Growing the number of satellites ready to be launched emphasizes the need for reduction of SPACE hardware and subsystems cost, volume, and mass. Realizing these reductions can be implemented deploying new mechanisms for SPACE STRUCTURES. The performance benefit margin of deploying STRUCTURES increases, as the size of the structure increases. Thus, it makes the technology more attractive for large-scale SPACE systems. Examples of satellite components benefiingt from the utilization of inflatable STRUCTURES including solar arrays, gravity gradient booms, communication antennas and solar sails. This paper discusses different types of deploying mechanism with their advantageous and disadvantageous focusing on solar arrays and required driven equipments after being placed in an operational orbit.

In this paper, we choose an approach to generalize the idea  of usual norm keeping up  analogous structure and introduce a  generalized norm, called  $ \Phi $-norm using a  function $ \Phi $ which satisfies some special condition. We show that the induced metric of it is $ \phi $-metric. We also study some basic properties and obtain some fundamental results in such  SPACEs.

In this article, the ant colony method is utilized for topology optimization of SPACE STRUCTURES. Strain energy of the structure is minimized while the material volume is limited to a certain amount. In other words, the stiffest possible structure is sought when certain given materials are used. In addition, a noise cleaning technique is addressed to prevent undesirable members in optimum topology. The performance of the method for topology optimization of SPACE STRUCTURES are demonstrated by three numerical examples.

A set of locally product STRUCTURES on tangent manifold TM of a SPACE form M is pointed out. This is found in a study of a type of Sasaki metric whose second term is a special deformation of the first one. Introducing an adequate almost product structure we find at first a large class of locally almost product STRUCTURES on TM for a (pseudo)-Riemannian manifold M. When M is a SPACE form, a subset of it is made of locally product STRUCTURES.

Sandwich panels are used in various industries due to their high special strength. It is used in ultra-light aeroSPACE STRUCTURES. In this paper the protective effect of sandwich STRUCTURES used in ultralight SPACE STRUCTURES against gamma rays is investigated. Eight STRUCTURES of the most widely used STRUCTURES used in SPACE STRUCTURES such as telecommunication antennas and satellite bodies are exposed to radioisotopic sources of gamma rays (Amercium barium and cesium) with energies of 60 kV, 80 kV, 382 and 66 kV, have been compared to each other. Surface material (aluminum and carbon), surface thicknesses and honeycomb cell dimensions are the most important evaluation parameters. In this paper, different STRUCTURES have been compared using the "special protection" parameter and the best structure from a protection perspective has been identified and reported.

1. Introduction: Optimization by explicit and deterministic variables is called deterministic optimization. It is known that there are wide varieties of uncertainties which are originated from the errors in modeling and simulation and condition of services such as changes in loading. Moreover, we must consider these uncertainties in different stages of design process of STRUCTURES. Some of the most important factors which should be considered in structural designing are variation of material properties, geometrical dimensions of the STRUCTURES, and the loading patterns. On the other hand, deterministic optimization on STRUCTURES uses the strong safety factors instead of uncertainties. Thus, the resultant designed-STRUCTURES are leading to the excessive conservative STRUCTURES that would not be economical and optimal. According to, existing some uncertainties in each level of engineering design process; it is required to consider safety factors in computation of the deterministic optimization. In order to resolve this problem, an efficient approach is recently developed which is called reliability based optimal design. In this method the safety of STRUCTURES are evaluated based on the failure probability and the aforementioned uncertainties are modeled by the probability distribution of random variables. Finally, the investigated components embedded in the assessed acceptable ranges of safety which is introduces with the failure definition. This practical method can be applied to different STRUCTURES...