| 固体火箭发动机性能蜕变的压强补偿 |
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| 引用本文： | 陈德恩,郭乃林,杨建军,邓建军.固体火箭发动机性能蜕变的压强补偿[J].推进技术,1996,17(5):35-38. |
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| 作者姓名： | 陈德恩 郭乃林 杨建军 邓建军 |
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| 作者单位： | 陕西三原空军导弹学院 |
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| 摘 要： | 介绍了采用缩小喷管喉径的方法，对固体火箭发动机燃烧室压强和推力进行补偿，以达到延长发动机使用寿命的目的。
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| 关 键 词： | 固体推进剂火箭发动机，推进剂燃速，内弹道计算，使用寿命 |
PRESSURE COMPENSATION FOR PERFORMANCE DEGENERACY OF SOLID ROCKET MOTORS |
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| Chen Deen,Guo Nailin,Yang Jianjun and Deng Jianjun.PRESSURE COMPENSATION FOR PERFORMANCE DEGENERACY OF SOLID ROCKET MOTORS[J].Journal of Propulsion Technology,1996,17(5):35-38. |
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| Authors: | Chen Deen Guo Nailin Yang Jianjun and Deng Jianjun |
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| Institution: | Air Force Missile Inst.,Sanguan,Shanxi,713800;Air Force Missile Inst.,Sanguan,Shanxi,713800;Air Force Missile Inst.,Sanguan,Shanxi,713800;Air Force Missile Inst.,Sanguan,Shanxi,713800 |
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| Abstract: | or double base propellant,the experimentally measured values of burning rate reducewith storage or servile, so the chamber pressure and thrust of solid rocket motor(SRM)also reduce,which is call"degeneracy".For SRM with a regulating nozzle,the regulating of critical area A, dependson not only initial temperature Ti but also serviced years of grain. On the basis of ex-factory value Atothe reduce Ae can compensate completely "pressure degeneracy"and compensate basically"thrustdegeneracy"according to the number of service years and using the"pressure steadiness regulationmethod". |
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| Keywords: | Soled propellant rocket motor Propellant burning rate Interior ballisticcalculation Service life |
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