Determination of Validity of Original Data of Burning Rate Test of Solid Propellant by Impulse Method

被引：0

作者：

Wang Y.-H. ^{[1
]}

Zhang X.-P. ^{[1
]}

Tang Z.-C. ^{[1
]}

Gu T. ^{[1
]}

Liang C. ^{[1
]}

Pang A.-M. ^{[2
]}

Li W. ^{[2
]}

机构：

[1] Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an

[2] Science and Technology on Aerospace Chemical Power Laboratory, Hubei Institute of Aerospace Chemical Technology, Xiangyang

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 04期

关键词：

Burning rate test; Ignition synchronization; Impulse method; Raw data; Solid propellant;

D O I：

10.13675/j.cnki.tjjs.2203028

中图分类号：

学科分类号：

摘要：

In order to define and clarify the application boundary of the impulse burning rate test，the de⁃ scending rate at the maximum pressure，by analyzing the deviation，which comes from“inconsistent ignition” “erosion combustion”or“propellant eccentricity”，between the final combustion surface and design value，is proposed as the criterion for the validity of the burning rate test data of impulse method. Besides，the criterion is capable of judging whether the surface of bare propellant grain has been ignited synchronously. Based on the prin⁃ ciple of conservation of mass，a numerical method to determine the validity of the original data is given. The data validity factor K is obtained by calculating the ratio of the theoretical pressure drop time to the actual value. The research shows that when the data validity factor K=1~1.2，the combustion rate test results of the impulse method are in good agreement with those of the constant pressure engine. Furthermore，it is verified that nozzle ablation can affect the pressure range of impulse burning rate test，but does not affect the burning rate test result. © 2023 Journal of Propulsion Technology. All rights reserved.

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