固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2014年
4期
435-441,462
,共8页
耗尽关机%能量管理%动态逆%多约束%固体火箭
耗儘關機%能量管理%動態逆%多約束%固體火箭
모진관궤%능량관리%동태역%다약속%고체화전
depleted shutdown%energy management%inverse dynamic%multi-constraints%solid rocket
针对具有速度控制能力的固体火箭多约束耗尽关机问题,建立以多余视速度增量为状态量的新型能量管理模型,分析了该模型能量管理动态特性,提出一种闭环动态逆能量管理( IEM)方式,得到了无约束和有约束关机时能量管理的收敛条件,并据此设计了IEM的2种具体实现。最后以数学仿真验证了该方法的特性、能量管理效果,分析了与其他2种闭环能量管理方法---通用能量管理(GEM)、样条能量管理(SEM)的异同。结果表明,IEM方法鲁棒性强、精度高、姿态变化缓慢,能量管理范围大,一组固定的参数实现了2.1%~83.3%的能量管理;当能耗小于41.3%时,关机点速度偏差小于0.25 m/s,速度倾角小于0.014°,姿态角速度小于0.25°/s,攻角小于5°。
針對具有速度控製能力的固體火箭多約束耗儘關機問題,建立以多餘視速度增量為狀態量的新型能量管理模型,分析瞭該模型能量管理動態特性,提齣一種閉環動態逆能量管理( IEM)方式,得到瞭無約束和有約束關機時能量管理的收斂條件,併據此設計瞭IEM的2種具體實現。最後以數學倣真驗證瞭該方法的特性、能量管理效果,分析瞭與其他2種閉環能量管理方法---通用能量管理(GEM)、樣條能量管理(SEM)的異同。結果錶明,IEM方法魯棒性彊、精度高、姿態變化緩慢,能量管理範圍大,一組固定的參數實現瞭2.1%~83.3%的能量管理;噹能耗小于41.3%時,關機點速度偏差小于0.25 m/s,速度傾角小于0.014°,姿態角速度小于0.25°/s,攻角小于5°。
침대구유속도공제능력적고체화전다약속모진관궤문제,건립이다여시속도증량위상태량적신형능량관리모형,분석료해모형능량관리동태특성,제출일충폐배동태역능량관리( IEM)방식,득도료무약속화유약속관궤시능량관리적수렴조건,병거차설계료IEM적2충구체실현。최후이수학방진험증료해방법적특성、능량관리효과,분석료여기타2충폐배능량관리방법---통용능량관리(GEM)、양조능량관리(SEM)적이동。결과표명,IEM방법로봉성강、정도고、자태변화완만,능량관리범위대,일조고정적삼수실현료2.1%~83.3%적능량관리;당능모소우41.3%시,관궤점속도편차소우0.25 m/s,속도경각소우0.014°,자태각속도소우0.25°/s,공각소우5°。
To solve the energy management problem of a solid rocket with multi-constraining depleted shutdown,a novel inverse dynamic energy management (IEM) method was proposed.Firstly,a novel model based on excess velocity capability was estab-lished,and its performance was studied.Secondly,a closed-loop IEM method with two specific realizations was proposed, and the constrained and unconstrained convergence condition was discussed.Finally,the IEM's performance,energy manage results and the difference with general energy management ( GEM) and spline energy management ( SEM) were verified by computer simulation, which demonstrates a strong robust,high control precision, low attitude maneuver,small terminal angle of IEM.Indeed,IEM can suc-cessfully manage 2%~83.3% energy under a sort of fixed parameters.As the ratio of excess energy is below 41.3%, the terminal ve-locity is less than 0.25 m/s,the flight-path angle is less than 0.014°,the attitude angular velocity is less than 0.25°/s,and the angle of attack is less than 5° .