文中按硬制导和软制导两种形式讨论了宇航器的入轨控制。所谓硬制导,对宇航器与目标的相遇速度没有要求,而软制导则要求相遇的相对速度为零。制导的自适应性表现为制导方程的制导系数可以在弹上自动确定。为了这些系数计算的精确与方便起见,文中还提出了算法时刻的概念,可以选择它与关机时刻相重合,也可以不重合。这为考虑制导方程中测量数据的误差曲线特性提供了依据与实际处理方法。宇航器的准确入轨,要求在轨道测量数据与控制参数之间建立准确的数量转移关系。这关系,随着宇航要求的提高,日益多样化了。本文将按两种制导形式,即硬制导与软制导进行讨论。后者入轨时要求宇航器的有效负载与目标相遇的相对速度为零,前者则不必。同时本文还将研究如何在弹上对上述数量转移关系中的制导系数实现自动选择。这将增加宇航器本身选择目标的机动性以及某些控制过程的自动化程度。例如,以卫星轨道形式运行于空间的宇航器,自动地准确地选择地面落点,等等。通常,为了制导的简易可行以及最佳化的目的,控制作用分成为程序控制部分与提高精度的控制部分(上称这部分为控制规律),这种分类在系统综合设计中体现为同样的两个步骤。我们也采用这一思想,所不同的是把精度控制中的一部分内容拿出来,移置到程序控制中去。粗略地说,程序控制是不考虑干扰因素时的控制规律,而提高精度控制则要考虑。刚说的“移置”,就是指把制导方程的具体形式的确立,放到弹上去完成,而不是在地面先定好。这样,在新的意义上,包含这部分内容的程序控制也就不能说没有考虑干扰因素了。 According to hard guidance and soft guidance, the article discusses the orbital control of spacecraft. The so-called hard guidance, the spacecraft meets the target speed is not required, but the soft guidance requires the relative speed of encounter is zero. Guidance adaptive performance as the guidance coefficient of the guidance coefficient can be automatically determined on the bomb. In order to calculate the exactness and convenience of these coefficients, the article also proposed the concept of algorithm moment, which can be chosen to coincide with the moment of shutdown, or not coincide. This provides the basis and practical method for considering the error curve characteristics of the measured data in the guidance equation. The exact orbit of the spacecraft requires that an accurate quantitative transfer relationship be established between the orbital measurement data and the control parameters. This relationship is increasingly diversified as aerospace requirements increase. This article will be guided by two forms, namely, hard-guided and soft guided discussion. The latter requires that the relative speed at which the payload of the spacecraft meets the target is zero, and the former does not have to. At the same time, this article will also study how to automatically select the guidance coefficient in the above quantitative transfer relationship on the bomb. This will increase the maneuverability of the spacecraft’s own selection of targets and the degree of automation of some control processes. For example, astronauts that operate in space in the form of satellite orbits, automatically and accurately select the ground fall, and so on. Usually, for the purpose of guidance, simplicity and optimization, the control action is divided into a program control part and a control part for improving accuracy (this part is called control law). This classification is reflected in the system integrated design as the same two Steps. We also adopt this idea, the difference is that the accuracy control part of the content out, transferred to the program control. Roughly speaking, the program control is to control the law without disturbing factors, and improve the accuracy of control should be considered. Just say “displacement”, refers to the establishment of the specific form of guidance equation, put it on the bomb to complete, rather than on the ground first set. Thus, in the new sense, program controls that include this part of the world can not be said to have disregarded interference.