanging supporting mechanism is identified as a follow-up control object; second, the characteristics including dynamic response time difference, motion speed and the like of the two independent supporting mechanisms in the combined supporting mechanism are tested and data of the characteristics are recorded; finally, the effect that the auxiliary supporting mechanism follows the main supporting mechanism in real time is achieved through sequential control of instructions, and corresponding safety strategies are adopted to cope with risks likely to exist in the process of a test, so that the test suffers no risk at all. The synchronous control method has the advantages that through the synchronous control over the two independent supporting mechanisms, combination supporting of an aircraft model is achieved, and a new test technology is provided for an aerodynamic test of the aircraft model in the wind tunnel; the method is good in operability, strong in engineering adaptability and high in safety and can meet special requirements in the technical field of wind tunnel supporting interference tests, greatly save equipment development expenditure and shorten the development period.
Owner:INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT

A navigation information filtering method increasing moving alignment precision

A navigation information filtering method increasing moving alignment precision is disclosed. The method includes receiving, by an information interface assembly, navigation data sent by a comprehensive navigation device, subjecting the navigation data to point elimination, limiting and filtering treatment, and outputting an angle, an angular velocity and a ship velocity. The method overcomes a problem of how to obtain smooth and continuous transfer alignment information used for aircrafts through processing high-frequency navigation data in a situation that a shipboard platform is accompanied with vertical and horizontal swing.
Owner:SHANGHAI INST OF ELECTROMECHANICAL ENG

Simulated analysis method of zero length emitting device

The invention discloses a simulated analysis method of a zero length emitting device, which includes steps of firstly building a three-dimensional model of every spare part of an unmanned machine emitting device; completing a topological structure model of every spare part of the unmanned machine emitting device according to mutual relationship of every spare part of the unmanned machine emittingdevice; establishing a restriction condition according to the topological structure relationship; applying all external loads to the simulation model; solving the unmanned machine on the emitting device during the emitting process and establishing the unmanned machine emission simulating model; simulating and outputting the simulating result; performing contrast analysis on the simulated emissiontest data and judging the correctness of the simulation method. Through replacing the entity experiment by the simulated analysis, the simulated analysis has low requirement on hardware and is simplein implementation condition, short in cycle and good in repeatability; the method can virtually verify the design scheme, exactly predict the test result while reduce the research expenses and shortenthe research cycle; besides, the method has good visible effect.
Owner:JIANGXI HONGDU AVIATION IND GRP

Photoelectric tracking system target simulation device and method

The invention relates to the technical field of photoelectricity, in particular to a photoelectric tracking system target simulation device and method. The device comprises an image input and output module, a serial port receiving and forwarding module and a chip module; the device is connected with a camera through the image input and output module, and is used for receiving image information; the device is connected with a servo mechanism through the serial port receiving and forwarding module, and receives azimuth and pitch information of a turntable; the chip module is used for superposing the simulation target on the image in real time according to the real-time orientation and pitching information of the photoelectric turntable; after the display control computer recognizes and tracks the target in the image, if the target is not in the center of the image, the servo mechanism is adjusted, and the target is adjusted to the center of the image; in this way, the target simulation purpose is achieved, various properties of the photoelectric tracking system can be fully verified in the development stage of photoelectric tracking products, the development progress is accelerated, and the development expenditures are reduced.
Owner:BEIJING INST OF ENVIRONMENTAL FEATURES

Parallel processing platform robot

The invention relates to a parallel processing platform robot. The parallel processing platform robot comprises a controller, a first moving mechanism, a second moving mechanism, a third moving mechanism and a processing platform. The first moving mechanism is connected with the processing platform through a first connecting rod. The second moving mechanism is connected with the processing platform through a second connecting rod. The third moving mechanism is connected with the processing platform through a third connecting rod. The controller is used for controlling the first moving mechanism, the second moving mechanism and the third moving mechanism to drive the three connecting rods to move to drive the processing platform to remain horizontal and rise and drop in the vertical direction. The first moving mechanism, the second moving mechanism and the third moving mechanism of the parallel processing platform robot are arranged in parallel, and the space can be saved; the parallelprocessing platform robot is simple in overall structure, easy to produce and machine and capable of increasing production benefits, reducing the labor risk and realizing factory automation and can beapplied to various types of processing and manufacturing fields, save the development cost and improve the operational capability of the processing platform.
Owner:霸州市华硕汽车零部件有限公司
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