Author Affiliations
Research Center for Space Optical Engineering, School of Astronautics, Harbin Institute of Technology, Harbin 150006, Chinashow less
Fig. 1. Schematic diagram of aircraft infrared imaging radiance transmission
Fig. 2. Flow chart of direct lighting reflection radiance calculation using multi-importance sampling
Fig. 3. Sampling distance distribution of line-of-sight transmittance sampling
Fig. 4. Schematic diagram of path radiance integral calculation based on line integration method
Fig. 5. Flow chart of exhaust plume radiance calculation using combining integration method
Fig. 6. Calculation relative errors of emissive radiation intensity experiments of skin
Fig. 7. Calculation relative errors of reflective radiation intensity experiments of skin
Fig. 8. Reflective radiance simulation images of skin
Fig. 9. Calculation relative errors of emissive radiation intensity experiments of thick medium
Fig. 10. Calculation relative errors of emissive radiation intensity experiments of thin medium
Fig. 11. Emissive radiance simulation images of exhaust plume
Fig. 12. Simulation calculation results of stealth aircraft flow field
Fig. 13. Geometric relationship of stealth aircraft simulation imaging. (a) Ground-based detection scene; (b) Air-based detection scene; (c) Line of detection sight
Fig. 14. Simulation calculation results of infrared radiation intensity of stealth aircraft
Fig. 15. Infrared radiance simulation images of stealth aircraft
Number of sampling rays/pixel | RRMSE by BRDF sampling | RRMSE by direct
lighting sampling
| 1 | 114.289% | 49.394% | 10 | 93.754% | 16.324% | 100 | 31.998% | 5.222% | 1000 | 10.353% | 1.785% | 10000 | 3.640% | 0.852% |
|
Table 1. [in Chinese]
Number of sampling rays/pixel | RRMSE by point
integration
| RRMSE by line integration | RRMSE by combining integration | 1 | 191.570% | 6.715% | 5.580% | 10 | 113.819% | 1.687% | 1.620% | 100 | 58.461% | 0.652% | 0.638% | 1000 | 19.159% | 0.299% | 0.020% |
|
Table 2. [in Chinese]
Parameter | Value | Atmospheric pressure/Pa | 3×104 | Atmospheric temperature/K | 255 | Atmospheric composition | Fluent ideal atmosphere model | Short-waveband solar radiance/W·sr−1·m−2 | 10.0 | Short-waveband solar direction | -Z axis of target body
coordinate system
| Flight height/km | 10 | Flight speed/Ma | 1.0 | Skin BRDF | Lambert | Skin material | Aluminum alloy | Engine inlet diameter/m | 1.4 | Engine inlet temperature/K | 650 | Engine inlet pressure/Pa | 2×105 | Engine outlet diameter/m | 0.5 | Fuel type | C5H12 | Fuel temperature/K | 300 | Fuel mass flow/kg·s−1 | 0.15 |
|
Table 3. [in Chinese]