| 摘要 |
PROBLEM TO BE SOLVED: To enhance increase in flight velocity by realizing heat control at a leading end dome. SOLUTION: A cooling liquid container section 12 is formed at the leading end dome 11. When the acceleration of a missile 10 is raised, cooling liquid contained in a cooling liquid reservoir section 17 is circulated and fed to the cooling liquid container section 12 at the leading end dome 11 by using the change of the acceleration so as to deprive the dome 11 of heat caused therein by aerodynamic heating, and then is guided to a cooler 16 and cooled. Again, the cooling liquid is contained in the reservoir section 17. When the acceleration is lowered along with decrease in flight velocity, a liquid supply passage is reversed so as to supply the cooling liquid contained in the reservoir section 17 to the cooling liquid container section 12 at the leading end dome 11 via the cooler 16 to cool the dome 11.
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