International market for a reusable launch vehicle

A reusable launch vehicle could be developed early next century if the X-33 program is successful. Its development will be funded by industry, and the vehicle will be operated privately. A critical task is to assess the future market for such a vehicle. The total number of commercial payloads could range between 40 and 60 satellites per year, taking into account the market elasticity due to the launch price reduction. The RLV would face important competition from expendable launch vehicles. However, the RLV could capture two-thirds of this market, or 26–33 commercial payloads per year.     

可重复使用运载器机翼外形优化

研究了有翼可重复使用运载器机翼平面外形参数优化设计问题。在高超声速配平和低速水平着陆性能等约束条件下，利用混合遗传算法和粒子群优化算法来选择最优机翼外形参数，使机翼重量最小化。在已知的不同质心位置下求得相应的最小重量机翼外形。亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。为了降低计算耗费，使用均匀设计和逐步回归方法建立了低速气动力回归模型。整个优化过程在Matlab集成环境下完成。     

亚轨道重复使用运载器总体多学科优化方法

针对亚轨道运载器总体设计多学科耦合的特点,从任务规划、学科建模、集成和求解策略等方面对多学科优化方法进行了研究。以助推亚轨道飞行器为对象,确定了学科模块组成、功能和数据耦合关系。建立了与总体设计过程相适应的7个学科模型,包括几何主模型、气动、推进、弹道、气动热、传热/热防护系统、结构。结合飞行器任务要求和基准方案,从系统级定义了多学科优化问题,包括目标函数、约束条件和设计变量。基于多学科软件框架集成学科模型,采用多学科可行法作为求解框架,建立了亚轨道飞行器多学科优化系统,选择SQP算法完成了以起飞总重为目标的优化。结果显示,优化后,发动机结构、热防护系统有所增加,但结构质量和燃油消耗减小,综合作用使总重减小2.4%,体现了多学科优化的协同作用。     

Federal tax incentives and financing for the reusable launch vehicle

Financing a very large new space transportation system is a major venture. It requires an initial investment of many billions of dollars and will be expected to perform successfully during its lifetime of at least twenty-five years. In the past, space systems of this magnitude have been funded, owned and operated by the government. Today, as the responsibility for opening and maintaining space systems is expected to shift from government to industry leadership, the reusable launch vehicle (RLV) presents the private sector with the challenge of finding ways of financing and building a system that will prove to be a successful private venture. The government, recognizing that it is a major customer of the RLV and that new technology must be developed for the RLV to work and to adequately reduce the cost of access to space, will fund some Initial technology development as well as provide some incentives for a private operator. This paper shows that using the current tax system's corporate investment benefits, coupled with a favorable debt financing arrangement, a profitable privately owned RLV system Is within the realm of possibility.     

垂直着陆重复使用运载火箭对动力技术的挑战

运载火箭采用垂直着陆方式实现重复使用的需求对火箭各分系统提出了新的挑战,而动力系统面临的挑战最大。垂直着陆重复使用运载火箭要求发动机提供正常的上升段推力外,还需提供运载火箭子级垂直着陆回收过程中的平稳减速力和稳健控制力,因而要求发动机具备可重复使用、大范围推力调节、二次起动、适应回收环境等多种能力,并具备较低成本。本文介绍了美国SpaceX公司开展FALCON 9系列运载火箭一子级垂直着陆回收技术研究和相关飞行试验的最新进展,研究并提出了垂直着陆重复使用运载火箭对动力技术的需求。     

可重复使用运载器复合材料低温贮箱应用研究

轻质高强度低温贮箱是发展可重复使用运载器（RLV）的关键技术之一。本文论证了聚合物复合材料作为低温贮箱材料的必要性和可行性,介绍了复合材料低温贮箱的研制现状,对聚合物基体和纤维选择、设计技术、复合材料的成型及其性能测试等进行了探讨,指出了复合材料低温贮箱的发展趋势,并就我国复合材料低温贮箱的发展给出了建议。     

Implications of previous space commercialization experiences for the reusable launch vehicle

In evaluating the prospects for the development of a commercially viable RLV, it may be useful to examine ’lessons learned‘ from previous space commercialization efforts– both those that succeeded and those that did not. It can be argued that several distinct streams of market and technological development may have to converge for successful commercialization of space systems to occur. Factors influencing the prospects for commercialization include the size and growth rate of the potential customer base, the extent to which a governmental customer exists to underpin the market, the development of associated ’value-added‘ markets, the stability of governmental policies, the availability of enabling or enhancing infrastructure, the levels of technological and business risk, and the degree to which competitive markets exist. This paper examines two previous space commercialization experiences, evaluates the relative importance of the various factors that influence the prospects for success of commercialization efforts, and assesses the implications of those factors for the commercial viability of the proposed RLV.     

可重复使用航天器金属热防护系统的结构优化进展

根据美国开发的金属热防护系统,分析了用于可重复使用航天器的金属热防护系统的发展和现状,详细介绍了几代金属热防护系统的总体结构、高耐热蒙皮结构、绝热结构的不断演化和设计的优化进展。并且从结构装配方面,阐述了单个金属热防护系统结构、多个金属热防护系统结构以及金属热防护系统与刚性结构的装配设计的优化发展,为工程在结构设计和优化方面提供一定的参考依据。     

IPL：运载火箭测试数据自动判读语言

为确保运载火箭测试数据的完整性与正确性,克服传统人工判读模式判读效率低、易误判漏判以及通用编程语言自动判读模式判读适应性、扩展性、复用性差的不足,提出并设计运载火箭测试数据处理领域的自动判读语言IPL（Interpretation Language）,以及配套的语言解析与执行器,实现了运载火箭测试判据的形式化定义与描述,减轻了业务人员的学习、判读成本,使得海量测试数据的判读在分钟级即可全部自动完成,目前已在多种新一代运载火箭工程实践中得到成功应用。     

Development trend review of foreign heavy-lift launch vehicle

重型运载火箭发展的核心问题是总体构型方案,包括箭体直径、发动机选型及技术继承性问题.通过对国外重型运载火箭发展脉络进行分析,研究其发展特点,总结了发展趋势,即重型运载火箭由传统的串联构型向捆绑助推器构型发展;重型运载火箭采用大直径箭体和大推力发动机;充分发挥液体、固体发动机的优势,实现最佳动力组合,并充分利用成熟技术.最后,提出我国重型运载火箭总体设计工作的相关建议.     

新一代运载火箭增压技术研究

随着新一代运载火箭研制的开展,新型120t级高压补燃液氧煤油发动机将得到广泛的使用,该发动机采用的推进剂贮箱增压系统设计被列为新一代运载火箭研制的重大关键技术之一。在对国内外主要液体运载火箭增压方案进行分析的基础上对120t级液氧煤油发动机的贮箱增压系统进行了研究,提出了液氧贮箱采用压力传感器与电磁阀组合的常温氦气加温增压,煤油贮箱采用压力传感器与电磁阀组合的常温氦气增压方案,并针对液氧贮箱采用常温氦气加温增压的方案开展了理论分析和全尺寸系统级试验研究。理论分析和试验结果表明,该增压方案可行。     

小型固体运载火箭运载能力分析

针对控制系统,采用姿控发动机和格栅舵的小型多级固体运载火箭开展了运载能力分析研究.给出了运载火箭飞行方案,提出了一种飞行程序角的工程设计方法.给出了姿控发动机工作模型,建立了六自由度弹道计算和优化模型,采用混合进化算法进行弹道优化,并给出了仿真算例.仿真计算及分析表明,小型多级固体运载火箭满足发射小卫星的运载能力要求,姿控发动机推进剂分配方案合理,为总体方案论证和初步设计提供了理论依据.     

国外重型运载火箭发展趋势述评

重型运载火箭发展的核心问题是总体构型方案,包括箭体直径、发动机选型及技术继承性问题。通过对国外重型运载火箭发展脉络进行分析,研究其发展特点,总结了发展趋势,即重型运载火箭由传统的串联构型向捆绑助推器构型发展;重型运载火箭采用大直径箭体和大推力发动机;充分发挥液体、固体发动机的优势,实现最佳动力组合,并充分利用成熟技术。最后,提出我国重型运载火箭总体设计工作的相关建议。     

运载火箭遥测数据智能判读算法应用

在运载火箭高发射密度、高判读需求、高数据量的背景下,现有自动化判读的判据覆盖率不全、判据编写门槛高、耗时多的问题日益凸显,缺少较通用的算法对传统判读算法未覆盖的判读任务进行判读补充,进而影响运载火箭效果评估与系统性能评定。为充分挖掘海量遥测数据中隐含的参数变化规律,设计智能判读算法作为传统算法的有益补充,提升传统判读的判读覆盖率和判读效率。以液体运载火箭长期加电试验产生的遥测数据为研究对象,设计集成神经网络智能判读算法,在给出的判读指标下研究得出,集成神经网络在频率异常、丢帧等五种现有判据难以描述的判读场景下,判读性能提升30%,提高了现有判据的覆盖率,后续可为判读体系完善和智能判读落地提供研究参考。     

中国重型运载火箭动力系统研究

分析了未来航天发展趋势,指出为实现载人登月和深空探测,发展重型运载火箭,研制大推力火箭发动机势在必行.提出了中国重型运载火箭主动力--_1500吨级液氧煤油发动机和200吨级液氧液氢发动机的总体方案,确定了发动机的主要参数,明确了发动机的关键技术,考虑了发动机的研制条件,进行了发动机研制策划.根据中国的技术水平和经济实...     

运载火箭静电带电理论研究与试验验证

运载火箭在大气中飞行会使箭体、发动机等表面带电,当静电累积达到一定量级并产生静电放电时,可能对箭上电气设备造成灾难性后果。在众多起电原因中,文章重点研究发动机喷流起电和摩擦起电过程,提出这2种起电方式的计算模型,并结合相关静电测量试验,确定这2种起电方式的等效充电电流,定量分析火箭最大静电带电电位,为指导单机设计及系统防护提供参考。     

国外固体运载火箭技术的新进展与启示

固体运载火箭作为快速进入空间的有效手段,已成为目前各国航天运输系统的重点发展方向之一。通过对国外固体运载火箭技术的发展脉络进行分析,研究其发展历程及特点,从四方面总结出其发展趋势,即向低成本、高可靠、快速机动发射发展;向固体运载与导弹技术共用发展,深层次拓宽军民融合领域;向与捆绑式运载火箭的大型固体助推器技术共同发展,并充分利用成熟技术;向模块化、可扩展化设计发展。最后,对国内发展固体小型运载火箭提出了相关建议。     

某火箭发动机系统振动特性测试和仿真分析

从计算和试验两方面分别研究了某火箭一级发动机的振动特性。侧重介绍了模态试验和商业有限元软件在发动机振动特性快速分析中的具体应用,以及发动机三维有限元模型如何应用于全箭有限元梁模型。计算结果和试验结果吻合较好。     

Developing new launch vehicle technology: The case for multi-national private sector cooperation

Space is now a global business, yet the cost of getting to space is still high. Developing new launch vehicles that are cheaper, safer, and more reliable is the key to both rapid commercial growth and to more and better government uses of space. However, the R&D process leading to new launch vehicles is expensive and technically challenging; the past 50 years have seen many government development programs, but no major technological breakthroughs. Perhaps, it is therefore time to think about other ways of developing new launch vehicles. The best expertise in this field resides primarily with private companies and is spread across many actors and nations. A consortium led by space firms might be a better approach to opening up space in the 21st century. Governments will have to develop new policies treating space as though it were a commercial industry, in particular, relaxing export trade restrictions wherever possible. Issues of dual-use may be outweighed by the rapidly growing widespread availability of launch capabilities. Since new launch vehicles will require large up-front R&D expenditures, government support will continue to be needed to supplement private capital funds. Contributions to this effort should be international. However, difficult it might be in today's security conscious environment to reorient government policy, doing so may offer the most efficient and successful way to break the technological and economic barriers to more reliable access to space.