吸气式激光推力器概念设计

以发射10kg级微小卫星为航天任务背景,基于地面推力1000N的设计指标,分析了吸气式激光推进的主要性能参数,依据所建立的激光推进能量相似律理论和数值计算研究结果,对激光参数、聚焦系统和喷管子系统进行设计,完成了封闭的吸气式激光推力器概念设计循环。所提出的二次反射聚焦系统与抛物形喷管组合的吸气式激光推力器概念模型经数值计算程序验证,可以获得地面500N/MW的冲量耦合系数。所提出的设计理论和方法对激光推力器概念设计有一定的参考价值,是研制激光推力器模型的重要基础。     

空间技术系统的讨论

从社会需求出发和以满足空间任务目标的角度, 依据一般系统论的原则, 提出了建立空间技术系统的新概念。将空间技术系统划分为航天器进入空间技术、空间功能运用技术、空间防护技术和空间武器技术四大分系统组成的技术系统, 这有别于以发展运载器和航天器为主要目标而建立的空间技术系统体系     

装药几何参数不确定性优化设计

1引言固体火箭发动机装药设计,一般要求在满足发动机内弹道性能和相关约束条件下,选择药型并确定其几何参数,同时综合考虑燃烧室壳体内部绝热层、衬层和人工脱粘层的设计要求。装药设计作为发动机设计的核心,其设计质量很大程度决定了发动机性能优劣。航天飞机固体助推火箭发动     

科学发展观是实现中原崛起的行动指南

实现中原崛起是科学发展观的重要内容,科学发展观是实现中原崛起的行动指南.必须结合河南省实际,把科学发展观贯彻到促进中原崛起的各项具体工作之中.     

JPL Innovation Foundry

Space science missions are increasingly challenged today: in ambition, by increasingly sophisticated hypotheses tested; in development, by the increasing complexity of advanced technologies; in budgeting, by the decline of flagship-class mission opportunities; in management, by expectations for breakthrough science despite a risk-averse programmatic climate; and in planning, by increasing competition for scarce resources. How are the space-science missions of tomorrow being formulated? The paper describes the JPL Innovation Foundry, created in 2011, to respond to this evolving context. The Foundry integrates methods, tools, and experts that span the mission concept lifecycle. Grounded in JPL's heritage of missions, flight instruments, mission proposals, and concept innovation, the Foundry seeks to provide continuity of support and cost-effective, on-call access to the right domain experts at the right time, as science definition teams and Principal Investigators mature mission ideas from “cocktail napkin” to PDR. The Foundry blends JPL capabilities in proposal development and concurrent engineering, including Team X, with new approaches for open-ended concept exploration in earlier, cost-constrained phases, and with ongoing research and technology projects. It applies complexity and cost models, project-formulation lessons learned, and strategy analyses appropriate to each level of concept maturity. The Foundry is organizationally integrated with JPL formulation program offices; staffed by JPL's line organizations for engineering, science, and costing; and overseen by senior Laboratory leaders to assure experienced coordination and review. Incubation of each concept is tailored depending on its maturity and proposal history, and its highest-leverage modeling and analysis needs.     

态势感知的概念与发展综述及微纳仿生态势感知系统的顶层设计

简要综述西方科技强国的态势感知概念、态势感知系统研发现状与应用、主要研发计划,总结其经验与教训,分析中国发展态势感知技术的迫切性与突破点.提供解决方案,介绍科研课题"微纳仿生空间态势感知器"中的态势感知概念、包括需求分析、模型设计、概要设计、应用设计的系统顶层设计内容.态势是指生物或系统对其内部状态和外部环境的"综合印象",包括自身状况和变化趋势、外部环境呈现出的某种状态和形势、发展趋势等.具有类似生物感知能力的态势感知器需要对自身状况、外界环境的多种物理量进行综合监测,其目的在于获取自身和环境的全面的、系统的信息.应用成熟的微纳米技术成果,以仿生学为主要理论导引,采用快速原型法设计开发基于微纳米技术和仿生学的态势感知器,可以广泛应用在太空、军事、环境保护、工业、消费电子等领域.     

正压检漏的漏率

分析了现有的漏率定义,从质量、能量观点重新解释漏率。     

载人太空实验室

文章介绍了载人太空实验室的概念,及其与空间站的根本区别。简述了载人太空实验室的基本情况。     

概念设计阶段起落架接地点设计

针对现代民用飞机设计特点,尤其是某些新技术的应用和飞机系列化发展的需求,在充分吸收和借鉴传统飞机概念设计阶段起落架设计方法的基础上,从工程应用角度出发,总结并提出一套现代民用飞机概念设计阶段起落架接地点设计流程及方法。同时,按照设计流程将影响起落架接地点设计的限制因素划分为适航安全、性能、结构、空间布置、运营等影响因素,明晰各限制因素对设计产生的影响。     

Criteria for hypersonic airbreathing propulsion and its experimental verification

Hypersonic airbreathing propulsion is one of the top techniques for future aerospace flight, but there are still no practical engines after seventy years' development. Two critical issues are identified to be the barriers for the ramjet-based engine that has been taken as the most potential concept of the hypersonic propulsion for decades. One issue is the upstream-traveling shock wave that develops from spontaneous waves resulting from continuous heat releases in combustors and can induce unsteady combustion that may lead to engine surging during scramjet engine operation. The other is the scramjet combustion mode that cannot satisfy thrust needs of hypersonic vehicles since its thermos-efficiency decreases as the flight Mach number increases. The two criteria are proposed for the ramjet-based hypersonic propulsion to identify combustion modes and avoid thermal choking. A standing oblique detonation ramjet (Sodramjet) engine concept is proposed based on the criteria by replacing diffusive combustion with an oblique detonation that is a unique pressure-gain phenomenon in nature. The Sodramjet engine model is developed with several flow control techniques, and tested successfully with the hypersonic flight-duplicated shock tunnel. The experimental data show that the Sodramjet engine model works steadily, and an oblique detonation can be made stationary in the engine combustor and is controllable. This research demonstrates the Sodramjet engine is a promising concept and can be operated stably with high thermal efficiency at hypersonic flow conditions.