The Study Of Aerodynamic Ablation For Hypersonic Projectile Wing And Numerical Calculation

This dissertation researches ablation phenomena of hypersonic right-angled trapezoid projectile wing. The interior temperature distribution and ablation model of projectile wing is established from general transmitting heat differential equation; At the same time, the heat flow density and pressure distribution model of projectile wing is also established. The model is solved with the finite difference method, the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns. Because these projectiles attain hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads, the survivability of the front region of projectile wing is very important for designer to consider. The paper simulate the transient thermal response of projectile wing according to the simulation software, and discuss the ablation characteristic when the projectile wing is in different initial velocity, in different wing shape, in different atmosphere condition and in different material condition. At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed. The theory, method and results presented in the paper are available for the study of hypersonic projectiles in the future.