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摘要
This work investigates the infrared radiation characteristics of high-temperature hypersonic flows with two reaction control system (RCS) plumes in the glide phase. Computational procedures are performed with thermal and chemical non-equilibrium fluid mechanics, gas-solid interaction, radiation physical parameter and transfer calculations. Hypersonic flows are simulated by solving two-temperature Navier-Stokes (N-S) equations with the finite volume technique. A 7-species, 6-reaction air-chemistry scheme and an 8-species, 10-reaction CO/H-2 plume reaction system are utilized. The line-by-line (LBL) method is used to evaluate radiative properties of high-temperature gases, and the radiation transfer equation (RTE) is integrated with the line of sight (LOS) method. Species formation, radiation properties of radiating species and radiation transfer calculations are verified against experimental and reference data. Three trajectory points of an HTV-2 type vehicle (at altitudes of 30, 50 and 70 km) are selected to analyze the radiation characteristics. Spectral intensities within the wavelengths of 2-12 mu m at different observation angles are calculated. Computational results indicate that species NO mainly forms in the shock layer and its mole fraction reaches 10(-2) order of magnitude. The high-temperature surfaces are near the head and leading edge of the vehicle, and surface emissions can be equivalent to a constant-temperature grey body. The spectral intensity of gases without RCS plumes is several orders of magnitude lower than surface emissions. Comparing the spectra with and without RCS plumes, it is shown that RCS plumes do change the spectral structure and increase the spectral intensity in the 2.7-mu m and 4.3-mu m bands. The integrated irradiances show that the instinct radiation intensity is closely related to the spectral band and the observation angle. In the 4.3-mu m band, the presence RCS plumes has a significant contribution to the radiation.
- 出版日期2018-8
- 单位哈尔滨工业大学
