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281.
David Kappel Gabriele Arnold Rainer Haus Giuseppe Piccioni Pierre Drossart 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
The successful long-duration radiation measurements performed by the VIRTIS instrument aboard ESA’s Venus Express spacecraft have provided an excellent collection of atmospheric and surface data that stand out due to their high temporal and spatial coverage of the planet and due to a high diversity of measurement and environmental conditions. 相似文献
282.
A low-energy, low-thrust transfer between two halo orbits associated with two coupled three-body systems is studied in this paper. The transfer is composed of a ballistic departure, a ballistic insertion and a powered phase using low-thrust propulsion to connect these two trajectories. The ballistic departure and insertion are computed by constructing the unstable and stable invariant manifolds of the corresponding halo orbits, and a complete low-energy transfer based on the patched invariant manifolds is optimized using the particle swarm optimization (PSO) algorithm on the criterion of smallest velocity discontinuity and limited position discontinuity (less than 1 km). Then, the result is expropriated as the boundary conditions for the subsequent low-thrust trajectory design. The fuel-optimal problem is formulated using the calculus of variations and Pontryagin's Maximum Principle in a complete four-body dynamical environment. Then, a typical bang–bang control is derived and solved using the indirect method combined with a homotopic technique. The contributions of the present work mainly consist of two points. Firstly, the global search method proposed in this paper is simply handled using the PSO algorithm, a number of feasible solutions in a fairly wide range can be delivered without a priori or perfect knowledge of the transfers. Secondly, the indirect optimization method is used in the low-thrust trajectory design and the derivations of the first-order necessary conditions are simplified with a modified controlled, restricted four-body model. 相似文献
283.
An experimental investigation is conducted to obtain the heat transfer and pressure drop data for an integral trailing edge cavity test section that simulates a novel turbine blade's internal cooling passage with bleed holes. Local heat transfer is measured on both the suction and pressure sides by a transient liquid crystal technique, while pressures at six positions are recorded by pressure calibrators. Moreover, flow characteristic and its effect on heat transfer are analyzed for conditions with or without bleed flow. The experimental results show that, in the cases with bleed flow, local heat transfer on the pressure side exceeds that on the suction side in the first and second channels. In the cases without bleed flow, in the first and third channels, local heat transfer on the suction side weakens whilst it increases significantly on the pressure side. For the second channel, non-bleed condition leads to a more balanced heat transfer distribution between the upstream and downstream channel. Besides, after the bleed holes are blocked, heat transfer in the first bend region on the suction side declines sharply, while the opposite phenomenon occurs for the second bend region on the pressure side. In both bleed and non-bleed cases, the total pressure of six measurement positions decreases continuously along the channel at the same Reynolds number and it promotes for higher Reynolds number. Among all the measurement points, under the same flow rate condition, the highest speed occurs at Position 5, which also shows the maximum difference between the total and static pressures. When the bleed holes are blocked, the total pressure at each measurement position appears to increase. 相似文献
284.
在风浪槽中进行水气动量交换实验,测量了不同风速和风区下的波浪及空气湍流流场。测量数据表明水面上风速分布符合对数律,水气界面附近在小范围的动量交换常通量层。阻力系数CD随风速增加线性增长,随波龄增加而减小。这一趋向与理论分析及外海帝测结果一致。对风浪发展过程中波浪和空气湍流谱结构的分析证明了水气运动的耦合关系。 相似文献
285.
Extensive experimental studies on the heat transfer characteristics of two rows of aligned jet holes impinging on a concave surface in a wing leading edge were conducted, where50000 Rej 90000, 1.74 H/d 27.5, 66° a 90°, and 13.2 r/d 42.03. The finding was that the heat transfer performance at the jet-impingement stagnation point with two rows of aligned jet holes was the same as that with a single row of jet holes or the middle row of three-row configurations when the circumferential angle of the two jet holes was larger than 30°. The attenuation coefficient distribution of the jet impingement heat transfer in the chordwise direction was so complicated that two zones were divided for a better analysis. It indicated that: the attenuation coefficient curve in the jet impingement zone exhibited an approximate upside-down bell shape with double peaks and a single valley; the attenuation coefficient curve in the non-jet impingement zone was like a half-bell shape, which was similar to that with three rows of aligned jet holes; the factors,including Rej, H/d and r/d, affected the attenuation coefficient value at the valley significantly.When r/d was increased from 30.75 to 42.03, the attenuation rates of attenuation coefficient increased only by 1.8%. Consequently, experimental data-based correlation equations of the Nusselt number for the heat transfer at the jet-impingement stagnation point and the distributionof the attenuation coefficient in the chordwise direction were acquired, which play an important role in designing the wing leading edge anti-icing system with two rows of aligned jet holes. 相似文献
286.
287.
热流限制下的最优气动力辅助变轨 总被引:4,自引:0,他引:4
以变轨能量消耗最小为优化目标,应用极大值原理研究了飞行过程受热流限制和升力系统约束下的气动力辅助共面变轨问题,飞行过程成分第一自由弧段,约束弧段,第二自由弧段三个部分,讨论了升力系数的最优表达式,分析了飞行过程中两种约束的相互作用,给出了约束弧起始位置的角点条件和终端的横截条件下,对不同的初值选取方法讨论了三种计算策略,并给出了数值算例。 相似文献
288.
本文介绍了在不同频率超声波及不同相转移催化剂条件下对安息香缩合反应的影响,实验发现,超声波的频率对安息香的收率有一定程度的影响,收率随着超声波频率的增加而增加。在选择的三种相转移催化剂中,采用苄基三乙基溴化铵效果最好,安息香的收率最高。 相似文献
289.
超燃冲压发动机燃烧室主动冷却模型制造和热考核试验的费用高昂、周期长,为了降低试验风险,采用三维计算和经济的验证试验相结合的方法开展了超燃冲压发动机燃烧室主动冷却设计。冷却结构基本参数设计和侧壁冷却流动设计是确定设计方案的两大基础,前者采用三维传热计算结合冷却面板传热验证试验完成,后者采用超临界燃料流动三维并行计算结合水流动验证试验完成。在此基础上,经过多轮的结构设计与三维传热及强度计算评估迭代,确定了最终的燃烧室主动冷却结构。设计的主动冷却燃烧室在来流马赫数2.5,总温1700K条件下成功通过200s热考核试验,表明所采用的设计方法、验证试验和计算工具是有效和可信的。 相似文献
290.
肋角度对气膜冷却特性的影响 总被引:1,自引:0,他引:1
在光滑二次流通道的基础上,分析对比了两种带肋通道(135°肋和45°肋)对气膜冷却特性的影响.采用瞬态液晶测试技术获得了气膜孔下游表面传热系数比与气膜冷却效率分布.使用Fluent软件RANS数值方法对相应结构进行了数值模拟,并使用了realizable k-ε湍流模型.光滑二次流通道模型中,气膜孔内流线呈螺旋状分布,导致较大的孔内速度分离与流动损失.冷气射流分成两部分,其中一股形成一对偏斜的对转涡.135°肋结构中,二次流通道上部分的旋转涡为顺时针方向,使得气流易于流入气膜孔,气膜孔内流线呈直线分布.45°肋结构中,二次流通道上部分旋转涡为逆时针方向,增强了气膜孔内旋转涡.45°肋结构中冷气流入气膜孔之后的流动结构与光滑二次流通道结构相似.135°肋结构气膜冷却效率最大而表面传热系数比最低. 相似文献