微型反无人机导弹抗滚转气动布局设计  

Antirolling aerodynamic configuration for micro anti-unmanned aerial vehicle missiles

作　　者：徐伟杰 李易[1] XU Weijie;LI Yi(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《国防科技》2023年第5期67-74,共8页National Defense Technology

基　　金：中国航天科技集团有限公司航天进入减速与着陆技术实验室2022年度开放基金项目(×××)。

摘　　要：承担反无人机等任务的微型导弹由于结构尺寸限制,常采用鸭式布局,利用鸭舵进行姿态控制,不可避免地会出现诱导滚转问题。针对该问题,提出一种基于两级鸭舵的微型导弹气动布局设计方法。该气动布局的一级鸭舵负责俯仰与偏航通道控制,利用呈I字布置的小尺寸二级鸭舵进行单独滚转通道控制,实现滚转通道在控制指令上与俯仰、偏航通道的解耦。在保证导弹具有高机动性的同时,降低导弹尾翼产生的诱导滚转影响,以实现对微型导弹滚转通道的控制。通过分析鸭舵诱导滚转的流动机理,提出二级鸭舵的布置方式,并利用计算流体力学方法验证该气动布局的有效性,进一步提出二级鸭舵的控制方法与控制限制条件,为相关工程应用提供一种有效方案。Micro anti-unmanned aerial vehicle missiles,constrained by their structural dimensions,often adopt a canard configuration.The canards are employed to control the attitude of the missile;however,they induce unintended rolling movements.To address this issue,a design methodology is proposed for the aerodynamic configuration of micromissiles featuring a two−stage canard configuration.In the proposed aerodynamic scheme,the primary canard controls the pitch and yaw channels,while a supplementary,compact secondary canard arranged in an“I”shape is implemented to regulate the roll channel independently.Through this approach,control commands for the roll channel are decoupled from those for the pitch and yaw channels,thereby enhancing missile maneuverability and reducing the effects of rolling induced by the tail fins.This serves the objective of roll channel control for micromissiles.By examining the aerodynamic mechanism that induces rolling via the canards,an approach to configuring the secondary canard is introduced.The effectiveness of this aerodynamic configuration is verified using computational fluid dynamics simulations.In addition,a control approach and control constraints for the secondary canard are outlined,providing an effective solution for pertinent engineering applications.

关 键 词：微型导弹 两级鸭式布局 诱导滚转 计算流体力学方法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]