Combustion diagnosis for analysis of solid propellant rocket abort hazards: Role of spectroscopy

22nd International Conference on Spectral Line Shapes

Gill, W.^1 ; Cruz-Cabrera, A.A.^2 ; Donaldson, A.B.^3 ; Lim, J.^4,6 ; Sivathanu, Y.^4,6 ; Bystrom, E.^2 ; Haug, A.^3 ; Sharp, L.^3 ; Surmick, D.M.^5

Sandia National Laboratories, MS1135, PO box 5800, Albuquerque

NM

87185-1135, United States^1

Sandia National Laboratories, MS1139, PO box 5800, Albuquerque

NM

87185-1139, United States^2

New Mexico State University, 1780 E University Ave, Las Cruces

NM

88003, United States^3

En'Urga Inc, Business and Technology Center, 1291-A, Cumberland Avenue, West Lafayette

IN

47906, United States^4

University of Tennessee, Space Institute, 411 B.H. Goethert Parkway, Tullahoma

TN

37388, United States^5

Center for Laser Applications, United States^6

关键词: Characteristic temperature;    Combustion diagnosis;    Off design condition;    Physical environments;    Plume temperature;    Solid propellant rocket;    Solid rocket propellant;    Spectroscopic method;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/548/1/012055/pdf
DOI  :  10.1088/1742-6596/548/1/012055

来源: IOP

【 摘 要 】

Solid rocket propellant plume temperatures have been measured using spectroscopic methods as part of an ongoing effort to specify the thermal-chemical-physical environment in and around a burning fragment of an exploded solid rocket at atmospheric pressures. Such specification is needed for launch safety studies where hazardous payloads become involved with large fragments of burning propellant. The propellant burns in an off-design condition producing a hot gas flame loaded with burning metal droplets. Each component of the flame (soot, droplets and gas) has a characteristic temperature, and it is only through the use of spectroscopy that their temperature can be independently identified.