论文部分内容阅读
本文讨论了地-地弹道导弹惯性制导的一种方法——闭路制导。在主动段中,导弹在飞出大气层前按固定程序控制,飞出大气层后采用“闭路制导”。“闭路制导”是:利用国外提出的“需要速度”概念,根据导弹当时的“状态”(速度(?)、位置(?)及时间t)和目标的位置(?)_T,实时地确定出“需要速度”(?)_R,并求出(?)_g=(?)_R—(?);而后控制弹的推力方向,使弹的绝对加速度(?)与(?)_g一致,以保证(?)_g在最短时间内达到零;当(?)_g=0时,关闭发动机。按照“需要速度”的定义,关机后导弹将经过被动段飞行而命中目标。本文主要解决了以下几个问题: 1.将带有一阶扁率的地球引力加速度展成级数,并在此基础上导出解算(?)、(?)的递推公式,避免了数值积分,简化了计算; 2.参考国外资料,系统地推导整理出两套计算(?)_R的公式; 3.根据使(?)与(?)_g一致的原则,给出了具体的导引计算公式; 4.为减少弹上计算机计算时延所造成的关机误差,而采取了两个措施:一是在关机点附近简化计算,从而减小计算步长;二是对关机时间进行线性预报。使计算机时延造成的导弹落点偏差降低到几十米。 实际计算结果表明,闭路制导的方法误差(包括计算机时延误差、被动段地球扁率计算误差等)小于100米,可见精度较高。它对弹上计算机的要求是:(1)平均计算速度十?
This paper discusses a method of inertial guidance of ground-to-ground ballistic missiles-closed-circuit guidance. In the active segment, the missiles were controlled by a fixed procedure before they flew out of the atmosphere and “closed-circuit guidance” was adopted after they had flown out of the atmosphere. The “closed-circuit guidance” is to make use of the concept of “required speed” proposed by foreign countries to determine in real time the missile’s “state” (speed, position and time) and the target position And then control the thrust direction of the projectile so that the absolute acceleration of the projectile (?) Agrees with (?) _g to ensure that the velocity of the projectile (?) _R is equal to (?) _g (?) _ g reaches zero in the shortest time; when (?) _ g = 0, turn off the engine. According to the definition of “required speed”, the missile will hit the target after passing through the passive section after shutdown. This paper mainly solves the following problems: 1.Expanding the gravitational acceleration of the Earth with first-order flattening rate into series, and on this basis, derive the recursion formula of solving (?), (?), Avoiding the numerical integral , Simplifying the calculation; 2. With reference to foreign data, systematically derive two sets of formulas to calculate (?) _ R; 3. According to the principle of making (?) Consistent with (?) _g, Formula; 4. In order to reduce the computer error caused by the shutdown delay caused by the error, and has taken two measures: First, in the vicinity of the shutdown point to simplify the calculation, thereby reducing the calculation steps; Second, the shutdown time linear prediction. The delay caused by the computer missile landing point deviation to tens of meters. The actual calculation results show that the error of closed-circuit guidance method (including the computer delay error and the calculation error of the Earth’s oblateness in the passive section) is less than 100 meters, showing a higher accuracy. It bomb on the computer requirements are: (1) the average computing speed of ten?