Wasserstein距离在液体火箭发动机故障检测中的应用

健康监控技术能够切实提高液体火箭发动机的可靠性,针对液体火箭发动机健康监控中的故障检测问题,提出基于Wasserstein距离的方法,利用液氢液氧火箭发动机地面热试车数据进行验证。该方法的核心思想是利用Wasserstein生成对抗网络模拟正常数据的样本分布,利用其判别器计算测试样本与模拟分布间的Wasserstein距离,进而实现故障检测。结果表明:该方法能够克服故障数据不足的困难,有效检测稳态过程中的故障,没有发生误报警,且对早期异常有较高敏感性;在训练样本较少的情况下,当Wasserstein距离阈值为3σ时对启动过程的早期异常有较高敏感性,取5σ时仍可有效检测启动过程中的故障,误报警率为12.5%。     

独立分量分析在液体火箭发动机故障检测中的应用

针对液体火箭发动机试车中,因噪声干扰、不同源信号之间的混叠而造成的信号信噪比低、信号分析和特征提取难度大的问题,提出采用独立分量分析(ICA)法对液体火箭发动机试车信号进行分离,以提高信号的信噪比,并能实时反映各子系统工作过程,为数据分析、特征提取和故障检测与诊断提供可靠的信号。通过对某型液体火箭发动机热试车压强信号进行实例分析,验证了该方法的有效性。     

多用途子母弹对集群目标毁伤效率评估模型

多用途子母弹是多功能火炮配备的一种集地面打击和防空袭于一体的新型弹药,为充分发挥该弹药的战技性能,并合理地研究其作战使用。在假定单个目标均匀分布的基础上,运用离散的方法研究并建立了单发多用途子母弹对集群目标射击的效率评定模型,在此基础上又建立了多发多用途子母弹对集群目标射击时的效率评定模型,并运用模型进行了计算分析,计算结果表明该模型计算过程简便、精度高、准确性较好。     

某高炮火控系统射击诸元采集装置设计

在高炮火控系统射击校正中,射击诸元需要以数字量形式送入校射系统作为输入信号使用,而高炮火控系统射击诸元大都是采用三相轴角信号形式的模拟信号。为了解决这一问题,设计了一种高炮火控系统射击诸元采集装置实现射击诸元模拟量向数字量形式的转换。首先分析了射击诸元的采集与测量原理,设计了SCOTT变压、采样保持、A/D转换、正峰值脉冲产生、数据处理与控制等硬件功能电路,阐述了采集装置的总体工作过程,在此基础上进行了软件程序设计。该射击诸元采集装置的研制为高炮火控系统射击诸元的采集以及校射工作提供了一种实用的方法。     

系统动力学炮兵侦察感知系统能力生成建模与仿真

信息化作战,侦察感知能力是炮兵获取决策优势与行动优势的基础。依据炮兵侦察感知系统的功能与构成,分析炮兵侦察感知信息流程,运用系统动力学分析侦察感知系统的各要素及影响关系,进而建立炮兵侦察感知系统作战能力生成的系统动力学模型。依据设定作战背景,仿真分析了传感器性能、网络性能等对炮兵侦察感知系统能力生成影响问题,得出了较为可靠的结论,为炮兵基于信息系统体系作战能力要素建设提供决策依据。     

Numerical studies on four-engine rocket exhaust plume impinging on flame deflectors with afterburning

This paper studies the four-engine liquid rocket flow field during the launching phase. Using three-dimensional compressible Navier-Stokes equations and two-equation realizable k-epsilon turbulence model, an impact model is established and flow fields of plume impinging on the two different shapes of flame deflectors, including wedge-shaped flame deflector and cone-shaped flame deflector, are calcu-lated. The finite-rate chemical kinetics is used to track chemical reactions. The simulation results show that afterburning mainly occurs in the mixed layer. And the region of peak pressure occurs directly under the rocket nozzle, which is the result of the direct impact of exhaust plume. Compared with the wedge-shaped flame deflector, the cone-shaped flame deflector has great performance on guiding exhaust gas. The wedge-shaped and cone-shaped flame deflectors guide the supersonic exhaust plume away from the impingement point with two directions and circumferential direction, respectively. The maximum pressure and temperature on the wedge-shaped flame deflector surface are 37.2% and 9.9% higher than those for the cone-shaped flame deflector. The results provide engineering guidance and theoretical significance for design in flame deflector of the launch platforms.     

A novel launch dynamics measurement system for multiple launch rocket system and comparative analysis with numerical simulations

In this paper,a novel launch dynamics measurement system based on the photoelectric sensor pair is built.The actual muzzle time(i.e.a time duration that originates from the initial movement to the rocket's departure from the muzzle)and the muzzle velocity are measured.Compared with the classical methods,the actual muzzle time is obtained by eliminating the ignition delay.The comparative analysis method is proposed with numerical simulations established by the transfer matrix method for multibody systems.The experiment results indicate that the proposed measurement system can effectively measure the actual muzzle time and reduce the error of classical methods,which match well with the simulation results showing the launch dynamics model is reliable and helpful for further analysis and design of the MLRS.