The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled ...The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.展开更多
介绍了一种材料为合金结构钢30Cr Mn Si A的双台阶固体火箭助推器壳体强力旋压工艺方法。通过分析零件的结构特点,确定出采用正向旋压方法,设计相应的旋压毛坯和旋压工装。通过工艺试验过程检测与数据分析,确定出合理的旋压工艺流程,经...介绍了一种材料为合金结构钢30Cr Mn Si A的双台阶固体火箭助推器壳体强力旋压工艺方法。通过分析零件的结构特点,确定出采用正向旋压方法,设计相应的旋压毛坯和旋压工装。通过工艺试验过程检测与数据分析,确定出合理的旋压工艺流程,经过生产验证旋压工艺流程的合理性和可行性,旋出满足设计要求的产品,为同类结构壳体旋压提供技术参考。展开更多
基金supported by the National Natural Science Foundation of China (Nos. 11502086 and 11502087)
文摘The variation of mass, and moment of inertia of a spin-stabilized spacecraft leads to concern about the nutation instability. Here a careful analysis on the nutation instability is performed on a spacecraft propelled by solid rocket booster（SRB）. The influences of specific solid propellant designs on transversal angular velocity are discussed. The results show that the typical SRB of End Burn suppresses the non-principal axial angular velocity. On the contrary, the frequently used SRB of Radial Burn could amplify the transversal angular velocity. The nutation instability caused by a design of Radial Burn could be remedied by the addition of End Burn at the same time based on the study of the combination design of both End Burn and Radial Burn.The analysis of the results proposes the design conception of how to control the nutation motion.The method is suitable to resolve the nutation instability of solid rocket motor with complex propellant patterns.
文摘介绍了一种材料为合金结构钢30Cr Mn Si A的双台阶固体火箭助推器壳体强力旋压工艺方法。通过分析零件的结构特点,确定出采用正向旋压方法,设计相应的旋压毛坯和旋压工装。通过工艺试验过程检测与数据分析,确定出合理的旋压工艺流程,经过生产验证旋压工艺流程的合理性和可行性,旋出满足设计要求的产品,为同类结构壳体旋压提供技术参考。
