某固体发动机反向喷管型面优化设计

某固体发动机推力终止装置结构空间十分有限，为保证推力终止时发动机负推力大于等于零的要求，必须尽可能地提高反推力效率。因此对推力终止装置进行了一系列优化设计，尤其是反向喷管连续锥形型面设计，在总结一般固体发动机研制经验的基础上，将非连续柱面型面改为连续锥形型面。通过理论分析和试验结果表明，该反向喷管的结构可靠性和反向推力效率较高。此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。

The design optimization technique of reverse nozzle contour for a solid motor

The structural space of thrust termination mechanism in the solid motor is very limited.In order to meet the demand that negative thrust of the motor is not less than zero, efficiency of reverse thrust must be improved as far as possible.Therefore, a series of design optimization must be done, especially the design of reversal nozzle continuous conical contour. Based on the experience of general models, non-continuous cylindrical contour was replaced with continuous conical contour.Theoretical analysis and experiment results prove that the structure is more reliable and reverse thrust is more efficient .This technique is available for the design of SRM with reverse nozzle.