In infrared image, the grey distribution of background and target are instability, so it has much difficulty in the target segmentation. In this paper, a novel image segmentation algorithm is presented which is based on Contourlet transform and background complexity. Firstly, using Contourlet transform, the structure information of target and background is obtained. Next, structure similarity of target and background is computed. Finally, through the structure similarity of target and background, segmentation threshold is adjusted adaptively. If the structure similarity of target and background is low, it indicates that background is simple, segmentation threshold is set with the grey information. If the structure similarity of target and background is high, segmentation threshold is set with the structure information. The simulation experiments show that the target can be segmented truly in the complex background environment. The algorithm not only reserves the advantage of the grey segmentation in simple background environment, but overcomes the limitation of the grey segmentation in complex background environment, shows better adaptability than the traditional image segmentation methods.
The infrared (IR) imaging missile’s dome will be heated when fly at high speed in the atmosphere because of the friction of the air flow blocking. The detector’s performance will be decline if the dome surface is heated to a certain temperature. In this paper, we find a right way to evaluate the aerothermal effects in the imaging and information processing algorithm. Which have three steps including the aerothermal radiation calculation, quantization and image reconstruction. Firstly, the aerothermal radiation is calculated by using a combination of both methods of theoretical analysis and experiment data. Secondly, the relationship between aerothermal radiation and IR images background mean gray and noise can be calculated through the analysis of the experiment data. At last, we can rebuild an aerodynamic heating effect of infrared images fusion with target and decoy, which can be used for virtual prototyping platform missile trajectory simulation. It can be found that the above constructed images have good agreements with the actual image according to comparison between the simulation data and experiment data. It is an economic method that can solve the lab aerodynamic heating simulation and modeling problems.
While flying in the aerosphere at high speed, it will form shock wave around the noddle of flight vehicle. The radiation of hot air behind shock wave is a major factor responsible for the infrared signature of the vehicle, and has an important influence on the infrared detection system mounted in it. Calculating the infrared radiation of high temperature gas is significant for selecting an optimal detection band and improving detection capability of the IR system. In this paper, focused on the high-speed flight in typical altitude, the line-by-line method was adopted to calculate the radiation properties of high temperature gas around the noddle of the vehicle to study the relationship with the flight altitude and velocity. At first, based on the flight altitude, the related parameters of the flow, such as pressure, temperature and density, were calculated using the standard atmosphere model. Then, the parameters of the air which had passed through the shock wave were calculated according to the shock wave theory. At last, the line-by-line method had been used to calculate the radiant absorption coefficient of high temperature gas in different velocity and flight altitude. The results of calculation show that in the same velocity, the average absorption coefficient of high temperature gas is smaller while the higher flight altitude; in the same flight altitude, the coefficient is bigger while the higher velocity. And so, while flying in low altitude with high speed, the radiation of the hot air should be taken into consideration more carefully for infrared system design.