87results about How to "Improve design reliability" patented technology

The invention discloses a magnetic field modulation hybrid excitation motor and a multi-working-wave design method thereof. The motor comprises a stator and a rotor, wherein the stator comprises a stator iron core, two sets of windings and permanent magnets, the two sets of windings comprise an armature winding and an exciting winding, the stator iron core is designed as an open slot, one set of windings is distributed in the open slot of the stator iron core, and is wound on one stator tooth in a centralized manner, the outer surface of each stator tooth is provided with a groove, the other set of windings is placed in the groove of the stator tooth, each stator tooth is split into two modulation teeth through the groove, one permanent magnet is placed on each modulation tooth, the otherwinding is wound on two adjacent modulation teeth formed by splitting different stator teeth in a centralized mode, and the magnetizing direction of the permanent magnets is consistent with or opposite to the direction of a magnetic field formed by the excitation winding on the modulation teeth. According to the invention, the permanent magnet magnetomotive force and the excitation magnetomotive force are connected in parallel on the magnetic circuit and are independent from each other, so that the risk of irreversible demagnetization caused by the introduction of an excitation current permanent magnet is avoided, and the effective exertion of the magnetic regulation capability is ensured.

The invention relates to a quick design method of an earth-moon L1 Lagrange point transfer orbit, and belongs to the technical field of spacecraft orbit design and optimization. The quick design method comprises the following steps: a detector applies a first-time maneuvering pulse to the ideal orbit entering point of a Halos orbit, and carries out reverse recursion on the first-time maneuvering pulse to a perilune position which meets leveraging constraints from the Halo orbit of the L1 Lagrange point; the detector applies a second-time maneuvering pulse to the perilune, and enters an earth-moon transfer orbit segment; and the detector applies a third-time maneuvering pulse and finally realizes earth parking orbit capture. Since the design method adopts an inverse integration strategy, a practical detector track departs from the earth, and finally, the Halo orbit of the earth-moon L1 Lagrange point can be achieved. The quick design method aims at different constraint sets, can automatically regulate the target orbit entering point of the Halos orbit, avoids the selection uncertainty of the orbit entering point, and has good reliability and practicality. In addition, speed increment required for finishing a task is small.

The invention discloses a star sensor software online fault monitoring system and a monitoring method thereof. The method comprises the following steps of: writing to-be-transmitted star sensor software key data into an FPGA module by a CPU module by utilizing an address mapping manner; after the FPGA module detects that the electric level state of a handshake signal sent by the CPU module changes, sending the star sensor software key data to ground reception equipment by the FPGA module; and analyzing and displaying star sensor software operation condition by the ground reception equipment in real time, and monitoring software faults online. According to the Star sensor software online fault monitoring system and monitoring method thereof, real-time online monitoring is carried out on star sensor software, the fault problems in the software operation process can be timely positioned, so that the visibility of the star sensor software faults is increased and the troubleshooting efficiency of the star sensor software faults is improved.

The invention provides a circuit board schematic diagram design method and device, electronic equipment and a storage medium. The method comprises the steps of receiving input design scheme data; according to the component library, calling a schematic diagram design model to analyze the design scheme data, and outputting a circuit board schematic diagram corresponding to the design scheme data; wherein the schematic diagram design model is obtained by training through a deep learning algorithm; the method comprises the following steps: automatically analyzing received design scheme data by utilizing a schematic diagram design model obtained by training a deep learning algorithm, and automatically obtaining a circuit board schematic diagram corresponding to the design scheme data input by auser according to related component design data obtained from a component library; the automatic design of the schematic diagram of the circuit board is realized, the design efficiency of the schematic diagram of the circuit board is improved, and the whole design process does not need manual participation, so that design errors caused by human factors are avoided, and the design reliability of the schematic diagram of the circuit board is improved.

The invention relates to heat engineering, power engineering and the field of electric heating of liquids, water for instance; it can be used in circulation water heating systems and hot water supply, and as a universal device for diverse electric heaters. An object of the invention are to enhance the ease of fabrication, fabricability, and operability for block electrodes and electrode heating boilers on the whole, to increase the reliability of device both in static and dynamic modes ones. The invention meets an object of extended performance capabilities, versatility and flexibility of the device, potential diversification and enhancement of adaptability in solving particular problems. Moreover, the invention allows improvement of convection in water heating boilers and reduction of uniformity of sludge and rust deposition on electrodes thus increasing the heater effective performance time. The invention object comprises an improvement of protection against breakdowns between the electrodes as well, phase current load imbalance reduction, electrode protection against non-uniform deformation during operation in dynamic conditions. It is also an object of the invention to extend i the range of constructional capacity control without design and dimensional changes. FIG. 2 provides a schematic of electrodes (1) arrangement on the basis (3) located on the inner case (2) side with electrodes (1) slightly deviating from the longitudinal symmetric axis of the case (2) and irregularly spaced on the basis, electrode longitudinal axes deviating from each other at small angles. (4)—outer electrode terminals (1).

The invention provides a cryogenic propellant thermodynamic exhaust system ground integration test device and method, the cryogenic propellant thermodynamic exhaust system ground integration test device comprises a storage tank (1), a vacuum container (2), an active thermodynamic exhaust system and a passive thermodynamic exhaust system, the storage tank (1) is located in the vacuum container (2)and is fixedly connected with the inner wall of the vacuum container (2); an interlayer between the storage tank (1) and the vacuum container (2) is vacuumized through a vacuum unit (21) to simulate the outer space environment. According to the ground integration test device and method, various exhaust schemes and combinations thereof can be tested, most test structural parts in each scheme are arranged outside the storage tank, maintenance is convenient, and the design reliability is improved; structural parts such as a jet mixing device arranged in the storage tank are simple in structure and high in stability.

The invention provides a differentiated simulation design method. According to the method, an electric performance result obtained by performing signal simulation on a wiring rule provided by a chip manufacturer is taken as a reference standard; and when the simulation result of a differentiated wiring design of a user product is better than the simulation result of the wiring rule of the chip manufacturer, the risk degree of the design is low, namely the differentiated wiring design is suitable for a product patternmaking test. The method comprises the following specific steps of: simulating the wiring rule provided by the chip manufacturer; taking the simulation result as a standard for judging whether the differentiated design is reliable; performing a large amount of analogue simulation on differentiated products to make a wiring rule which has a better simulation result than the wiring rule provided by the chip manufacturer; and performing a subsequent design according to the wiring rule. By adopting the differentiated simulation design method, the design reliability of the products is improved greatly, and the differentiated design of the products is realized.

The invention discloses an environmental stress screening time optimizing method and environmental stress screening time optimizing equipment for an electronic product, and belongs to the field of reliability tests of electronic products. Environmental stress screening is an important means for eliminating early failures of a product, and is achieved by applying an appropriate environmental stressto the product before leaving a factory and eliminating potential defects so as to guarantee using reliability of the product. Implementation of the environmental stress screening can reduce the maintenance cost after the product is put into use while the production cost is increased. During the environmental stress screening, component-level and assembly-level screening cost is fully considered,and especially calculation of time and expense cost is introduced, so that the screening time cost is fully considered during the environmental stress screening, and while the design reliability is improved, the screening time is shortened and the production cost is reduced so as to improve the economic efficiency and the production efficiency of an enterprise.

The invention relates to a battery signal acquisition module and a battery protection system using the battery signal acquisition module. The battery signal acquisition module comprises a plurality ofacquisition lines and a acquisition circuit, wherein the acquisition lines are connected with an external battery assembly; the acquisition circuit is connected with the plurality of acquisition line; the acquisition circuit obtains monitoring data of voltage, current or temperature of the battery assembly through the plurality of acquisition lines; the plurality of acquisition lines and the acquisition circuit are arranged on a first flexible circuit board.

The invention relates to a method for each Ethernet data processing module of a verifying base station and equipment thereof. When network data flow is stable, and a sudden peak value of the network data flow happens, the Ethernet data processing module is respectively simulated into a uniform distribution model and a normal distribution model. One Ethernet data processing module is verified whether the module can achieve seamless butt joint with other Ethernet data processing modules by simulated working environment in design stage, thereby remarkably improving design reliability of the Ethernet data processing modules, and simultaneously improving design efficiency of the Ethernet data processing modules.

The invention discloses a ferrite switch driver with a self-feedback latch switch-off function. The ferrite switch driver comprises a logic conversion circuit, a driver amplifying circuit, an H-bridgepower driving circuit and a comparator feedback circuit. The logic conversion circuit receives a superior control signal and a feedback signal of the comparator feedback circuit, processes the signals, inputs the signals to the driver amplification circuit for amplification, and then inputs the signals to the H-bridge power drive circuit to drive the ferrite coil. Meanwhile, the comparator feedback circuit samples the current of the ferrite coil, and when the current reaches a preset value, the comparator feedback circuit sends a positive pulse to the logic conversion circuit to turn off theH-bridge power driving circuit. Under the condition that a microcontroller or an FPGA or a CPLD is not used, the ferrite coil can be effectively driven to the preset current, and automatic feedback and latch turn-off can be achieved. Compared with a ferrite switch driver using a microcontroller or an FPGA or a CPLD, the ferrite switch driver has the advantages of being simple in structure, lower in cost, higher in speed and higher in reliability.

The invention discloses a storage battery and voltage stabilizing source switching power supply circuit applied to a cubesat. The circuit comprises a storage battery power supply circuit and a voltagestabilizing source power supply circuit; the front end of the storage battery power supply circuit is connected with a storage battery module on a satellite; the front end of the voltage stabilizingsource power supply circuit is connected with a voltage stabilizing source device outside the satellite; and the rear ends of the storage battery power supply circuit and the voltage stabilizing source power supply circuit are connected with a bus of an on-satellite power supply system. After the voltage stabilizing source power supply circuit is connected with the voltage stabilizing source device outside the satellite, the voltage stabilizing source power supply circuit connects a voltage stabilizing source with the bus, the storage battery power supply circuit disconnects a storage batteryfrom the bus, the voltage stabilizing source provides power consumption during debugging of the whole satellite, and electric energy in the storage battery is not used. When the voltage stabilizing source power supply circuit is not connected with the voltage stabilizing source device, the storage battery power supply circuit connects the storage battery with the bus, and the storage battery provides power consumption for the whole satellite during working. The power supply can be automatically switched, the use is convenient, the thought is novel, and the problem of insufficient power storageof the storage battery during long-time debugging of the cubesat is solved.

The invention discloses a method and a device for transferring and testing an interlayer board card. The interlayer board card switching method comprises the steps of welding a board card connector connected to an interlayer board card to one side of a switching circuit board; Welding a PCIE slot connected to the consistency test fixture to the other side of the switching circuit board; Arrangingwiring on the switching circuit board to enable the board card connector to be connected with the PCIE slot; And testing the consistency of the interlayer board cards by using a consistency testing jig. According to the technical scheme provided by the invention, switching and testing can be performed for different interlayer board cards or different types of interlayer board cards, so that the consistency of the interlayer board cards can be evaluated, and the design reliability of the interlayer board cards can be improved according to test feedback.

The invention discloses a space closed type flexible precise adjusting device and an assembling method thereof. The device comprises a rhombic elastic structure (1), a spiral assembly 1 (2), a spiralassembly 2 (3), a translation screw rod (4), a limiting stud (5), a motor assembly (6), an angular displacement sensor (7), an anti-torque support (8) and a linear displacement sensor assembly (9). According to the closed type flexible precise adjusting device, through the transmission design of a differential screw, submicron-level high precision and high self-locking performance are achieved, and meanwhile displacement transmission is conducted through the rhombus elastic structure (1); and the torsion resistance of the device is greatly improved through the anti-torque support (8). The assembling method plays an important role in guaranteeing the performance of the device and mainly comprises the steps of firstly completing assembling of the main spiral assembly, the standby spiral assembly and a translation screw rod, then installing the structure with the rhombic elastic support as the reference, installing the linear displacement sensor assembly, then installing the main motor assembly and the standby motor assembly, and finally installing the anti-torque supporting structure.

The driving torque design method of the large overload spacecraft driving mechanism of the present invention considers the large deformation reaction of the flexible load battery wing, and solves it in real time through rigid-flexible coupling dynamics reverse, based on the generalized modal mass matrix full coupling algorithm in rigid-flexible coupling dynamics, determined in The torque design envelope of the driving mechanism under each working condition of the rail is selected, and the motor and harmonic reducer are selected through the recursive relationship of the transmission chain. The driving torque design method of the large overload spacecraft driving mechanism of the invention improves the design accuracy and work efficiency of the driving mechanism torque, and the driving mechanism design provides technical conditions with high reliability.

The invention discloses a deflected and folded inflatable block point connection space capsule shell structure which is cylindrical and is composed of an inner thin film, an outer thin film and protective layers. The protective layers are connected between the inner film and the outer film in a blocking mode, and all the protective layer blocks are integrally and evenly arranged on the periphery of the space capsule. The protective layer blocks forming the protective layers are cuboids, different protective layer blocks are closely arranged at intervals, each cuboid is provided with an upper inner edge and a lower outer edge, each edge is provided with two corner points, and the protective layer blocks are connected with the inner film at the corner points of the upper inner edges of the protective layer blocks. One corner point of the outer edge of the lower part of a body diagonal line of the corner point, connected with the inner thin film, of the protective layer block is connected with the outer thin film, and deflection unfolding of the space capsule is carried out by taking the connected corner point as the center. According to the invention, overall thickness folding can be fully considered, micro meteorite impact from the space can be resisted more effectively, lethal cosmic rays from the sun in the space can be isolated, and therefore the safety of the space capsule is guaranteed, and meanwhile a larger internal space can be expanded under the same compression state volume.

The invention discloses a backlight module and a display device, and belongs to the technical field of display and comprises a casing, a plurality of light sources and a light guide plate, the backlight module is a side-entry backlight module, the casing at least comprises a back plate and a side plate which are integrally formed, a flexible circuit board extending along a first direction is fixedly arranged on the surface of one side, close to the light guide plate, of the back plate, and the light sources are positioned on one side, away from the back plate; the backlight module further comprises a diffusion sheet and a brightening sheet. The brightening sheet and the light guide plate are at least partially overlapped along the direction vertical to the light emitting surface of the backlight module; a shading strip is attached to the surface of the side, close to the light guide plate, of the diffusion sheet. The display device comprises a liquid crystal display panel and the backlight module which are oppositely arranged. The manufacturing process is simple, the narrow frame of the backlight module can be achieved without changing the original manufacturing process of the backlight module, meanwhile, the firefly phenomenon can be avoided, and the display quality of the backlight module can be improved.