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宁全利 , 蒋滨安 , 梁希 , 等 . 火炮发射环境下弹载光电器件结构动态响应研究 [J ] . 兵工学报 , 2015 , 36 ( 11 ): 2185 - 2189 . DOI: 10.3969/j.issn.1000-1093.2015.11.025 http://doi.org/10.3969/j.issn.1000-1093.2015.11.025 为了研究弹载光电器件抗高过载机理，针对火炮发射环境特点，以某型特种弹所用弹载光电器件为例，建立了加装减载组件的弹载光电器件有限元分析模型并进行仿真分析。采用应力波理论，建立了反映弹载光电器件动力学过程的理论分析模型，计算求解作用于镜头的应力、相对位移和相对速度等，得到了弹载光电器件的动力学响应。结果表明：数值计算与仿真模拟结果有较好的一致性，验证了所建立的理论分析模型的正确性，可用于火炮发射环境下不同弹载器件的动态特性研究和抗高过载设计的理论分析。

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钱立志 . 弹载任务设备抗高过载方法研究 [J ] . 兵工学报 , 2007 , 28 ( 8 ): 1017 - 1021 . 针对某特种炮弹弹载任务设备的结构特点和受力环境，设计了由橡胶垫和碟簧组合的复合减振装置，经仿真计算，该装置能有效减缓结构受到的冲击，变形值亦在其许可范围之内。此外，通过改善连接关系、对关键器件采取封装固化等措施从结构设计上提高抗高过载能力。经试验验证，抗高过载设计方法合理可行，满足系统的隔振抗冲要求。

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司朝伟 , 韩国威 , 宁瑾 , 等 . 高性能音叉结构MEMS陀螺的抗冲击设计 [J ] . 微纳电子技术 , 2014 , 51 ( 5 ): 302 - 307 .

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李杰 , 刘俊 . 制导弹药用微惯性测量单元结构设计 [J ] . 兵工学报 , 2013 , 34 ( 6 ): 711 - 717 . DOI: 10. 3969/ j. issn. 1000-1093. 2013. 06. 009 http://doi.org/10. 3969/ j. issn. 1000-1093. 2013. 06. 009 针对制导弹药空间狭窄和发射过载高的环境特点, 提出了一种基于微机电系统 (MEMS)惯性器件的嵌入式一体化抗高过载微惯性测量单元(MEMS-IMU) 结构设计方法。在分析 MEMS-IMU结构设计原则和要求基础上,设计加工了MEMS-IMU 结构并研制了惯性测量系统。该 MEMS-IMU通过合理利用空间,极大地减小了体积和重量,同时采用一次性嵌入式的设计与加工方法,以及特殊的灌封材料与工艺,显著提高了结构的抗高过载性能。有限元分析结果表明该结构力学性能良好,马歇特落锤试验和地面炮击试验结果也表明该结构可满足制导弹药对MEMS-IMU 的小体积和抗高过载等要求。

LI J , LIU J . Design of micro-electromechanical systems inertial measurement unit structure for guided ammunition [J ] . Acta Armamentarii , 2013 , 34 ( 6 ): 711 - 717 . (in Chinese) DOI: 10. 3969/ j. issn. 1000-1093. 2013. 06. 009 http://doi.org/10. 3969/ j. issn. 1000-1093. 2013. 06. 009 A miniature embedded and holistic and anti-high-overload structure of micro inertial measurement unit in which micro-electromechanical systems(MEMS) based inertial sensor is used is proposed for the environment features of small installing volume and high-g launching overload of the guided ammunition. Based on the analysis of design principle and requirements MEMS inertial measurement unit(MEMS-IMU) structure, the structure of MEMS-IMU is designed and manufactured, and its actual MEMS-IMU is built. The volume and weight of MEMS-IMU are reduced by making reasonably use of its installing space, and its anti-high overload performance is evidently improved by using one-off embedded design and process technique, and the special filling material and techniques. The results of the finite element model analysis show that this structure has the good dynamic performance, and the results of the land and gunshot experiments also show that it can meet the requirements of the guided ammunition in volume and anti-high overload.

李杰 , 赵诣 , 刘俊 , 等 . 高旋弹药飞行姿态测量用半捷联MEMS惯性测量装置研究 [J ] . 兵工学报 , 2013 , 34 ( 11 ): 1398 - 1403 . DOI: 10.3969/j.issn.1000-1093.2013.11.009 http://doi.org/10.3969/j.issn.1000-1093.2013.11.009 针对高速旋转弹药姿态测量中，传统的MEMS捷联惯性测量系统由于角速率传感器在量程和精度上不能同时满足测试要求而存在姿态测量精度低的问题，提出了半捷联MEMS惯性测量的概念、原理和半捷联MEMS惯性测量的实现方法；同时针对半捷联MEMS惯性测量系统的组成结构，对半捷联MEMS惯性测量装置进行了介绍。通过对动力输出仓、控制-驱动电路安装仓、惯性信息敏感仓和惯性信息采集仓的结构和功能说明，阐述了半捷联MEMS惯性测量的实现方法。该装置可在弹药高速旋转情况下为微惯性测量单元提供稳定测试环境，有效抑制高旋弹药对惯性系统姿态测量精度的影响，为高旋弹药姿态测量和常规弹药制导化提供了新的思路，具有一定的工程应用价值。

LI J , ZHAO Y , LIU J , et al. Research on semi- strapdown MEMS inertial measurement device for flight attitude measurement of high-speed rotating ammunition [J ] . Acta Armamentarii , 2013 , 34 ( 11 ): 1398 - 1403 . (in Chinese)

段晓敏 , 李杰 , 刘俊 . 被动式半捷联平台的动力学模型及其稳定性分析 [J ] . 兵工学报 , 2014 , 35 ( 9 ): 1436 - 1442 . DOI: 10.3969/j.issn.1000-1093.2014.09.016 http://doi.org/10.3969/j.issn.1000-1093.2014.09.016 在某些高速滚转的制导炮弹中，捷联式惯性测量系统无法同时满足测试精度与量程的要求。被动式半捷联平台可以通过隔离弹体滚转运动有效解决这一问题。通过对弹体及被动式半捷联平台进行力学分析建立了半捷联平台内筒的动力学模型，通过4阶龙格-库塔法对动力学模型进行了数值求解，得出不同弹体俯仰角下平台内筒的滚动角度和角速率值。在三轴高速转台上进行了地面半实物仿真实验，转台实验结果与数值计算结果相符。计算及实验结果表明弹体飞行俯仰角越小，平台内筒的滚动角度和角速率就越小，被动式半捷联平台就越稳定。本研究适用于常规弹药的制导化改造，具有一定的工程应用价值。

DUAN X M , LI J , LIU J . Research on the dynamic model of a partial strapdown platform and the impact analysis of pitching angle and the stability of platform [J ] . Acta Armamentarii , 2014 , 35 ( 9 ): 1436 - 1442 . (in Chinese)

段晓敏 , 李杰 , 刘俊 . 空气升力对被动式半捷联平台稳定性影响分析 [J ] . 兵工学报 , 2014 , 35 ( 11 ): 1813 - 1818 . DOI: 10.3969/j.issn.1000-1093.2014.11.012 http://doi.org/10.3969/j.issn.1000-1093.2014.11.012 安装在高速滚转的常规炮弹上的被动式半捷联平台是基于重力作用下的复摆运动原理工作的装置。由于弹体在飞行时受到空气升力的作用，所以空气升力的变化会导致弹体在竖直方向上的加速度变化，而弹体在竖直方向的加速度变化会导致被动式半捷联平台的等效复摆回复力矩发生变化并影响平台的稳定性。为了研究空气升力对被动式半捷联平台稳定性的影响，对弹体和弹体内的被动式半捷联平台内筒进行了力学分析，建立了空气升力作用下的平台内筒的运动微分方程。通过对运动微分方程进行计算仿真，得到了不同空气升力作用时被动式半捷联平台内筒的滚转角度曲线和角速率曲线，并得到了平台保持稳定时空气升力所需满足的范围。仿真结果表明，弹体受到的空气升力越大，被动式半捷联平台的稳定性越高。当空气升力小于0.005 75 m_pg(m_p为弹体质量，g为重力加速度)时，被动式半捷联平台将失去稳定作用。在三轴高速转台上进行空气升力和重力相等时的被动式半捷联平台内筒运动状态的地面实验，实验结果验证了仿真结果的正确性。

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张樨 , 李杰 , 范建英 , 等 . 半捷联微惯性测量系统同轴度误差解析评定 [J ] . 兵工学报 , 2015 , 36 ( 3 ): 503 - 509 . DOI: 10.3969/j.issn.1000-1093.2015.03.018 http://doi.org/10.3969/j.issn.1000-1093.2015.03.018 半捷联微惯性测量方法的提出为高旋弹药飞行姿态的高精度测量提供了一种全新的解决方案，而复杂的半捷联机械结构又给测量系统带来了不可忽略的同轴度问题。针对半捷联系统的同轴度问题，在介绍半捷联微惯性测量系统基本组成结构与工作原理的基础上，分别提出了适用于半捷联系统外筒与内筒的同轴度解析评定方法。其中，外筒的同轴度测定方法参考现有标准测量方法，而内筒的同轴度测定，则是在推导存在同轴度误差角时微惯性测量组合（MIMU）输出模型的基础上，详细设计了适合半捷联内筒同轴度的动态标定方法，利用系统自身组部件完成了同轴度误差角标定，并在实验条件下对径向陀螺输出作了误差补偿，验证了该方法的可行性，最终完成了半捷联微惯性测量系统同轴度误差的综合解析评定。

ZHANG X , LI J , FAN J Y , et al. Analysis and evaluation of coaxiality error of semi-strapdown micro inertial measurement system [J ] . Acta Armamentarii , 2015 , 36 ( 3 ): 503 - 509 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2015.03.018 http://doi.org/10.3969/j.issn.1000-1093.2015.03.018 The semi-strapdown micro inertial measurement method is a new solution to high precision attitude measurement of the high-speed rotation ammunition. The complex mechanical structure of semi-strapdown platform causes a non-ignorable coaxiality error. The basic structure and working principle of the system are introduced, and the analytical evaluation methods suitable for the coaxiality evaluation of the outer and inner cylinders of semi-strapdown system are proposed. The evaluation method of outer cylinder is based on the existing standard measurement method. A dynamic evaluation method for the inner cylinder coaxiality of semi-strapdown system is designed in detail based on the deduction of miniature inertial measurement unit（MIMU）output model in consideration of coaxiality error angle. The coaxiality error angle is calibrated using the component in the system, and makes the error compensation for the radial gyro output under the experiment condition. The analysis and evaluation of the coaxiality error of semi-strapdown micro inertial measurement system are performed. The results show that the proposed method is feasible.

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