A thermal environment simulation partition heat flow calibration method for attitude control power system
A technology of thermal environment simulation and power system, applied in calorimeter, heat measurement, machine/structural component testing, etc., can solve problems such as inability to provide heat flow for products, achieve high precision and ensure accuracy
Active Publication Date: 2020-08-21
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology
[0003] The main purpose of the present invention is to solve the technical problem that the heat flow value collected by the lamp array heat flow meter is different from the actual arrival heat flow value on the product surface in the ground heat insulation test of the aerospace engine, and the heat flow cannot be accurately provided for the product, and to provide an attitude control Thermal environment simulation partition heat flow calibration method for the whole power system
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[0030] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.
[0031] The heat flow calibration method of the thermal environment simulation partition of the whole machine of the attitude control power system of the present invention can be used for the ground hot wall test run of the whole machine of the liquid attitude control power system. Such as image 3 , the infrared lamp array 5 is set on the periphery of the cabin body 4, and the surface of the cabin body 4 is heated by the infrared lamp array 5. The partitions of the infrared lamp array 5 correspond to the partitions on the surface of the cabin body 4, and each partition of the cabin body 4 is composed of a corresponding The partitioned infrared lamp arrays 5 are heated, and the cabin body 4 and the infrared lamp...
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The invention provides a partitioned heat flow calibration method simulating the whole thermal environment of an attitude control power system, belongs to an aerospace engine test method, and aims tosolve the technical problems that in the prior art, a heat flow value acquired by a lamp array heat flow meter is different from a heat flow value actually reached by the surface of a product and heatflow cannot be accurately provided for the product. The method comprises the steps 1, establishing a simulation cabin; 2, dividing the simulation cabin into twelve areas; 3, mounting a lamp array heat flow meter; 4, installing a calibration heat flow meter; and 5, collecting a heat flow value, and performing fitting calculation. When the cabin needs to be heated, the heat flow value correspondingto the lamp array heat flow meter can be conveniently and rapidly obtained, and the infrared lamp arrays in all areas can be conveniently controlled.
Description
technical field [0001] The invention belongs to an aerospace engine test method, and in particular relates to a method for calibrating heat flow in a thermal environment simulation zone of a complete machine of an attitude control power system. Background technique [0002] In the ground heat insulation test of the aerospace engine, it is necessary to carry out heat flow loading on the orbit control cabin. The thermal load loading area is divided into four areas: the windward cone section, the windward column section, the leeward cone section, and the leeward column section. , and heat loading should be carried out according to the target heat flux curve required by the task. Among them, not only the total heating power of the lamp array is required to meet the thermal load requirements of the whole machine, but also the thermal load load of each area is required to meet the requirements at the same time. Due to the difference in the arrangement position of the heat flow met...
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IPC IPC(8): G01K19/00G01M99/00
CPCG01K19/00G01M99/002
Inventor 李广会寇鑫李民民吕欣李志勋李红林华程吴飞飞刘丽宁刘阳刘珅李林永刘宇峰向红艳高静
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST