弹道式飞行器惯性制导机电式方法的研究历史

以分析最初的资料和报告为基础,介绍了前苏联进行的弹道式飞行器沿“刚性”和“柔韧”(自适应)轨迹惯性制导机电方法数学论证和研制方面的历史,叙述了以著名惯导专家伊什林斯基为首的学派研究出的飞行器惯性制导方案在3个方面的实现情况:1)在被称作λ,μ惯性制导泛函形式下,使用视加速度积分陀螺仪,可以不用积分计算仪表而在飞行器本体上构成主要的制导方程；2)主要的制导方程可以转换成被称作α,β惯性制导泛函的形式,在飞行器本体上构成该泛函时完全不需要复杂的计算装置；3)所研究的机电方法不仅能够通过修正所设计的主动段的距离实现在垂直平面内对飞行器质心运动轨迹的单参数修正,也即沿被称作“刚性的”轨迹制导,而且还能对所设计的俯仰转弯角进行修正,也即实现双参数修正,沿着被称作“柔韧性的”轨迹制导.对于使用固体火箭发动机,推力调节有困难的情况,后者具有重要的意义.给出了某些方法的方块图,其中包括最简单的一种一按α,β泛函制导的情况.

The History of Inertia Guidance Electromechanical Method for Ballistic Aircraft

Based on the primary documents and research reports,the overview of electromechanical mathematic argumentation and the development of ballistic aircraft towards rigidity and flexility track inertia guidance is presented.The three aspects of the achievement for aircraft inertia guidance scheme proposed by inertia guidance expert known as Ishlinsky are described.Firstly,with the functionality formation of λ,μ inertia guidance,the major ballistic trajectory equations can be generated by avoiding integrating settlement instruments,which applies apparent acceleration integrating gyroscope.Secondly,the formation of α,β inertia guidance universal function can be transformed from the major ballistic trajectory,and the computing mechanism is not required when the universal function is reformed on the aircraft entity.Thirdly,the single-parameter correction of aircraft mass center motion locus is realized in the vertical plane by correcting the designed booster phase distance in the proposed electromechanical method,which is known as rigidity track guidance.In addition,the correction of designed pitchout angle can be achieved as well as the double-parameter correction is realized,which is named as flexible track guidance.Due to the difficulty of the thrust regulation of solid propellant rocket engine,the flexible track guidance shows the significance in practice.The histograms of the proposed methods are illustrated,and the simplest method for the situation of α,β universal function guidance is included to present.