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这篇报告综合提出关于624A飞行器、状态A的全部预期的飞行和地面载荷。这里考虑了第1至17次飞行的全部飞行器状态A。适用的状态由624A的芯级和标准鼻锥整流罩组成,假有效载荷重量为800,1500或5000磅。这篇报告分为飞行载荷和地面载荷两个主要部分。因为助推器结构的设计主要是根受据飞行时所承受的载荷,所以首先讨论这一问题。这里提供了飞行全过程的飞行载荷,从发射后不久整个瞬变过程都已衰减消失时起直到包括Ⅰ、Ⅱ和Ⅲ级飞行。发射载荷在地面载荷部分提供。地面载荷条件一般是由规范要求所规定的。然而,在飞行载荷方面,为了确定引起最大载荷的特殊风向和高度等,适当的探索工作是必要的。为此,在文中已详细地提供了如载荷随马赫数和风向的变化等等这些典型形式的资料,以表明最大载荷条件已正确地确定了。最大合成载荷的独特情况是最详细地叙述了。除了最大合成载荷外,还有由各种原因引起的各个载荷分量,如基本飞行弹道载荷、偏差载荷、阵风载荷和抖振载荷都在分别的标题下详细给出了。一些原始数据,像质量特性数据、飞行弹道数据、自动驾驶仪增益和空气动力学数据也给出来了。
This report synthesizes all expected flight and ground loads for the 624A aircraft, State A. This takes into account all aircraft status A from the 1st to the 17th flight. The applicable condition consists of a 624A core and a standard nose cone fairing, with dummy payloads of 800, 1500 or 5000 pounds. This report is divided into two main parts, the flight load and the ground load. Since the design of the booster structure is mainly based on the loads borne on the fly, this issue will be discussed first. The flight loads for the entire flight are provided here, from the moment when the entire transient process has disappeared and disappeared shortly after launch to the time of flight including stages I, II and III. The launch load is provided on the ground load section. Ground loading conditions are generally specified by the specification requirements. However, in the case of flight loads, proper exploration work is necessary in order to determine the particular wind direction and altitude that cause maximum loads. For this reason, typical information such as load changes with Mach number and wind direction, etc. has been provided in detail in the text to show that the maximum load conditions have been correctly determined. The unique case of maximum composite load is described in more detail. In addition to the maximum composite load, there are various load components caused by various causes, such as the basic flight trajectory load, the deflection load, the gust load and the buffeting load, which are given under the separate headings. Some of the raw data, such as quality profile data, flight trajectory data, autopilot gain, and aerodynamic data are also presented.