Aircrafts such as helicopters, fighter planes, transport planes, and special military aircraft may be attacked by missiles or rockets fired by armed personnel during a conflict. Airborne Electro-Optical (EO) warning system can warn the incoming missiles or rockets, so that the airborne aircraft can take countermeasures and improve the survivability of the airborne aircraft. This paper introduces methods of testing the main function and performance of the airborne EO warning system, which can effectively and objectively evaluate the performance of the system and effectively improve the bidding efficiency.
Hypersonic target in near space put forward new challenge to the early warning system. The airborne IR early warning system is an important part of air-based infrared detection system to hypersonic vehicle, which will play a part in the preparedness of space echelons of missiles warning systems. The infrared radiation strength of near space hypersonic vehicle is discussed. It utilized MODTRAN software to simulate the atmospheric transmission rate under different conditions. The Hudsons classic distance formula is used to calculated the caliber. It discussed the feasibility on infrared detection system to hypersonic vehicle. It designed an onboard infrared detection system to hypersonic vehicle which can function well on the target 900 km away.
There is a strong demand for lightweight, miniaturization and non-heating in the design of airborne infrared dual band optical system. A transmissive infrared optical system is introduced, which can meet the confocal requirements of medium wave infrared and long wave infrared light and can realize non heating design in the temperature range of - 55 ℃~+71 ℃. By deeply analyzing the non-thermal mathematical and physical core, combining the difference of dispersion coefficient and thermal difference coefficient of different materials, using germanium, zinc sulfide and zinc selenide with appropriate positive and negative optical powers, a common optical path structure of the secondary imaging optical system with a "4+4" configuration is designed, with a focal length of 200mm and a F number of 2; Indium steel and aluminum are used for the base and the mirror tube, and the difference of thermal expansion coefficient between the two materials is used to achieve heat dissipation difference. This design method can realize the design of dual band non thermal optical system at a lower cost. Its transmissivity, distortion, MTF, cold reflection and other indicators meet the design requirements. The optical system achieves the imaging effect of high transmissivity of medium and long wavelength infrared light.
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