火力与指挥控制
火力與指揮控製
화력여지휘공제
FIRE CONTROL & COMMAND CONTROL
2012年
5期
71-76
,共6页
三体问题%中途修正%连续推力%最优控制%轨道控制
三體問題%中途脩正%連續推力%最優控製%軌道控製
삼체문제%중도수정%련속추력%최우공제%궤도공제
three-body problem%midcourse correction%continuous thrust%optimal control%orbit control
基于小偏差理论,对无摄三体动力学方程沿标称轨道线性化,推导了三体动力模型的误差线性模型.在此基础上,进一步利用该最优控制方法推导了转移轨道周期内的连续小推力控制方案,验证了控制加速度及状态量的收敛.同时针对整周期控制方式在超调后状态量收敛速度慢的问题,通过分段连续推力控制模式(Segmental Continuous Thrust Control,SCTC)来近似瞬时脉冲推力控制模式,并给出了最短分段控制时间的计算方法.实验表明,SCTC模式加快了轨道状态的收敛速度.对于km级入轨偏差,通过1次控制即可使实际轨道收敛至标称轨道.
基于小偏差理論,對無攝三體動力學方程沿標稱軌道線性化,推導瞭三體動力模型的誤差線性模型.在此基礎上,進一步利用該最優控製方法推導瞭轉移軌道週期內的連續小推力控製方案,驗證瞭控製加速度及狀態量的收斂.同時針對整週期控製方式在超調後狀態量收斂速度慢的問題,通過分段連續推力控製模式(Segmental Continuous Thrust Control,SCTC)來近似瞬時脈遲推力控製模式,併給齣瞭最短分段控製時間的計算方法.實驗錶明,SCTC模式加快瞭軌道狀態的收斂速度.對于km級入軌偏差,通過1次控製即可使實際軌道收斂至標稱軌道.
기우소편차이론,대무섭삼체동역학방정연표칭궤도선성화,추도료삼체동력모형적오차선성모형.재차기출상,진일보이용해최우공제방법추도료전이궤도주기내적련속소추력공제방안,험증료공제가속도급상태량적수렴.동시침대정주기공제방식재초조후상태량수렴속도만적문제,통과분단련속추력공제모식(Segmental Continuous Thrust Control,SCTC)래근사순시맥충추력공제모식,병급출료최단분단공제시간적계산방법.실험표명,SCTC모식가쾌료궤도상태적수렴속도.대우km급입궤편차,통과1차공제즉가사실제궤도수렴지표칭궤도.
Base on small deviation theory,the three-body dynamic equations are linearized,and the error linear model of three-body dynamic model is deduced.Then,continuous small thrust controlling law by using optimal control in a transfer period is deduce and the astringency of acceleration and state is also validated.At the same time,aim at the problem that speed of state astringing by total period control mode after overshoot is low,method for calculating the shortest segmental control time is given by using segmental continuous thrust control mode to simulate instantaneous impulse mode.Experiment shows that SCTC mode accelerate astringing speed of orbit state and practical orbit is able to astringe to standard orbit by using only one control with the entering orbit error grade of kilometers.
