涡喷发动机H∞控制参数化Riccati方程的解

由分块矩阵的奇异值不等式关系,给出了初猜值γ０、λ０的对半求解法,在此基础上直接给出带参数的Ｒｉｃｃａｔｉ方程迭代求解法。用此方法对涡喷发动机不确定性系统设计控制器并在发动机气动热务学非线性模型上进行了仿真验证,结果表明控制系统能够取得满意的鲁棒性能,抗干扰性能和伺服跟踪性能。     

燃气轮机系统仿真集成概念及其分布对象实现

本文提出燃气轮机系统仿真集成的概念, 分析了关键实现技术, 然后从跨平台性入手, 给出 1个分布异构计算机平台上的面向对象实现方案。算例表明, 这一方案成功实现了系统仿真集成的主要功能, 从而为发动机系统的多学科开发、研制和实验提供了有效的仿真软、硬件平台, 并使发动机的远程协同设计成为可能。      

交会对接任务碰撞规避策略制定研究简

针对交会对接任务目标飞行器与追踪器轨道运行特性,综合考虑规避策略计算方法与工程实际相结合的问题,提出高度规避、时间规避以及与正常轨控相结合的碰撞规避策略计算方法等三种空间目标碰撞规避策略计算方法.高度规避计算方法采用了Lambert飞行原理,用简化二体开普勒模型取代高精度轨道预报方法,迭代求解规避机动速度增量,实现了通过约束过交点与目标径向距离差得到速度增量的最优解;时间规避计算方法通过轨道周期与速度增量的关系,实现了通过约束过交点与目标的时间差得到速度增量的最优解;与正常轨控相结合的碰撞规避策略计算方法,在正常控制考虑冗余控制量的基础上,对控制策略的控制开始时间或沿迹方向的速度增量进行较小的修正,使两者通过碰撞点的时刻或径向距离错开,达到碰撞规避的目的,该方法不仅可以节省燃料、而且对任务的影响较小.通过对三种空间目标碰撞规避策略计算方法仿真分析结果表明,完全适用于交会对接任务,可为我国载人航天任务飞行安全提供技术保障.     

一种定向凝固高温合金低周疲劳性能的研究

研究了同成分合金在定向凝固（ＤＳ）和普通铸造（ＣＣ）状态下７６０℃的低周疲劳性能。结果表明，ＤＳ合金的疲劳寿命比ＣＣ合金在应力控制条件下高２倍左右，而在应变控制条件下可提高寿命２０倍左右。ＣＣ合金的疲劳裂纹往往萌生在与表面相连的晶界或某些缺陷（如孔洞）上，由外向内沿晶界扩展。而ＤＳ合金裂纹则起源于纵向晶界的横段或预开裂的碳化物，并沿枝晶间穿枝干扩展。     

Mars Global Surveyor Observations of Solar Wind Magnetic Field Draping Around Mars

We examine the magnetic field in the martian magnetosheath due to solar wind draping. Mars Global Surveyor provided 3-D vector magnetic field measurements at a large range of altitudes, local times, and solar zenith angles as the spacecraft orbit evolved. We choose orbits with very clean signatures of draping to establish the nominal morphology of the magnetic field lines at local times of near-subsolar and near-terminator. Next, using a compilation of data from Mars Global Surveyor, we determine the average magnetic field morphology in the martian magnetosheath due to the solar wind interaction. The topology of the field is as expected from previous observations and predictions. The magnetic field magnitude peaks at low altitude and noon magnetic local time and decreases away from that point. The magnetic field has an inclination from the local horizontal of 5.6° on average in the dayside magnetosheath and 12.5° on the nightside. The inclination angle is closest to zero at noon magnetic local time and low altitude. It increases both upward and to later local times. The magnetic field in the induced magnetotail flares out from the Mars—Sun direction by 21°. Finally, we compare the observations to gasdynamic model predictions and find that the shocked solar wind flow in the martian magnetosheath can be treated as a gasdynamic flow with the magnetic pileup boundary as the inner boundary to the flow.     

耐腐蚀性过滤器用多孔陶瓷材料的制备（I）多孔先驱体的合成及其陶瓷化

对泡沫状多孔聚碳硅烷（PCS）的合成反应条件进行了较为详细的研究，通过控制化学反应的温度、压力和反应时间制备出了熔点高达380℃、相对分子质量Mn〉3000、陶瓷产率达79％（质量分数），密度〈0．6g／cm^3的多孔聚合物。对不同反应条件下所制得的多孔PCS的性能进行了表征，并利用IR、TG等手段对泡沫状多孔PCS的热解机理进行了初步探讨。     

利用导弹制导误差补偿规律修正不完全弹道测量的数据融合技术

论述不完全弹道测量的数据融合处理问题。在惯性器件天地关系一致的前提下,导弹惯性器件误差补偿量变化规律,就反映了飞行中制导工具误差的变化规律,即遥外差的变化规律。因此,可以利用补偿量视速度的变化规律约束条件,内插出不完全测量段落的遥外差数据,在建立节省参数的弹道估计的联合模型基础上,融合少量的高精度测元来解算弹道参数。落点验算表明：利用该方法计算的落点接近实际落点。     

开关点预置三相四线SPWM逆变器研究

脉宽调制型交直交变速恒频电源采用开关点预置SPWM逆变器,该逆变器由三相桥,交流滤波器,中点形成变压器及控制、驱动电路组成。绝缘栅双极性晶体管是一种新型的电力电子器件;应用该器件为功率器件,研制了一套15kVA开关点预置SPWM逆变器。由于对电路各个部分均进行了充分分析和优化设计,实际制作的逆变器具有较小的体积、重量,并具有优越的电性能。     

The Magnetic Field of Mercury

The magnetic field strength of Mercury at the planet’s surface is approximately 1% that of Earth’s surface field. This comparatively low field strength presents a number of challenges, both theoretically to understand how it is generated and observationally to distinguish the internal field from that due to the solar wind interaction. Conversely, the small field also means that Mercury offers an important opportunity to advance our understanding both of planetary magnetic field generation and magnetosphere-solar wind interactions. The observations from the Mariner 10 magnetometer in 1974 and 1975, and the MESSENGER Magnetometer and plasma instruments during the probe’s first two flybys of Mercury on 14 January and 6 October 2008, provide the basis for our current knowledge of the internal field. The external field arising from the interaction of the magnetosphere with the solar wind is more prominent near Mercury than for any other magnetized planet in the Solar System, and particular attention is therefore paid to indications in the observations of deficiencies in our understanding of the external field. The second MESSENGER flyby occurred over the opposite hemisphere from the other flybys, and these newest data constrain the tilt of the planetary moment from the planet’s spin axis to be less than 5°. Considered as a dipole field, the moment is in the range 240 to 270 nT-R _M ³ , where R _M is Mercury’s radius. Multipole solutions for the planetary field yield a smaller dipole term, 180 to 220 nT-R _M ³ , and higher-order terms that together yield an equatorial surface field from 250 to 290 nT. From the spatial distribution of the fit residuals, the equatorial data are seen to reflect a weaker northward field and a strongly radial field, neither of which can be explained by a centered-dipole matched to the field measured near the pole by Mariner 10. This disparity is a major factor controlling the higher-order terms in the multipole solutions. The residuals are not largest close to the planet, and when considered in magnetospheric coordinates the residuals indicate the presence of a cross-tail current extending to within 0.5R _M altitude on the nightside. A near-tail current with a density of 0.1 μA/m² could account for the low field intensities recorded near the equator. In addition, the MESSENGER flybys include the first plasma observations from Mercury and demonstrate that solar wind plasma is present at low altitudes, below 500 km. Although we can be confident in the dipole-only moment estimates, the data in hand remain subject to ambiguities for distinguishing internal from external contributions. The anticipated observations from orbit at Mercury, first from MESSENGER beginning in March 2011 and later from the dual-spacecraft BepiColombo mission, will be essential to elucidate the higher-order structure in the magnetic field of Mercury that will reveal the telltale signatures of the physics responsible for its generation.     

Research into Configuration and Flow of Wall Oil Film in Bearing Chamber Based on Droplet Size Distribution

The lubrication design and heat transfer determination of bearing chambers in aeroengine require a sufficient understanding of the oil droplet-film interaction and physical characteristic in an oil/air two-phase flow state.The analyses of oil droplet movement,mass and momentum transfer during the impingement of droplet/wall,as well as wall oil film thickness and flow velocity are very important for the bearing chamber lubrication and heat transfer calculation.An integrated model in combination with droplet movement,droplet/wall impact and film flow analysis is put forward initially based on the consideration of droplet size distribution.The model makes a contribution to provide more practical and feasible technical approach,which is not only for the study of droplet-film interaction and physical behavior in bearing chambers with oil/air two-phase flow phenomena,but also useful for an insight into the essence of physical course through droplet movement and deposition,film formation and flow.The influences of chamber geometries and operating conditions on droplet deposition mass and momentum transfer,and wall film thickness and velocity distribution are discussed.The feasibility of the method by theoretical analysis is also verified by the existing experimental data.The current work is conducive to expose the physical behavior of wall oil film configuration and flow in bearing chamber,and also significant for bearing chamber lubrication and heat transfer study under oil/air two-phase flow conditions.