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双语推荐：气动发射

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气动发射武器以弹药结构简单和发射能量可控的优势在反恐防暴领域有着巨大应用前景，提出了一种以压缩空气作为动力源的气动发射武器的工作原理；基于气体动力学理论和赫兹接触理论，建立了其变质量热力学模型和摩擦力模型，从而建立了发射过程的动力学模型。采用MATLAB/Simulink对模型进行了数值仿真，得到了恒压气源条件下的膛内气体状态参数和弹丸运动参数的变化规律；并在此基础上分析了结构参数和动力源参数变化对气动发射武器发射过程的影响。研究结果对压缩空气驱动的气动发射武器的研发和设计具有理论指导意义。
The pneumatic weapon has broad application prospects with advantages of simple structure of ammunition and controllable launch energy.The working principle of a kind of compressed air-driving weapon was proposed here. Based on the theories of gas dynamics and Hertz contact,the model of its variable mass thermodynamic process and the friction force model were established,and the dynamic model of its launching process was built.With MATLAB /Simulink,the numerical simulation solutions to the state parameters of inner gun-barrel gas and the motion parameters of the projectile were obtained under the condition of a constant pressure of air supply.Furthermore,the effects of compressed air pressure changes and structure parameters on the launching process were analyzed.The results have great theoretical significances to guide the research and design of compressed air-driving weapons.

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为获得高速破片、稳定弹道性能，自行设计加工了用于破片发射的气动脱壳弹。分析了该气动脱壳弹气动脱壳的原理及气室的充排气规律，计算了某火炮发射该气动脱壳弹时不同气孔面积和气室容积下其气室的压力变化，分析了影响该气动脱壳弹设计的关键因素。分析结果证明：气孔面积和气室容积在气动脱壳中起着非常重要的作用，是该种气动脱壳弹设计的关键要素。
In order to obtain high-speed fragments, stable ballistic performance, designed and processed the gas-propelled sabot-discarding pill for launching fragments. Analyzed the principle of gas-propelled sabot-discarding and the gas-filling and exhaust gas law of gas chamber, the motion of the gas-propelled fragments has been carefully calculated under the different spiracle areas and gas chamber volumes during the discarding process in certain artillery, and the key factor influencing the design of the gas-propelled sabot-discarding pill has been analyzed. The results show that the stoma area and the gas chamber cubage play a very important role in the gas-propelled sabot-discarding motion, it is a key factor of gas-propelled technology.

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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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介绍了一种无人机气动弹射系统的组成、结构、工作原理和发射过程。通过对其物理模型进行简化，采用基于封闭矢量环法与力平衡方程的联立约束法分析推导了该无人机弹射系统的动力学求解数学模型。在Matlab／Simulink环境中创建了弹射系统发射过程的动态仿真模型，得到了无人机的加速度和速度随时间变化的曲线等参数。并将遗传算法与Simulink有机结合，方便实现了气动弹射系统的仿真与优化。结果表明：该无人机弹射系统改善了现有弹射系统弹射加速度有明显峰值、发射轨道利用率低、发射长度过长等不足，为无人机气动弹射系统的工程研制提供了重要的理论参考，优化后进一步缩短了发射长度，减小了最大过载和加速度波动，为无人机气动弹射的系统级建模、动态仿真与性能优化提供了一个工作平台。
The constitution, structure, working principle and launching process of an UAV pneumatic launcher are described.Dynamic mathematical model of the pneumatic launcher is analyzed and established by using the simulta-neous constraint method based on the closing-vector-circle method and the equations of force balance by simplifying its physical model.In order to get the parameters such as the variations of velocity and acceleration with time, the dynamic simulation model of the launching process is established in the environment of Matlab/Simulink.By combi-ning Genetic Algorithm with Simulink, the simulation and optimization of the pneumatic launcher are realized .The results and their analysis show preliminarily that: the pneumatic catapult launcher suppresses the drawbacks of the existing launch devices such as requiring substantial space, acceleration peak,and low efficiency of track;it offers significant theoretical reference for the manufacture of the UAV pneumatic launcher

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基于气动不平衡式发射装置的基本特点,通过弹道建模仿真,得出较大深度时提高发射水雷出管速度的方法并保证发射阶段的安全性。仿真结果表明,通过控制泄放装置开启(关闭)状态可以在较大深度时有效地保证发射水雷安全离开发射平台。
The paper is based on aerodynamic non-balance torpedo launcher characteristics, Through the simulation of the mod-el,results of the muzzle speed of the mine and the launching security influenced on the relief device. The simulation results show that through control the relief device state of open or close can be effectively ensured the safety of platform of launcher.

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对某水下气动发射装置进行了理论分析，研究了其内弹道特性。利用数学建模方法对发射过程进行了建模并对内弹道性质进行了计算。对影响内弹道性能的3个主要参数：武器运动的初始阻力、发射阀最大开启面积和发射气瓶初始充气压强进行了分析。计算结果表明：发射管最大膛压的主要影响参数为武器运动初始阻力；而武器出管速度的主要影响参数为发射气瓶初始充气压强和发射阀的最大开启面积。
An underwater pneumatic launcher was studied to analyze its interior bal istic character-istics.Using mathematical modeling method,the interior bal istic model was established.The in-fluences of three parameters were discussed including the critical moving resistant force,the maximum open area of the launch valve and the initial inflation air-bottle pressure.The results show that the maximum chamber pressure is mainly determined by the critical resistant force, and the exit velocity of the weapon out of the launch tube is mainly determined by the initial infla-tion air-bottle pressure and the maximum open area of the launch valve.

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作为舰载无人机系统的重要组成部分,无人机的发射环节一定程度上影响了无人机系统的作战效能。为了提高无人机发射效能和非战时维护贮存能力,针对舰载小型无人机系统,提出了一种舰载箱式无人机发射系统的设计方案。该系统采用贮运发一体结构,由大型贮运传动箱体、发射平台以及推拉机构组成,贮运传动箱体由机械框架结构和气动及液压系统组成,由PLC控制实现传动自动化可视化;发射平台由二自由度位置伺服系统构成,采用交流永磁同步伺服电机驱动,从而使系统可获得舰体摇摆状况下的高精度传动与发射;推拉机构的设计,使得发射平台可以在两个贮存箱体之间切换,实现多箱无人机共用同一发射平台,减小系统占据舰艇空间。该系统可有效提高无人机维护保养能力和发射效能。
As an important part of a carrier-based Unmanned Aerial Vehicle (UAV)system,to some extent,the launch part of UAV affects the operational effectiveness of UAV system. In order to improve the launching performance and capability of non-war time routine maintenance and storage of the UAV,the design scheme of a carrier-based box-type UAV launch system was presented by aimed at a small carrier-based UAV system. An integrated structure of launching,transmission and storage was used by the system, which was made from large storage transmission box,launch platforms and sliding mechanism. Storage transmission box frame structure was consisted of mechanical frame and pneumatic and hydraulic system components,driven by the PLC controller to implement visible automated transmission. The launch platform was constructed by a 2-D position servo system that driven by AC permanent magnet syn-chronous servo motor,thereby allowing the system to obtain high-precision of transmission and launchi

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潜射无人机因其平台的特殊性,有干式、湿式等不同的发射方式,其中关键技术之一是机翼折叠技术。设定潜射无人机的运动过程为从水中到空中,将水流场分为水下无粘条件和水下有粘k-e条件,通过计算不同折叠翼方案潜射无人机的主要气动性能,分析比较得出:机翼纵向后掠部分折叠的方案比较适合潜射无人机的湿式发射,机翼纵向完全折叠进入机身的方案比较适合干式发射。
Because of the particularity of its platform , submarine -launched UAV has different launch modes , such as dry and wet .One of the key technologies is the folding wing technology .For several different folding wing schemes , it designs a sample with the same body structure .A movement process is set from water to air , and the flow field is divided into underwater non viscous conditions and underwater viscous k -e conditions .The paper compares and analyzes the aerodynamic performance calculations of different folding wing schemes .The re-sults indicate that longitudinal swept partially folding wing scheme is more suitable for wet launch , longitudinal completely folding into the fuselage wing scheme is more suitable for dry launch .

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无人机单侧导弹发射后，无人机重量特性、重心位置、气动特性发生变化并同时产生附加的干扰力矩，无人机需要在控制系统作用下尽快恢复稳态飞行。通过在Matlab/Simulink中建立无人机六自由度非线性力学模型、控制系统模型、发动机模型、重力模型、标准大气模型、flight gear软件接口等，模拟仿真无人机单侧导弹发射过程，同时将仿真结果进行可视化视景输出，确保无人机系统平台在导弹发射过程中无人机能够很快恢复稳定姿态并按照预定轨迹飞行。视景模拟仿真结果表明：该无人机平台能够顺利完成导弹的安全发射。
During one side missile launching, Unmanned Aerial Vehicle ( UAV) many characteristics such as weight char-acteristics, center of gravity, aerodynamic characteristics will be changed. Disturbance moments will be generated, which may influence the security of UAV. Under such circumstance, UAV need to maintain a steady flight with flight control sys-tem. To solve this problem, UAV six degrees of freedom nonlinear dynamic model, flight control system model, engine mod-el, gravity model, standard atmosphere model and flight gear software interface are established in Matlab/simulink to simu-late the launching process. Visual simulating technology is used to obtain a straight and apparent view of the results. The dy-namics results of the UAV during this launching process such as recovering to a stable attitude and keeping the specified flight path can be analyzed easily. The simulation results imply that the UAV platform can accomplish missile launching mis-sion successfully, safel

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抛投器广泛应用于多种救援场合，目前抛投器的动力主要有气动式和火药式两种。本文首先介绍了目前抛投器发展现状，根据现有抛投器的技术参数，提出了一种采用电磁力给抛投器提供动力的新方式。接着综合分析三种电磁发射方法，选取线圈型电磁发射方式，根据异步感应式直线电机基本原理和有限元电磁场数值计算理论，利用COMSOL Multiphysics软件建立电磁抛投器结构图和有限元仿真模型，对这种新型电磁抛投器不同抛体金属套材料和不同初、次级空气长度这两个重要结构参数进行仿真分析对比，给电磁抛投器选择了一组优化的结构参数。
Throwing device is widely used in a variety of rescue occasions. At present, its power mainly uses pneumatic power or gun powder. This paper first discussed the present situation of throwing device. According to the existing throwing device’s technical parameters, the paper suggested a new method that using electromagnetic force for a throwing device. After analyzing synthetically three kinds of electromagnetic emission methods, this paper finally chose the coil electromagnetic emission method. By the basic principle of asynchronous induction motor and the numerical calculation of electromagnetic field theory in finite element, this paper utilized the software COMSOL Multiphysics to establish a structure of the electromagnetic throwing device and its simulation model of finite element. Then the paper simulated and analyzed comparatively the throwing devices with different metal materials of projectile and different air length between primary coils and secondary projectile, t

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