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30results about How to "Avoid technical risks" patented technology

Novel heat-resisting titanium alloy and processing and manufacturing method and application thereof

ActiveCN104018027AAvoid uniformityAvoid forging crackingHeat stabilityTitanium
The invention belongs to the field of titanium-based alloys, and particularly relates to a novel heat-resisting titanium alloy and a processing and manufacturing method and application thereof. The processing and manufacturing method comprises the composition elements of alloy components, smelting, heat processing, heat treatment and the like, wherein the alloy components are as follows (in percentage by weight): 5.4%-6.3% of Al, 3.0%-5.0% of Sn, 2.5%-6.4% of Zr, 0.0%-0.96% of Mo, 0.25%-0.5% of Si, 0.2%-0.5% of Nb, 0.3%-3.4% of Ta, 0.2%-1.6% of W, 0.0%-0.07% of C, less than or equal to 0.17% of O, less than or equal to 0.03% of Fe and the balance of Ti and inevitable impurity elements. The novel heat-resisting titanium alloy disclosed by the invention can obtain different matching of tensile strength, plasticity, permanence, creep strength and heat stability through the combination of different heat processing process and heat treatment processes, can be used for manufacturing parts, namely blades, coil assemblies and the like which are positioned on the high-temperature parts of an advanced aircraft engine, is used for a long time within a range of 600-650 DEG C, can also be used for manufacturing high temperature-resistant structural members, namely aerospace craft skin and the like, is used for a short time at about 700 DEG C and can be used as a material and the like used for high temperature-resistant corrosion-resistant valves of an automobile and a boiler.
Owner:INST OF METAL RESEARCH - CHINESE ACAD OF SCI

System and method for expanding model driving development capability by applying plug-in

ActiveCN102033743ASolve the problem of insufficient description abilityExpandable and flexibleSpecific program execution arrangementsModel descriptionStationary model
The invention relates to a system and method for expanding the model driving development capability by applying a plug-in. In the system and the method, a'model and plug-in' combined mode is provided to describe and establish a software system, firstly a model designing tool is used for establishing basic model description of the software system and then establishing a plurality of reusable plug-pin model for further describing a basic model object, the plug-in model can be expanded randomly on various basic model objects, and the plug-in can complete a software function with any complexity, therefore, the expansion of the model driving development capability is realized. By utilizing the invention, the technical problems of the existing model driving development method that because a fixed model is adopted, the describing capability of complex service system is poor, and the software system with the model driving development can not be established, expanded and maintained visually and dynamically under the operating state and the like are solved. The system developed by using the method has the advantages that the development complexity degree is low, the development speed is fast, the reusable degree of technology is high, the expansion is flexible, the maintenance is convenient and the reliability is high.
Owner:广州翼风信息科技股份有限公司

Automatic controllable general test launch and control system

The invention discloses an automatic controllable general test lunch and control system. The system comprises a remote control console, a test lunch and control host, a zero-second forwarding box andan AC / DC power supply case; the remote control console and the test lunch and control host are connected through a cable, and are in network communication through a fiber optical transceiver or a network switch; the test lunch and control host comprises a computer board, an I / O board, an AD acquisition board, a communication board and an interface backplane; the computer board, the I / O board, theAD acquisition board and the communication board are plugged in the interface backplane through printed board connectors; the computer board comprises a DSP, a clock circuit and a memory, wherein theclock circuit and the memory are connected with the DSP; the DSP is used for sending an on-off output signal to the I / O board, receiving on-off input data fed back by the I / O board and analog quantitydata fed back by the AD acquisition board and performing parsing to realize output control and condition monitoring of an aircraft. Through modular function board cards and standardized interfaces and buses between the board cards, the integration and generality of the system are improved, and the maintenance cost is saved.
Owner:HUBEI SANJIANG AEROSPACE HONGFENG CONTROL

Preparation method of high-temperature titanium alloy bar

The invention belongs to the field of titanium-base alloys and particularly relates to a preparation method of a high-temperature titanium alloy bar. The preparation method comprises the following steps: heating a prepared Ti60 titanium alloy cast ingot to 1150-1200 DEG C, and carrying out blank-opening forging in a beta phase region by virtue of a rapid forging machine or a hydraulic press; heating to 1080-1150 DEG C, carrying out repeated upsetting and swaging forging by virtue of the rapid forging machine or the hydraulic press, heating the forged blank to Tbeta-120 DEG C to Tbeta-30 DEG C(Tbeta is a Ti60 titanium alloy alpha+beta/beta phase inversion temperature), and carrying out repeated upsetting and swaging forging by virtue of the rapid forging machine or the hydraulic press until the blank is in a required size, so as to obtain the titanium alloy bar, wherein the macrostructure of the titanium alloy bar is a fuzzy crystal, and the microstructure of the titanium alloy bar isuniform. After the prepared Ti60 titanium alloy bar is subjected to solid dissolving and ageing thermal treatment, the matching degree of the obdurability of the bar is relatively good, and the matching degrees of the durability, creeping strength and thermal stability are relatively good. The preparation method is convenient in operation and relatively strong in process controllability, and the batch stability of the prepared Ti60 titanium alloy bars is good.
Owner:INST OF METAL RESEARCH - CHINESE ACAD OF SCI +2

Method for rapidly achieving solidification falling welding of satellite-borne software program at low risk

A method for rapidly achieving solidification falling welding of a satellite-borne software program at a low risk comprises the steps of respectively independently designing printed boards for an electrically-erasable programmable read-only memory (EEPROM), a programmable read-only memory (PROM), an application memory and other peripheral devices, and inserting an EEPROM memory board in a main circuit board through a pluggable interconnection plug-in at a program debugging stage; when the program debugging is finished and the program needs to undergo solidification falling welding, enabling finally solidified software to be burned in the PROM, enabling the well burned PROM to be welded to a PROM memory board, pulling out the EEPROM memory board on the main circuit board, enabling the PROM memory board to be plugged in the main circuit board through a pluggable interconnection plug-in, and finally enabling the main circuit board with the program having undergone solidification falling welding to enter the space to be used. According to the method, the development cost is reduced, system dismantling and installing operation during software program solidification is omitted, the technical risk and hidden danger are avoided, system reliability is improved, program solidification time is shorted, the development cycle is shorted, the program solidification risk is reduced, and system reliability and availability are improved.
Owner:SHANGHAI RADIO EQUIP RES INST

A kind of preparation method of high temperature titanium alloy bar

The invention belongs to the field of titanium-base alloys and particularly relates to a preparation method of a high-temperature titanium alloy bar. The preparation method comprises the following steps: heating a prepared Ti60 titanium alloy cast ingot to 1150-1200 DEG C, and carrying out blank-opening forging in a beta phase region by virtue of a rapid forging machine or a hydraulic press; heating to 1080-1150 DEG C, carrying out repeated upsetting and swaging forging by virtue of the rapid forging machine or the hydraulic press, heating the forged blank to Tbeta-120 DEG C to Tbeta-30 DEG C(Tbeta is a Ti60 titanium alloy alpha+beta / beta phase inversion temperature), and carrying out repeated upsetting and swaging forging by virtue of the rapid forging machine or the hydraulic press until the blank is in a required size, so as to obtain the titanium alloy bar, wherein the macrostructure of the titanium alloy bar is a fuzzy crystal, and the microstructure of the titanium alloy bar isuniform. After the prepared Ti60 titanium alloy bar is subjected to solid dissolving and ageing thermal treatment, the matching degree of the obdurability of the bar is relatively good, and the matching degrees of the durability, creeping strength and thermal stability are relatively good. The preparation method is convenient in operation and relatively strong in process controllability, and the batch stability of the prepared Ti60 titanium alloy bars is good.
Owner:INST OF METAL RESEARCH - CHINESE ACAD OF SCI +2

A kind of preparation method of high temperature, high thermal stability, high creep resistance titanium alloy bar

The invention belongs to the field of titanium-based alloy and particularly relates to a preparation method for a high-temperature titanium alloy bar. The preparation method comprises the steps that aprepared Ti55 titanium alloy cast ingot is heated to 1150 DEG C-1200 DEG C, and then cogging forging is conducted in a beta phase region through a fast forging machine or a hydraulic press; and thenthe Ti55 titanium alloy cast ingot is heated to 1050 DEG C-1100 DEG C, upsetting and drawing-out forging are conducted repeatedly through the fast forging machine or the hydraulic press, then the forged blank is heated to Tbeta-100 DEG C-Tbeta-20 DEG C (Tbeta is Ti55 titanium alloy alpha+beta / beta phase transformation temperature), upsetting and drawing-out forging are conducted repeatedly throughthe fast forging machine or the hydraulic press till the needed size is obtained, and the titanium alloy bar of which the macrostructure is fuzzy crystals and the microstructure is uniform is obtained. After subjected to solution+aging heat treatment, the Ti55 titanium alloy bar prepared through the preparation method is good in strength and toughness match, good in endurance and creep strength and heat stability match, and high in fracture toughness. Operation is convenient, process controllability is high, and the prepared Ti55 titanium alloy bar is good in batch stability.
Owner:INST OF METAL RESEARCH - CHINESE ACAD OF SCI +2

System and method for expanding model driving development capability by applying plug-in

ActiveCN102033743BSolve the problem of insufficient description abilityExpandable and flexibleSpecific program execution arrangementsModel descriptionStationary model
The invention relates to a system and method for expanding the model driving development capability by applying a plug-in. In the system and the method, a'model and plug-in' combined mode is provided to describe and establish a software system, firstly a model designing tool is used for establishing basic model description of the software system and then establishing a plurality of reusable plug-pin model for further describing a basic model object, the plug-in model can be expanded randomly on various basic model objects, and the plug-in can complete a software function with any complexity, therefore, the expansion of the model driving development capability is realized. By utilizing the invention, the technical problems of the existing model driving development method that because a fixed model is adopted, the describing capability of complex service system is poor, and the software system with the model driving development can not be established, expanded and maintained visually and dynamically under the operating state and the like are solved. The system developed by using the method has the advantages that the development complexity degree is low, the development speed is fast, the reusable degree of technology is high, the expansion is flexible, the maintenance is convenient and the reliability is high.
Owner:广州翼风信息科技股份有限公司

Flow and heat transfer process numerical simulation analysis method of hot air drum type phoenix single fir tea leaf fixation machine

The invention discloses a flow and heat transfer process numerical simulation method of a hot air drum type phoenix single fir tea leaf fixation machine, and uses the hot air drum type phoenix singlefir tea leaf fixation machine which is scientific and reasonable in structure, good in fixation effect, high in efficiency, low in cost and easy to realize. According to the numerical simulation analysis method for the flow and heat transfer process in the fixation machine, calculation fluid dynamics software FLUENT is adopted for carrying out numerical calculation on the dehydration process of tea leaves in the drum-type fixation machine and the accompanying heat exchange and mass transfer process between the tea leaves and hot fluid, high cost and raw material waste caused by experiments orblind design are avoided, and the method has certain guiding significance for improving the fixation quality of the tea. High cost and technical risks caused by tests or blind design are avoided to acertain extent; programs of the numerical simulation analysis process are easy to implement, and the method has remarkable value in application of the efficient tea leaf fixation process.
Owner:SOUTH CHINA AGRI UNIV

An autonomous and controllable universal test launch and control system

The invention discloses an automatic controllable general test lunch and control system. The system comprises a remote control console, a test lunch and control host, a zero-second forwarding box andan AC / DC power supply case; the remote control console and the test lunch and control host are connected through a cable, and are in network communication through a fiber optical transceiver or a network switch; the test lunch and control host comprises a computer board, an I / O board, an AD acquisition board, a communication board and an interface backplane; the computer board, the I / O board, theAD acquisition board and the communication board are plugged in the interface backplane through printed board connectors; the computer board comprises a DSP, a clock circuit and a memory, wherein theclock circuit and the memory are connected with the DSP; the DSP is used for sending an on-off output signal to the I / O board, receiving on-off input data fed back by the I / O board and analog quantitydata fed back by the AD acquisition board and performing parsing to realize output control and condition monitoring of an aircraft. Through modular function board cards and standardized interfaces and buses between the board cards, the integration and generality of the system are improved, and the maintenance cost is saved.
Owner:HUBEI SANJIANG AEROSPACE HONGFENG CONTROL

An aircraft with two-stage orbital separation and horizontal inter-stage separation and its anti-shock wave shock method

The invention discloses a two-stage orbit-entry horizontally separated aircraft, comprising a booster-level aircraft and an orbital-level aircraft, the orbital-level aircraft is attached to the upper surface of the booster-level aircraft; the anti-shock wave impact method includes An anti-shock device is installed at the end of the aircraft; when the orbital-level aircraft and the booster-level aircraft are in a two-stage horizontal separation environment, the orbital-level aircraft accelerates and separates along the surface of the booster-level aircraft under the thrust of its own engine; the anti-shock device is in orbit In the process of the horizontal separation of the booster-stage aircraft and the booster-stage aircraft, the leading-edge bow shock wave formed by the leading edge end of the orbital-stage aircraft first passes through, and the leading-edge bow-shaped shock wave is gradually transformed into an anti-shock The conical shock wave formed by the device is then transformed into a curved shock wave when the anti-shock device fully protrudes from the leading edge end of the booster-stage vehicle until the orbital-stage vehicle and the booster-stage vehicle are completely horizontal separation.
Owner:INST OF MECHANICS CHINESE ACAD OF SCI
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