Structure of deployable space parabolic-reflector antenna

One of the basic requirements to parabolic-reflector aerials is observance of requirements on execution of the set curvature of a form-building surface. In case of transformed aerials when the reflecting surface finishes and stretches while deploying, this requirement is supplied with high rigidity of a structure. At low rigidity mutual geometrical displacement of the interface points of attachment of a reflecting cloth to a structure is inevitable that attracts to deviations of the form of a reflecting surface from nominal. Another major aspect of designing of space engineering is decrease in final weight of a product. The most typical line of designing of various systems of space vehicles is compromise search between decrease in weight of a product, and, as consequence, decrease rigidity and strength properties of a structure. In the article the proposed option of a design of a transformed parabolic-reflector aerial is offered. The basic load-bearing element is thin-walled composite torus, divided into some segments. Selection of the given type of a structure is proved by two kinds of analyses: the kinematic analysis of a deployment from a shipping rule in working, and the mechanical analysis for reliability acknowledgement on strength. The parametric analysis of geometry of a design is carried out, optimum versions are shown. For deeper optimization of design parameters it is necessary to carry out the following engineering analyses which have been not presented within the limits of the given article: - the analysis of reliability of a deployment of mechanical devices; - the modal analysis; - the analysis of temperature deformations and so forth. The given design can be applied as the power basis to parabolic-reflector aerials, screens, and cluster orbital systems.