|Table of Contents|

The parameter response characteristic of starting acceleration of rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年05期
Page:
96-102
Research Field:
测控与试验
Publishing date:

Info

Title:
The parameter response characteristic of starting acceleration of rocket engine
Author(s):
ZHAO Wanming;  SHI Chao;  TANG Yunlong
(Xi’an Aerospace Propulsion Test Technology Institute, Xi’an 710100,China)
Keywords:
rocket engine test;  starting acceleration;  structural factor;  fitering characteristic
PACS:
434.3
DOI:
-
Abstract:
The speed of the rocket engine start can be reflected by the value of engine starting acceleration.Comprehensive analysis of the test system, parameter measurement of the starting acceleration and the factors of step response are necessary to the deciding of the starting characteristic.The reason of different starting acceleration value calculated by different parameters was researched to get reliable calculation method.The effect of several mechanical structure factors such as thrust measurement geometry of ground test system and sensor mouting patterns on the starting acceleration characteristic of the engine were analysed.Besides, effect of signal conditioner filter property of measuring parameter configuration on delay action of step signal was studied, which includes thrust, rotating speed and pressure.The starting acceleration characteristic of the large liquid rocket engine was also analyzed in this paper.The results of the analysis show that the main reason of different starting acceleration value calculated by different parameters are factors as structural factor of test system and filtering factor of parameter measurement.The computational result of the starting acceleration can be accurate and reliable when they are based on the analysis of structural factors of test system and filtering factors of parameter measurement system in large liquid rocket engine tests.

References:

[1] 液体火箭发动机地面测量方法:GJB 2898[S].北京:国防科学技术工业委员会,1997.
[2] 液体火箭发动机地面稳态推力测量规范:QJ 1084[S].北京:中华人民共和国航天工业部,1987.
[3] 朱子环, 董文华, 管理.管路流体对氢氧发动机推力测量的影响分析[J].低温工程, 2008(2): 46-50.
[4] 朱子环, 蔡睿.氢氧火箭发动机高空模拟试验推力测量装置研制[J].宇航计测技术, 2016, 36(6): 50-55.
[5] 谢显奇.液氢-液氧火箭发动机的推力测量[J].导弹与航天运载技术, 1997(2): 60-62.
[6] 晏卓, 李志勋.姿控发动机试验缓变参数数据修正方法[J].火箭推进, 2018, 44(1): 87-94.YAN Z, LI Z X.Data correction methods of slowly varying parameters in attitude control engine test[J].Journal of Rocket Propulsion, 2018, 44(1): 87-94.
[7] 章萌, 唐云龙, 张小松.液体火箭发动机试验推力校准测控系统设计[J].弹箭与制导学报, 2014, 34(5): 126-130.
[8] 李正兵, 李永斌, 田宝云, 等.可调低温环境压力传感器校准装置实现[J].火箭推进, 2016, 42(4): 103-109.LI Z B, LI Y B, TIAN B Y, et al.Realization of calibration device for adjustable cryogenic pressure sensor[J].Journal of Rocket Propulsion, 2016, 42(4): 103-109.
[9] 赵万明.流量转速参数信号调理技术[J].火箭推进, 2008, 34(2): 49-54.ZHAO W M.Signalmodulating technique of flow and rotating speed parameters[J].Journal of Rocket Propulsion, 2008, 34(2): 49-54.
[10] 苏金明, 阮沈勇.MATLAB实用教程[M].北京: 电子工业出版社, 2008.
[11] 郭霄峰.液体火箭发动机试验[M].北京: 宇航出版社, 1990.
[12] 张金容, 汪亮.液体火箭发动机起动过程的动态仿真计算[J].低温工程, 2008(2): 22-27.
[13] 深圳金洪仪器技术开发有限公司.太平洋6000DAS传感器数据采集与控制系统硬件操作使用手册 [M].深圳:[s.n.],2008.
[14] 沙占友.智能传感器系统设计与应用[M].北京: 电子工业出版社, 2004.
[15] 威廉姆斯 A B.模拟滤波器与电路设计手册[M].路秋生,译.北京:电子工业出版社,2016.

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Last Update: 2019-10-25