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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >Rapid Initial Detumbling Strategy for Micro/Nanosatellites Using a Pitch Bias Momentum System
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Rapid Initial Detumbling Strategy for Micro/Nanosatellites Using a Pitch Bias Momentum System

机译：使用音调偏置动量系统对微/纳米卫星进行快速初始脱粒的策略

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摘要

When a satellite separates from the launch vehicle, an initial high angular rate or a tip-off rate is generated. B-dot logic is generally used for controlling the initial tip-off rate. However, it has the disadvantage of taking a relatively long time to control the initial tip-off rate. To solve this problem, this paper suggests a new detumbling control method that can be adapted to microanosatellites using a pitch bias momentum system, and presents simulation results. The proposed detumbling method was able to control the angular rate within 20 min, which is a significant reduction compared to conventional methods. In addition, the momentum wheel initial start-up must be done under stable conditions, and a conventional pitch spin-stabilized initial wheel start-up method is commonly used. Since the conventional wheel start-up method cannot be used if the detumbling controller proposed by this paper is used, a method is also proposed for bringing up the momentum wheel speed to nominal rpm while maintaining stability. The performance of the method is compared and verified through simulation. The overall results show a much faster control time compared to the conventional methods, and achievement of nominal wheel speed and 3-axis stabilization while maintaining stability.
机译：当卫星与运载火箭分离时，会产生初始的高角速率或倾翻速率。 B点逻辑通常用于控制初始加速率。但是，其缺点是需要花费相对较长的时间来控制初始倾翻率。为了解决这个问题，本文提出了一种新的降落控制方法，该方法可以使用俯仰偏置动量系统适应微/纳卫星，并给出了仿真结果。所提出的脱粒方法能够在20分钟内控制角速度，与传统方法相比，这是一个显着的降低。另外，动量轮的初始启动必须在稳定的条件下进行，并且通常使用常规的螺距旋转稳定的初始轮的启动方法。如果使用本文提出的减速控制器，则无法使用传统的车轮启动方法，因此，还提出了一种在保持稳定性的同时将动量车轮速度提高至标称rpm的方法。通过仿真比较了该方法的性能。总体结果表明，与传统方法相比，控制时间要快得多，并在保持稳定性的同时实现了标称轮速和3轴稳定性。

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