II.1.1 SSRの機体設計について(1 機体および構造)(II.関連研究)

概要

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The design of SSR is characterized by its slenderness of the rocket body and by that the Al-alloy is used as main structural material. The former feature is favorable both from the aerodynamical point of view and also from the point of the motor design. It is shown in this paper that the optimum ratio of the length of the combustion chamber to its diameter can be analytically determined by maximumizing the mass ratio of the rocket. By the analysis, this size ratio in the case of SSR becomes about the value 22. 5, which is the largest among the solid propellant rocket motors up to the present. In the actual rocket, the diameter of the rocket body is 110mm, while the total length is 3,050mm in SSR-RT and 3,310mm in SSR-TM. Nextly, a practical simple method to determine the aerodynamical critical speed of such a slender elastic rocket body (see Eq. (17)) Finally, this paper explains why we use the Al-alloy (61S-T6) as the material of cylinder wall and of tail surface and also this paper describes about the heat insulation coatings used in this rocket.
宇宙航空研究開発機構の論文