Projectile body front surface temperature non-contact infrared measuring device of missile high-temperature pneumatic thermal test

Abstract

A projectile body front surface temperature non-contact infrared measuring device of missile high-temperature pneumatic thermal test comprises a conical water-cooled infrared anti-aliasing guild pipe, a tungsten-based conical infrared guild head, a water-cooled tube, an infrared thermometer and a computer; in the transient high temperature pneumatic thermal shock test which imitates the hypersonic flight of a missile, a conical light-passing pipeline composed of high temperature resistant and small diameter tungsten-based conical infrared guild head and the conical water-cooled infrared anti-aliasing guild pipe is arranged between the surface of the missile body and the receiving lens of an infrared thermoscope so that the infrared light beams sent from the small size spot areas on the front surface of the missile housing can directly pass through the heating zone of the infrared radiation heat source array with higher temperature to reach the receiving lens of the infrared thermoscope. The invention can work under the condition of high temperature ranging 1300 DEG C-1500 DEG C generated by the infrared radiation heat source array and can effectively avoid the aliasing interference to the infrared light beams of the front surface of the missile by the high temperature infrared radiation heat source array so that the measurement result on the projectile body front surface of the missile body of the missile high temperature pneumatic thermal test is more accurate and reliable.

Description

technical field [0001] The invention relates to a non-contact infrared measuring device for the temperature of the front surface of a missile high-temperature aerodynamic thermal test. Background technique [0002] Due to the needs of defense penetration, anti-missile, high-altitude and high-speed reconnaissance, missiles and other aircraft are flying faster and faster. The leading edge temperature of hypersonic cruise missiles with a flight Mach number of Mach 8-9 will exceed 1200°C. Since the deformation of metal materials such as titanium alloys and high-temperature alloys increases significantly when the temperature exceeds 800 °C, the deformation of the metal shell will seriously affect the aerodynamic shape and flight trajectory of the missile body. The new development direction to solve this problem is to use high-temperature ceramics or carbon fiber composite materials with small deformation at high temperatures as the shell material of missile warheads or warheads. ...

AI Technical Summary

Problems solved by technology

[0007] However, there are no reports of relevant technologies at home and abroad

Images