- 期刊
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鼻錐罩偏折斜率及接戰時間對氣動控制飛彈之穩定性和性能影響分析
Stability and Performance Analyses of Radome Refraction Slope Errors and Time-To-Go on Aerodynamically Controlled Missiles
摘要
本文首先針對鼻錐罩偏折(radome refraction)效應對飛彈系統穩定性及引致之誤失距離(miss distance)提出理論分析及電腦數值模擬結果。文中導出線性及非線性鼻錐罩誤差對飛彈穩定性之定量分析結果，由該結果，系統設計者可簡易地估測全彈所能容忍的鼻錐罩偏折斜率誤差(radome refraction slope error)上限，而不致於在高空攔截狀況下，因爲該寄生誤差導致系統不穩定。爲補償鼻錐罩誤差，本文亦提供一簡易設計準則可供參考。其次，本文利用有限時間超穩定性理論(finite time hyperstability theory)，導出歸向迴路穩定需求下飛彈系統所能容許的接戰時間(time-to-go)範圍。文中針對比例導引系統各項參數變化對穩定接戰時問範圍的影響進行電腦數值解算及分析。利用所提出的量化分析結果，設計者可根據任務特性，調整適宜的穩定接戰時問範圍，亦可據此評估系統參數對終端穩定性及飛彈性能之影響。
並列摘要
This paper provides theoretical and numerical simulation analyses for the radome refraction effect on stability and induced miss distance of missiles guided by proportional navigation. Quantitative results for the stability analysis are derived with respect to linear and nonlinear radome errors, by which system designers could easily estimate the permissible upper hound such that the parasitics will not cause instability during high altitude engagement. A simple compensator design criterion is proposed to compensate the errors. Furthermore, the finite time hyperstability theory is used to derive a feasible range of time-to-go under which proportional navigation systems will remain stable. We show with some numerical studies that the changes of the design variable directly affect the stability range of time-to-go. Based on our proposed results, missile system designers could easily tune an appropriate stability range of time-to-go according to the specific characteristic of targets to be intercepted.