基于序列近似优化算法的固体运载火箭弹道设计

采用打靶法研究固体运载火箭弹道优化设计问题。针对打靶法中智能优化算法效率、优化问题中约束条件提法等方面的不足,引入序列近似优化算法,提出算法中径向基函数高斯核宽度的高效确定方法。数值仿真实验表明,提出的方法可在基本不带来计算量增加的前提下,显著提高代理模型精度,使序列近似优化算法得到改进,提高优化效率。设计固体运载火箭飞行程序。建立弹道优化设计问题数学模型,并将模型中相关等式约束合理转化为不等式约束,降低优化问题求解难度;基于改进后的序列近似优化算法完成某固体运载火箭弹道优化,原始计算模型调用308次之后便搜索到最优解,较传统智能优化算法显著提高了优化效率,优化方案末助推级液体推进剂消耗比原方案减少25.7%。     

航空发动机过失速及退喘模型研究

针对涡喷和涡扇发动机,通过求解带源项的2维欧拉方程组,发展了模拟发动机整机过失速及退喘动态过程的理论模型,实现了2种发动机稳定状态-喘振/旋转失速-退喘动态过程的模拟。分析了某单轴涡喷发动机算例,模拟结果展现出喘振和旋转失速相应的基本特征;对某小涵道比双轴混排涡扇发动机进、退喘模拟结果进行分析,发现风扇与压气机均发生了喘振,且喘振频率相等,并最终都恢复至稳定状态。     

Multi-objective Optimization Method for Automatic Drilling and Riveting Sequence Planning

 There are numerous riveting points on the large-sized aircraft panel, irregular row of riveting points on delta wing. It is es-sential to plan the riveting sequence reasonably to improve the efficiency and accuracy of automatic drilling and riveting. Therefore, this article presents a new multi-objective optimization method based on ant colony optimization (ACO). Multi-objective optimization model of automatic drilling and riveting sequence planning is built by expressing the efficiency and accuracy of riveting as functions of the points’ coordinates. In order to search the sequences efficiently and improve the quality of the sequences, a new local pheromone updating rule is applied when the ants search sequences. Pareto dominance is incorporated into the proposed ACO to find out the non-dominated sequences. This method is tested on a hyperbolicity panel model of ARJ21 and the result shows its feasibility and superiority compared with particle swarm optimization (PSO) and ge-netic algorithm (GA).     

快速阀控制电路

本文介绍快速阀控制电路的用途、技术指标、框图及电路原理。对克服严重现场干扰、使控制电路具有高度可靠性方面所采取的具体措施也进行了比较系统的介绍。     

高超声速飞行器二元进气道试验和计算

设计了一种吸气式面对称高超声速飞行器,针对进气道性能,分别在两座风洞开展通流试验研究。针对第1次风洞试验大攻角状态(α=8°)测量值偏离线性的问题,辅助采用数值模拟手段分析原因,并对试验方案进行改进设计,解决了首次试验出现的问题。结果显示,在典型状态(Ma=5~6)下,进气道起动正常,性能良好,具有一定的抗侧滑能力;随来流马赫数增加,进气道流量系数增大,总压恢复系数减小,计算结果和试验结果一致;试验结果和数值计算的差异主要表现为基本测压方案α>4°后,流量系数和总压恢复系数出现严重的非线性。数值模拟结果表明,主要原因为模型支撑方式及测压方式所引起的偏差,通过改进试验方案,解决了大攻角状态下测量值偏离正常趋势的问题。     

自适应天线抗干扰性能研究

分析了适用于雷达抗干扰的一些自适应天线波束形成算法,将子空间正交投影算法应用于雷达抗干扰,针对子空间分解过程中特征向量不能完全正交的问题,采用约束化子空间分解算法,来保证子空间特征向量的正交性.最后通过仿真证明:子空间跟踪算法相对于传统的一些自适应算法具有更强的抗干扰性能.     

地球同步卫星BSR硅太阳电池阵输出功率衰减规律分析

长期受粒子辐照、紫外辐照等因素的影响,地球同步卫星的太阳电池阵输出功率会出现较为明显的衰减。这里选取某地球同步卫星使用的背表面反射(BSR)硅太阳电池阵为研究对象,采用光强因子和温度因子修正太阳电池阵的输出功率,使用局部加权回归散点平滑法(LOWESS)分析了其在设计寿命期间的输出功率衰减规律;同时基于LOWESS建立了预测模型,用于硅太阳电池阵超寿运行期间的功率预测。实测数据表明:本文构建的预测模型可以满足超寿地球同步卫星在轨管理使用需求。     

Application in prestiction friction compensation for angular velocity loop of inertially stabilized platforms

To overcome the influence of the nonlinear friction on the gimbaled servo-system of an inertial stabilized platforms(ISPs) with DC motor direct-drive, the methods of modeling and compensation of the nonlinear friction are proposed. Firstly, the inapplicability of LuGre model when trying to interpret the backward angular displacement in the prestiction regime is observed experimentally and the reason is deduced theoretically. Then, based on the dynamic model of direct-drive ISPs, a modified LuGre model is proposed to describe the characteristic of the friction in the prestiction regime. Furthermore, the state switch condition of the three friction regimes including presliding, gross sliding and prestiction is presented. Finally, a composite compensation controller including a nonlinear friction observer and a feedforward compensator based on the novel LuGre model is designed to restrain the nonlinear friction and to improve the control precision. Experimental results indicate that compared with those of the conventional proportion–integration–differentiation(PID) control method and the PID plus LuGre model-based friction compensation method, the dwell-time has decreased from 0.2 s to almost 0 s, the position error decreased to 86.7%and the peak-to-peak value of position error decreased to 80% after the novel compensation controller is added. It concludes that the composite compensation controller can greatly improve the control precision of the dynamic sealed ISPs.     

A nonlinear background removal method for seismo-ionospheric anomaly analysis under a complex solar activity scenario: A case study of the M9.0 Tohoku earthquake

A precise determination of ionospheric total electron content (TEC) anomaly variations that are likely associated with large earthquakes as observed by global positioning system (GPS) requires the elimination of the ionospheric effect from irregular solar electromagnetic radiation. In particular, revealing the seismo-ionospheric anomalies when earthquakes occurred during periods of high solar activity is of utmost importance. To overcome this constraint, a multiresolution time series processing technique based on wavelet transform applicable to global ionosphere map (GIM) TEC data was used to remove the nonlinear effect from solar radiation for the earthquake that struck Tohoku, Japan, on 11 March, 2011. As a result, it was found that the extracted TEC have a good correlation with the measured solar extreme ultraviolet flux in 26–34 nm (EUV_26–34) and the 10.7 cm solar radio flux (F_10.7). After removing the influence of solar radiation origin in GIM TEC, the analysis results show that the TEC around the forthcoming epicenter and its conjugate were significantly enhanced in the afternoon period of 8 March 2011, 3 days before the earthquake. The spatial distributions of the TEC anomalous and extreme enhancements indicate that the earthquake preparation process had brought with a TEC anomaly area of size approximately 1650 and 5700 km in the latitudinal and longitudinal directions, respectively.     

月面高温下推力器可靠性试验

嫦娥五号着陆上升组合体落月后将经历月昼强红外辐射环境，由于推力器喷管导热影响，使推进剂管路与电磁阀面临高温环境，推进系统存在管路内氧化剂汽化和推力器性能下降甚至无法正常工作的问题，影响上升器月面起飞正常姿态控制。为了研究高温下推力器的工作性能，进行了高温下氟塑料阀芯与氧化剂相容性调研，提出了电磁阀和推力器可靠性增长及可靠性验证试验方法，分析了温度与电磁阀阀芯行程的关系，获取了高温环境下推力器的稳态及脉冲工作性能，在小子样条件下评估了推力器可靠性置信下限及月面起飞上升推进系统可靠度，通过月面高温排气及月面起飞上升姿态控制对研究结果进行了航天器在轨飞行验证，圆满完成了上升器月面起飞上升任务。所提出的研究方法及思路具有很好的工程适用性。