共查询到20条相似文献,搜索用时 15 毫秒
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First results of PRECISE—Development of a MEMS-based monopropellant micro chemical propulsion system
PRECISE focuses on the research and development of a MEMS-based monopropellant micro chemical propulsion system for highly accurate attitude control of satellites. The availability of such propulsion systems forms the basis for defining new mission concepts such as formation flying and rendezvous manoeuvres. These concepts require propulsion systems for precise attitude and orbit control manoeuvrability. Application-oriented aspects are addressed by two end-users who are planning a formation flying mission for which the propulsion system is crucial. Basic research is conducted aiming at improving crucial MEMS technologies required for the propulsion system. Research and development also focuses on the efficiency and reliability of critical system components. System analysis tools are enhanced to complement the development stages. Finally, the propulsion system will be tested in a simulated space vacuum environment. These experiments will deliver data for the validation of the numerical models. 相似文献
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A practical small satellite variable-speed control moment gyroscope for combined energy storage and attitude control 总被引:1,自引:0,他引:1
A recent effort to develop single-gimbal variable-speed control moment gyroscopes (VSCMGs) for a combined energy storage and attitude control subsystem (ESACS) on small satellites has culminated in laboratory validation of the concept. A single actuator prototype comprised of a cutting-edge Carbon Fiber rotor and COTS motor/generator components has been developed, balanced, bench tested, and integrated onto a spherical air-bearing structure. This structure is used to demonstrate the primary capability of a VSCMG to act as a dynamo whilst simultaneously changing a spacecraft's orientation in a controlled fashion. As originally predicted, the actuator's flywheel spins up when energy is supplied (supported via a direct energy transfer power architecture), then spins down when the energy source is removed, porting the energy released to run a resistive load.The work presented gives an overview of the governing principles of the technology, addresses the underlying mission and design requirements, and presents the prototype design. Then, effectiveness of the prototype integrated on a three-axis test article is presented along with its associated test data. Finally, discussion of these results and identification of future research concludes the work. The benefits of this technology for future space missions are that system consolidation permits mass reduction, higher instantaneous peak power is available as compared to conventional secondary battery systems, state-of-charge measurement is readily available from wheel speed feedback, and torque amplification through gimballing permits efficient actuator control. The technology demonstrated is exciting and leaves the door open for future development via inclusion of magnetic levitation. 相似文献
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J.Steven Newman 《Acta Astronautica》2001,48(5-12)
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国外单组元变推力发动机应用与关键技术 总被引:1,自引:0,他引:1
介绍了国外单组元变推力发动机的应用现状,阐释了单组元变推力发动机的结构和设计原理,总结了研制和改进过程中的关键技术,主要包括径向双层夹套催化床设计、径向喷注器设计、流量稳定调节技术和催化床空穴控制技术等。美国为火星软着陆研制的MR-80和MR-80B无水肼单组元变推力发动机分别应用于“海盗”号和“好奇”号着陆器下降级推进系统。MR-80发动机可实现275~2835 N变推力调节,推力变比为10∶1,比冲为205 s,呈120°均布于“海盗”号着陆器三角形基座的长边。“好奇”号下降级推进系统由2个高压氦气瓶、3个推进剂贮箱、8台单组元变推力发动机、8台单组元250 N姿控发动机、1个压力控制组件和3个推进剂控制组件组成,MR-80B发动机可产生31~3603 N的真空推力,推力变比达到100∶1,比冲范围为204~223 s。 相似文献
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针对主从式结构飞行器协同编队控制问题,以侧滑转弯飞行器为研究对象,采用制导控制一体化(Integrated guidance and control, IGC)方法设计编队控制器。首先在惯性坐标系中定义相对运动坐标系,建立相对运动模型,结合飞行器动力学模型,得到全状态制导控制一体化模型;然后采用反演方法,结合滑模变结构与神经网络自适应理论设计了编队控制器,并证明了控制系统稳定性;最后在高速情况下进行了六自由度数值仿真,对比了IGC设计方法与分离设计方法的控制性能。仿真结果表明所设计的IGC控制器能够快速精确地对期望编队队形进行构建与保持,并且较分离设计方法具有优越性。 相似文献
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《Acta Astronautica》1987,15(11):823-832
The paper presents design of a near optimal orbit and attitude control system for a very large flexible rectangular flat plate-like spacecraft in geostationary orbit, with its normal kept in the orbital plane in an inertial orientation. First, assuming the plate to be rigid, an optimal control system is designed. Two control systems are needed: one to balance the gravity gradient torque and the other to control the plate's orbit and attitude against disturbances. The interaction of the structural dynamics with the control system is investigated next. It is shown that the structural dynamics destabilizes the control system. The control design is modified to reduce the interactions, by including just a couple of flexural modes into the control logic and by optimally locating the thrusters a little away from the corners. The control structure interaction which is measured by the residual flexural energy after an orbit or attitude correction, is shown to be reduced by several orders of magnitude by the simple modifications. An approach to find an optimal location of actuators and a concept of “associated modes” are also proposed to help the designer evolve a very simple coupled orbit and attitude controllers with minimum control/structure interactions for very large flexible space systems of the future. This configuration considered represents the proposed solar power satellite, solar reflectors, communication platforms, etc. 相似文献
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天地信息网络融合可以实现空间与地面网络资源的充分共享和高效利用,国内外已提出多种天地一体化信息网络架构并从不同角度进行理论研究和关键技术攻关。面向CCSDS数据系统体制与空间通信协议规范(SCPS),在分析CCSDS协议体系结构及其应用发展基础上,讨论卫星链路应用TCP/IP的问题与关键机制,并综述星地一体化协议IPoC(IP over CCSDS)的技术研发与仿真研究进展。通过分析空间CCSDS协议体系与地面IP网络机制,为天地信息网络融合系统设计与网络协议研究提供参考。 相似文献
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以空间太阳能电站为应用代表的微波功率传输系统中,微波功率发射阵列是其中的核心组成部分。为保证特定传输距离限制下的波束收集效率,目前国际上多种空间太阳能电站方案中收发天线口径都达到了km级以上。在空间构建大尺度的微波功率发射有源相控阵,面临的主要问题有:发射阵列电性能的高要求、发射阵列折叠状态的总体积限制、大功率发射阵列的热控问题。针对这些问题,文章提出了新型大尺度空间微波功率发射阵列的一些研究及设计考虑,主要包括大尺度阵列同源分发倍频的频率分配方案;高效率高集成功率发射组件技术;大尺度阵列相位同步与误差自校正技术;低剖面天线结构及型面误差补偿技术;大型天线3D打印在轨建造方案设想以及空间微波功率发射阵列热控新思路等。文章提出了新型大尺度空间微波功率发射阵列3个方面的6个主要问题,可为空间太阳能电站系统提供可优化、开放性的设计与发展思路。 相似文献
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Basic points of the concept of contactless space systems of active optics are formulated. They include the principles of construction, the logic of control, and structural and designing features. The generalized structure of a typical subsystem is constructed, and the basic control algorithms corresponding to the conditions of structural decomposition of similar systems are defined. 相似文献
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《中国航天(英文版)》2016,(1)
The origin,formation and evolution of the systems engineering theory accompanied QIAN Xuesen's whole life.The systems engineering theory is the concentrated reflection of QIAN's achievements and theory in all aspects.From returning to China to pioneer China's space industry,creating a new management mode of "one overall design department,two command lines",publishing Organization and Management Technology:Systems Engineering,to proposing the theory of Open Complex Giant System(OCGS) and the theory of Metasynthetic Wisdom,all these mark the formation of the Chinese school of systems engineering.Guided by QIAN's academic ideas,various major Chinese space programs have been implemented successfully which verified the fact that the systems engineering is scientific.The systems engineering has been applied to different fields of the national economy and has a development process with the distinguished characteristics of Chinese systems science.On one hand,the systems engineering is put forward deeply along the traditional systems engineering thought and theory;on the other hand,a batch of innovations that break the traditional shackles have occurred,making the Chinese systems engineering unique and outstanding compared with foreign counterparts. 相似文献
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《中国航天(英文版)》2021,(1)
China's space technology has gradually improved from the early stages' introduction, absorption and re-innovation based on backward design to independent innovation based on forward design. It is necessary to develop a new approach of systems engineering to improve the quality and efficiency of space systems design considering the large number of original design problems expected in the future. Adopting Model-Based Systems Engineering(MBSE) and Digital Twin method are important development initiatives in the field of modern engineering design. In the initial phase of system design, it is necessary to generate firm system architecture models based on the needs of stakeholders. The quality of the system design in this phase has a great impact on the detailed design and implementation for the subsequent system, and also plays an important role in the performance, development progress and cost of the whole system. Through the collaboration of cross-professional teams, modeling and model execution, comparing the model execution with expected results, MBSE has enabled digital model-level verification and validation before test verification and validation based on physical products, thus improving the design exactness, completeness and greatly reducing design errors or defects. This paper explores the logical ideas behind modeling of system architectures in order to promote the adoption of MBSE in the field of space systems. 相似文献
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空间机械臂是广泛应用于空间探索与实验的重要机电设备,柔顺抓捕技术为其执行主要任务的基础。空间机械臂柔顺抓捕技术主要分为结构设计与控制方法两个方面。首先介绍了目前已成功应用的空间机械臂末端执行器系统,分析了其结构与抓捕原理特点,说明了相应优势与不足,并给出结构优化的合理建议。然后介绍柔顺抓捕的控制方法在空间任务以及部分非空间任务中的成功应用,比较了其特性与优劣,归纳出优化的空间机械臂柔顺抓捕控制策略。本研究期望为空间机械臂柔顺抓捕技术的研究提供思路。 相似文献