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双语推荐：发射架

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研究了一种用于研究子弹在不同角度高速入水的气动发射架。主要从发射架结构构成、发射原理分析和计算机模拟等方面对发射架进行分析。建立了子弹发射过程的数学模型，选用 Matlab软件对模型分析求解，得出了子弹速度的时域变化曲线。通过改变发射边界参数，对比得出各参数对子弹发射的影响。对子弹在不同角度下高速入水研究进行技术储备和参考，同时也为气动发射架的设计提供理论依据。
This dissertation focuses on an angle adjustable bullet pneumatic emission launcher which is used to study the bullet enter water at high velocity.It is mainly analysis from the struc-ture,principle and gets system simulation for the launcher.The bullet launch mathematic model is established,and solved with Matlab software.It is concluded the temporal change curve of the bullet velocity.Changing the boundary conditions and solving result.Compare the influence of conditions on the launch.The results were compared with the experimental correction to study technical reserves and reference in this area,and also provide theoret-ical basis for the design of the pneumatic launcher.

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针对同心筒结构的共架发射系统，研究多武器共架发射时为保证舰艇和武器安全需解决的发射协调问题，提出了时域协调的方法。首先，给出了时域协调的概念，分析了发射速率、燃气排导、初始飞行弹道交叉、防空导弹发射优先等因素对时域协调的影响；然后，建立了基于发射令控制的发射时序模型、发射时间间隔模型及发射优先级模型；最后，对时域协调方法进行了算例验证。结果表明：通过时域上合理地控制武器发射间隔时间可以保证系统安全，同时最大程度地发挥系统效能。
Aiming at the common-frame launching system with concentric canister launcher ,this paper deals with the problem of common-frame weapon launching coordination and proposes the time coordi-nation method .Firstly ,it defines the concept of time coordination ,and analyzes the effects of launch rate ,combustion gas exhaust ,initial trajectory intersection and anti-air missile launch priority on the time coordination .Then ,according to the time coordination ,models for launch sequence ,launch time spacing and launch priority are established .Finally ,some arithmetic examples are used to verify the method of time coordination .The result indicates that the reasonable control of weapon launching time interval in terms of time coordination can ensure the system safety and display the system effi-ciency to the greatest extent .

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导弹发射时导发架的受力情况很复杂,其动力学特性的研究是一个难点。本文将导发架看成一个两端简支的梁,导弹简化为一个沿导发架移动的质点,建立了导发架的动力学模型,并运应用振型分解法对模型的解进行初步研究。所得结果为未来的研究奠定一定的基础。
@@@@The force working on missile launcher is very complex during missile launching , the re-search on dynamic characteristic of missile launcher is a difficult problem .In this paper, dynamic model of missile launcher is established while missile launcher is looked as a simply supported beam and missile is simplified as a moving particle along rack of missile launcher .The model solutions are investigated by mode analysis method.The conclusion lays a foundation for further research .

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以某型兵器发射塔架摆杆系统为研究对象,采用基于软件接口的协同仿真策略,拟定了动力学协同仿真方案。利用MSC.ADAMS和Easy5仿真软件建立了塔架摆杆系统的机液耦合仿真模型。通过仿真,得到塔架摆杆系统的受力及运动情况,并与试验数据进行对比,验证了该联合建模方法的有效性和实用性,并提出了解决塔架摆杆系统工作时速度波动问题的方法。
By setting a certain type of weapon launch tower pendulum system as the research object,using software based inter-face co-simulation strategy,the dynamics co-simulation program were developed.A mechanical-hydraulic coupling simulation model of the tower pendulum system was established by using the simulation software of MSC.ADAMS and Easy5.By the simulation,the movement and force of the system were gotten and compared with the experimental data.The effectiveness and practicality of the estab-lished model by coupling method are verified,and the way to solve the tower pendulum system''s speed fluctuation problem is proposed.

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研究裸弹垂直热发射过程系统的动态响应及其对导弹运动的影响。对车载导弹发射系统进行了简化和等效建模,进行了导弹起飞过程的理论分析,基于动力学和有限元软件建立了系统刚柔耦合多体动力学模型,对发射过程展开了动力学仿真与分析,并进行了多刚体与刚柔耦合两类模型计算结果对比。数值模拟结果表明,导弹起飞过程与发射车的耦合作用明显,系统振动对导弹起飞姿态产生影响,发射车振动衰减特性良好,柔性发射台模型能够较好反映发射过程系统动态响应以及弹架耦合特性。
The missile-launcher coupling and the dynamic response of missile system in bare missile vertical thermal launch process were mainly researched.Simplifying and equivalent modeling were discussed for track-based missile system.The process of missile taking off was theoretically analysed.A rigid-flexible coupling multi-body dynamics model was created based on dynamics and finite element software.The dynamics simulation and analysis were carried out for the process of missile launch.The results of the two kinds of models were compared.The numerical simulation results indicate that the coupling is obvious between the missile and launcher during missile taking off.The vibration of missile system has influence on the taking off attitude.Vibration damping characteristics of the launchers are suitable.The rigid-flexible coupling model can reflect the dynamic performance of missile launch better than the rigid model.

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针对火炮的多射角工况特性,建立火炮上架结构的有限元模型,依据火炮发射时上架的结构受力特性及其技术设计要求,对其进行静态刚强度分析,在此基础上以提高上架刚度为目标,先运用拓扑优化方法寻求上架的最佳材料分布,确定加强筋的合理布局,再运用尺寸优化方法对上架进行详细设计,获取最终的结构优化方案。优化后多射角工况下左右耳轴中心位移显著减小,最大减小比率为32.61%,同时结构质量减小了1.42%,达到了提高上架刚度的优化设计目标。
Aimed at the working condition of multiple firing angles of gun in use,a finite element model of the gun top carriage was constructed,and the static stiffness and strength analysis were performed accord-ing to the load features and the design requirements of the gun top carriage during the gun was firing. Based on this,in order to increase the stiffness of the gun top carriage,the topology optimization was used to search for the optimized material distribution,and then the reasonable layout of the stiffeners was determined.Size optimization was applied to the detailed design of the gun top carriage,and the final structural optimization scheme was acquired.After optimization,displacement of left and right trunnions centre under the working conditions of multiple firing angles were significantly decreased,the maximum reduction ratio was 32.61%.At the same time,the structure mass was reduced by 1.42%.The study re-sult showed that the optimization design goal to improve the stiffness of gu

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针对车载导弹在低机动条件下的传递对准问题,根据车辆不能沿纵轴和横轴作大的角机动的特点,提出了充分利用导弹发射前的刹车,起竖发射架这一系列的过程来进行传递对准的机动方案;针对主惯导、发射架和子惯导之间的连接为多刚体柔性联接,主子惯导之间的挠曲变形建模复杂的问题,提出了将挠曲变形视为不确定性干扰,利用H∞滤波来实现传递对准的方法。仿真结果表明,在不对挠曲变形进行建模和车载导弹只做射前准备机动而不做其它机动的情况下,导弹可在起竖完成前完成对准,且对准精度可达4′。
To solve the transfer alignment problems of land-launched missile under low dynamical maneuver, an improved alignment method is proposed which sufficiently take use of the vehicle brake and the launcher uprising. To solve the problem of the difficult in deducing the flexure model between the master inertial navigation system(INS) and the slave INS since their connection are multi-rigid body join, an H∞ filter is designed for the transfer alignment which deems the flexure as the indeterminate interference. The simulation results show that the transfer alignment can be accomplished before the launcher uprising finished, and the accuracy of transfer alignment is within 4′ when the flexure model is not considered and the land-launched missile do the launch preparation maneuver only.

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为了模拟飞机、两型发射架及导弹的电气信号特征,实现凉性发射装置及其配套发控盒研制过程中调试、系统联试功能一体化,设计开发了某型便捷式发控装置电气调试系统;介绍了该系统的总体设计、硬件配置、适配器的设计、软件工作流程等;经测试,该系统安全、可靠,完全满足设计要求。
To simulate aircraft,two types of launchers and electrical signal characteristics of missiles,and achieve the inte-gration of debugging,system testing and commissioning in the development process of cool launcher and its supporting control box,a debugging system for certain type of portable electropult is designed and developed. The overall system design,hardware configuration,the adapter design and software workflows are introduced;Test result shows that the system is safe,reliable,and can fully meet the design requirements.

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介绍一种车载多架无人机快速供电测试和启动系统的设计，包括车载地面检测计算机、直流电源、电气控制装置、发射箱供电测试及启动装置、地面检测计算机、供电测试接口装置和车载配电网络。其中车载直流电源为无人机供电测试和发动机启动提供电源；地面检测计算机发出的供电测试、启动指令送给电气控制装置，通过供电测试接口装置、车载配电网络向无人机供电，当无人机测试正常后，则可进行发动机启动。发动机的启动电源采用多个发射箱启动直流母线并联供电。该系统提高了多架无人机供电测试和启动发动机的自动化程度。
This paper presents a design of vehicle multiple UAVs fast power test and starting system. It includes vehicle ground detection computer, DC power supply, electrical control devices, equipment of launch box power testing and starting, ground detection computer, power supply test interface device and vehicle distribution network.Vehicle DC power supply provides power to test the UAV and start engine. Power test and start command of vehicle ground detection computer transmit to the electric control de-vices.Through the power supply test interface device and vehicle distribution network, it supplies power to the UAV.When the UAV tests are normal, you can start the engine.The power of starting engine uses DC bus in parallel.The system improves the automation level of multiple UAVs power test and starting engine.

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为了寻求一种低后坐发射技术,以30mm自动榴弹发射器为主体研究对象,建立其三维模型,运用MATLAB软件计算内弹道、后效期及导气室内的气体压力,结合动力学分析软件ADAMS计算含有缓冲器的榴弹发射器动力学特性曲线。基于动力学刚柔耦合理论,分别对驻锄与脚架之间添加缓冲器、枪身与脚架之间添加液压缓冲器、枪身与枪架之间添加弹簧缓冲器3种情况的榴弹发射器的发射过程进行动力学仿真计算,探讨了这3种情况下的仿真结果并比较分析榴弹发射器的后坐特性,为进一步研究低后坐发射技术提供理论依据。
The main research object of this paper focuses on the 30mm Automatic Grenade Launcher(AGL).It realizes the dynamic simulation about this AGL , including building the 3-D model by SolidWorks software and calculating the gas pressure during the periods of internal ballistic and after -effect and the gas pressure of the gas chamber by MATLAB language .It simulates the launching process of the grenade launcher on the base of the coupled dynamics theory , analyzes the results about the grenade launcher recoiling characteristics on each case , compares these results on covering the addition of the buffer -type spade and hydraulic and spring buffer between the gun mount and the receiver on the AGL .

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