Abstract
In order to solve the problems of difficult assembly and adjustment and poor operation accessibility in the assembly process of multi-point pressure-type large-scale equipment on spacecraft, this paper presents a method of multi-point compact assembly of space mechanism driven by measurement. The method establishes the geometric constraint mathematical model of the equipment pressing mechanism, proposes the assembly coordinate system based on the mounting hole and the compensation method based on the rigid body transformation, and develops the relevant software according to the method. This method has been verified during the installation of the equipment and has achieved good results, which can be used as a reference for other digital assembly methods of aerospace equipment.
Highlights
In recent years, digital assembly technology has flourished, and because of its high precision, high efficiency and low risk, it is gradually replacing traditional assembly technology
In order to solve the above problems, considering that the mounting holes of the pressing mechanism are provided on the tooling and the reference assembly, and the hole position layout is consistent with the topological relationship, the installation hole of the pressing mechanism at some specific positions is taken as the reference hole position established in the coordinate system
According to the existing working conditions, there are three options for selecting the measured value of the mounting hole of the pressing mechanism as follows: - Select the design theoretical value given by the design coordinate system and the coordinate system transfer route is from the design coordinate system to the assembly coordinate system; - Select the measured value obtained by the designer according to the physical measurement and verification
Summary
Digital assembly technology has flourished, and because of its high precision, high efficiency and low risk, it is gradually replacing traditional assembly technology. In order to ensure that the equipment does not damage during the launching process, the connection mode between the equipment and the spacecraft cabin is designed as a multi-point compression self-locking connection[4,5]. Multi-point compression equipment assembly generally uses the position and attitude of the pressing mechanism that the gasket adjustment device cooperates with the cabin. There is a problem of poor accessibility during the installation and alignment of the equipment due to the relatively complicated layout position of the equipment pressing mechanism. Aiming at the structural characteristics and assembly requirements of a certain type of multi-point pressuretype large-scale equipment on manned spacecraft, this paper proposes a measurement-driven multi-point compression fitting method to solve the problems of difficult installation and adjustment, poor accessibility and low efficiency exist in the loading process of this kind of equipment
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