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

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 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 provides an aerodynamic characteristic value result correcting method, which belongs to the technical field of helicopter. According to the aerodynamic characteristic value result correcting method, through acquiring the aerodynamic characteristic wind tunnel test value and the CFD calculation value of the existing helicopter with a similar aerodynamic structure as a target helicopter, a correcting coefficient of the aerodynamic characteristic CFD calculation value is obtained, and through the correcting coefficient, the aerodynamic characteristic CFD calculation value of the target helicopter is obtained. Compared with a method of acquiring an aerodynamic characteristic value by the wind tunnel test, the aerodynamic characteristic value result correcting method provided in the invention can shorten the design time by 70% and reduce the cost, and an effective and feasible method is provided for rapid design and cost reduction of the helicopter.

The invention provides a satellite integrated controller, comprising: a computer module and an interface module; the computer module integrates the calculation and data processing unit of the lower computer of the attitude and orbit control computer, the star computer, and the power supply and distribution controller The corresponding computer functions are uniformly realized by the computer module; the interface module is used to provide the interface function required for the computer module to communicate with external devices; the external devices include: sun sensors, star sensors, magnetic One or more of strong gauges, gyroscopes, flywheels, magnetic torque devices and power supply and distribution controllers. The present invention carries out an integrated design on the existing satellite platform resources, simplifies the design of the satellite platform, and saves the resources of the satellite platform.

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 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 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.