A method to automatically find the combustion termination time of solid rocket motors

A solid rocket, automatic search technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of poor repeatability of processing results, low accuracy, and large human factors, so as to achieve automatic data processing, Avoid processing errors and ensure repeatable results
CN110500202BActive Publication Date: 2022-03-15XIAN AEROSPACE PROPULSION TESTING TECH RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
XIAN AEROSPACE PROPULSION TESTING TECH RES INST
Publication Date
2022-03-15

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Abstract

The present invention proposes a method for automatically finding the combustion termination time of a solid rocket motor. First, the actual pressure-time curve of the solid rocket motor propellant combustion rate test is obtained, and secondly, the pressure value P is normalized by time, and then the differential is determined. The interval step of derivation, calculate the derivative of the transformed pressure point by point, get the first derivative and the second derivative, and then get the curvature of each point in the transformed pressure curve, and the time corresponding to the maximum value of the curvature Points to calculate burn time. The method proposed by the present invention can be used as an alternative to the artificial double tangent method in the test of the combustion rate of the solid rocket motor propellant, which realizes automatic data processing, improves the data processing efficiency, ensures the repeatability of the processing results, and avoids Due to processing errors caused by human factors, the combustion time obtained by processing is numerically closer to the design parameters, and the processing results are more accurate.
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Description

technical field

[0001] The invention belongs to the technical field of solid rocket motor testing, in particular to a method for automatically finding the combustion termination time of a solid rocket motor. Background technique

[0002] During the testing process of solid rocket motors, the burning time is the calculation basis of ballistic parameters such as the burning rate, average pressure, average thrust, and characteristic speed of the solid rocket motor. At present, the double tangent method is mainly used to determine the termination time point of the engine combustion in practice. Specifically, the method is as follows: draw two tangent lines of the steady section and the descending section of the pressure curve respectively, and take the intersection point of the angle bisector of the two tangent lines and the pressure curve as the termination time point of engine combustion. However, the currently used double tangent method does not clearly define the stable segm...

Claims

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