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首页> 外文期刊>International journal of aerospace engineering >Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops
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Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops

机译：角速环轿车导向双旋丸的飞行稳定性

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摘要

Generally, as a precision-guided weapon, the missile has many disadvantage such as high price, difficult maintenance, and low yield. Modern war requires more and more new guided ammunition with high precision, low cost, and low collateral damage. Therefore, as a simple guided conventional ammunition technology, the dual-spin projectile has attracted the attention of ammunition experts recently. This paper proposes a dual-spin projectile scheme based on the rotation control method. Firstly, the concept of the dual-spin projectile is introduced. Secondly, the mathematical model of the dual-spin projectile is established, and the angular motion equation is finally obtained by using some linearized assumptions. Finally, the sufficient and necessary conditions of coning motion stability for dual-spin projectile with angular rate loops are analytically derived and further verified by numerical simulations. It is noticed that the upper bound of the control gain is affected by the delay angle of the control system and the spinning rate of the projectile.
机译：通常，作为一种精密引导武器，导弹具有许多劣势，如高价格，难以维护，产量低。现代战争需要越来越多的新导弹弹药，精度高，成本低，隔板低。因此，作为一种简单的传统弹药技术，双自旋射弹最近引起弹药专家的注意。本文提出了一种基于旋转控制方法的双自旋射弹方案。首先，介绍了双自旋射弹的概念。其次，建立了双自旋射弹的数学模型，最后通过使用一些线性化假设来获得角运动方程。最后，通过数值模拟分析和进一步验证了具有角速率环的双自旋射弹的足够和必要条件。注意到控制增益的上限受到控制系统的延迟角度的影响和射弹的旋转速率。

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