CAJ | 학술논문

研究了同时具有终端角度(攻击角度)和终端时间(攻击时间)约束的制导问题.通过将非线性运动学制导模型中的自变量由导引时间变换为速度方向角,可以利用最小值原理直接推导出一种闭环形式制导律,而不必引入任何的线性化处理.在该制导律的导引下,导弹能够精确击中目标并且精确满足终端时间和角度的约束.为了研究该制导律的可行性,本文定义并分析了若干重要参数的可行域.该闭环制导律及其可行性分析被应用于多弹齐射攻击的两种情况.数字仿真结果验证了所提出方法的有效性.
연구료동시구유종단각도(공격각도)화종단시간(공격시간)약속적제도문제.통과장비선성운동학제도모형중적자변량유도인시간변환위속도방향각,가이이용최소치원리직접추도출일충폐배형식제도률,이불필인입임하적선성화처리.재해제도률적도인하,도탄능구정학격중목표병차정학만족종단시간화각도적약속.위료연구해제도률적가행성,본문정의병분석료약간중요삼수적가행역.해폐배제도률급기가행성분석피응용우다탄제사공격적량충정황.수자방진결과험증료소제출방법적유효성.
A guidance problem with both impact angle and impact time constraints is investigated in this paper. The independent variable in the nonlinear engagement model is changed from the flight time to the heeding angle of the missile. Then a new closed-form guidance law can be derived based on the transformed engagement model via the minimum principle without any linearization. The proposed guidance law can home a missile to the target with zero miss distance as well as satisfying both of the impact angle and time constraints. Furthermore, to evaluate the feasibility of the proposed law, feasible regions of some key parameters are defined and analyzed. The closed-form guidance law and its feasibihty analysis are applied to several salvo attack scenarios.Numerical simulations are performed to demonstrate the effectiveness of our approaches.