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双语推荐：发射

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火箭弹发射控制电路为火箭弹提供检测和点火信号，发射控制电路关系到火箭弹发射的可靠性与安全性，具有重大意义。设计了一种火箭弹发射控制电路，采用钝感点火头，可实现小电流检测，大电流点火，保证检测阶段不让火箭弹点火，发射阶段确保火箭弹发射，保证了火箭弹发射的可靠性与安全性。
Rocket projectile launch control circus is designed to test and launch a rocket projectile. It is closely related with the reliability and safety of the launch of projectile,which is of great importance. The thesis designs a launch circus with insensitive igniter to use small circus to test and big circus to ignite, which can make sure not to mistakenly launch the rocket projectile during the test,and to securely launch the projectile during the ignition. It makes sure of the reliability and security of the launch of rocket projectile.

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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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为了研究某空空导弹内埋弹射发射系统结构参数对其发射分离参数的影响，针对多刚体模型不能准确仿真发射过程中发射俯仰角速度存在强烈柔性波动效应的问题，基于刚柔耦合多体动力学理论，建立了某空空导弹发射系统刚柔耦合动力学仿真模型；采用该模型对发射系统的导弹发射分离参数进行仿真，详细讨论了导弹重心、弹射发射行程、结构刚度等设计参数对导弹发射分离角速度的影响；发现导弹重心位于垂直作动筒作用点后，4根同步杆和4个转动臂需保证较好的刚度，且发射行程不超过350 mm时，导弹弹射分离角速度不会产生抬头效应，发射安全性较好。
In order to study the influence of structure design parameters of air-to-air missile buried eject launcher to launching separation parameter,multi-rigid-body system cannot simulate the problem that the pitching angular velocity has high volatility during launching.Based on the rigid-flexible coupled multi-body dynamics theory,an air-air missile launcher system dynamics model was established and used to ana-lyze the launcher system dynamics characteristic.This paper focuses on analyzing the infection of important design parameter to missile launch separate angle speed,including the center of missile mass,launch dis-tance,and machinery rigidity.Results show that,the center of missile mass must behind vertical actuator, synchronous connecting rod and rotor arm must have enough rigidity,the launching distance must beyond 350 mm.

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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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研究了空间平台发射追踪器的相关技术和组合机动路径规划策略。首先对空间发射方式、发射窗口和发射初始姿态需求进行了系统分析,选择了合理的发射方式,提出了发射方案设计策略。针对空间平台发射追踪器实现与目标远程交会的组合机动问题,进行了基于投放发射的空间交会任务分析。建立了非线性多冲量推进最优变轨数学模型,以及基于空间发射的多约束多参数组合机动路径规划模型。设计了遗传算法+序列二次规划串行混合求解策略进行求解,并对发射方案和参数选择的必要性进行了仿真分析。仿真结果表明,本方法能够有效实现基于空间发射的远程交会任务设计及组合机动路径规划。研究结果为空间发射任务和组合机动路径规划提供了有价值的参考。
Launching technology that space platform releases the chaser,together with trajectory planning of combined maneuver,is studied in this paper. Based on analysis on launch mode,launch window and initial launch attitude requirement,drop launch is chosen,and launch scheme is proposed as well. Aiming at the representative combined maneuver which is a long-distance rendezvous based on space launch technology,mission analysis is carried out. Nonlinear mathematical model for optimal multiple -impulsive rendezvous is given,and trajectory planning model subject to constraints is established for combined maneuver. A serial hybrid algorithm combining GA with SQP is designed. Moreover,the necessity analysis and simulation is carried out for launch scheme and parameters. Simulation results indicate that the analysis and strategies can availably implement the space launch mission design and trajectory planning for combined maneuver. Some results are valuable for applications on space operations.

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针对发射药的受力特点,采用巴西试验对发射药的力学性能进行了试验研究,应用弹性接触理论和弹性力学平面问题的相关理论分析了其应力分布规律,结合Griffith强度准则得到了发射药抗拉强度的计算公式。结果表明,初始裂纹发生在发射药的中心部位,并发生对径劈裂,表明巴西试验适用于测量发射药的抗拉强度;发射药抗拉强度是由发射药破碎时的载荷和发射药和压头的接触面宽度决定;当储存时间由39 a延长到47 a时,发射药的抗拉强度由13.11 MPa变为12.58 MPa,减小4%。
For the loading features of propellant,the mechanical properties were studied by brazilian test. Theories of Hertz elastic contact and elastic mechanics plane stress were applied to analyze the stress distribution law,and the formula was obtained to cal-culate tensile strength for propellant from Griffith strength criteria. Results show that the initial crack forms at the center region of propellant and propagates along the loading direction,which proves that the Brazilian test is suitable for measuring tensile strength of propellant. The tensile strength of propellant is determined by the load when the splitting happens and the contact width be-tween propellant and indenter. When the storage time extends from 39 years to 47 years,the tensile strength of propellant changes from 13. 11 MPa to 12. 58 MPa,decreasing by 4%.

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在数字 B 中,发射波束合成器驱动超声探头产生超声信号,并通过对多通道超声信号发射时间的控制完成发射聚焦.该文结合实际应用,完成了一个32通道的发射波束合成器的硬件电路设计和发射控制器的FPGA实现.
In the digital B-Ultrasonic system, the transmit beamformer drives ultrasound probe to produce ultrasound signal, and complete the transmit focusing through controlling the multi-channel ultrasonic signal transmission time. In this paper, according to a practical application, complete a 32-channel transmission beamformer hardware circuit design and the transmission controller FPGA implementation.

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英国海军的“鱼狗”箱式鱼雷发射装置集储存与发射功能于一身,具有大大简化发射准备工作、根据实际情况模块化组合并通过机械形式集中施力等特点,近年来已逐渐成为鱼雷发射装置的研究热点.通过对英国“鱼狗”箱式鱼雷发射装置结构特点的详细分析,提出了我国舰用鱼雷发射装置应加强标准化、模块化设计,加强箱式发射装置、加强便捷化、加强新的发射技术等方面的研究,从而进一步提高舰艇快速反应能力,应对日益复杂的海洋战争.
British Navy′s kingfisher box-type torpedo launcher integrates storage function with launching function to greatly simplify the launching preparation. And it possesses the advantages of modular combination according to actual situation and exerting concentrated force on torpedo mechanically. Hence, it has become a hot spot in torpedo launcher research. In this paper, the structural characteristics of the kingfisher box-type torpedo launcher are analyzed. And sug-gestions about researches on shipborne torpedo launchers in China are offered, i.e. more attention should be paid to standardized and modular design, box-type torpedo launcher, convenient operation, and new launching technologies for gaining rapid reaction ability of warships.

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与普通热阴极相比较，场致发射电子源利用高场强下的隧穿效应产生电子发射，不需要高温加热，有利于器件的小型化和集成化，在平板显示器、微波放大器和 X 射线管等电子器件中有很好的应用前景。在微波放大器、X射线管和离子推进器等电子器件中，通常要求较大的阴极发射面积（几平方毫米）和较大的发射电流（几十毫安）。现有的场致发射电子源，由于诸多因素的限制，其发射电流远不能达到器件的要求。本文深入探讨了影响场发射电流的因素，采用新的发射体结构，增强了发射体与基底的附着能力，有效地提高了场发射电子源的电流发射能力，从直径为1mm的发射面积上获得了43.6 mA的发射电流。
Comparison with the thermonic cathode, the electrons are emitted from the field emitters due to tunnel effect with high electric field. Because the cathode need not be heated, the field emission electron source is quite easy to be integrated in a small device. It has a promising application in flat display panel, microwave amplifier, and X ray tubes. However, in these electron devices, a large field emission current (multiple ten mA) is required. The field emission cathode can not provide such a big current at this moment. After the analysis of the mechansim of field emission current limitation, a new structure of field emitters is proposed in this paper. With the strong adhension between emitters and the substrate, a very large field emission current as 43.6 mA is obtained from a circle region with 1 mm diameter.

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为降低发射成本,充分利用运载能力,双星发射成为当前国际商用卫星发射普遍采用的一种发射方式。根据北斗导航系统组网需求,北斗导航系统中某类非静止轨道卫星要求采用一箭双星的发射模式,为适应双星发射需要,研制了卫星整流罩、卫星支架、仪器舱等重要结构。从设计原则、方案论证与比较、总体方案确定、系统级地面试验验证等4个方面对CZ-3A系列结构总体双星发射技术的研制现状进行总结,同时指出未来多星发射技术的发展方向,为后续双星乃至多星发射任务提供研制借鉴。
In order to reduce the launch costs, and to make full use of launch capacity, dual launch strategy is widely used in current international commercial satellite launch. Based on the networking requirements of BeiDou Navigation Satellite System, the dual launch mode is required by certain types of non-geostationary satellite. Some important components are created to meet the requirements of dual launch, such as the payload fairing, payload adapter, vehicle equipment bay, etc. In this paper, the development status of structure overall design over the dual launch technologies of the LM-3A series launch vehicle are summarized from four aspects, which including the design principles, the argumentation and comparison of scheme, the determination of overall scheme and the validation of system-level ground test. The development trend of multi-launch technologies are indicated, which will provide references and evidences for the research of future dual launch or multi-launch technologies.

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