8results about How to "Reduce trial risk" patented technology

This invention relates to the field of aero-engine technology, and discloses an inlet swirl adjustment device and its design method for an afterburner test component. A flow divider ring is used to segment the test flow channel into an inner flow channel and an outer bypass flow channel for simulating the airflow in the inner flow channel. The remaining linkage control structures are installed in the outer bypass casing or outer bypass flow channel to reduce interference with the inner flow channel. The linkage adjustment assembly performs overall synchronous adjustment of all adjustable guide vanes, ultimately achieving adjustment of the inner airflow angle, thereby simulating the inner airflow of the afterburner and reducing testing costs and overall engine verification risks. The inlet airflow swirl adjustment device of this invention comprehensively considers the relevant requirements of total pressure recovery coefficient and airflow uniformity index, ensuring high-precision and high-stability simulation of the inner airflow of the afterburner. Furthermore, its simple structure allows for easy assembly and replacement, providing flexible support for afterburner performance testing under different operating conditions.

This utility model discloses a pedal impact testing device, comprising: a frame; a quick-change fixture disposed at one end of the frame; a pendulum impact column body fixture disposed in the middle of the frame; a magnetic platform placement welding frame disposed at the other end of the frame, wherein an electromagnetic suction platform is disposed on the magnetic platform placement welding frame and connected to the pendulum impact column body fixture; and a rotating device disposed between the magnetic platform placement welding frame and the pendulum impact column body fixture and connected to the pendulum impact column body fixture. Through the application of this utility model, a pedal impact testing device is proposed. Compared with manual operation, it can not only shorten the single test time and speed up the overall testing process, but also reduce the test errors caused by manual operation and the risk of contact between the person and the pendulum, which is beneficial to improving the accuracy and safety of the test.

The application relates to the technical field of transformers, and provides a transformer bushing withstand voltage test system, one end of the bushing is provided with an exhaust plug and a wiring terminal, the transformer bushing withstand voltage test system comprises an oil tank and a pressurizing device, the oil tank is provided with an oil inlet, the oil inlet is used for injecting transformer oil into the oil tank, the bushing is used for being connected to the oil tank, and the other end of the bushing away from the exhaust plug is inserted into the oil tank and is in communication with the oil tank; the pressurizing device is used for being electrically connected to the wiring terminal, so as to apply a test voltage to the bushing. The application can realize the off-line withstand voltage test of the transformer bushing, effectively reduces the test risk, and improves the test efficiency.

This invention provides a combustion chamber testing apparatus and method. The combustion chamber testing apparatus includes a combustion chamber test piece, a simulated bleed air test piece, and an outlet guide test piece. The combustion chamber test piece includes an outer casing, a diffuser, a flame tube, and an inner casing. The diffuser is located at the front of the flame tube, and air enters the first airflow channel, the second airflow channel, and the third airflow channel through the diffuser. In the first stage of the test, the simulated bleed air test piece is placed at the outlet of the combustion chamber test piece, and the air flowing out of the first and third airflow channels passes through the simulated bleed air test piece and exits the combustion chamber test piece. In the second stage of the test, the outlet guide test piece is placed at the outlet of the combustion chamber test piece, and the air flowing out of the first, second, and third airflow channels passes through the outlet guide test piece to obtain the pressure value inside the flame tube, thereby obtaining the thermoacoustic-structural coupled oscillation boundary of the combustion chamber.

The invention relates to a method and a device for determining a sensitivity calibration coefficient of a nuclear reactor detector. The method comprises the following steps: carrying out a whole core flux diagram experiment to obtain an actually measured current of a detector; determining a sensitivity correction factor according to the actually measured current and the predicted current of the detector; determining out-of-pile axial power deviation according to the sensitivity correction factor and out-of-pile response current distribution; the out-of-pile response current distribution represents a current set of all out-of-pile detectors in each axial section; fitting to obtain a response sensitivity calibration coefficient according to the out-of-pile axial power deviation and the in-pile axial power deviation; the in-pile axial power deviation is obtained based on theoretical xenon oscillation simulation. By adopting the method, the test cost and the test risk can be greatly reduced.

The application discloses an aero-engine lubricating oil interruption test method, sets monitoring parameters in the S1 step, records the monitoring parameters of the engine in the S2 step to the S4 step, obtains monitoring parameter alarm values through the monitoring parameters, interrupts the lubricating oil supply of the engine in the S7 step, and monitors whether the second current gas generator rotating speed, the second current output power, the second current power turbine inlet temperature and the second current ball bearing wall temperature exceed the corresponding first alarm values within the second preset time. Since the signs of bearing failure are directly judged through the monitoring parameters, the situation that the signs of bearing failure are judged by artificial through abnormal phenomena is avoided, the efficiency and accuracy of judging the signs of bearing failure are improved, the monitoring parameters of the engine are obtained through the S2 step to the S4 step, the monitoring parameter alarm values are obtained according to the monitoring parameters, the monitoring parameter alarm values correspond to the actual situation of the engine, and the inaccurate test results caused by the differences between different engines are avoided.

The invention discloses an automatic design method of an aircraft structure test lever loading system. The method comprises the following steps: acquiring basic data required by lever beam unit modeling; constructing a finite element analysis model; generating a lever beam unit wireframe model, and synchronously completing grid division and assembly constraint application; verifying whether the strength and rigidity of the lever beam unit wireframe model meet preset conditions or not, and if yes, outputting design parameters; carrying out stress constraint topological optimization on the initial design domain of the lever component, and solving to obtain an optimal hole configuration; constructing a structured hole feature database; the hole size matched with the design parameters is output, the hole size is adjusted, and stress is checked; calibrating the gravity center of the lever based on an automatic counterweight algorithm; and outputting the lever three-dimensional model. According to the method, the automatic design of the aircraft lever loading system is realized based on parameterized finite element modeling and multi-objective collaborative optimization, and the design efficiency and reliability are remarkably improved while the structural strength and rigidity are ensured.

The application discloses a kind of clinical trial case report form automatic generation method and system, the application is related to medical instrument test technical field, the method includes: the target clinical trial scheme document is parsed, and medical instrument data is extracted;Based on medical instrument data, the corresponding target case report subform is matched from structured template database;Structured template database includes the hierarchical mapping relationship between medical instrument type and case report subform;The target case report subform is combined, and case report form document is generated.The application is structured to the target test scheme Parsing, then according to the medical instrument data of parsing structured template database is obtained standardization format target case report subform according to the automatic matching, finally, based on target case report subform combination generates case report form document, to significantly shorten the design time of medical instrument clinical trial case report form, improve design efficiency.At the same time, reduce human error, guarantee the reliability of case report form.