Abstract
Abstract According to the mission of a satellite with maneuver capability, the collaborative optimization (CO) method was introduced for the satellite system design, and the related multidisciplinary design optimization (MDO) model was established. The possessing and needed velocity increments Δv and Δv n e e d were taken as the measurement of maneuvering capability of the studied satellite, which were then combined with total mass of the satellite to form the optimization objective in the systematic level of the MDO problem. The design variables and constraints of the MDO problem dealt with disciplines or subsystems as guidance, navigation and control (GNC), power, and structure, and corresponding engineering analysis models were also built. A program system to solve the MDO problem wasdeveloped by integrating a non-nested CO method, the commercial and user-supplied codes on framework software iSIGHT. The result showed that the satellite performance could be obviously improved, which also indicates MDO technique is feasible and effective for the spacecraft design problem. The modeling and optimization procedure of the work can be referred for further research and engineering design.
Highlights
Electronic supplementary material The online version of this article contains supplementary material, which is available toauthorized users.W
According to the mission characteristics of a maneuver satellite, this paper discussed the measurement and analyzed the maneuvering capability of the studied satellite, i.e. the possessing and needed velocity increments v and vneed, which were combined with total mass of the satellite to form the optimization objectives in the systematic level of the multidisciplinary design optimization (MDO) problem
As the maneuver capability measured by velocity increment is the most important for a maneuver satellite, the total mass of satellite is always expected to be as low as possible, and the optimization objective of this work is taken as max v− vneed mt ot al where mtotal is the satellite mass; v is the velocity increment the satellite possesses, and vneed is the velocity increment the satellite needs to realize the maneuver mission, which can be presented as vneed = va + vθ + v, (9)
Summary
Electronic supplementary material The online version of this article (doi:10.1007/s00158-014-1087-x) contains supplementary material, which is available toauthorized users. When entering a stage, the satellite system design can be stated as an optimization problem to determine a series of systematic parameters Such kind of a problem is extremely computational intensive, and inevitably requires multiple disciplinary analyses which are commonly conducted by different technical groups of a company, so that it is almost impossible to be solved by directly using methods for. It has been reported that MDO methods were successfully applied to a series of aerospace engineering programs and made sufficiently benefits through the design technology (Choi et al 2006; Nobuhiro et al 2005; Yokoyama et al 2007; Blouin et al 2004; Braun et al 1997; Allison et al 2006) These researches showed that MDO is effective and efficient in dealing with the coupling among multi-subsystems. More details in each disciplinary modeling as well as velocity increment calculations can be referred to the Electronic Supplementary Materials (ESM)
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