基于RBCC的天地往返运载器动力方案研究

基于火箭基组合循环发动机(RBCC)的结构组成、工作过程和特点,结合某吸气式重复使用天地往返运载器所提出的动力需求,分析了采用RBCC组合循环发动机作为该运载器动力方案的可行性和动力系统指标,设计并计算了RBCC组合循环发动机在各个工作模态下的性能参数.针对相同的运载器使用要求,采用相同的总体和气动力参数,通过飞行弹道仿真,计算和比较了采用RBCC发动机和纯火箭发动机两种动力方案的天地往返运载器方案.研究结果表明,相对于纯火箭动力,采用RBCC动力能明显减小运载器的燃料消耗,并增大其航程.     

Sq(H) field variations at Sonmiani geomagnetic observatory,Pakistan for solar cycle 24

In this study, Sq(H) field results for Sonmiani geomagnetic observatory (SON), Pakistan are presented first time for solar cycle i.e., Solar Cycle 24. Sonmiani observatory was established in 2008 and was included in the list of INTERMAGNET Magnetic Observatory (IMO) in 2012. The analysis of Sq(H) field is performed to examine diurnal, annual and seasonal behaviour of Sq(H) field at Sonmiani along with Honolulu which is used as reference observatory. Both the observatories lie at the Equatorial Ionisation Anomaly (EIA) crest. In general strong dependency of Sq(H) field on solar cycle has been observed. First peak of SC24 was visible in Sq(H) field at both observatories. However, at HON maximum Sq(H) was observed in 2015 instead of 2014, a year later than the year of solar maximum. Prominent longitudinal difference has been noted between both observatories. At HON, maximum Sq(H) was observed during equinox while at SON it was noted during equinox and summer as a consequence of shift in latitude of Sq focus. Phase shift of Sq(H) at SON followed a general trend, that is maximum Sq(H) shifted to later hours in solar maximum as compared to solar minimum. Whereas, an opposite trend was noted at HON which might be due to coastal effect. In case of seasonal phase shift, at both observatories maximum Sq(H) occurred at later hours in summer than in winter which is opposite to the results obtained by many workers. These points need further investigation and geomagnetic as well as wind, and electric field data of other observatories situated at the EIA crest region is required to interpret the Sq(H) phase shift extensively.     

Simulation of the land surface temperature from moon-based Earth observations

The land surface temperature (LST) is a key parameter for the Earth’s energy balance. As a natural satellite of the Earth, the orbital of the moon differs from that of current Earth observation satellites. It is a new way to measure the land surface temperature from the moon and has many advantages compared with artificial satellites. In this paper, we present a new method for simulating the LST measured by moon-based Earth observations. Firstly, a modified land-surface diurnal temperature cycle (DTC) method is applied to obtain the global LST at the same coordinated universal time (UTC) using the Moderate Resolution Imaging Spectroradiometer (MODIS) LST products. The lunar elevation angles calculated using the ephemeris data (DE405) from the Jet Propulsion Laboratory (JPL) were then applied to simulate the Earth coverage observed from the moon. At the same time, the modified DTC model was validated using in situ data, MODIS LST products, and the FengYun-2F (FY-2F) LST, respectively. The results show that the fitting accuracy (root-mean-square error, RMSE) of the modified DTC model is not greater than 0.72?°C for eight in situ stations with different land cover types, and the maximum fitting RMSE of the modified model is smaller than that of current DTC models. By the comparison of the simulated LST with MODIS and FY-2F LST products, the errors of the results were feasible and accredited, and the simulated global LST has a reasonable spatiotemporal distribution and change trend. The simulated LST data can therefore be used as base datasets to simulate the thermal infrared imagery from moon-based Earth observations in future research.     

Ascent guidance law for a horizontal take-off vehicle with a multi-combined cycle engine

This paper researches the ascent guidance law for the vehicle with a multi-combined cycle propulsion. The guidance law comprises two parts, namely, the off-line optimal trajectories generation and online guidance. With respect to the off-line part, disturbances are discretized and incorporated into the trajectory optimization problem; subsequently, a set of trajectories is calculated to constitute a database. To quickly obtain a database that comprises a large number of trajectories, a novel ascent profile is proposed with respect to height and velocity. Based on this profile, only inequity constraints exist in the optimization model, and the original optimization problem is converted to a parameter searching problem. The optimal trajectories are calculated using a hybrid optimization method that comprises a particle swarm optimization (PSO) method and the Hooke-Jeeves (HJ) method. With respect to online guidance, the profile is updated using a radial basis function neural network (RBFNN) based on the current flight states and the database. Simulation validates the efficiency of the proposed optimization method by comparing the method with the pseudospectral method; the robustness of the guidance law is also validated using Monte Carlo simulation.     

燃气发生器循环变推力发动机频率响应分析

采用分段集中参数的有限元方法建立了发动机模块化模型,以此模型搭建了燃气发生器循环液体火箭发动机仿真模型,对变推力发动机在变工况下的系统特征及频率响应进行了研究。研究表明:发动机系统在变工况后系统特征频率及其对应的阻尼系数有明显变化。通过提取变工况过程中的主要频率,发现对应能量峰值的频率为5.34 Hz。在发动机系统工况转换过程中,输入带有该频率的扰动的入口压力信号,仿真结果证明这种低频扰动使系统稳定裕度降低,应当避免该频率下扰动信号出现。     

Spectra of the two official GLEs of solar cycle 24

Based on ground-level data and on satellite data we determine in this work the observational spectrum of both, the Ground Level Enhancement of May 17, (2012) the so-called GLE71 and the Ground Level Enhancement of September 10, 2017 (GLE 72). We describe a simplified method to obtain the experimental spectrum at ground level. Data of the GLE71 and GLE72 indicate the presence of two different populations, each one with a different energy spectrum. On the other hand, we explore the kind of phenomena that take place at the source in these two particular events. In contrast with other methods based on the temporal synchronization between electromagnetic emissions of flares and coronal mass ejections (CME), here we develop an alternative option based on the study of the accelerated particles, by adjusting our theoretical spectra to the observational spectra. The main results of this work are the derivation of the source and acceleration parameters involved in the generation process. These results lead us to construct possible scenarios of particle generation in the source for each one of the two studied GLEs.     

基于分层体系的现代作战飞机方案评估

针对目前作战飞机方案评估中体系与方法的不足,依据飞机发展的时序性和评估内容的细化程度,确定了现代作战飞机方案评估的5个层次,它们分别为综合作战能力层、综合作战效能层、综合使用效能层、综合使用效费层和方案评价决策层.在分析各评估层特性的基础上,建立了各评估层的细化指标体系,改进和完善了各评估层的理论模型和计算方法,通过现...     

基于直升机飞行性能需求的涡轴发动机设计参数选取方法研究

以直升机性能计算方法为基础,辅以考虑尺寸效应及设计能力的涡轴发动机设计方法,建立了以直升机旋翼桨盘载荷及最大起飞功重比为特征参数的直升机/涡轴发动机性能约束分析模型、任务分析模型及基于直升机飞行性能需求的涡轴发动机设计参数选取模型。针对涡轴发动机部件/系统设计能力及直升机飞行性能需求,首先开展了给定涡轴发动机循环参数下的流量匹配计算,然后开展了涡轴发动机循环参数选取研究。研究表明,所建立的直升机/涡轴发动机性能约束分析模型、任务分析模型可实现给定飞行任务的直升机/涡轴发动机性能耦合设计;在给定涡轴发动机循环参数条件,由于尺寸效应,涡轴发动机部件效率受进口流量的影响,其设计点功率并不随流量等比例变化,从而使得直升机起飞总重呈现非等比例变化;在涡轴发动机循环参数选择时,在满足直升机飞行性能需求下,存在涡轴发动机耗油率与单位功率之间权衡下的循环参数选取,使得直升机起飞总重最小。     

超/亚声速混合层压力不匹配时流动特征

为了获得压力不匹配对超/亚声速混合层空间分布与增长、压力分布和相似性等特征的影响规律,开展试验和数值模拟研究。通过粒子图像测速技术PIV测量混合层空间分布,标准k-ω模型模拟稳态流场特征。超声速气流马赫数为1.32,亚声速气流马赫数为0.11,五组不同压比分别为0.82,0.95,1.11,1.22和1.47。研究结果表明：压力不匹配对混合层增长的影响较弱;当压比>1时,混合层沿流向呈现波纹分布,静压呈现高、低压交替分布;压比增加,混合层内无量纲速度分布不变,无量纲总压减小,而湍流强度增加。基于无粘假设的预测模型捕捉了波节的基本结构与分布。     

A new method to predict fatigue crack growth rate of materials based on average cyclic plasticity strain damage accumulation

By introducing a fatigue blunting factor, the cyclic elasto-plastic Hutchinson-Rice-Rosengren (HRR) field near the crack tip under the cyclic loading is modified. And, an average damage per loading-cycle in the cyclic plastic deformation region is defined due to Manson-Coffin law. Then, according to the linear damage accumulation theory-Miner law, a new model for predicting the fatigue crack growth (FCG) of the opening mode crack based on the low cycle fatigue (LCF) damage is set up. The step length of crack propagation is assumed to be the size of cyclic plastic zone. It is clear that every parameter of the new model has clearly physical meaning which does not need any human debugging. Based on the LCF test data, the FCG predictions given by the new model are consistent with the FCG test results of Cr2Ni2MoV and X12CrMoWVNbN 10-1-1. What’s more, referring to the relative researches, the good predictability of the new model is also proved on six kinds of materials.