热管辐射器热分析

大多数航天器的热控制都是利用空间辐射器作为排热部件。在空间辐射器上，安装热管将极大地提高空间辐射器的散热能力。热管辐射器是一种传热性能极好、运行安全可靠的空间辐射器。文中介绍了典型热管辐射器的结构型式，对平面双组热管辐射器和柱面双组热管辐射器进行了详细的热分析，完成了典型柱面双组热管辐射的性能计算，并计算出流体温度和辐射肋片温度的变化。     

飞机主起刹车冲压空气冷却系统性能分析

从理论分析和试验研究两个角度研究了冲压空气冷却主起落架刹车系统性能随飞行条件、起落架舱反压等的变化。理论分析部分由冲压空气冷却系统进气口处的附面层理论，推导出冲压空气经过进气口的压力恢复系数，从而得到冷却系统各部分分流量的变工况特性。为验证理论分析结果，进行了冲压空气冷却系统的全尺寸模拟试验。试验结果与理论分析结果进行比较后发现两者基本吻合，说明了理论分析方法的正确性，因此本文提出的理论分析方法可为设计主起刹车冲压空气冷却系统提供理论指导。     

加工钛合金大口径深盲孔的研究

钛合金属难加工材料,其深孔加工的难度更为突出,加工质量不易保证。本文通过实验对比,对加工钛合金大口径深盲孔中出现的偏孔、切屑堵塞、切削振动、刀具破损等主要问题进行了分析,提出了解决办法,得出了切削用量的优化参数。由于钛合金的化学亲和作用,深孔加工刀具的导向条表面易于粘附,结果拉伤已加工表面,造成表面粗糙度上升。加大导向条与孔壁的间隙虽可减少导向条表面的粘附,但同时会引起切削振动的加剧。针对这一矛盾,本文着重对加工刀具的导向条分布、导向条与孔壁的间隙以及导向条的选材方面进行了探讨,提出了以非金属导向条代替硬质合金导向条进行钛合金深孔精加工的方法,使得已加工表面的粗糙度大大降低。这些研究结果对实际加工具有一定的指导作用。     

基于流体网络法的喷管冷却气流量分配计算方法

流体网络法对喷管气膜冷却问题具有独特的优势,但难以反映出入流对冷却气流道静压变化的影响。针对此引入了可反映出入流导致静压变化的管道元件,并基于孔口速度落后角对静压变化量进行了建模。验证算例表明,这一改进使沿程静压变化趋势与实际吻合较好,使冷却气流量分配计算误差降低到0.5%以下。将改进后的流体网络法与主流通道的计算流体力学模拟耦合用于分析喷管冷却气流量分配,与全计算流体力学模拟相比结果差异小于1.2%,且大幅降低计算量;在某型喷管设计中的应用表明,可以有效反映冷却结构改变对冷却气流量分配的影响。      

网格阵列填充冷却通道内超临界正癸烷流动传热特性的数值研究

采用碳氢燃料冷却壁面是超燃冲压发动机常用主动冷却方式。为减轻主动冷却通道结构重量、提高冷却效率,本文探讨了以网格结构为填充的新型通道,从结构轻质化、流动特性及综合传热能力等方面与常规矩形主动冷却通道进行了比较。结果表明,在相同工况下,由错排网格填充的冷却通道结构综合性能最佳,其减重效果达39.93%,壁面温度显著下降,且努塞尔数最高达到光通道的2.156倍。从流动传热机理分析可看出,网格前缘冲击效应形成的马蹄涡和后缘附近发卡涡结构对强化传热贡献最大,扰动边界层和激发湍动能也是强化传热的重要因素。     

Flow field design and process stability in electrochemical machining of diamond holes

The metal grille, commonly composed of an amount of diamond holes, has been grow-ingly used as a key structure on stealth aircraft. Electrochemical machining (ECM) promises to be increasingly applied in aircraft manufacturing on the condition that process stability is guaranteed. In this work, a flow field model was designed to improve the process stability. This model is endowed with a variety of flow channel features, together with vibrating feeding modes. The flow field distribution on the bottom surface of the diamond hole was discussed and evaluated as well. The numerical results show that a short arc flow channel could significantly enhance the uniformity of electrolyte velocity distribution and a vibrating feeding of the cathode enables to reduce both fluctuations of the electrolyte velocity and pressure on the bottom surface of the diamond hole. Consequently, the flow field mutations were eliminated. It is verified from the experimental results that a short arc flow channel, when combined with vibrating feeding, is capable of improving machining localization and process stability markedly. What is more, the side gap on the bottom surface of the diamond hole could also be reduced by the abovementioned approach.     

Numerical simulation of aerodynamic interaction for a tilt rotor aircraft in helicopter mode

A rotor CFD solver is developed for simulating the aerodynamic interaction phenomenon among rotor, wing and fuselage of a tilt rotor aircraft in its helicopter mode. The unsteady Navier–Stokes equations are discretized in inertial frame and embedded grid system is adopted for describing the relative motion among blades and nacelle/wing/fuselage. A combination of multi-layer embedded grid and ‘‘extended hole fringe" technique is complemented in original grid system to tackle grid assembly difficulties arising from the narrow space among different aerodynamic components, and to improve the interpolation precision by decreasing the cell volume discrepancy among different grid blocks. An overall donor cell searching and automatic hole cutting technique is used for grid assembly, and the solution processes are speeded up by introduction of Open MP parallel method. Based on this solver, flow fields and aerodynamics of a tilt rotor aircraft in hover are simulated with several rotor collective angles, and the corresponding states of an isolated rotor and rotor/wing/fuselage model are also computed to obtain reference solution.Aerodynamic interference influences among the rotor and wing/fuselage/nacelle are analyzed,and some meaningful conclusions are drawn.     

SCAT弹头热防护的简化计算方法

本文对自适应发汗冷却（ＳＣＡＴ）弹头的热防护问题作了简化分析，并导得了热防护计算的简化计算公式。对铊，铟，锡和水四种冷却剂的情况，给出了算例。本文导行的公式，计算较简便，可作为弹头热防护设计的一种工程计算方法。这种工程计算方法亦可以用于地模拟实验前的予算。     

舱外航天服热控系统仿真

针对人体穿着航天服处于过热状态下的散热问题，在分别建立人体热调节系统、金属氢化物冷源和液冷服数学模型的基础上，将3个模型进行结合，对舱外航天服热控系统在5．5h的时间轴上进行综合的仿真计算，求出人体各节段的温度分布情况，液冷服的入口及出口水温，金属氢化物冷源的出口水温等参数，分析航天员的热舒适性，对航天服热控系统的设计有一定的指导作用，并为今后进一步的研究打下了基础．     

日地共转扰动似稳结构及其反相和漂移规律的最新证据

日地共转扰动似稳结构及其反相现象在第２１及２２周再次显现，从而证实了上述发现是一种在长达世记的时间尺度内存在的普遍规律。包括１９９１－１９９２年内的百年地磁扰动资料还说明偶数太阳周的共转似稳结构扰动峰有逆太阳自转而线性性漂移的趋向。对即将来临的极小年前可能出现的共转扰动作了试验性的预测。