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.

中文翻译：

---

遥感卫星的姿态控制系统：被动扫描成像模式的快速性能调整

目的

姿态确定和控制子系统（ADCS）是地球观测卫星（EO-Satellites）的重要组成部分，它控制着卫星的旋转运动和指向。在设计如此复杂的子系统时，应考虑许多参数，包括任务，系统和性能要求（PR）以及系统设计参数（DP）。设计周期延长了持续时间并因此增加了设计过程的成本，这是由于这些参数相互依赖。本文旨在描述一种基于性能策略设计的快速调整大小的方法，该方法可以最大程度地减少传统方法带来的设计周期。

设计/方法/方法

所提出的技术是飞机工业中用于飞机设计的技术的改编，并提供了很少的工程工时的球场形象。作者已经展示了如何将这种设计技术推广到涵盖EO卫星平台ADCS。作者将系统要求分为五个类别，包括可操纵性，敏捷性，准确性，稳定性和耐用性。这些要求已被公式化为空间分辨率的函数，这是EO任务PR的最高水平。通过设计驱动程序确定了ADCS主要组件的大小，匹配图的参数特征。

发现

在任务的关键阶段基于PR集成设计边界，只需两次迭代就可以选择设计空间中的最佳点作为基线设计。使用提议的方法确定可操作的敏捷EO卫星的ADCS的大小。结果表明，所提出的方法能够以可接受的准确度显着降低EO卫星中ADCS的性能估算过程的复杂度和持续时间。

创意/价值

使用匹配图技术快速确定EO卫星ADCS的性能，因此，通过最小化设计周期来显着减少设计时间，这使这项研究变得新颖，并代表了该领域的宝贵贡献。