Endgame Performance Analysis Of Exo-atmosphere Interceptor

The guidance precision of the endgame guidance of exo-atmosphere interceptor isan important performance indicator. The effect of interceptor can be evaluated byanalyzing its error propagation characteristics, respective actions to improve itsperformance can also be proposed. The endgame guidance of exo-atmosphereinterceptor is selected as the object to study. The relative dynamic equations betweeninterceptor and target in IRPL (the instantaneous rotation plane of line of sight), theanalytic result of the error propagation of LOS rate, the relation between handovervolume error and miss distance as well as major factors affecting guidance and controlprecision are studied in this dissertation.The relative dynamic equations and dimension-reduced analysis method areconducted in IRPL. The three dimensions relative motion is decomposed into therelative motion in IRPL and the rotation of the IRPL. With the advantage of decouplingthe relative motion in IRPL from the rotation of the IRPL, the conclusion is obtainedthat the rotation of the IRPL is ineffective for the effect of interceptor. The erroranalysis of endgame guidance can be carried out on the basis of the above.Based on the Covariance Analysis Describing Function Technique (CADET),the analytic results of LOS rate error propagation characte ristics in the endgameguidance are conducted. Taking LOS rate estimation error and interceptor airframeacceleration limit into consideration, the continuous/discrete-time systems of guidanceand control are analyzed by CADET. In addition, the correctness and efficiency of theequations conducted are verified by Monte-Carlo method.The relationship between handove r volume error and LOS rate error isstudied, whose influence on miss distance is also discussed. Based on covarianceconversion method, taking advantage of the quantitative relationship of the LOS reteand relative state, handover volume error is converted into initial LOS rate error. Thenthe mean and variance of miss distance is conducted, whose validity is verified bysimulation results.The major factors that impact on the guidance precision of the endgameguidance are analyzed. Based on the conducted computational model of errorpropagation of LOS rate and calculation method of miss distance, main factors, LOSrate estimation error, interceptor airframe acceleration limit, guidance control period, aswell as handover volume error, that have an influence on the guidance precision of theendgame guidance are discussed. The relation of each of the factors and guidanceprecision is also obtained.The model, based on CADET, built to analyze the guidance precision of theendgame guidance of interceptor is more accurate and effective than traditional methods, Monte-Carlo, for instance, to study missile’s guidance performance, which can alsopresent a further explanation of the main factors influencing on the guidance precision.The study can be applied to practical engineering of analysis on guidance controlprecision of interceptor.