CAJ | 학술논문

为尽可能避免导弹固体发动机故障引发全弹自毁造成飞行失败，针对固体发动机喷管和喉衬故障常出现在关机附近的情况，采用子级弹体自毁方案，提出一种适用此方案的自适应制导方法，对导弹上面级发动机能量进行最优管理，在能量充足时确保导弹仍能成功完成打击任务。仿真结果表明，该自适应制导能量管理有效，方法误差小，证明了方法的正确性。
위진가능피면도탄고체발동궤고장인발전탄자훼조성비행실패，침대고체발동궤분관화후츤고장상출현재관궤부근적정황，채용자급탄체자훼방안，제출일충괄용차방안적자괄응제도방법，대도탄상면급발동궤능량진행최우관리，재능량충족시학보도탄잉능성공완성타격임무。방진결과표명，해자괄응제도능량관리유효，방법오차소，증명료방법적정학성。
Self?destruction of whole missile and flight failures resulted from by the fault of the solid engine of missile should be avoided to the largest extent.In the paper,for the nozzle and throat insert fault of the solid engine,a safety self?destruction project of the missile substage body and the adaptive guidance method for it were put forward,by optimization of energy management for the upper stage engine,which ensue that the missile can still accomplish the impact task when the engine energy of the upper stage en?gine is enough.The results show the energy management of the adaptive guidance method is valid and there is little error by simula?tion calculation.