Numerical Simulation of Infrared Spectrum and Radiance Characteristics of Rocket Engine Exhaust Plume

摘要

Exhaust plume from the rocket engine produces strong infrared radiation signals, widely used for target diagnosing, detecting and identifying. Exhaust plume flow field have the characteristics of high temperature, high speed and multi-species reacting flow. The radiation mechanism is very complex in the flow field. Infrared spectrum of exhaust plume involving complex gaseous kinetic and thermodynamic processes, which makes the exhaust plume have a complex spectral structure. On the base of a rocket motor, the two-dimensional axisymmetric and Reynolds Averaged Navier-Stokes equations (RANS) coupled with chemical reactions are solved. With the flow field of the exhaust plume, line-by-line method and LOS method are used to calculate the infrared radiation of the exhaust plume. The spectral radiation characteristics of H_2O, CO_2, CO and HCL in 2μm to 8.6μm band are analyzed in detail, and the characteristics of radiance distribution in typical gas emission bands are studied.