|Table of Contents|

Radiant heat flux measuring system and its application(PDF)

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

Issue:
2014年01期
Page:
85-91
Research Field:
测控与试验
Publishing date:

Info

Title:
Radiant heat flux measuring system and its application
Author(s):
DUAN Wen-hao1;  YU Tao1;  YANG Ying2
1. Beijing Institute of Aerospace Testing Technology, Beijing 100074, China; 2. Beijing Aerospace Propulsion Institute, Beijing, 100076, China
Keywords:
rocket engine;  simulation thermal vacuum test;  heat flux measurement;  radiation
PACS:
V433.9-34
DOI:
-
Abstract:
According to the requirements of ground simulation thermal vacuum test for a certain type of rocket engine, the thermal vacuum environment simulation system was established. On the basis of analyzing the heat measurement principle, a radiant heat flux measurement system was used to test the heat flux around the engine while the engine was working. The system composition, working principle, the calibration method of heat flux measurement sensor are introduced emphatically in this article. Through the comparison between the heat flux distribution calculation of thermal radiation device and the results of actual measurement, the facticity and reliability of the data got by the heat flux measuring system was verified.

References:

[1]仲伟聪, 张峰. 单喷嘴燃烧流场仿真研究[J]. 火箭推进, 2009, 33(5): 27-30.
[2]SHINGO M, JUNJI S, YASUHIRO M, et al. A numerical investigation on shear coaxial LOX/GH2 jet flame at supercritical pressure, AIAA 2006-761[R]. USA: AIAA, 2006.
[3]TSOHAS J, CANINO J V, HEISER S D. Computational modeling of rocket injector internal flows, AIAA 2007- 5571[R]. USA: AIAA, 2007.
[4]CHEHROUDI B, TALLEY D, MAYER W, et al. Under- standing injection into high pressure supercritical environments, ADA417985[R]. USA: ADA, 1985.
[5]MCBRIDE B J. GORDON S, RENO M A. Cofficients for calculating thermodynamic and transport properties of individual species[R]. USA: NASA, 1993.
[6]POSCHNER M M, PFITZNER M. Real gas CFD simu- lation of supercritical H2-LOX combustion in the Mascotte single-injector combustor using a commercial CFD code, AIAA 2008-952[R]. USA: AIAA, 2008.
[7]DE GIORGI M G, SALENTO U D, LEUZZI A, et al. CFD simulation of mixing and combustion in LOX/CH4 spray under supercritical conditions, AIAA 2009-4038[R]. USA: AIAA, 2009.
[8]YU D, NEGISHI H, YAMANISHI N, et al. Combustion and heat transfer modeling in regeneratively cooled thrust chambers (multi-injection flow features), AIAA 2011-5625 [R]. USA: AIAA, 2011.
[9]TUCKER P, MENON S, MERKLE C, et al. Validation of high-fidelity CFD simulations for rocket injector design, AIAA 2008-5226[R]. USA: AIAA, 2008.

Memo

Memo:
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Last Update: 1900-01-01