开展静不稳定火箭弹设计有利于提高火箭弹的机动和射程能力,从火箭弹低成本的要求出发对静不稳定火箭弹自动驾驶仪进行了设计,提出过载反馈自动驾驶仪形式及参数设计方法,对控制系统设备动态特性对系统性能的影响进行分析,结果表明该方案可有效指导火箭弹的设计。

The static unstable design conduces to enhancing the maneuver capability and range of artillery rockets. To lower the cost, an autopilot is designed for longitudinal static unstable artillery rockets in this paper. Additionally, the form and parameter design method of the overload feedback autopilot are proposed, which is followed by an analysis about the effect of equipment’s dynamic characteristics of control system on system performance. The results can serve as an effective reference for artillery rocket design.

火箭弹由于散布大一直不能作为主要的防空力量,近年来,由于精确制导技术不断发展,基于末端修正的火箭防空技术研究越来越受人们重视。可以强化现有的弹炮防空体系。本文主要研究末端修正的火箭防空技术中的弹目偏差问题,根据弹箭外弹道原理和目标的运动模型,实时动态解算火箭弹命中目标的预测偏差,为火箭弹进行命中目标前的末端修正提供修正依据。

The rocket cannot be used as a major air-defense force all the time owing to its large dispersion pat-tern. In recent years, the rocket air defense technology based on terminal correction has received more and more at-tention because of continuous development of precision guidance technology;and this can intensify available gun-missile air defense system. This paper mainly studies the issue on deviation of projectile-target of rocket air-de-fense technology based on terminal correction. The predicted deviation of rocket missile hitting a target is calculated dynamically in real time according to principle of the artillery rocket exterior trajectory and the moving object mod-el,and this can provide basis for terminal correction prior to rocket missile hitting the target.

为了满足多管火箭炮能够发射无控火箭弹、制导火箭弹等多种型号火箭弹的要求，提出了一种基于TMS320F2812型DSP为核心的多管火箭炮地面发射控制装置。研究了其功能和系统方案，重点对硬件中的弹种检测、状态监测电路、无控火箭弹发射点火电路等关键技术进行详细说明，并进行了系统软件设计。在实际的试验中，该系统能够安全可靠地完成多种型号火箭弹的发射任务，实现了火箭炮地面发射控制装置的智能化和多功能化。

For satisfying requirements of multi-barrel rocket launching free rocket, guided rocket and so on, put forwards multi-barrel rocket ground launch and control equipment which taking TMS320F2812 DSP as core. Research its function and system scheme, focus on describing key technology such as ammunition detection in hardware, status detection circuit, free rocket launch ignition circuit and so on. Then carry out system software design. In practice, the system can safely and reliably launch different type rockets, and realize intelligent and multi-functional rocket ground launch and control device.

针对体积庞大的火箭弹轴向尺寸和径向尺寸难以测量的问题,提出了一种基于位移传感器的火箭弹几何尺寸测量系统。首先将弹体稳定支撑,然后通过测量装置对火箭弹轴向尺寸、径向尺寸及翼展进行测量,最后对测量结果进行精度分析。结果表明,文中提出的火箭弹几何尺寸检测系统,可用于直径达500mm、长度达5000mm的火箭弹的非接触测量。并实现对火箭弹的径向尺寸和轴向任意两点之间距离以及翼展的测量,具备测量精度高、自动化程度好、测量时间短、实用性强等优点。

For bulky rockets, it is difficult to measure the axial dimension and radial dimension, in order to solve this problem the rockets geometry measurement system was proposed which based on the displacement sensor. Firstly the projectile was supported stably. Then the radial size and axial size of rockets were measured through measuring device. Finally the measurement results were analyzed accurately. The results show that the rocket geometric dimension mea-surement system can be used for noncontact measurement of rockets which diameter is up to 500mm and length is up to 5000mm. The measurement of the distance between the radial dimension and the axial measurement and the wing-span measurement are realized.At the same time it has the advantages of high accuracy, good degree of automation, time saving and practical.

采用Pro/Engineer参数化建模方法，创建6管旋回俯仰火箭发射装置三维模型，并导入ABAQUS/CAE环境中，建立火箭发射装置有限元模型；通过对发射单发火箭弹时炮口的振动响应分析，估算出火箭弹实际射角与理论射角的偏差，表明发射多发火箭弹需要根据炮口振动确定发射间隔时间；研究结果为火箭弹射击密集度分析提供重要理论依据。

In this paper,we used the Pro/Engineer parametric modeling method,created 6 cycle pitch rocket launcher 3D model device,input 3D model device into ABAQUS/CAE,and established finite ele-ment of model rocket launcher.By estimating deviation between the actual shooting angle and the theory shooting angle through analysis of the muzzle vibration responses on single firing rockets,it indicates that it requires the muzzle vibration to determine the transmission time interval of the multiple launch rockets. Research results provide an important theoretical basis for rocket firing dispersion analysis.