“Wasted performance” minimization of the multi-purpose mini-satellite platform for an EO mission using a dynamic simulation-based model

Saghari, Asad; Rahmani, Shima; Kosari, Amirreza

doi:10.1016/j.ast.2017.11.038

Cited by 3 publications

(1 citation statement)

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“…Because of the processing limitations, the pixel elongation due to the slew maneuvers cannot exceed 40% (Saghari et al , 2018). For pixel size ratio of 1.4, B/H equals to 0.6 and the constraint θ S ≤ 30°, could be considered for the slew angle.…”

Section: Constructing the Attitude Determination And Control Subsystem Matching Diagrammentioning

confidence: 99%

Remote sensing satellite’s attitude control system: rapid performance sizing for passive scan imaging mode

Kosari

Sharifi

Ahmadi

et al. 2020

AEAT

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Purpose Attitude determination and control subsystem (ADCS) is a vital part of earth observation satellites (EO-Satellites) that governs the satellite’s rotational motion and pointing. In designing such a complicated sub-system, many parameters including mission, system and performance requirements (PRs), as well as system design parameters (DPs), should be considered. Design cycles which prolong the time-duration and consequently increase the cost of the design process are due to the dependence of these parameters to each other. This paper aims to describe a rapid-sizing method based on the design for performance strategy, which could minimize the design cycles imposed by conventional methods. Design/methodology/approach The proposed technique is an adaptation from that used in the aircraft industries for aircraft design and provides a ball-park figure with little engineering man-hours. The authors have shown how such a design technique could be generalized to cover the EO-satellites platform ADCS. The authors divided the system requirements into five categories, including maneuverability, agility, accuracy, stability and durability. These requirements have been formulated as functions of spatial resolution that is the highest level of EO-missions PRs. To size, the ADCS main components, parametric characteristics of the matching diagram were determined by means of the design drivers. Findings Integrating the design boundaries based on the PRs in critical phases of the mission allowed selecting the best point in the design space as the baseline design with only two iterations. The ADCS of an operational agile EO-satellite is sized using the proposed method. The results show that the proposed method can significantly reduce the complexity and time duration of the performance sizing process of ADCS in EO-satellites with an acceptable level of accuracy. Originality/value Rapid performance sizing of EO-satellites ADCS using matching diagram technique and consequently, a drastic reduction in design time via minimization of design cycles makes this study novel and represents a valuable contribution in this field.

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Section: Constructing the Attitude Determination And Control Subsystem Matching Diagrammentioning

confidence: 99%