火工品包装箱抗震性能的线性动力学分析

通过静力学分析,忽略接触摩擦,将火工品包装箱的抗震性能分析转化为线性动力学问题,建立了有限元模型并分析模态,得到了前20阶振动频率,在此基础上对包装箱进行了随机振动和水平冲击测试。该方法对优化火工品包装箱设计以提高箱体结构的抗震性能,具有实际意义。     

基于PID控制技术的卫星有效载荷舱包装箱的反共振实现

结合XX-1型卫星有效载荷舱的特点及功能需求,分析了其包装箱在不同环境、交通方式和路况下的振动工况,采用PID控制技术对其进行了反共振补偿,建立了系统状态方程,并通过反共振振幅控制试验对其抑制能力进行了分析。结果表明:提出的主动隔振措施较好地实现了全频域点的减振效果,对卫星有效载荷舱的勤务运输提供了较为理想的防护。     

可折叠水产品运输保温包装箱结构设计

目的 开发可折叠水产品运输保温包装箱。方法 借鉴纸包装结构设计中的可折叠设计思想, 以塑料中空板为箱体材料, 结合保温材料, 得到可折叠水产品运输保温包装箱结构设计方案, 将其与普通塑料泡沫箱进行物流成本对比分析, 通过抗压试验测定分析不同类型水产品运输保温包装箱的抗压强度。结果 该包装箱实现了空箱储运时可折叠, 降低了物流成本; 箱子抗压强度好, 优于市场上常用的水产品塑料泡沫箱, 同时可通过调整外箱体材料及保温材料来优化包装箱的各方面性能; 在采用该包装箱进行水产品包装时, 需在内包装中增加塑料袋来满足水产品物流运输过程中防水渗漏的要求。结论 该可折叠水产品运输保温包装箱的结构设计方案可行, 力学性能好。     

局部以纸代木包装箱的研究

为缓解木材的供需矛盾,提出了局部以纸代木包装箱的概念。对比了全胶合板包装箱和局部以纸代木包装箱的结构,对局部以纸代木包装箱的力学性能进行了分析。结果表明,在满足应用条件的情况下,局部以纸代木包装箱比全胶合板包装箱更经济实用,具有更广泛的应用潜力。     

卷烟包装箱回收物流系统调度优化模型

为优化烟草行业包装箱回收工作,结合烟草行业包装箱回收物流过程的特殊性,针对卷烟工厂、卷烟包装箱回收中心、卷烟商业地区性配送中心构成的闭环物流系统网络,将卷烟工厂生产计划所需包装箱需求、卷烟包装箱回收过程中各环节的回收合格率、包装箱处理检测费用、处理中心回收能力、各环节之间单位运费等因素引入模型,建立了总成本费用最小的卷烟包装箱回收物流系统调度优化模型,结合实际案例数据,利用优化软件CPLEX得到其最优调度方案,而且对影响优化方案的两个关键因素进行了分析。研究结果表明:利用包装箱回收物流系统调度优化模型可提高企业的经济效益,回收的包装箱合格率越高,回收经济效果越好;回收环节处理的成本越高,回收包装箱越没有价值。     

木质包装箱结构优化设计

目前我国市场使用大量的包装箱仍以木材为主,经调查木质包装箱用料过剩的现象比较严重.以某厂一款产品的包装箱为例,对其进行了结构分析,发现在设计方法上造成木材大量的浪费.为此提出了木质包装箱优化设计的方案,阐述了木质包装箱优化设计的方法和步骤.采用新的木质包装箱优化设计的方法,使该款产品包装箱在满足使用条件的情况下,其木材用量节约30%左右.     

国内外弹药包装材料的研究进展

主要介绍了国内外弹药包装用材料的发展,分析了弹药包装箱储存的环境条件及其使用性能要求,总结出木材和金属材料已经不再适合于制备弹药包装箱。复合材料具有比强度高、比刚度高、耐腐蚀等一系列优点,将成为包装箱用材料的首选,实现其多功能一体化和减重。     

某新型导弹包装箱动力学特性分析

目的 研究某新型结构导弹包装箱的动力学特性。方法 利用有限元分析方法对导弹包装箱进行模态分析和随机振动分析。结果 得到了导弹包装箱的固有频率和振型,以及结构在随机载荷作用下的动力学响应结果,导弹包装箱的前6阶固有频率分布在13~44 Hz范围内,在随机载荷的作用下,导弹包装箱3个方向的最大应力分别为97.6,149.3,151.1 MPa。根据导弹包装箱的动响应结果确定了箱体在随机振动环境下的危险部位。结论 在路面随机载荷作用下,箱体的整体结构满足设计要求,为导弹包装系统的设计和校核提供了依据。     

炮弹塑料包装应用探讨

通过对国内外弹药包装的研制现状和发展趋势的分析，得出了塑料炮弹箱的应用将成为炮弹包装箱的主流。从力学、阻燃、密封和环保等8个方面分析了炮弹塑料包装箱的优点。结合国内情况，对其研制的可行性从技术上有重点地进行了分析，从而得出了可以研制出能够达到设计技术要求的炮弹塑料包装箱的结论。     

气体包装在卫星包装上的运用

正笔者多次撰文谈到气体包装在民用或军事领域内的运用,特别是在高科技领域内的运用,最近见行业刊物的报道,杭州某厂低温液化有限公司,首次承接的卫星包装箱通过中科院上海某公司验收评审,顺利完成交付使用。卫星安装在火箭前,要严格进行保护,以防止意外发生。卫星上天后处在真空中运行和工作,因此卫星研制后其内仪器仪表要防止外界环境的污染,因此卫星发射前必须得到有效的保     

整星隔振器动态特性的测试

整星隔振系统由若干个隔振器组成，均匀布置在适配器和星箭界面之间，能有效减小发射阶段卫星所承受的环境载荷，对提高卫星发射的可靠性和降低发射成本具有重要意义，是近十年来航天界发展的一项新兴技术。探讨了隔振器的结构设计形式，通过测试3种不同方案的单个隔振器的动态特性，比较其动态性能参数，对进一步研究整星隔振系统的设计和应用具有一定参考意义。     

Computer simulation methods for launch vehicle mission and control problems

The flight control system of a launch vehicle is the result of the right tradeoff between different objectives, such as the interaction between the control, guidance and performance aspects of a mission with specified end conditions and the analysis of the mission trajectories and vehicle systems under a variety of normal and failure modes. Hence an evaluation of the design and performance of such a system is not feasible through purely analytical means even with simplified models. This, together with the necessity for step-by-step refinement of the models used for the vehicle and its environment, calls for the computer simulation approach. The various considerations involved in developing and selecting the simulation model and implementing it on a computer are discussed. To illustrate the approach, a hybrid simulation evaluation of the performance of the first stage control system of a satellite launch vehicle and that of the controlled vehicle under different operational modes is presented.     

基于并联空气弹簧结构的卫星运输减振系统设计及振动特性分析

随着航天科技的发展以及日益增长的性能需求,对卫星的可靠性要求越来越高,对运输过程中的振动也提出了更严格的要求,导致目前的减振系统难以满足未来的运输需求。针对这种情况,设计了基于空气弹簧并联结构的卫星包装运输减振系统,并对其振动特性进行了分析。结合卫星运输箱的结构和减振需求提出了并联空气弹簧减振系统方案。基于实测参数建立了并联空气弹簧减振系统的多体动力学仿真模型,并验证了方案的可行性,并进一步研究了不同运输工况下系统的减振效率及安全性。构建了减振系统进行不同工况下的实车运输测试。研究结果证明基于空气弹簧并联结构的运输减振系统在实车运输中具有较好的减振效率,并可以保证设备在运输过程安全。该研究结果可为大型精密设备运输减振系统的设计提供参考。     

Multidisciplinary design and optimization of an air launched satellite launch vehicle using a hybrid heuristic search algorithm

A multidisciplinary design and optimization strategy for a multistage air launched satellite launch vehicle comprising of a solid propulsion system to low earth orbit with the implementation of a hybrid heuristic search algorithm is proposed in this article. The proposed approach integrated the search properties of a genetic algorithm and simulated annealing, thus achieving an optimal solution while satisfying the design objectives and performance constraints. The genetic algorithm identified the feasible region of solutions and simulated annealing exploited the identified feasible region in search of optimality. The proposed methodology coupled with design space reduction allows the designer to explore promising regions of optimality. Modules for mass properties, propulsion characteristics, aerodynamics, and flight dynamics are integrated to produce a high-fidelity model of the vehicle. The objective of this article is to develop a design strategy that more efficiently and effectively facilitates multidisciplinary design analysis and optimization for an air launched satellite launch vehicle.     

Performance evaluation of multi-sensor data-fusion systems in launch vehicles

In this paper, the utilization of multi-sensors of different types, their characteristics, and their data-fusion in launch vehicles to achieve the goal of injecting the satellite into a precise orbit is explained. Performance requirements of sensors and their redundancy management in a typical launch vehicle are also included. The role of an integrated system level-test bed for evaluating multi-sensors and mission performance in a typical launch vehicle mission is described. Some of the typical simulation results to evaluate the effect of the sensors on the overall system are highlighted     

基于压电堆和粘弹性材料的新型整星混合隔振系统

摘　要：为了降低振动载荷对卫星的影响,采用压电堆和粘弹性材料作为主被动隔振元件,设计一种新型的整星混合隔振系统,并对其隔振原理进行理论分析。通过有限元方法建立该隔振系统的有限元模型并分析其频率响应特性,根据分析结果,运用特征系统实现算法获取系统的最小阶状态空间模型来设计控制器,完成离线仿真。在此基础上,对低柔性模拟卫星进行整星混合隔振试验。仿真和试验结果表明,整星混合隔振系统能够有效地降低运载火箭传递到卫星的振动载荷。与整星被动隔振系统相比,整星混合隔振系统对低频振动分量具有显著的抑制作用,证明了该隔振系统的可行性和有效性,大大提高了卫星的安全性和可靠性。     

Development of navigation guidance and control technology for Indian launch vehicles

The orbital injection accuracy of any payload depends on the calibre of the inertial guidance system used on board the launch vehicle. This paper outlines the mission definition and the rationale for the selection of a proper guidance system to meet final mission objectives. The functions and the architecture of the navigation, guidance and control are discussed. The developmental aspects of the sophisticated inertial sensors, inertial systems, associated complex electronics, on-board computers, control actuators and systems are reported. The complexity of the on-board control and guidance software and the test and evaluation procedures used for their validation are included. The general scheme of the inertial guidance systems and the critical role played by them in the realization of Indian satellite launch vehicles SLV-3, ASLV and PSLV are presented in brief.     

A branch and cut algorithm for the VRP with satellite facilities

An important aspect of the vehicle routing problem (VRP) that has been largely overlooked is the use of satellite facilities to replenish vehicles during a route. When possible, satellite replenishment allows the drivers to continue making deliveries until the close of their shift without necessarily returning to the central depot. This situation arises primarily in the distribution of fuels and certain retail items. When demand is random, optimizing customer routes a priori may result in significant additional costs for a particular realization of demand. Satellite facilities are one way of safeguarding against unexpected demand. This paper presents a branch and cut methodology for solving the VRP with satellite facilities subject to capacity and route time constraints. We begin with a mixed-integer linear programming formulation and then describe a series of valid inequalities that can be used to cut off solutions to the linear programming relaxation. Several separation heuristics are then outlined that are used to generate the cuts. Embedded in the methodology is a VRP heuristic for finding good feasible solutions at each stage of the computations. Results are presented for a set of problems derived from our experience with a leading propane distributor.     

新型整星隔振系统动力学分析

在卫星的服役周期中,发射阶段的动力学环境最为恶劣,期间受到多种复杂载荷的作用。传统的星箭连接适配器由于刚度较大,给航天器的参数设计及生产带来了极大的困难。为了达到多轴隔振的目的,基于粘弹性材料受到剪切力作用时产生较大阻尼损耗的原理设计了一种新型整星隔振器。针对该隔振系统进行了简化,以质量刚度阻尼耦合的形式来模拟卫星和隔振器之间的关系,对其进行了隔振效果的分析。其中,重点对仿真中出现的隔振系统的一阶模态结构阻尼系数的饱和现象提供了详尽的理论和数值分析。最后,针对新型整星隔振器的工程具体应用提出了两点参考准则。     

一种整星隔振器的研制

在不改变卫星和运载火箭结构前提下,针对某型号的配重卫星模型的隔振要求和约束条件,研制出一种新型的整星隔振器,安装在适配器和星箭界面之间,阐述隔振器的设计路线,建立合理的有限元模型,进行隔振器的结构参数灵敏度分析和频率响应计算,最后对整星隔振系统的进行动态性能测试。有限元计算结果和试验数据表明,所研制的整星隔振器能够有效地隔离卫星在宽频带上横向和纵向振动,降低发射时运载火箭传递给卫星的环境载荷。