CAJ | 학술논문

为精确预测拦截高速飞行的临近空间飞行器时的零控脱靶量，根据拦截临近空间飞行器的特点对拦截弹及目标飞行器动力学模型进行了合理简化，推导了拦截弹与目标飞行器相对运动状态解析表达式，得出了一种具有较高精度的零控脱靶量解析计算方法。为验证该算法精度，建立了尽可能接近真实情况的动力学模型，并采用数值积分方法进行仿真对比，结果表明该算法精度较高。将该算法应用于一个简单的中制导律，证明了其在拦截临近空间飞行器时的可行性。
위정학예측란절고속비행적림근공간비행기시적령공탈파량，근거란절림근공간비행기적특점대란절탄급목표비행기동역학모형진행료합리간화，추도료란절탄여목표비행기상대운동상태해석표체식，득출료일충구유교고정도적령공탈파량해석계산방법。위험증해산법정도，건립료진가능접근진실정황적동역학모형，병채용수치적분방법진행방진대비，결과표명해산법정도교고。장해산법응용우일개간단적중제도률，증명료기재란절림근공간비행기시적가행성。
To accurately predict the zero effort miss for intercepting the near space aircraft(NSA) with high velocity,three-dimensional simplified dynamic model was presented according to the characteristics of NSA,which was transformed into linear differential equation with constant coef-ficients.The analytic expressions of motion of interception missile relative to aircraft was deduced.The high-precision method of calculating zero effort miss was obtained.To verify the precision of the method,the dynamic model as close to the actual conditions as possible was built, and the comparison was carried out by numerical integration.The simulation results show that the analytical formula is feasible.The zero effort miss calculation was applied in a simple mid-course guidance law to verify the interception effect in engineering application.