Abstract
Space technology is the core competitiveness of a powerful country. Space maintenance technology has just started in our country. The biggest innovation of this article is to design a set of interface system, which is suitable for on-orbit maintenance of space science instruments. It represents that this technology from scratch in our country. A new measuring method is proposed. According to the homogeneous coordinate transformation, the mathematical models of the relationships between fit clearances of interface system and the six-degree of freedom change of the maintenance module are derived. According to the index requirements, the corresponding fit clearance and repeat positioning accuracy are determined. Set up an experimental platform, and use autocollimator and laser tracker to measure the repeated positioning accuracy of the module. Based on the theory of small displacement, the least square method is used to deduce the rotation angle and translation amount of the module through the change of the characteristic point coordinates. The experiment proves that the interface meets the requirement of on-orbit maintainable operation, and the experimental data proves that the theoretical equation is correct. Providing engineering reference for other space maintenance scientific instruments.
Highlights
In a complex space environment, all space science instruments may at any time affect their value due to failure, degradation or obsolescence
The maximum error of the angle measured by the laser tracker relative to the data of the autocollimator in the three directions of XYZ is less than 11%, which proves that the rotation angle measured by the two instruments is true and reliable
The relationship between the theoretical rotation angle and the fitting clearance is derived, and the fitting clearance of the mechanism is designed with the rotation angle index as a constraint
Summary
In a complex space environment, all space science instruments may at any time affect their value due to failure, degradation or obsolescence. The clearance of the interface mechanism determines the repeated positioning accuracy of the back-end module, which must be reasonably allocated. Interface A restricts the three translation of the module in space and releases three rotational degrees of freedom in space. The principle of releasing thermal stress on-orbit: Since the degrees of freedom of the three translation directions of point A are completely limited, when the space temperature changes, the module will deform uniformly along the XY directions. B. SPACE LAYOUT OF INSTALLATION INTERFACE The plane of three points ABC is parallel to the focal plane, and the center of the three points coincides with the projection of the center of the focal plane in the direction of the optical axis. There are 24 different combinations of the form of the module change matrix F, all of which can be approximated with F1 Means
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