偏转弹头导弹动力学建模研究

摘要

偏转弹头导弹是一种新颖的变外形导弹,通过操纵弹头相对弹体偏转改变导弹的气动特性并产生机动过载.而弹头偏转造成的影响并不局限于气动方面,导弹的动力学模型本身也随之改变.为了发展偏转弹头技术,对其进行动力学建模研究十分必要.文章采用质点系的动量定理和动量矩定理推导了偏转弹头导弹的动力学模型,引入矢量的代数表达形式精简了推导过程,并且采用定性分析和仿真的手段对动力学模型进行了适当的简化,兼顾了模型的精确性和适用性.%Aim. The introduction of the full paper points out that it is not possible practically to make the mass center of the head of deflectable nose missile coincide with the center of hinge. We propose the exploration mentioned in the title with this noncoincidence. Sections 1 through 4 explain our exploration and its evaluation. Fig. 1 in section 2 shows the above-mentioned noncoincidence. Section 3 establishes the dynamics model of deflectable nose missile with the above-mentioned noncoincidence considered; it utilizes momentum theorem, angular momentum theorem and dimension analysis; eqs. (14) through (19) are worth noticing. Figs. 4 through 7 in Section 4 show simulation results. Section 5 , based on section 4' s analysis of simulation results, gives two preliminary conclusions about two simplifying assumptions made by us in establishing the dynamics model of deflectable nose missile with noncoincidence considered: ( 1) one assumption is satisfactory; (2) the other assumption is not satisfactory.