Structural Design And Analysis Of Deployable Parabolic Cylinder Antenna And Fractionated Payloads

Space exploration is an important way to develop space science. It is not only a significant direction of space technology, but also a frontier in which the worldwide space powers compete fiercely. Currently, in addition to expand traditional methods, space powers have been giving priority to cultivate the burgeoning new methods to explore the space, and they all want to occupy the domination of the space exploration technology. Focusing on the requirements and applications of space exploration vehicles, this thesis took two specific space exploration programs of China into account: XXX space exploration satellite program and netted fractionated payloads exploration program for terrestrial physical field exploration on multiple scale. The design and analysis of the structures of the deployable antenna and the fractionated payloads was presented, including facilities layout design.With the assistance of Computer-Aided Design(CAD) and Computer-Aided Engineering(CAE), and featured the design and analysis of the structures of spacecraft, this thesis did research in the design of reflectors structures of the deployable antenna, and the design of the structures of fractionated payloads, and the design of facilities layout design.First, according to the requirements of the reflectors of deployable antenna, a preliminary design was carried out mainly in two aspects: the structure of the frame carrier and the mechanical interface. And a design combine the structure topology, material, size and the mechanical interface was brought forward. By implementing the structure dynamic analysis, the above design proposal was proven to satisfy all the requirements. However, if the analysis results was kept under observation, there is still some space for optimization. Therefore, an optimization was launched on the aspects of the structure mass, structure topology and the mechanical interface. Then, the structure dynamic analysis was implemented on the optimized structure, including modal analysis, acceleration analysis and sine oscillation analysis. With the satisfaction of the requirements, the analysis results suggested a substantial increase in the structure rigidity and strength.Second, concerning the problems from the national and international study, and to meet the design constraints, the design of structure and facilities layout of the fractionated payloads was carried out in the second part of the thesis. The design was discussed from two respects: the facilities layout and the primary structure, while both of which could restrain each other and interact mutually. In the context of attempting to satisfy all of the demands from all subsystems, the facilities layout were implemented in the first place. And then, the design primary structure launched immediately, along with the corresponding adjustments of the layout in detail. As the primary structure was completed, it was analyzed by model analysis and acceleration analysis. And the analysis results indicated that the above design was capable of satisfying all the requirements and had certain feasibility.The facts contributed to the research on the design of spacecraft structure were listed as the following:a. A relatively complete solution to the frame carrier of the reflectors in jumbo size, high precision and light weight was presented, including material selecting, structure topology, ribbed slab size and the mechanical interface, etc.b. A relatively feasible optimization approach to the frame carrier of the reflectors was offered, by which an optimized plan was completed, and had a decent optimal effect.c. Under the condition of multiple devices and strict constraints, a solution to the facilities layout of the nano-satellite was proposed. The solution could fill the demand, had more conveniences in the equipment installation and sufficient space for cable.d. Subjected to the strict constraints, a relatively complete solution to the primary structure for the nano-satellite was proposed. It only kept the weight of the primary structure account for 20% of the whole satellite, with sufficient power supply and high stiffness and strength.