66results about How to "Accelerate the development progress" patented technology

The invention discloses a billboard management system and a billboard management method, wherein the system comprises: a basic configuration module, which establishes a data interface with the system, performs debug on process faults, inputs models, fascicules, working procedures, process steps, assorted tables and key working procedures, and maintains correlative information of a structure tree; a material warehouse module, which manages material assorted information, performs material distribution, warehousing and ex-warehouse management, and finishes allocation management of the materials between models; a process management billboard module, which is used for achieving temporary process documentation and process modification, solving on-site technical problems and compiling process rated details; a production plan management module, which is used for finishing production flow design and production route design, and establishing and adjusting or distributing a production arrangement plan; a workshop operation plan billboard module, which generates an intraday task list according to a scheduled production plan and distributes the task list to each working position billboard for instructing the intraday work; a execution billboard module, which finishes plan decomposition and appoints the starting time and ending time of the plan for each working procedure task, inspects the completed working procedures in the system at the first time when the working procedures are completed, and fills in inspection records and prints assembling process cards; and an on-site inspection module, which fills in quality control cards of the key working procedures and manages a single closed loop for soling the technical problems. The billboard management system and the billboard management method optimize the general assembly working mode and the production flow and solve various links unadaptable to a batch production mode in the process of the general assembly currently.

The invention discloses a fault simulation method and system for a flight control system, and belongs to the field of flight control systems. The system mainly comprises a flight control system testing control platform, a simulation management system, and a bus signal simulation system. The flight control system testing control platform collects the output of the flight control system, and correspondingly transmits the output to the simulation management system. The simulation management system carries out dynamics mathematic model solving and transmits the solving results to the bus signal simulation system. The bus signal simulation system converts the solving results into various types of bus simulation signals, needed by the flight control system, through a bus signal conversion device, and transmits the signals to the flight control system. The flight control system makes the corresponding posture response according to various collected bus simulation signals. During fault simulation testing, the flight control system testing control platform sets various faults of the flight control system in real time through corresponding fault setting means, thereby achieving the testing of the response capability of the flight control system to various faults.

The invention discloses a processing method for annular type engine-case radial narrow groove, and belongs to the field of machinery manufacture. In consideration of the integral rigidity of a part, the method employs a layered progressive helix-track one-time milling mode for realizing small cutting depth and high feeding, fully gives play to the cutting performance of a cutter, improves the processing efficiency, guarantees the processing dimension, and successively solves the problems that numerical-control milling processing of the annular type engine-case radial narrow groove is low in efficiency and not high in quality. Also the method is applicable to processing of narrow grooves with any shapes. Along with application of the technology to annular type engine-case parts, the processing method determined by the technology possesses guidance meaning, and provides good establishment for accelerating research progress of novel aviation engines and reducing research cost. From another point of view, the method creates relatively large value for improving efficiency, reducing cost and improving quality of aviation engines in the future and being applied to large-batch production.

The invention relates to a semi-physical real-time simulation system for a hydraulic undercarriage of an airplane, which includes a human-computer interface device and a semi-physical simulation device, wherein the human-computer interface device includes a digital simulation system, a comprehensive management system, a signal simulation system and an instrument display system; the semi-physical simulation device includes a simulation target machine; the digital simulation system is used for building a model for a hydraulic undercarriage of an airplane, performs digital simulation and generates an object code; the comprehensive management system is used for downloading the object code into the simulation target machine for real-time semi-physical simulation, and manages the entire semi-physical simulation process in a unified manner; during the simulation, the signal simulation system is used for providing simulated avionic signals; the instrument display system is used for displaying related data and status information of the hydraulic undercarriage of the airplane. According to the system, the human-computer interface device is combined with the semi-physical simulation device to form a semi-physical real-time simulation system, the efficiency for developing the hydraulic undercarriage of the airplane can be improved, the developing process can be quickened, and the research and development quality can be guaranteed.

The invention discloses a method for optimizing an SAR antenna directional diagram test. The method includes the steps of establishing an active phased array antenna directional diagram calculating mathematics model according to the electromagnetic field theory, obtaining and calculating basic data of an active phased array antenna, calculating and storing all wave position antenna amplitude phase weight coefficients of the SAR antenna according to the design requirement and engineering realizability, and using a near-field test method to obtain antenna sub-array directional diagrams at different positions of an antenna array plane under a planar near-field test system environment. The test time of an SAR antenna directional diagram test is greatly shortened, the satellite development progress is ensured and accelerated and a reference is provided for test SAR antenna directional diagram of subsequent radar satellite models.

The invention discloses an integrated tile active phased-array antenna. The antenna comprises an array antenna layer, a heat dissipation cavity, a radio frequency layer, a transition layer, a power supply and control layer and a cover plate layer. A plurality of first slots are formed in one side, close to the transition layer, of the radio frequency layer, first radio frequency chips are arrangedin the first slots, a plurality of second slots are formed in one side, close to the transition layer, of the power supply and control layer, and second radio frequency chips are arranged therein; acontrol device is arranged on one side, close to the cover plate layer, of the power supply and control layer and used for power supply and signal control; the transition layer plays a role in radio frequency signal transition and radio frequency isolation; the array antenna layer is electrically connected with the radio frequency layer at high frequency through a first radio frequency connectionstructure arranged on the heat dissipation cavity; the radio frequency layer is electrically connected with the power supply and the control layer at high frequency through a second radio frequency connection structure arranged on the transition layer; the cover plate layer is electrically connected with the power supply and control layer. According to the antenna, the multi-channel, multi-polarization or multi-frequency multifunctional high-integration integrated design is achieved, the overall size is small, the weight is light, and the thickness is small.

The invention provides a manufacturing method for a large-scale thin-wall skin with inner ribs and complex mold cavities. The manufacturing method comprises the steps that 1, simulation flattening is conducted on the skin according to a skin parameter, a parameter of the flattened skin is collected, a rough machining programming and a finish machining programming are conducted, and a minimum workblank is calculated; 2, the minimum workblank is selected to be machined roughly in order to release residual stress inside the workblank in advance; 3, a roughly machined skin plate is adsorbed and fixed through a vacuum tire, finish machining is conducted on the skin plate, and the rib strips and the weight reducing cavities inside the skin are machined out through numerical control milling machining; 4, a plurality of base plates which can fill and level up each weight reducing cavity are prepared, it is ensured that the skin machined through the step 3 again becomes a slab with the flat surface after each base plate is cushioned, and then the skin is machined to be formed through a matched mould thermal forming method, and 5, annealing and stress-relieving are conducted. According to the manufacturing method for the large-scale thin-wall skin with the inner ribs and the complex mold cavities, the deformation of the thin-wall skin in the machining process is effectively controlled, and the molded surface precision of the skin is greatly improved.

The invention relates to a transport aircraft inlet splash testing method for transport aircraft splash testing. According to the method, before a splash test, configuration of a test aircraft for test flight, various running statues of an engine and test aircraft glide speed point required by testing are determined according to the type of the test aircraft; materials and position of a test pool in a runway, coloring position of an aircraft body and selection of coloring materials, a video-recording method, test aircraft glide modes meeting the testing requirements and the like are determined; tests are performed one by one according to the test aircraft glide speed required by testing. The method has the advantages that splash testing is performed according to the airworthiness regulation for test aircraft, by studying, the configuration state of the test aircraft during splash testing, a building method of the test pool, coloring of the test aircraft for judging test results, a test video-recording technique, acquisition of test key data, final identification modes of data and the like are determined, and a standard set of methods and programs for transport aircraft splash testing is formed.

The invention discloses a method for constructing a testing environment of a satellite control system. The method comprises the following steps of classifying component parts of a satellite control system to be tested, establishing a standardized model of each part and performing modular packaging; classifying input and output ports in each standardized model according to respective signal type, and counting various signals of a single part model; performing number maximized configuration on hardware interfaces of test equipment according to types and numbers of parts possibly used by different satellite control systems; and fixedly connecting hardware interface signals of the test equipment and modular models, and fixedly connecting part models and a dynamical model to form a closed loop. By the method, the current situation of constructing the testing environment of the satellite control system by 'customizing for each satellite' is changed, the development speed is improved, the efficiency of constructing the testing environment is improved by modularizing and standardizing the interfaces, the method is convenient to use, and manpower, material resources and time cost are saved.

The invention provides a full-digital simulation system based on satellite information flow. The system comprises an information flow simulation system, an integrated development environment, a clocksynchronization device and a real-time network communication device. The information flow simulation system comprises a chip-level simulation unit, a circuit-level simulation unit and a computer-likesimulation unit. The chip-level simulation unit directly runs the target code and performs instruction analysis, or a register interface and state rotation exist. The circuit-level simulation unit removes a register interface and takes an electric signal as main input and output. The computer-like simulation unit performs behavior-level simulation to replace the running target code. The information flow simulation system, the integrated development environment, the clock synchronization device and the real-time network communication device form a platform-level simulation unit, and the data flow of the platform-level simulation unit is consistent with the data flow of a real satellite.

The invention discloses a laser guidance missile changing laser energy simulation method for unmanned aerial vehicles and system. The method comprises: (1) calculating laser energy at different distances by using a laser guidance head detector according to an aerial hanging flight test or a ground running test or a target flight test of a laser guidance missile laser guidance head of the unmannedaerial vehicle to draw a laser energy-distance curve; (2) determining the laser energy value received by the laser guidance head detector at the current moment according to the target relative position relation resolved in real time in a simulation process in combination with the laser energy-distance curve; and (3) sending a laser to the laser guidance head detector in a laser direct mode at thesimulation process, so that the laser energy value received by the laser guidance head detector at the current moment is consistent with the laser energy value determined at the corresponding moment in (2). According to the laser guidance missile changing laser energy simulation method for the unmanned aerial vehicles and the system, the flight process of the missile in the air is simulated more completely, thereby improving the efficiency and the accuracy of a semi-physical simulation system.

The invention discloses a self-test platform for testing a serial RapidIO network switching module, and the platform comprises bottom plate hardware and test software, and the bottom plate hardware comprises a plurality of port pins, two FPGA chips, and two debugging serial ports. The port pins are used for leading each outer outgoing port of the switching module to a bottom plate, and a self-loopback relation is formed between any two port pins by adopting an external self-loopback mode; the debugging serial port is used for outputting a test request to the FPGA chip; one SRIO interface is led out of the two FPGA chips to be connected with any port pin in an external jumper mode according to test requirements, and the same test software resides in the two FPGAs; and the test software comprises a switch driver, a RapidIO controller and a function test unit and is used for completing various test items. Under the condition of not depending on a system testing environment, the platform is suitable for testing functions and performances of various customized serial RapidIO network switching modules.

The invention relates to the technology of analyzing vibrating characteristics of airplanes and in particular relates to a ground sliding vibrating characteristic analyzing method of a large airplane.The method comprises the following steps: determining an arranging position of a sensor according to a modal analyzing result of a large airplane dynamic model; recognizing modal parameters of the large airplane through a GVT test; acquiring data of a ground sliding vibrating sensor and flying parameters of the large airplane through a ground sliding test and carrying out spectral analysis on thedata of the vibrating sensor to acquire a maximum attribution frequency, and determining a maximum frequency type and a generated cause by comprising the maximum attribution frequency with the modalparameters acquired by the GVT test; and determining a vibrating source by combining the flying parameters and improving a related structure according to a analyzing result. By systematically analyzing the ground sliding vibrating characteristics of the large airplane, the cause of vibration can be acquired quickly, thereby providing a ground for researching vibration generated in the sliding process of the airplane effectively, and accelerating the researching progress of the large airplane.

The invention discloses a method for optimizing an SAR antenna directional diagram test. The method includes the steps of establishing an active phased array antenna directional diagram calculating mathematics model according to the electromagnetic field theory, obtaining and calculating basic data of an active phased array antenna, calculating and storing all wave position antenna amplitude phase weight coefficients of the SAR antenna according to the design requirement and engineering realizability, and using a near-field test method to obtain antenna sub-array directional diagrams at different positions of an antenna array plane under a planar near-field test system environment. The test time of an SAR antenna directional diagram test is greatly shortened, the satellite development progress is ensured and accelerated and a reference is provided for test SAR antenna directional diagram of subsequent radar satellite models.

The invention provides a satellite integrated controller. The controller comprises a computer module and an interface module; the computer module integrates an attitude and orbit control computer, a house-keeping computer and a calculation and data processing unit of a lower computer of a power supply controller, and corresponding computer functions are achieved through the computer module uniformly; the interface module is used for providing the interface function needed by communications of the computer module and external devices; the external device comprises one or more of a sun sensor, astar sensor, a magnetometer, a gyroscope, a flywheel, a magnetorquer and the power supply controller. Accordingly, integration design is conducted on an existing satellite platform resource, design of a satellite platform is simplified, and the satellite platform resource is saved.

The invention provides a structure / damping integrated design method suitable for a novel spacecraft. The method comprises the following steps: (1) establishing a simulation model; (2) determining a response peak value when the spacecraft structure needs to reduce vibration; (3) determining principal oscillation corresponding to the response peak value when the spacecraft structure needs to reduce vibration; (4) determining optimal laying position of a spacecraft damping; (5) determining a damping material, damping thickness, and structural parameters of a restraint layer, to complete integrated design of structure / damping. The spacecraft structure / damping integrated design method is simple and feasible, and prevents development cost for repeated design and repeated tests, and can effectively develop damping buffer effect of an aircraft.

The invention discloses a spiral bevel gear size silvering method, belonging to the electroplating field. The method comprises the following steps of: (1) oil removing, (2) weak corrosion, (3) copper preplating, (4) silver preplating and (5) silvering, wherein, in the silvering step (5), the constituents of a silvering bath liquid comprise 30-40g / l of AgCl, 110-125g / l of total KCN, 70-85g / l of free KCN and not more than 50g / l of K2CO3, the temperature of the bath liquid is 15-25 DEG C, bidirectional pulse current is used, and the pulse power supply parameters are shown as follows: the frequency of the forward pulse is 1000Hz, the duty cycle of the forward pulse is 20% and the current density of the forward pulse is 0.8A / dm<2>; and the frequency of the negative pulse is 1000Hz, the duty cycle of the negative pulse is 10% and the current density of the negative pulse is 0.2A / dm<2>. The growth speed of the obtained silver layer is 1 micrometer / 3 minutes, and the thickness of the silvering layer is controlled to be in a range of 5-6 micrometers. With the method, the crystal of the silvering layer is fine and uniform, and the thickness of the silvering layer can be accurately controlled to be in the range of 5-6 micrometers.

The invention provides a device for molding a ceramic core of a directionally solidified blade. The device comprises an upper formwork (1), an upper mold (2), a lower mold (3), an upper mold loose piece (4), an upper mold pressing block (5), a lower mold loose piece (6), a lower mold insert (7), a lower mold front loose piece (8), a lower mold rear loose piece (9), a linking plate (10), a front edge loose piece (11), a wax injection plate (12), a stepped bolt (13), a handle (14) and a positioning pin (15), wherein the lower mold (3) comprises a front face a and a bottom face b; a core injection opening is formed in a part A on the left side of the front face a, and a positioning hole and a screw hole are respectively formed in the left end face of the front face a; the wax injection plate (12) is fixed on the lower mold (3) by virtue of the cylindrical pin (15) and the stepped bolt (13). The device has the advantages of high processing accuracy, compact assembly, small space, light weight and convenience in operation.

The invention discloses a novel airtight tile type phased array antenna. The radio frequency chips are arranged in the slots of the dielectric cavity layer one by one, the slots are sealed by the cover plate layer, the dielectric cavity layer is connected with the array antenna layer on the back surfaces of the slots, and the radio frequency chips are connected with the array antenna layer. A ball mounting layer is arranged on the dielectric cavity layer and around the slots, and the ball mounting layer is connected with each radio frequency chip through a radio frequency link and a low frequency link. A micro-channel is designed in the medium cavity layer, and heat generated by the radio frequency chip is conducted to the ball mounting layer through the micro-channel. Compared with an existing tile-type or brick-type phased array antenna, the phased array antenna is smaller in size, lighter in weight and thinner in thickness, can be directly produced and assembled through an SMT automatic labeling process, and is high in production efficiency. According to the invention, the use of connectors is reduced, and the high airtightness requirement can be realized.

The invention provides a coating friction and wear performance test method equivalent to an engine rack test run examination. The method comprises the following steps of (1) using a coating moving ring and a static ring to carry out pairing, carrying out a friction and wear test by using a start-stop examination test method under a high PV value work condition; and (2) repeating a start-stop examination test for several times to investigate friction and wear performance of a coating, and providing effective prediction for an engine rack test run examination effect. The method is equivalent to an engine short-range rack test run examination under a high PV value and rigorous wear work condiiton.

The invention discloses a generalized commercial satellite housekeeping simulation system and method. The invention relates to the technical field of aerospace satellite simulation. In order to solvethe problems that an existing commercial satellite housekeeping simulation system is low in universalization in the software simulation process, the problems that the hardware state cannot be truly reflected, and the in-orbit real operation state of a satellite cannot be fully simulated exist, the invention provides a universal commercial satellite housekeeping simulation system and simulation method. The universal commercial satellite housekeeping simulation system comprises a housekeeping simulation computer, a cable switching device, a signal expansion device, a single-machine simulation computer, a programmable power supply, a database server, a debugging computer, a main control computer, a data analysis computer and a network switch, the development progress of satellite housekeepingand attitude and orbit control software is accelerated; the system is high in universality and suitable for development of remote sensing satellites and communication satellites of different models,and the product cost of project verification parts is saved; simulation of components on a satellite is integrated, and meanwhile, a ground test system is integrated, so that working debugging and useare facilitated, and the working efficiency is improved.

The invention belongs to the field of solid rocket engine combustion chamber pressure intensity calculation, and relates to a method for calculating double-combustion-chamber solid rocket engine smallcombustion chamber pressure intensity. The method comprises the steps that firstly, collecting the pressure of a large combustion chamber; initializing small combustion chamber pressure data Ps0; determining that the small combustion chamber is in an inflated or deflated state by comparing the pressure Pb of the large combustion chamber with the pressure Ps of the small combustion chamber; calculating the gas variation of the small combustion chamber according to a flow formula, and finally determining the pressure of the small combustion chamber; and repeating the calculation process until the pressure intensity data of the large combustion chamber is completely read. The influence of a throttling hole and the gunpowder performance on the pressure intensity in the small combustion chamber can be comprehensively considered, parameter adjustment by designers is facilitated, and the product development progress is accelerated.

The invention discloses a convenient PXIe module debugging tool comprising a tool board card. One end of the tool board card is provided with first sockets capable of being docked with a PXIe case backboard socket. The other end of the tool board card is provided with second sockets capable of being docked with a PXIe module. The first sockets and the second sockets are connected in a one-to-one correspondence way so as to lead out all the signals of the case backboard. The beneficial effects of the convenient PXIe module debugging tool are that all the signals of the case backboard are led out through the tool board card without difference, the attenuation of the signals is controlled through the integrated circuit, the line width and the line length of the high-speed difference signals between the case backboard and the PXIe module are matched by the switch, the service life is prolonged by using the steel protection structure design, then the debugged PXIe module is inserted in thetool socket to be debugged and the signal of each position of the PXIe module can be clearly, rapidly, conveniently and accurately tested through the test instrument so that the module debugging timecan be shortened, the debugging efficiency can be enhanced and the development progress can be accelerated.

The invention discloses a sub-surface detection radar sub-satellite point pulse precise positioning method. The method includes the following steps that: a real-time acquisition module performs real-time acquisition and processing on satellite information inputted by a satellite platform; an along-orbit resolution processing module performs along-orbit resolution processing on the satellite information so as to obtain current along-orbit resolution; and pulse scene processing is performed through a pulse space-time unification module, a coordinate transformation module, and a pulse scene processing module. With the sub-surface detection radar sub-satellite point pulse precise positioning method of the invention, the pulse scenes of a sub-surface detection radar can be accurately positioned; the size of an imaging scene can be accurately controlled; accurate results are provided for signal processing and windowing size control; the amount of data processing for the signal processing canbe reduced; development progress can be accelerated; verification costs can be reduced; subsequent changes can be reduced; and product safety and reliability are improved.

The invention relates to a testing system for electronic delayers. The testing system comprises an AC / DC module, a DC / DC module, a computing control module, an address test module, a communication module, a plurality of time power supply modules and a plurality of A / D modules, wherein each to-be-tested electronic delayer is connected with an A / D module and a time power supply module respectively through testing cables; the input end of the AC / AD module is connected with an alternating current power supply; the output end of the AC / AD module is connected with the input end of the DC / DC module through a power line; the output end of the DC / DC module is connected with the computing control module through a power line; the computing control module is connected with the address test module, the communication module, each time power supply module and each A / D module through data lines; the communication module is connected to an industrial control computer through a data line and a communication interface; and the address test module is connected to one reference electronic delayer through a data line. The testing system can automatically finish testing the electronic delayers, the testing of the electronic delayers is more accurate, rapid, reliable and convenient, and the quality of the delayers is guaranteed.

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.