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Efficient and compact pre-cooling heat exchanger for pre-cooling gas sucking type engine
ActiveCN107218133AGuaranteed heat exchange effectReduce welding difficultyTurbine/propulsion engine coolingGas turbine plantsEngineeringCurrent technology
The invention discloses an efficient and compact pre-cooling heat exchanger for a pre-cooling gas sucking type engine. The efficient and compact pre-cooling heat exchanger for the pre-cooling gas sucking type engine comprises a pre-cooling heat exchanger body in the shape of a similar cylinder; the cross section of the similar cylinder is in the shape of a ring different in diameter; the longitudinal section of the similar cylinder is formed by two symmetrically arranged arc segments; the center angle of each arc segment is 45 degrees; the pre-cooling heat exchanger body comprises a cold flow outlet pipe, a cold flow inlet pipe and a plurality of heat exchanging pipes; each heat exchanging pipe is in the shape of an arc; the arc-shaped center angle of each heat exchanging pipe is 45 degrees; and the heat exchanging pipes are distributed into the similar cylinder in a crossed manner. The efficient and compact pre-cooling heat exchanger for the pre-cooling gas sucking type engine can have the engineer realizability on the premise that the heat exchanging effect is guaranteed, so that air incoming flow in front of a gas compressor can be pre-cooled, the high temperature over-running problem of gas compressor blades is solved, the engine thrust is increased, the flight envelop is extended, the welding difficulty is effectively reduced, the frosting blockage problem is effectively solved, the engineer realizability is achieved under the current technology, and after the efficient and compact pre-cooling heat exchanger for the pre-cooling gas sucking type engine is applied to the pre-cooling gas sucking type engine, the engine performance can be substantially improved.
Owner:PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
System and method for detecting low-speed small target under sea cluster background
ActiveCN104215951ATroubleshoot probing issuesSuppress false alarmsWave based measurement systemsTime frequency domainEnvironmental geology
The invention discloses a system and a method for detecting a low-speed small target under a sea cluster background. The method includes that S1, a radar transceiving unit acquires signals of the low-speed moving small target under the sea cluster background; S2, the radar transceiving unit sends received signals to a radar echo processing unit to be processed to generate radar echo data and sends the radar echo data to a detection unit; S3, the detection unit processes multiple continuous radar echoes and establishes corresponding time frequency domain two-dimension planar graphs to effectively eliminate false-alarm targets in different areas. The system and the method are suitable for detection of dim and small targets moving at low speed under sea cluster background interference during downward-looking detection of sea-surface targets through radar. By the system and the method, the problem of radar downward-looking detection of the low-speed moving small target under the sea cluster background can be solved; time frequency domain CFAR (constant false alarm rate) processing technology is adopted to decompose target echoes and sea cluster data to a time frequency domain two-dimension plane for processing.
Owner:SHANGHAI RADIO EQUIP RES INST
Method of using sum and difference channels of radar antenna for restraining radar side lobe interception
ActiveCN104777468AReduce complexityReduce the number of channelsWave based measurement systemsPhase correctionRadar systems
The invention relates to a method of using sum and difference channels of a radar antenna for restraining radar side lobe interception. According to the method, antenna patterns of the sum channel and the difference channel of the radar main antenna are optimized, self-correcting signals of a radar system are used for obtaining amplitude and phase errors with the sum channel as the datum, and the amplitude and phase errors are used for error correction of the sum channel and the difference channel; according to the target position in the sum channel, the corresponding position, in the difference channel, of a target is searched for, and amplitude and phase correction is carried out on the complex number value of the position, where the target is located, in the difference channel by means of the amplitude and phase errors of the sum channel; the complex number modulus value of the position, where the target is located, in the sum channel is compared with the corrected complex number modulus value of the target in the difference channel to judge whether target echoes enter from main lobes or side lobes of the main antenna. Therefore, the radar system using the method can directly use the main antenna for recognizing side lobe targets without depending on an auxiliary antenna, the design difficulty of the radar antenna is effectively lowered, the number of the channels of the antenna is effectively reduced, and the reliability of the antenna is improved.
Owner:SHANGHAI RADIO EQUIP RES INST
Compression perception radar high resolution imaging equipment under low signal to noise ratio and imaging method thereof
InactiveCN105467388AHigh resolution imagingSuppress noiseRadio wave reradiation/reflectionHigh resolution imagingTransceiver
Compression perception radar high resolution imaging equipment under a low signal to noise ratio and an imaging method thereof are disclosed. A radar transceiver unit carries out continuous multi-time transmitting and receiving along a radar azimuth and acquires a plurality of target scene echo signals under a noise background. A compression sampling unit carries out aliasing downsampling on the acquired echo signals and acquires radar echo data after aliasing downsampling under a single pulse. A signal processing unit establishes time-domain two-dimensional data planes under different orientation angles according to the plurality of radar echo data. An imaging identification unit constructs a distance dimension basis matrix and an orientation dimension basis matrix. The time-domain two-dimensional data planes are projected to the distance dimension basis matrix. A radar imaging model is constructed on the orientation dimension. Through an inverse optimization method, a high resolution image is acquired. In the invention, a small aperture radar effectively restrains a noise interference and a side lobe through a small echo data volume and simultaneously realizes high resolution imaging, and a performance index of a small aperture radar system is increased.
Owner:SHANGHAI RADIO EQUIP RES INST
Satellite figured antenna anti-intrusion based on high-resolution algorithm
InactiveCN1897486ANarrow searchReduce computationSpatial transmit diversityCode division multiplexBand-pass filterCenter frequency
The method manages to solve the problem of high resolution and high arithmetical complexity existed in normal approach in order to reach main beam-forming and be capable of making real time process for multi high strength interferences. It comprises: a beam selector is used to make channel selection control in order to select several channels under interference; sending the signals from the selected channels into a process branch circuit; the selected signals firstly are converted down to 1.0 GHZ and are sent to band filter; the signals outputted from the filter are sent to the phase detector, and negative frequency spectrum is removed from the those signals, and the real signals are converted into the complex signals. The algorithm used in current system is implemented by using the correction of amplitude and phase, high resolution angle measurement and self-adaptive zeroing process.
Owner:XIDIAN UNIV
Determination method and device for flight path command of flight vehicle
InactiveCN104156595AGuidance control facilitatesGuidance and control stabilitySpecial data processing applicationsGuidance systemControl system
The invention discloses a determination method and device for a flight path command of a flight vehicle. The determination method comprises the steps that according to voyage to be flown, provided by a guiding system, of the flight vehicle, a speed command parameter Vcx of the flight vehicle is calculated; according to the flight speed, provided by the guiding system, of the flight vehicle, a drag acceleration command parameter Dcx, a drag acceleration derivative order parameter cx, a height command parameter Hcx and a tilt angle command parameter thetacx of the flight vehicle are calculated; according to all the calculated command parameters, the flight path command of the flight vehicle is generated and sent to a control system of the flight vehicle. As the flight path command of the flight vehicle can be quickly given according to the flight speed and the voyage to be flown, the determination method and device are beneficial to guidance control over the flight vehicle.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
Engineering testing method of vibration field of non-uniform arrangement structure
ActiveCN107741312ASolve the problem of optimal layout of noise measuring pointsSolve problems that are difficult to test easily and accuratelyVibration testingMonitoring systemWorkload
The invention relates to an engineering testing method of the vibration field of a non-uniform arrangement structure. Based on the condition number of a structural vibration modal matrix, vibration measuring points causing an increase of the condition number of the matrix are removed in the loop iteration process, so that reduction of the number of the measuring points and optimization of the positions of the measuring points are achieved. Then based on a mode superposition method, only measuring data of the optimized measuring points with the number reduced is adopted, and vibration field reconstruction of the whole large structure is achieved. According to the method, a few sensors are optimized for position arrangement, and the vibration response field of the whole structure is reconstructed by means of the measuring data of the sensors, so that space and weight are saved, the testing workload is significantly relieved, and a monitoring position optimization method is provided for avibration monitoring system.
Owner:CHINA SHIP DEV & DESIGN CENT
A system and method for implementing collision resolution scheduling in satellite optical burst switch
ActiveCN109040865AIncrease success rateImprove data throughputMultiplex system selection arrangementsTime-division multiplexBroadband transmissionComputer terminal
A system and method for implementing collision resolution scheduling of satellite optical burst switch. According to the topology of space-based broadband transmission backbone network and the statusof each switching node, through the scheduling method of network resources pre-allocation, at that boundary of the space-based broadband transmission backbone network, the data to be transmitted and exchanged to the space-based broadband transmission backbone network is controlled, the switching time and the forwarding path of each optical burst data entering into the space-based broadband transmission backbone network are planned in advance, and the collision resolution scheduling of the optical burst data exchange of the space-based broadband transmission backbone network is realized. The optical burst data of the space-based broadband transmission backbone network is generated by the electric domain. After completing the electro-optical conversion at the edge node of the backbone network, the optical burst data enters the backbone network for optical burst exchange. After reaching the destination edge node, the optical burst data is converted, and then the data is sent to the processing terminal to complete the data routing exchange process. Through pre-planning and scheduling, the system can resolve the collision of satellite optical burst switch by using network resources.
Owner:XIAN INSTITUE OF SPACE RADIO TECH
Method of forming stable adaptive wave beams of space distribution scattering source
InactiveCN103259584ASolve the blockageEasy to implementSpatial transmit diversityRadarMedical imaging
The invention discloses a method of forming stable adaptive wave beams of a space distribution scattering source. Firstly, received data are utilized to form a covariance matrix, secondly, mismatch constrained parameters are selected and an optimum weighting vector of an adaptive beam former is calculated according to the method of forming the stable adaptive wave beams of the space distribution scattering source, and finally the method of forming the stable adaptive wave beams is obtained. The method of forming the stable adaptive wave beams of the space distribution scattering source can solve the problem how to improve sharp performance reduction of the adaptive beam former when an assumed signal array response is not matched with an actual value, and the technical problem that the performance of the adaptive beam former is reduced due to signal mismatch and other mismatches under the condition that all mismatches exist, and can be widely applied to adaptive array processing in the field of radars, communication, medical imaging, microphone micro-arrays, seismic exploration and the like.
Owner:JIANGSU HENGXIN TECH CO LTD
Method for solving attitude angle of swinging spray nozzle
The invention discloses a method for solving attitude angle of a swinging spray nozzle. The method specifically comprises the following steps of 1, determining the initial value of the attitude angle;2, determining a conversion matrix of the measuring value; 3, collecting data of an MEMS gyroscope; 4, converting the data of the MEMS gyroscope; 5, updating quaternion; 6, solving the attitude angle. The method has the characteristics that the engineering realizability is realized, and the attitude angle can be solved in the rotation process of the swinging spray nozzle; the attitude angle can be decoupled, and the automatic reading of the data is simultaneously completed; the universality is realized, and the method can be applied to the testing of the swinging spray nozzles of other models.
Owner:BEIJING INST OF ELECTRONICS SYST ENG
Monte Carlo simulation method for active critical device in approximate critical process
PendingCN112069670AThe calculation results of physical quantities are correct and reliableRealize simulationDesign optimisation/simulationSpecial data processing applicationsNeutron transportChemistry
The invention relates to a Monte Carlo simulation method for an active critical device in an approximate critical process, which is suitable for the field of neutronics physical analysis of a nuclearcritical device with an external neutron source. According to the invention, the method comprises the steps: decomposing a continuous neutron transport process into successive generations of analog calculation, and according to successive generations of system neutron effective proliferation factors and successive generations of physical quantity statistical counting, and carrying out the weightedsummation to obtain final calculation results of physical quantities such as nuclear critical device power level and neutron flux distribution are obtained. According to the method, Monte Carlo simulation of the transport process of the external neutron source in the approaching critical process of the nuclear critical device is achieved, and the situation that infinite transport calculation of the external neutron source of a certain generation is not terminated due to randomness of the Monte Carlo method is avoided; the Monte Carlo simulation method for the neutron transport process of theactive critical device is advanced and has engineering feasibility.
Owner:CHINA NUCLEAR POWER ENG CO LTD
GEO satellite external multilayer thermal insulation assembly earthing system and method
ActiveCN105923173AComply with charging potential control requirementsCompliance with control requirementsCosmonautic vehiclesCosmonautic radiation protectionThermal insulationEngineering
The invention discloses a GEO satellite external multilayer thermal insulation assembly earthing system and method. The judgment criterion of the number of multilayer thermal insulation assembly earthing devices on a monoblock multilayer thermal insulation assembly is designed, the GEO satellite external multilayer thermal insulation assembly earthing system comprising the multilayer thermal insulation assembly earthing devices, an earthing ridge and an O-shaped terminal is designed, and an installation method and the test criterion for guiding multilayer thermal insulation assembly earthing implementation are designed. By using the GEO satellite external multilayer thermal insulation assembly earthing system and method provided by the invention, on the premise that the surface charging potential control requirements during GEO satellite in-orbit operation period are met, the defects that a plurality of earthing wires are led out of the multilayer thermal insulation assembly, but limited satellite surface earthing points cannot meet the earthing wire lap jointing requirements for the multilayer thermal insulation assembly can be overcome; and the surface charging and discharging risks of the GEO satellite can be reduced, and GEO satellite in-orbit abnormal situation caused by surface charging and discharging effects is greatly relieved.
Owner:CHINA ACADEMY OF SPACE TECHNOLOGY
Unmanned aerial vehicle cluster formation flight method for saving communication bandwidth
ActiveCN114415733AFormation flight is normalReduce data trafficPosition/course control in three dimensionsTelecommunications linkNetwork link
The invention relates to an unmanned aerial vehicle cluster formation flight method for saving communication bandwidth, which comprises the following steps that: a computer control program for processing strategy information and long and short messages of a long aerial vehicle in formation flight is pre-integrated in each unmanned aerial vehicle Fi in an unmanned aerial vehicle cluster based on an ad hoc network link; when the unmanned aerial vehicle Fi receives the long and short messages shared by other unmanned aerial vehicles Fj, the unmanned aerial vehicle Fi checks that the own identifier is the same as the long aerial vehicle identifier in the long and short messages, and the long aerial vehicle processes the strategy information and updates the own level information and shares the long message at the same time; the long message is message information which has position information and is shared by a lead aircraft, and the short message is message information which does not have position information and is shared by unmanned aerial vehicles as wing aircrafts. According to the method provided by the invention, the unmanned aerial vehicle can flexibly switch the long unmanned aerial vehicle, send the position as required and dynamically use the bandwidth, so that the sharing of invalid data is avoided, and the technical problems that the networking communication link is poor in stability and the communication bandwidth is occupied in the prior art are effectively solved.
Owner:BEIHANG UNIV
A UAV swarm formation flying method for saving communication bandwidth
ActiveCN114415733BFormation flight is normalReduce data trafficPosition/course control in three dimensionsTelecommunications linkSimulation
The present invention relates to a formation flying method for swarms of unmanned aerial vehicles for saving communication bandwidth. i It is pre-integrated with a computer control program for the long aircraft in formation flight to process strategy information and long and short messages. When the UAV F i Other UAV F received j For shared long and short messages, check that its own ID is the same as the long machine ID in the long and short messages. At the same time, the long machine processing policy information updates its own level information and shares the long message; the long message has location information and is shared as the long machine. The message information of the short message is the message information without location information shared by the UAV as a wingman. In the method of the invention, the UAV can flexibly switch the long plane, send the position on demand, dynamically use the bandwidth, avoid the sharing of invalid data, and effectively solve the problems of poor stability of the network communication link and occupied communication bandwidth in the prior art. technical problem.
Owner:BEIHANG UNIV
Seabed frame fixed type group anchor system
The invention relates to a seabed frame fixed type group anchor system. The system comprises an anchor frame assembly; the top of the anchor frame assembly is of a hexagonal anchor type structure; a central short cylinder structure is arranged in the middle of the anchor frame assembly; six pieces of radial channel steel are evenly arranged on the outer circumferential face of the center short cylinder structure at intervals; the head of each piece of radial channel steel is connected with a hollow cylinder shell; an upper end cover is installed at the top of each hollow cylinder shell; everytwo adjacent hollow cylinder shells are connected through external channel steel; and the six pieces of external channel steel are connected to form a hexagonal structure; a triangular plate is installed at the bottom of each piece of external channel steel; a damping plate is installed at the bottom of each piece of radial channel steel; a guide column is installed in each hollow cylindrical shell in a matched mode; a protective sleeve is installed at the bottom of each guide column; and a first thorn plate and a second thorn plate are symmetrically installed on the outer circumferential faceof each guide column. The work of the system is reliable .
Owner:CHINA SHIP SCIENTIFIC RESEARCH CENTER (THE 702 INSTITUTE OF CHINA SHIPBUILDING INDUSTRY CORPORATION)
Extra-high voltage half-wavelength power transmission system integrated voltage control method and system
ActiveCN108429267AImprove transmission power factorTargetedReactive power adjustment/elimination/compensationAc network voltage adjustmentElectric power transmissionCapacitance
The invention discloses an extra-high voltage half-wavelength power transmission system integrated voltage control method and system. The method comprises the steps that original data of an extra-highvoltage half-wavelength power transmission system is acquired; initialization setting is carried out before voltage control; leading node voltage adjustment, half-wavelength line transmission power factor improvement and reasonable distribution for electric generator reactive output are taken as a secondary voltage control objective, a voltage control optimization model is constructed, and a linear objective programming is utilized for solving; a coordinated relationship between continuous and discrete control variables is considered, and a capacitance\electric reactor switching principle based on a running mode is applied; a voltage control plan is verified, it is determined whether or not actual system voltage control requirements are satisfied. The method and system take the leading node voltage adjustment, the half-wavelength line transmission power factor improvement and the reasonable distribution for electric generator reactive output as the secondary voltage control objective,have pertinency, and have a wide use range.
Owner:SHANDONG UNIV
Mars detection ground antenna pointing correction method based on error quaternion
PendingCN111967125AError protectionEngineering feasibilityDesign optimisation/simulationSpecial data processing applicationsQuaternionComputational physics
The invention relates to a Mars detection ground antenna pointing correction method based on error quaternion, and the method comprises the specific steps: S1, defining the quaternion of spatial three-dimensional rotation, and building a detector mechanical coordinate system; s2, correcting the final X-axis driving angle alpha and Y-axis driving angle beta of the ground antenna by adopting a gradual error correction strategy based on the ground accurate measurement data; s3, based on the on-orbit calibration data, obtaining error angles d alpha under different X-axis driving angles alpha and error angles d beta under different Y-axis driving angles beta, and obtaining the relation between the error angles and the driving angles through one-time linear fitting to be corrected. According tothe method, correction is carried out on two aspects of a ground accurate measurement result and an on-orbit calibration result, the ground accurate measurement result correction is based on a rotation quaternion, the on-orbit calibration result correction is based on one-time linear error fitting, and errors under different driving angles can be effectively guaranteed.
Owner:SHANGHAI AEROSPACE CONTROL TECH INST
Method for determining lift aircraft reentry guidance resistance accelerated speed change rate
InactiveCN104787361AImprove tracking control accuracySuppress fluctuationsSpacecraft guiding apparatusGuidance controlEngineering
The invention discloses a method for determining the lift aircraft reentry guidance resistance accelerated speed change rate. The method includes the steps that a mapping relation between the flight speed and a preset attack angle command is determined according to a task requirement; according to a pneumatic parameter model, fitting is carried out to obtain a fitting relational expression between a pneumatic resistance parameter and an attack angle, and an estimation value of the pneumatic resistance parameter is obtained according to the fitting relational expression; according to the estimation value of the pneumatic resistance parameter and the mapping relation between the flight speed and the preset attack angle command, the pneumatic resistance coefficient change rate is obtained through calculation; the height change rate and the speed change rate are calculated according to a navigation parameter and an approximation formula; according to the height change rate, the speed change rate and the pneumatic resistance coefficient change rate, a resistance accelerated speed change rate is obtained through calculation. By means of the method, influences of sampling noise on the reentry guidance control accuracy can be effectively avoided, and the tracking control accuracy of the resistance accelerated speed is improved.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
A method for monitoring and managing redundancy of a fault-tolerant system for improving availability
ActiveCN105550053BImplement Redundancy ManagementEnsure credibleHardware monitoringReliability/availability analysisFault toleranceComputerized system
The invention discloses a redundancy management method for improving the availability of a monitoring pair based fault tolerant system. The method comprises the steps of intra-node voting and monitoring and node-level voting and monitoring. During the intra-node voting and monitoring, a controller A and a controller B are consistent by comparison and data of the controller A are selected to enter the node-level voting and monitoring. During the node-level voting and monitoring, a mid-value is selected as a reference value of monitoring from values of three signals of three nodes, and if a difference between other two non mid-value signals and a mid-value signal is within a threshold range, then the non mid-value signals are normal, otherwise, the non mid-value signals are faulted. According to the redundancy management method, the redundancy management of a monitoring pair based three-node or two-node fault tolerant computer is realized; the credibility of system data of a fault tolerant computer system can be ensured; and compared with fault silence based monitoring pair fault tolerance, the redundancy degradation of the system is slowed down, and a backup controller can be reconfigured to be a main controller when a fault occurs once in a node through a software and hardware combination mode, so that the system is ensured not to be degraded.
Owner:XIAN AVIATION COMPUTING TECH RES INST OF AVIATION IND CORP OF CHINA
Nondestructive Fault Injection Method Supported by Airborne Redundancy Computer for Fault Tolerant Verification
ActiveCN103019904BSimple structureEngineering feasibilityError detection/correctionNon destructiveFault tolerance
The invention provides a non-destructive fault injection method for supporting fault tolerance verification of an on-board redundancy computer. A main program of a channel of the on-board redundancy computer is taken as the target object for injecting a fault. The non-destructive fault injection method includes the steps that a fault injection interaction terminal edits fault content and sends a fault injection command to a fault injection interrupt handling routine; the fault injection interaction terminal sends a fault injection interrupt request and enables the fault injection interrupt handling routine through interrupt interlock control; and the fault injection interrupt handling routine is executed. The non-destructive fault injection method enables the on-board redundancy computer to have the capability of supporting fault tolerance verification and can realize non-destructive fault injection in a fault simulation experiment on the basis of not causing any physical damage and not destructing the reliability and the safe performance characteristic of a product.
Owner:AVIC NO 631 RES INST
A rendezvous and approach method with minimum velocity increment
ActiveCN109839116BSmall speed incrementEngineering feasibilityInstruments for comonautical navigationClassical mechanicsControl theory
The invention provides a rendezvous approach method with the minimum speed increment. The method comprises the steps that the position and speed of a mooring track and a target track are acquired according to the parameters of a maneuvering satellite and a target satellite; the intersection vector of the mooring track and the target track and related parameters are solved; the intersection point of a maneuvering satellite and a target satellite is calculated; the optimal track control point is determined according to single-pulse track design under perturbation; phase is controlled and adjusted by closing the tracks; and the maneuvering satellite and the target satellite eventually intersect and approach at the intersection point.
Owner:SHANGHAI ENG CENT FOR MICROSATELLITES
Method for improving maneuverability of marine diesel engine propulsion system
PendingCN114237030AEngineering feasibilityImprove mobilityPower plants being motor-drivenEngine controllersDieselingPropeller
The invention discloses a method for improving maneuverability of a marine diesel engine propulsion system. The method comprises the following steps: step 1, loading according to a set loading rate; 2, according to the real-time rotating speed and load of the propulsion diesel engine, comparing the real-time rotating speed and load of the propulsion diesel engine with a propulsion diesel engine load limiting line to judge the overload limiting line trend condition, and if the overload limiting line trend exists, executing the step 3; if the overload limit line trend is relieved, executing the step 4 until acceleration loading is completed; step 3, load active control screw pitch reduction: propulsion monitoring still sends a rotating speed instruction to a propulsion diesel engine in real time at a preset speed increasing speed to carry out rotating speed adjustment; meanwhile, a pitch reduction instruction is sent to the controllable-pitch propeller to carry out pitch reduction operation, and the second step continues to be carried out; 4, the load actively controls the pitch rising, wherein propelling monitoring still controls the rotating speed of the propelling diesel engine at the preset increasing rotating speed rate; and a pitch raising instruction is sent to the controllable-pitch propeller for pitch raising operation, and the second step continues to be carried out.
Owner:CHINA SHIP DEV & DESIGN CENT
A system and method for realizing satellite optical burst switching conflict resolution scheduling
ActiveCN109040865BIncrease success rateImprove data throughputMultiplex system selection arrangementsTime-division multiplexBroadband transmissionOptical burst switching
Owner:XIAN INSTITUE OF SPACE RADIO TECH
FFT (fast Fourier transform) method based on point-by-point sequential step-by-step processing flow
ActiveCN105335333AImprove real-time performanceGet transformation results quicklyComplex mathematical operationsFast Fourier transformRadar signal processing
The invention provides an FFT (fast Fourier transform) method based on point-by-point sequential step-by-step processing flow. The FFT method comprises the following steps: utilizing linear properties of the FFT to realize point-by-point sequential step-by-step processing; splitting N-point FFT into the addition of N FFTs with simple sequences; utilizing table lookup to reduce transformation time of the FFTs with simple sequences; finally, improving transform efficiency of the whole sequence. The method can pre-process first-in data in advance under the condition that a to-be-transformed sequence is incomplete, and the FFT transform results can be output after the sequence is complete. According to the method, the integral processing time of FFT is fragmented, and time of a preparation process of data is sufficiently utilized to complete transform work, so that the FFT method is especially suitable for a radar signal processing system of a pipeline processing structure.
Owner:SHANGHAI RADIO EQUIP RES INST
Helicopter Target Recognition Method under Radar LPRF Working Condition
ActiveCN109633584BImprove recognition rateImprove accuracyWave based measurement systemsRadar systemsElectromagnetic environment
Owner:SHANGHAI RADIO EQUIP RES INST
Spent fuel dissolver critical safety analysis method considering fuel assembly burnup distribution
PendingCN113871047AIncrease throughputEngineering feasibilityNuclear energy generationReactor fuel elementsNeutron poisonAtomic physics
The invention relates to a spent fuel dissolver critical safety analysis method considering fuel assembly burnup distribution. According to the method, burnup distribution of each axial section of each fuel rod of a maximum reactivity assembly is determined, the mass proportion of fuel in each burnup interval is determined, and the fuel is arranged in a layered mode from inside to outside according to the reactivity of the fuel (the fissile nuclide content), so that the composition of the fuel in a spent fuel dissolver is closer to the real situation, and a certain critical safety analysis conservative margin exists, so that the treatment capacity of the spent fuel dissolver can be improved or the use of neutron poison materials can be reduced under the condition of ensuring safety. According to the method, refined critical safety analysis of the spent fuel dissolver is realized. The method is an advanced spent fuel dissolver critical safety analysis method with engineering feasibility.
Owner:CHINA NUCLEAR POWER ENG CO LTD
Differential distribution device of travel trailer braking force
The invention discloses a differential distribution device of travel trailer braking force. The differential distribution device of the travel trailer braking force can be divided into four parts, that is, an angle capturing part, a supporting arm, a slide rheostat part and a hydraulic distribution part. The angle capturing part can capture the horizontal rotation angle of a ball head and convertthe rotation angle into the movement of slide rheostat sliding sheets. The device is provided with two slide rheostats. The change of a resistance value of the rheostats directly causes the change ofthe stroke of a push-pull electromagnet in the hydraulic distribution part, so that the change of the position of a piston in a hydraulic cavity is caused. The hydraulic cavity communicates with brakes of a left wheel and a right wheel of the trailer. The movement of the piston changes the braking force generated by the brakes, and the braking force applied to the left wheel and the right wheel isdifferent, so that the differential distribution of the braking force of the trailer is achieved. Mechanical transmission and hydraulic braking methods are adopted, and the differential distributiondevice of the travel trailer braking force has stable work and high reliability and is convenient to install, disassemble and maintain.
Owner:JIANGSU UNIV
Distribution force optimization method for transforming cylindrical surface into parabolic groove surface
PendingCN113820856ASmall radial errorEliminate distributed controlDesign optimisation/simulationCondensersEngineeringRadial error
The invention relates to a distribution force optimization method for transforming a cylindrical surface into a parabolic groove surface. According to the method, the force enabling the arc to deform into the parabola is obtained, when n unknown forces are needed, in order to minimize the radial error of the simulation optimization result and the target ideal parabola, the parameter focal diameter ratio, namely the ratio of the paraboloid focus to the cylinder radius, is defined, the parabolic equation closest to the arc is determined, the parabola closest to the arc is taken as the target, the radial error is minimized through optimization analysis, and the corresponding distributed control force for eliminating the displacement error is obtained.
Owner:HARBIN INST OF TECH
Determination Method of Drag Acceleration Rate for Reentry Guidance of Lift Vehicle
InactiveCN104787361BImprove tracking control accuracySuppress fluctuationsSpacecraft guiding apparatusRe entryGuidance control
The invention discloses a method for determining the lift aircraft reentry guidance resistance accelerated speed change rate. The method includes the steps that a mapping relation between the flight speed and a preset attack angle command is determined according to a task requirement; according to a pneumatic parameter model, fitting is carried out to obtain a fitting relational expression between a pneumatic resistance parameter and an attack angle, and an estimation value of the pneumatic resistance parameter is obtained according to the fitting relational expression; according to the estimation value of the pneumatic resistance parameter and the mapping relation between the flight speed and the preset attack angle command, the pneumatic resistance coefficient change rate is obtained through calculation; the height change rate and the speed change rate are calculated according to a navigation parameter and an approximation formula; according to the height change rate, the speed change rate and the pneumatic resistance coefficient change rate, a resistance accelerated speed change rate is obtained through calculation. By means of the method, influences of sampling noise on the reentry guidance control accuracy can be effectively avoided, and the tracking control accuracy of the resistance accelerated speed is improved.
Owner:BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
A Method of Suppressing Radar Sidelobe Interception Using Radar Antenna and Difference Channel
ActiveCN104777468BReduce complexitySolve the interception problemWave based measurement systemsRadar antennasPhase correction
The invention relates to a method of using sum and difference channels of a radar antenna for restraining radar side lobe interception. According to the method, antenna patterns of the sum channel and the difference channel of the radar main antenna are optimized, self-correcting signals of a radar system are used for obtaining amplitude and phase errors with the sum channel as the datum, and the amplitude and phase errors are used for error correction of the sum channel and the difference channel; according to the target position in the sum channel, the corresponding position, in the difference channel, of a target is searched for, and amplitude and phase correction is carried out on the complex number value of the position, where the target is located, in the difference channel by means of the amplitude and phase errors of the sum channel; the complex number modulus value of the position, where the target is located, in the sum channel is compared with the corrected complex number modulus value of the target in the difference channel to judge whether target echoes enter from main lobes or side lobes of the main antenna. Therefore, the radar system using the method can directly use the main antenna for recognizing side lobe targets without depending on an auxiliary antenna, the design difficulty of the radar antenna is effectively lowered, the number of the channels of the antenna is effectively reduced, and the reliability of the antenna is improved.
Owner:SHANGHAI RADIO EQUIP RES INST
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