Analysis of Ultraviolet Radiation Characteristics of Solid Propellant Rocket Motor Exhaust Plume

Aiyan, 国爱燕 Guo; Tingzhu, 白廷柱 Bai; Haihe, 胡海鹤 Hu; Yi, 唐义 Tang

doi:10.3788/aos201232.1016002

Cited by 1 publication

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“…The Al 2 O 3 particles in the exhaust plume emit in the ultraviolet spectral range because of the high temperature that reaches values in the range of 2000-3000 K. Moreover, hightemperature iron oxide particles are emitted in the ultraviolet spectrum. Finally, the unburned fuels in the exhaust plume generate high amounts of C, N, and H, which produce free photons by chemical reactions with ultraviolet radiation [3].…”

Section: Introductionmentioning

confidence: 99%

Optical Diagnostics for Solid Rocket Plumes Characterization: A Review

et al. 2022

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In recent decades, solid fuel combustion propulsion of spacecraft has become one of the most popular choices for rocket propulsion systems. The reasons for this success are a wide range of applications, lower production costs, simplicity, and safety. The rocket’s plumes leave the nozzle at high temperatures; hence, the knowledge of produced infrared (IR) emissions is a crucial aspect during the design and tests of the rocket motors. Furthermore, rocket plume composition is given by N2, H2, H2O, CO and CO2, while solid rocket motors (SRM) additionally inject some solid particles, given by metal fuel additives in the propellant grain, i.e., aluminum oxide (Al2O3) particles. The main issue is the detection of the particles remaining in the atmosphere due to the exhaust gas of the solid rocket propulsion system that could have effects on ozone depletion. The experimental characterization of SRM plumes in the presence of alumina particles can be conducted using different optical techniques. The present study aims to review the most promising ones with a description of the optics system and their potential applications for SRM plume measurements. The most common measurement techniques are infrared spectroscopy imaging, IR imaging. UV–VIS measurements, shadowgraph, and Schlieren optical methods. The choice of these techniques among many others is due to the ability to study the plume without influencing the physical conditions existing in and around the study object. This paper presents technical results concerning the study of rocket engines plumes with the above-mentioned methods and reveals the feasibility of the measurement techniques applied.

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Section: Introductionmentioning

confidence: 99%