超音速巡航的发展

探讨军用飞机超音速巡航的发展历程和关键技术,为我国未来军用飞机实现超音速巡航提供借鉴。     

运用多重属性风险评估量化跑道侵入严重等级

随着航空运输业的迅速发展,交通密度逐渐增大,机场跑滑系统越来越复杂,航空安全问题也随之增多,其中跑道侵入是影响航空安全的重要方面.引起跑道侵入的因素多种多样,本文主要研究人为因素对跑道侵入严重性等级的影响,根据跑道侵入严重等级的划分,利用多重属性风险评估模型对跑道侵入严重性等级进行量化,通过实例计算和对所得数据的分析,表明多重属性风险评估模型可为跑道系统提供通用的跑道侵入风险评估方法,并指出实际工作中存在的问题及预防措施.     

Evaluation of simulation-based training for aircraft carrier marshalling with learning cubic and Kirkpatrick’s models

Simulation-based training is a promising way to train a carrier flight deck crew because of the complex and dangerous working environment. Quantitative evaluation of simulation-based training quality is vital to make simulation-based training practical for aircraft carrier marshalling.This paper develops a personal computer-based aircraft carrier marshalling simulation system and a cave automatic virtual environment(CAVE)-based immersive environment. In order to compare the training effectiveness of simulation-based training and paper-based training, a learning cubic model is proposed and a contrast experiment is carried out as well. The experimental data is analyzed based on a simplified Kirkpatrick’s model. The results show that simulation-based training is better than paper-based training by 26.80% after three rounds of testing, which prove the effectiveness of simulation-based aircraft carrier marshalling training.     

大涵道比涡扇发动机侧风试验方法研究

侧风条件对大涵道比涡扇发动机性能稳定性有重要影响。为开展大涵道比涡扇发动机侧风试验,分析了侧风试验标准要求及侧风发生装置的工作原理与调试标定方法,进行了大涵道比涡扇发动机侧风试验研究,制定了侧风试验数据分析方法。开发了1种用于模拟侧风环境的试验装置,并提出了1种风速标定方法和开展侧风试验的程序。结果表明:该试验装置可有效实现航空发动机侧风试验环境,该标定方法可得到侧风试验装置工作状态与试验所需风速之间的映射关系,具有重要的工程指导意义。     

舰载遥测设备伺服跟踪视轴稳定方法研究

论述了舰船摇摆对视轴稳定的影响,给出了由于舰船摇摆所引起的视轴附加角速度公式;分析了陀螺稳定回路的性能,给出了数学模型。所采用的视轴稳定方法,经过海上试验,船摇隔离度满足技术指标的要求。     

基于极点配置的改进晕轨道控制方法

基于小偏差理论,对无摄动三体动力学方程沿标称轨道线性化,推导了其误差线性模型。在线性系统极点配置原理的的基础上,利用标准轨道状态向量选择闭环目标极点,通过设计闭环极点配置状态反馈增益阵K,实现了对地月系L1点附近受摄晕轨道的保持控制。针对K中三通道使用单一控制量级带来的控制误差,提出了利用入轨误差比例设计的可变反馈阵系数(Variable feedback matrix Kcoefficient,VKC)设计方法。VKC方法改善了原有控制方法的控制效果,在不同等级误差下减小跟踪方差和并获得了闭合周期轨道,试验证明了方法的有效性。     

A Celestial Analytic Positioning Method by Stellar Horizon Atmospheric Refraction

This article, in allusion to the limitation of conventional stellar horizon atmospheric refraction based on orbital dynamics model and nonlinear Kalman filter in practical applications, proposes a new celestial analytic positioning method by stellar horizon atmospheric refraction for high-altitude flight vehicles, such as spacecraft, airplanes and ballistic missiles. First, by setting up the geometric connexion among the flight vehicle, the Earth and the altitude of starlight refraction, an expression for the relationship of starlight refraction angle and atmospheric density is deduced. Second, there are produced a novel measurement model of starlight refraction in a continuous range of altitudes (CRA) from 20 km to 50 km on the basis of the standard atmospheric data in stratosphere, and an empirical formula of stellar horizon atmospheric refraction in the same altitudes against the tangent altitude. Third, there is introduced a celestial analytic positioning algorithm, which uses the least square differential correction instead of nonlinear Kalman filter. The information about positions of a flight vehicle can be obtained directly by solving a set of nonlinear measurement equations. The stellar positioning algorithm adopts the characteristics of stellar horizon atmospheric refraction thereby removing needs for orbit dynamics models and priori knowledge of flight vehicles. The simulation results evidence the validity of the proposed stellar positioning algorithm.     

Assessing attitude error of FORMOSAT-3/COSMIC satellites and its impact on orbit determination

An attitude determination and control system (ADCS) is critical to satellite attitude maneuvers and to the coordinate transformation from the inertial frame to the spacecraft frame. This paper shows specific sensors in the ADCS of the satellite mission FORMOSAT-3/COSMIC (F3/C) and the impact of the ADCS quality on orbit accuracy. The selection of main POD antenna depends on the beta angles of the different F3/C satellites (for FM2 and FM4) during the inflight phase. In particular, under the eclipse, alternative attitude sensors are activated to replace the Sun sensors, and such a sensor change leads to anomalous GPS phase residuals and a degraded orbit accuracy. Since the nominal attitude serves as a reference for ADCS, the 3-dimensional attitude-induced errors in reduced dynamic orbits over selected days in 2010 show 9.35, 10.78, 4.97, 5.48, 7.18, and 6.89 cm for FM1–FM6. Besides, the 3-dimensional velocity errors induced by the attitude effect are 0.10, 0.10, 0.07, 0.08, 0.09, and 0.10 for FM1–FM6. We analyze the quality of the observed attitude transformation matrix of F3/C and its impact on kinematic orbit determination. With 249 days of GPS in 2008, the analysis leads to the following averaged 3-dimensional attitude-induced orbit errors: 2.72, 2.62, 2.37, 1.90, 1.70, and 1.99 cm for satellites FM1–FM6. Critical suggestions of geodetic payloads for the follow-on mission of F3/C are presented based on the current result.     

A generalized rough set-based information filling technique for failure analysis of thruster experimental data

Interval-valued data and incomplete data are two key problems for failure analysis of thruster experimental data and have been basically solved by the proposed methods in this paper. Firstly, information data acquired from the simulation and evaluation system formed as intervalvalued information system （IIS） is classified by the interval similarity relation. Then, as an improvement of the classical rough set, a new kind of generalized information entropy called ＂H＇-information entropy＂ is suggested for the measurement of uncertainty and the classification ability of IIS. There is an innovative information filling technique using the properties of H＇-information entropy to replace missing data by some smaller estimation intervals. Finally, an improved method of failure analysis synthesized by the above achievements is presented to classify the thruster experimental data, complete the information, and extract the failure rules. The feasibility and advantage of this method is testified by an actual application of failure analysis, whose performance is evaluated by the quantification of E-condition entropy.     

管式电除尘器中粉尘颗粒运动轨迹的数值模拟

对管式电除尘器中的气固两相流动流场进行数值模拟 ,实质上是研究粉尘颗粒在有电场力作用下的运动轨迹。计算中 ,将气相作为连续介质 ,采用 K- ε双方程湍流模型 ,并用 SIMPL E算法对流场进行数值模拟 ;将固相作为离散体系 ,采用颗粒轨迹法计算其运动轨迹。计算时分别选取 4种电压、4种气流速度和 4种颗粒直径为计算工况 ,计算结果显示出颗粒运动特性和除尘效率 ,并指出其与电压、气流速度和颗粒粒径等 3个主要因素相关。计算结果与实验较为一致 ,表明文中提出的理论模型可用于管式电除尘器中颗粒运动的数值模拟 ,对电除尘器的研究和设计有重要的指导意义