Objectif
The stress and strain exist in many elements of space platforms, antenna sets and in other parts of space structures. Such apparatus are subjected to significant force and/or temperature loads. The goal of this project is elaboration of theoretical methods for control of stress and strain (or shape stability) in space structure. The receipt of the prescribed stress and strain (and/or displacements) can be realized by control at the stage of manufacture of the structure and at the stage of exploitation. The control parameters at the stage of manufacture are the scheme of lay-up of composite material (number and angles of different layers of fibers) and mechanical properties of the material (Young's modulus, Poisson's ratio). At the stage of exploitation complementary heating or cooling may realize the control.
The effective way is the use of control elements (piezo-actuators) with appropriate position, size and voltage. In the proposed project, the effective methods for theoretical analysis of optimal control of thermal stress and strain in space construction will be elaborated. The problem of obtaining the prescribed thermal stress and strain (shape control) distribution in structure during its thermo-elastic (or thermoplastic) deformation will be formulated as an optimisation problem of mechanics of deformable solids. For solution, the objective function describing a thermal stress distribution will be introduced. An algorithm for the solution of that optimisation problem is based on non-linear numerical methods. The control parameters are: number and angles of different layers of composite material at the stage of manufacture, Young's modulus, Poisson's ratio of material, position and size of control elements (piezo-actuators) at the stage of exploitation, their voltage. Analogous approach will be introduced for receipt of the prescribed thermal strain and/or displacement distribution (shape control). The algorithm and computer programs will be compiled. These results are directly applied in engineering of optimal design of space structures. The optimal design of elements of space platform will be accomplished. At the final stage of the project, the experimental verification of received results will be performed.
Appel à propositions
Data not availableRégime de financement
Data not availableCoordinateur
1040 Wien
Autriche