Methodology of spacecraft structural components position fine adjustment

Design, construction and manufacturing of flying vehicles


Boyko S. O.

Compani «Information satellite systems of academician M.F. Reshetnev», 52, Lenin str., Zheleznogorsk, Krasnoyarsk region, 662972, Russia



With significant increase of satellite structural components size specifics of their relative position adjustment occur, associated with singular masses separate by a certain distance and structural elements coupling them.

All structural components are affected by various space factors, including temperature impact, which leads to satellite structure optimal geometric disposition changing due to deformations. The author suggests employing the six-degree-of-freedom adjustment actuator to ensure fine adjustment.

To control the adjustment device movement the author suggests the methodology based on implementation of measuring machine, three measuring spheres and an algorithm for measurement results processing. Contacting the spheres in at least four points, the measuring machine computes the coordinates of the position of each sphere’s center, which defines the spatial position of the adjustment device upper base. Data spheres’ centers position control is performed at the initial position (prior to spacial movement performing) and end position (after spacial movement performing). Position determining technique consists in the following. Using the obtained coordinates, we determine the values of the three linear and three angular movements of the plane, formed by the centers of the three spheres.

To determine the movemeents one should compute coefficients of coordinates’ transformation matrix for the displacement from the initial position to the end position.

Analyzing theoretical (defined by control block) and actual (computed from co-ordinate measuring device data) values of the adjustment actuator spatial movement allows evaluate transmission errors for every degree-of-freedom. Specified errors led to satellite structural components relative offset in an area, which depends on their distance from each other.

The proposed final adjustment methodology of structural elements and mechanical devices allows account for interaction of separate actuators in adjustment devise and structure of satellite geometry changing to achieve the specified parameters during ground experimental tests and on-orbit satellite functioning.


satellite, fine adjustment mechanism, reference point, six degree-of-freedom actuator


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