针对传统鸭式布局野战火箭滑翔段升阻比低、被动段操控性差、射程受限等问题,开展了鸭式布局火箭气动特性分析,并根据分析结果提出了一种新的大长细比高性能远程火箭气动布局设计方案。仿真结果表明,8°攻角下,鸭舵气动效率随马赫数增加急剧下降,而对弹体升力贡献显著增加;Ma为4~6时,鸭舵升力占比低于阻力占比,对全弹气动增益为负,而弹体升力占总升力达61%~67%。据此,提出了一种尾控式大长细比高性能火箭弹布局,通过减少高速飞行时低效的舵面/翼面数量,并将舵面后置进行配平和机动。数值仿真结果表明,尾控布局显著提高了火箭弹的升阻比,拥有更大的可用攻角和机动性,是更加适用于高超音速飞行的远程火箭弹布局。

Aiming to address the issues of low lift-to-drag ratio during the gliding phase, poor maneuverability in the passive flight segment, and limited range inherent in traditional canard-layout field rockets, this study analyzes the aerodynamic characteristics of canard-layout rockets. Based on these findings, a novel aerodynamic layout design scheme is proposed for high-performance long-range rockets with a large aspect ratio. Simulation results indicate that at an 8° angle of attack, the aerodynamic efficiency of the canard control surfaces decreases sharply with increasing Mach number, while their contribution to the projectile's lift force increases significantly. When Ma ranges from 4 to 6, the proportion of lift generated by the control surfaces is less than the drag they produce, resulting in negative aerodynamic gains for the entire projectile. In contrast, the body lift accounts for 61%~67% of the total lift. Based on these insights, a tail-controlled high-performance rocket layout with a large aspect ratio is proposed. This design reduces the number of inefficient control/wing surfaces during high speed flight and enhances balance and maneuverability through optimized rear-positioned control surfaces. Numerical simulation results confirm that the tail-control layout substantially improves the rocket's lift-to-drag ratio, provides a larger usable angle of attack, and enhances overall maneuverability, making it a more suitable configuration for long-range rockets in hypersonic flight.