基于时间延迟理论的航空发动机维修优化模型

在对航空发动机维修现状进行分析的基础上,阐述了包括缺陷和故障两个因素的时间延迟模型的概念及其原理,并在系统分析航空发动机故障特点和维护特点的基础上,建立了航空发动机维修优化模型.通过对航空发动机维修周期模型进行实例研究,验证表明,时间延迟模型能够明显优化发动机的维修周期,提高航空发动机维修效能.     

Numerical simulation of time delay interferometry for a LISA-like mission with the simplification of having only one interferometer

In order to attain the requisite sensitivity for LISA, laser frequency noise must be suppressed below the secondary noises such as the optical path noise, acceleration noise etc. In a previous paper (Dhurandhar, S.V., Nayak, K.R., Vinet, J.-Y. Time delay interferometry for LISA with one arm dysfunctional. Class. Quantum Grav. 27, 135013, 2010), we have found a large family of second-generation analytic solutions of time delay interferometry with one arm dysfunctional, and we also estimated the laser noise due to residual time-delay semi-analytically from orbit perturbations due to Earth. Since other planets and solar-system bodies also perturb the orbits of LISA spacecraft and affect the time delay interferometry (TDI), we simulate the time delay numerically in this paper for all solutions with the generation number n ? 3. We have worked out a set of 3-year optimized mission orbits of LISA spacecraft starting at January 1, 2021 using the CGC2.7 ephemeris framework. We then use this numerical solution to calculate the residual optical path differences in the second-generation solutions of our previous paper, and compare with the semi-analytic error estimate. The accuracy of this calculation is better than 1 cm (or 30 ps). The maximum path length difference, for all configuration calculated, is below 1 m (3 ns). This is well below the limit under which the laser frequency noise is required to be suppressed. The numerical simulation in this paper can be applied to other space-borne interferometers for gravitational wave detection with the simplification of having only one interferometer.     

电站典型大滞后过程自适应预估控制器设计及应用

电站典型大滞后过程难于控制的原因在于其大滞后本身导致系统不稳定及锅炉负荷频繁变化导致的参数时变特性。本文设计了一种模型参考自适应预估控制算法,引入二阶惯性与时间滞后两个补偿器,其主要参数如增益、时间常数和滞后时间均可在线自适应调整,致使过程与参考模型时刻匹配。该算法已应用于电站200 MW锅炉机组再热汽温过程控制,控制精度达到2℃以内。     

一种新型双组元卫星推进剂的研究

通过热力学计算,选择NHO-3作为甲基肼高能添加剂,通过冰点测试、着火延迟期测试确定了NHO-3的含量,该种以甲基肼为主体的新型燃料与氧化剂MON-20组成的双组元推进剂具有冰点低、比冲高、着火延迟期短的优点,可应用于卫星、飞船等领域。     

基于多模PPP-AR技术的大气水汽探测性能分析

精密单点定位（precise point positioning，PPP）反演大气可降水量（precipitable water vapor，PWV）具有精度高、实时性强等优点，能够在灾害监测、降雨预报及探测降水信息等方面发挥重要作用。为评估整周模糊度固定模式下PPP-AR（PPP ambiguity resolution）反演PWV的性能，选取全球范围16个MGEX站2022年4个时段的观测数据，采用最终精密星历解算，设置不同星座组合（GPS,BDS-3,GPS+BDS-3,GPS+GLO+GAL+BDS-3）获取对流层延迟（zenith total delay，ZTD）估值，并转换为PWV。从PPP-ZTD与IGS-ZTD的相关性、PPP-ZTD收敛时间、ZTD估值精度和PPP-PWV估值精度4个方面评价多模PPP-AR探测水汽的性能。结果表明，与单（G、C）、双系统（GC）固定解相比，多系统（GREC）固定解获取ZTD估值更加精确，相关系数更高。相较于单、双系统，多系统具有更快的收敛速度，收敛时间分别缩短了27%,25%和20%，多系统固定解与浮点解相比收敛时间缩短11%。此外，对GNSS PPP反演的PWV与探空站PWV（RS-PWV）进行对比，结果表明，WUH2站与HOB2站单、双、多系统固定解、多系统浮点解（float-GREC）的平均均方根误差分别为6.40 mm,6.48 mm,6.19 mm,6.17 mm,6.19 mm和5.82 mm,5.77 mm,5.72 mm,5.62 mm,5.70 mm。多模下得到的PWV估值精度最高，可为高精度的水汽反演提供支持。     

用于气动导数辨识的试飞数据处理方法研究

飞行试验的测量环境十分复杂,未经处理的试飞数据直接用于飞机的气动导数辨识会降低辨识精度,甚至导致辨识的迭代过程发散或收敛到错误值。提出一套从野值剔除、数据平滑、时延修正到相容性检验的试飞数据处理方法,并将其应用到真实试飞数据的气动导数辨识中,通过对比分析数据处理前后的辨识过程和辨识结果,验证了本文提出的数据处理方法在改善辨识过程收敛特性和提高辨识精度上的有效性。     

一种用于同步静止卫星监测的微型VLBI网

针对地球静止轨道（GEO）卫星全天时全天候高精度的监测需求，考虑传统甚长基线干涉（VLBI）测站高成本、高投入和GEO卫星专用观测时段有限等制约条件，研发了简易型VLBI观测系统，并组建了包括上海、都匀和乌鲁木齐三站的微型VLBI网（micro VLBI network，MVN），开展了并置站测试以及对GEO卫星亚太6C的连续监测，并评估了当前MVN的观测能力。结果表明MVN扣除系统差后的单站接收精度为2ns，各基线观测时延拟后残差约几纳秒，GEO目标实测位置精度为百米级（内外符精度分别约100m和400m）。不同于传统VLBI和其他GEO监测手段，MVN还具备全天时、全天候、低造价、易布设及易推广等特点，充分表明了其在GEO卫星监测领域的应用价值。     

Ionospheric correction using GPS Klobuchar coefficients with an empirical night-time delay model

We proposed an ionospheric correction approach called NKlob to mitigate the ionospheric delay errors. NKlob is a modification of the original GPS Ionospheric Correction Algorithm (ICA), which uses an empirical night-time model depending on the time, geomagnetic location and periodicities of the ionospheric behavior to replace the night-time constant delay in GPS ICA. Performance of NKlob was evaluated by the independent total electron contents (TECs) derived from Global Ionospheric Maps (GIMs) of the International GNSS Services (IGS) and Jason-2 altimetry satellite during 2013–2017. Compared to GIM TECs, NKlob corrects 51.5% of the ionospheric delay errors, which outperforms GPS ICA by 6.3%. Compared to Jason-2 TECs, NKlob mitigates the ionospheric errors by 58.1%, which is approximately 3.7% better than that of GPS ICA. NKlob shows significant improvement in low-latitude and equatorial regions with respect to GPS ICA, meanwhile exhibiting comparable performance at middle and high latitudes. Since NKlob only requires slight technical changes at the processing level of GPS receivers, we suppose that it can be easily implemented for better ionospheric delay corrections of real-time GPS single-frequency applications.     

北斗GEO卫星CEI相时延解算方法研究

连线端站干涉测量(connected element interferometry，CEI)是高精度测角技术，在中高轨卫星、月球及深空航天器定轨定位中有良好的应用前景。基于CEI技术特点，提出了一种新的测量方法，即在相干测距模式下利用测距音和载波信号作为信号源进行连线端站干涉测量。构建了CEI试验系统对北斗GEO卫星进行观测，利用相干测距模式下的下行信号解算群时延、相时延。利用北斗GEO卫星精密星历计算的时延理论值，对北斗GEO卫星CEI群时延和相时延结果进行评估。结果表明，相干测距模式下CEI群时延和相时延残差均值分别为0.47ns、0.08ns，标准差(3σ)分别4.2ns、0.13ns。该项研究验证了相干测距模式下CEI相时延解算的可行性，可为共位地球同步卫星精密相对定位、月球探测器CEI测量提供技术参考。     

A composite disturbance observer and H_∞ control scheme for flexible spacecraft with measurement delay and input delay

In this paper, the attitude control algorithm of flexible spacecraft with unknown measurement delay and input delay based on disturbance observer is designed. The influence of measurement delay and input delay on the attitude control system and disturbance observer is analyzed. The disturbance estimation error equation is transformed into a differential system with a pure delay. Then, the observer gain is chosen based on the 3/2 stability theorem to ensure the stability and disturbance attenuation performance of the pure delay system. Next, the controller gain is designed based on the Linear Matrix Inequality(LMI) approach to guarantee the stability of the composite system and achieve H_∞ performance with two additive delays. The simulation results show that the proposed method can improve the anti-disturbance ability of the attitude control system.