design structure matrix

A new approach is presented for the management of controlling the changes in design process of a triaxis gyroscopic stabilizer for a camera mounted on a flying robot. It includes decision-making and the way of identifying the best Investigation of the control process. As a prototype, the Phantom Flying Robot is considered with 32 components which half of them are related to the geometry of its drone and the others to the triaxis gimbal. Structural links between elements the assumed to be symmetric and are arrayed in a design structure matrix. A constant value for change effect for all links is assumed as well as three values: 0.3, 0.5, and 0.8 for low, medium, and high change properties respectively. Additionally, various components of the system are classified as acceptors or reflectors of changes with aid of some indicators. A normal change diffusion index between -1 and +1 shows the relative strength of each component in absorber-to-enhancer spectrum. The method is implemented in the prototype.

The purpose of this research is design of solar panels for a satellite which put in to geostationary orbit considering siutable reliability. The process of solar panel design is conducted according to the Design Structure Matrix (DSM) method. In this regard, an initial plan, a subsequent design process improvement, and a final optimized design process are provided. The first level of designed mechanism product tree includes released mechanism, development mechanism, lock and rotation components. Given the importance of ensuring the proper operation of mechanisms in space and reported mission failures due to lack of mechanism’s operation, the reliability network of designed mechanism is constructed and the reliability of designed panel is calculated. The amount of achieved relaiability is then verified according to the mission and system engineering requirements. Nessecary changes are applied on initial design to achieve into the satisfactory reliability for whole solar mechanism. In this regard, the critical paths in reliability network which lead to reduced reliability are investigated, and improvement of the critical path are proposed, to the extend of increasing reliability by discarding redundant components for critical parts.

In this paper, we introduce a new system design process for a cube satellite system which in turn, the design structure matrix method as a powerful design tool is employed for the system analysis. The cube satellite is a type of Pico satellites and the proposed systematic design process is applied to a typical version of these satellites type by illustrating, optimizing the dependency of design parameters driving the satellite conceptual design phase. Based on the systematic decision making logic including in the DSM approach, system design framework could be decomposed into smaller components and parts in design matrix which could show the dependency inherently defined between the actual satellite designs parameters. This fact is demonstrated, based on the supporting theory and considered case study, which the design parameters should influence the selection of each component at multiple levels of design requirements, mission, system and subsystem specified. Finally, the design matrix is developed and should be analyzed for a basic student cube satellite and then design structure matrix could support the enhancing the design formation parameters. In this case, 135 systematic driving and design parameters of cube satellite are identified based on a conceptual design phase activity and then these parameters passing through mathematical clustering procedures to form design process partitions and also design recursive loops.