Carrier rocket section precise docking coordination method

A technology of a launch vehicle and a coordination method, applied in the field of spacecraft, can solve the problems of poor manual multi-point measurement accuracy, affecting the docking effect, and lengthening the development cycle of the docking coordination node, so as to shorten the development cycle, achieve good application effects, and meet the design requirements. The effect of force transfer requirements
CN112078829AActive Publication Date: 2020-12-15TIANJIN AEROSPACE CHANGZHENG ROCKET MFGCO
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
TIANJIN AEROSPACE CHANGZHENG ROCKET MFGCO
Publication Date
2020-12-15

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Abstract

The invention provides a carrier rocket section precise docking coordination method. The method comprises the following steps of: step 1, precisely measuring the relative positions of a first end faceand a second end face, and obtaining data of the relative positions of the first end face and the second end face; step 2, precisely measuring the relative positions of a third end face and a fourthend face, and obtaining data of the relative positions of the third end face and the fourth end face; step 3, selecting an intermediate coordinate system for fitting of the data finally obtained in the step 1 and the step 2; and step 4, carrying out intermediate coordinate system conversion fitting of the data finally obtained in the step 1 and the step 2 to obtain a docking gap characteristic data packet between a storage tank and a shell section. The carrier rocket section precise docking coordination method solves the technical problems that defects such as lag of docking coordination nodes, prolonged development period and poor manual multi-point measurement precision exist in the docking process of a novel storage tank and a shell section in the prior art, and the docking effect is affected.
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Description

technical field

[0001] The invention belongs to the technical field of spacecraft, and in particular relates to a precision docking coordination method for launch vehicle segments. Background technique

[0002] In the structure of the launch vehicle, the propellant tank and all the shell segments constitute the shell of the rocket, which is the main load-bearing part of the rocket body structure. End-frame docking coordination is the most commonly used docking structure for the assembly and docking of various segments of a launch vehicle. After the end faces of the frames at both ends of adjacent segments are aligned, the mechanical connection of the two segments is completed through a number of bolts to realize the coordination of segment docking and rocket body structure. For force transmission, generally only one butt joint surface is designed between two sections, such as figure 2 shown.

[0003] Due to the special force transmission structure requirements of the new-t...

Claims

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