Simulation method for multi-thread based independent-adjustment configurable temperature control system
A temperature control system, independent adjustment technology, applied in the direction of using electric means for temperature control, auxiliary controller with auxiliary heating device, etc., can solve the problem of single operation mode of the temperature control simulation system The value and the upper and lower limits of the target temperature are not adjustable, so as to achieve the effect of improving the proficiency.
Active Publication Date: 2016-06-15
BEIJING INST OF SPACE LAUNCH TECH +1
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Problems solved by technology
[0005] However, the operation mode of the temperature control simulation system is single, and only one temperature control system can be simulated at a time, and the temperature value and the upper and lower limits of the target temperature cannot be adjusted
[0006] The temperature on the launch vehicle is affected by many factors, so the above-mentioned defects of the prior art limit the simulation effect of the temperature control system of the launch vehicle, which is not suitable for actual combat simulation and drills, and is not conducive to the debugging and testing of the temperature control system
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[0044] The technical solution of the present invention will be described below in conjunction with the accompanying drawings.
[0045] Such as figure 1 As shown, the multi-threaded independently adjustable configurable temperature control system simulation method based on the launch vehicle temperature control system includes the following steps:
[0046] (1) Obtain temperature setting information;
[0047] (2) Simulate the temperature value according to the temperature setting information;
[0048] (3) Output the simulated temperature value.
[0049] Preferably, said step (1) includes:
[0050] (11) Install a temperature control combination panel, a fan power supply panel and an interface combination panel in the temperature control system of the launch vehicle;
[0051] (12) Collect the temperature configuration information of the temperature control combination panel, which includes the upper and lower limit temperatures of the launching device of the launch vehicle, th...
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The invention provides a simulation method for a multi-thread based independent-adjustment configurable temperature control system, and aims at meeting temperature control requirements for a launcher vehicle under effects of different factors as well as requirements for simulated soldier training of the temperature control system of the launching vehicle in new situation. The simulation method comprises that (1) temperature setting information is obtained; (2) the temperature value is simulated according to the temperature setting information; and (3) the simulated temperature value is output. According to the simulation method of the invention, independent operation of the temperature control system is realized, operation modes of a practical temperature control system of the launching vehicle is reproduced flexibly, and the proficiency in weaponry of soldiers is greatly improved.
Description
technical field [0001] The invention relates to the technical field of networked simulation control, and more specifically, to a simulation method for a configurable temperature control system based on multi-thread independent adjustment. Background technique [0002] The stand-alone product of the launch vehicle control system that meets the requirements of "three modernizations" of informatization, digitalization, and networking is aimed at meeting the functional requirements of strategic and tactical missile launch vehicles for mobile launch control functions, and comprehensively considers various user needs of various types of launch vehicles. The product is designed according to the development idea of productization, and through different configurations of serialized products, it forms a general stand-alone product that meets the needs of different users. [0003] In order to adapt to the combat needs of soldiers in the new situation, provide a multi-faceted and inte...
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IPC IPC(8): G05D23/30
CPCG05D23/30
Inventor 刘杰李向阳李荣张帆黎兰赵京坡赵龙飞李仁洙敖鹰
Owner BEIJING INST OF SPACE LAUNCH TECH