Hypersonic vehicles have a very complex trajectory and excellent maneuverability, which makes them effective in breaking the defence of enemy. Due to the strong and sustained infrared radiation emitted when they cruising rapidly in Near Space, researchers have paid attention to the infrared radiation characteristics of hypersonic targets and early warning detection mechanism. In order to acquire infrared radiation characteristics of hypersonic vehicles and collate research in infrared early warning detection technology phylogeny by the way, we have researched the Chinese and foreign progress of infrared radiation made by hypersonic target projectile, plume and the target entirety firstly; then the discussion of main method of infrared warning detection mechanism, technical models and conclusions as well. Lastly we discuss the main research directions in future by combining with the current research progress.
In order to study the space-based infrared remote sensing characteristics of hypersonic vehicles, this paper takes the simplified projectile model of HIFIRE-1 aircraft as the object to carry out simulation research. Firstly, the infrared radiation calculation model of the target projectile is established, including the aerodynamic thermal effect engineering simulation model, the projectile temperature calculation model and the projectile infrared radiation calculation model; Secondly, the space-based infrared detection model of hypersonic targets by calculating the spectral contrast between the target and the background is established; Finally, space-based infrared remote sensing characteristics of high orbit infrared early warning satellite for hypersonic vehicles under typical conditions are simulated and analyzed. The results show that, when the hypersonic vehicles fly at a speed of 6Ma at 25km, the detection ability of high orbit infrared early warning satellite for hypersonic target projectile is weak.
Intensive study on the system noise of infrared detection system in optical satellites could provide an important for the
detection performance research and system design. The source of system noise of the infrared detection system in optical
satellites is analyzed and the models of system noise including electronic noise, background noise and optic system noise
are constructed. Firstly, the electronic noise model is built based by comprehensive analysis of system equivalent power
and scan parameters; then, the earth and atmosphere background noise is established on the basis of the Combined
Atmospheric Radiative Transfer software; lastly, the optic system heat radiation noise is studied using blackbody radiation
theory. On the basis of those models, the electronic noise, background noise and optic system noise are studied, furthermore,
the rule by which the system noise varies according to the changes of temperature and the influence on system noise of
each noise source is studied. The results show that, firstly, the optic system noise could be ignored when the system
temperature blowing 250K; secondly, the electronic noise is the primary source of system noise at 2.7μm and the
background noise is the primary source at 2.7μm and 2.85μm4.19μm.
Hypersonic cruise vehicles emit intense infrared radiation when maneuvering at high speed in the near space, which highlights the practical significance of studying their infrared remote sensing characteristics. This paper makes a survey on the previous research into the infrared radiation characteristics of scramjet plumes, the infrared radiation characteristics of hypersonic cruise vehicle bodies and the infrared remote sensing characteristics of hypersonic cruise vehicles in the near space. Survey results show that, tentative studies have been carried out on infrared remote sensing technologies for hypersonic cruise vehicles, but more thorough and systematic research need to be conducted in depth. Further studies should focus on the infrared remote sensing mechanism of hypersonic cruise vehicles in the near space, and specific research is supposed to be targeted in particular to calculate the total infrared radiation intensity, with not only the infrared radiation of scramjet plumes and vehicle bodies taken into account, but also atmospheric attenuation and background radiation into consideration.
In order to study the temperature distribution characteristics of near-space hypersonic vehicles, the numerical calculation method was adopted to simulate and analyze the aerodynamic heating effect of hypersonic vehicles in this paper. The simulation process consisted of model establishment, mesh division, and CFD numerical calculation. Based on the simulation results, the temperature distribution characteristics of hypersonic vehicles and the influence of flight speed on the body temperature were analyzed. The results show that hypersonic flight will increase the body temperature significantly. The temperature at the stagnation point of the warhead can reach up to 2185K, and the temperature in other areas along the axis of the projectile gradually decreases. As the flight speed increases, the temperature of the vehicle body rises rapidly. When the flight speed is at 6.58Ma, 8Ma, 9Ma, and 10Ma, the temperature at the stagnation point of the missile body can reach 2185K, 3172K, 3792K and 4772K respectively
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