系统工程与电子技术
繫統工程與電子技術
계통공정여전자기술
SYSTEMS ENGINEERING AND ELECTRONICS
2014年
12期
2484-2489
,共6页
能量管理%主动段制导%终端多约束%弹道优化%固体火箭
能量管理%主動段製導%終耑多約束%彈道優化%固體火箭
능량관리%주동단제도%종단다약속%탄도우화%고체화전
energy management%ascent guidance%multiple constraints%traj ectory optimization%solid rocket
针对不同高度的单箭多轨道运载任务，提出了一种多级固体火箭上升段分步满足终端多约束的能量管理制导方法。火箭前期飞行通过程序指令控制基准弹道，以满足期望的高度与当地弹道倾角约束为目的将弹道优化转参数优化问题处理，减少了约束条件；后期飞行通过姿态交变机动的闭路能量管理制导方法，耗散多余能量控制飞行速度，达到了满足终端速度、高度、倾角等多约束条件的火箭不同高度入轨。仿真结果表明，该能量管理制导方法有效可行且在不同轨道运载任务中具有较好的适用性。
針對不同高度的單箭多軌道運載任務，提齣瞭一種多級固體火箭上升段分步滿足終耑多約束的能量管理製導方法。火箭前期飛行通過程序指令控製基準彈道，以滿足期望的高度與噹地彈道傾角約束為目的將彈道優化轉參數優化問題處理，減少瞭約束條件；後期飛行通過姿態交變機動的閉路能量管理製導方法，耗散多餘能量控製飛行速度，達到瞭滿足終耑速度、高度、傾角等多約束條件的火箭不同高度入軌。倣真結果錶明，該能量管理製導方法有效可行且在不同軌道運載任務中具有較好的適用性。
침대불동고도적단전다궤도운재임무，제출료일충다급고체화전상승단분보만족종단다약속적능량관리제도방법。화전전기비행통과정서지령공제기준탄도，이만족기망적고도여당지탄도경각약속위목적장탄도우화전삼수우화문제처리，감소료약속조건；후기비행통과자태교변궤동적폐로능량관리제도방법，모산다여능량공제비행속도，체도료만족종단속도、고도、경각등다약속조건적화전불동고도입궤。방진결과표명，해능량관리제도방법유효가행차재불동궤도운재임무중구유교호적괄용성。
For carrier missions on different orbits of solid rockets,the segmented ascent guidance with mul-tiple terminal constraints is proposed based on energy management.Flight trajectory is controlled by program commands during the former segment,in which constraints can get reduced as a result of the transition from traj ectory optimization to parameters optimization.Considering that increasing angle-of-attack can decrease ve-locity gain,the latter segment,the last stage of the rocket,adopts a closed-loop energy management guidance to consume the redundant fuel.By alternating attitude the rocket achieves different orbits with terminal constraints of velocity,altitude and local trajectory angle.Simulation results indicate that the proposed guidance strategy shows theoretical feasibility as well as good adaptability in multiple carrier missions.
