RPC-MIP: the Mutual Impedance Probe of the Rosetta Plasma Consortium

The main objective of the Mutual Impedance Probe (MIP), part of the Rosetta Plasma Consortium (RPC), is to measure the electron density and temperature of Comet 67P/Churyumov-Gerasimenko’s coma, in particular inside the contact surface. Furthermore, MIP will determine the bulk velocity of the ionised outflowing atmosphere, define the spectral distribution of natural plasma waves, and monitor dust and gas activities around the nucleus. The MIP instrumentation consists of an electronics board for signal processing in the 7 kHz to 3.5 MHz range and a sensor unit of two receiving and two transmitting electrodes mounted on a 1-m long bar. In addition, the Langmuir probe of the RPC/LAP instrument that is at about 4 m from the MIP sensor can be used as a transmitter (in place of the MIP ones) and MIP as a receiver in order to have access to the density and temperature of plasmas at higher Debye lengths than those for which the MIP is originally designed.     

Fatigue life research and experimental verification of superalloy thin-walled structures subjected to thermal-acoustic loads

Rapid alternating stress is formed in structure subjected to harsh thermal-acoustic loads, which will affect fatigue performance and reduce fatigue life seriously. First, fatigue experiment of superalloy thin-walled structure was carried out to obtain fatigue damage location and failure time of the experiment specimen, and S-N curves of superalloy thin-walled structure at 723 K were fitted. Then, dynamic response simulation of superalloy thin-walled structure under the same load as experiment was implemented, and fatigue life was estimated based on the fatigue life prediction model which mainly included: improved rain-flow counting method, Morrow average stress model and Miner linear cumulative damage theory. Further, comparisons between simulation solutions and experimental results achieved a consistency, which verified the validity of the Fatigue Life Prediction Model (FLPM). Moreover, taking a rectangle plate as the analysis object, the distributions of Fain-low circulation blocks and damage levels of the structure were discussed respectively. Finally, current research indicates that in pre-buckling the structure is in softened area and fatigue life decreases with the increase of temperature; in post-buckling the structure is in hardened area and fatigue life increases with the increase of temperature within a certain range.     

亚跨超风洞现代试验设计方法研究

开展了基于现代试验设计方法(MDOE)的亚跨超风洞试验研究,以八号标模尾翼为试验对象研究其气动特性,采用同时改变攻角-侧滑角的多变量方法,而不是传统的单变量(OFAT)方法进行试验。对自变量攻角和侧滑角进行试验设计(DOE),应用响应面法建模,用IV-最优方法对测量点分布进行设计。在FD-12亚跨超风洞完成了试验,并和传统的OFAT方法结果进行比较分析。结果表明:MDOE方法获得的数据和传统的OFAT方法的数据吻合很好;MDOE采集样点数减少了46%,吹风的时间比OFAT减少30%左右,提高了风洞试验效率,缩短了试验周期;MDOE试验方法可以给出设计空间内任意给定自变量对应的响应值及其置信区间。     

两相脉冲爆轰发动机尾喷管的实验研究

为了提高脉冲爆轰发动机的推进性能,实验研究了12种不同构型尾喷管对火箭式两相脉冲爆轰发动机爆轰特性和推进性能的影响,并对各类尾喷管的增推原因进行分析。结果表明满填充工况下各类喷管内的爆轰特性不尽相同,收敛喷管可得到最大压力峰值;在满填充工况下频率为10Hz时12种喷管构型中拉伐尔喷管的推力增益最大,塞式收敛扩张喷管其次;拉伐尔喷管的出口面积比对推力增益有较大影响,但收敛段-扩张段长度比对推力增益影响甚微。     

Ozone trends in the mid-latitude stratopause region based on microwave measurements at Lindau (51.66° N, 10.13° E), the ozone reference model,and model calculations

We compared 8 years of ozone measurements taken at Lindau (51.66° N, 10.13° E) at altitudes between 40 and 60 km using the microwave technique with the CIRA ozone reference model that was established 20 years ago (Keating et al., 1990). We observed a remarkable decrease in ozone density in the stratopause region (i.e., an altitude of 50 km), but the decrease in ozone density in the middle mesosphere (i.e., up to 60 km in altitude) is slight. Likewise, we observed only a moderate decrease in the atmospheric region below the stratopause. Other studies have found the strongest ozone decrease at 40 km and a more moderate decrease at 50 km, which is somewhat in contradiction to our results. This decrease in ozone density also strongly depends on the season. Similar results showed model calculations using the GCM COMMA-IAP when considering the increase in methane. In the lower mesosphere/stratopause region, the strongest impact on the concentration of odd oxygen (i.e., O₃ and O) was observed due to a catalytic cycle that destroys odd oxygen, including atomic oxygen and hydrogen radicals. The hydrogen radicals mainly result from an increase in water vapor with the growing anthropogenic release of methane. The finding suggesting that the stratopause region is apparently attacked more strongly by the water vapor increase has been interpreted in terms of the action of this catalytic cycle, which is most effective near the stratopause and amplified by a positive feedback between the ozone column density and the ozone dissociation rate, thereby chemically influencing the ozone density. However, the rising carbon dioxide concentration cools the middle atmosphere, thereby damping the ozone decline by hydrogen radicals.     

低速风洞中的洞壁干扰计算

本文按照文[1]的方法,通过壁压测量影响函数法计算洞壁干扰。文中对H/B=0.75、0.8333、1.00,以及矩形切角风洞进行了计算,并在H/B=0.8333的风洞中作了修正试验。计算与试验表明,本文的计算是可靠的,提供的曲线可供实际使用。     

载人航天器微量污染控制装置实验研究

在分析中长期载人航天器舱室内的微量气态污染来源，以及比较国内外微量污染净化系统方案的基础上，提出适合我国将来发展的空间实验室微量污染净化系统，它由活性炭吸附床、高温催化反应装置、常温催化反应装置、风机、阀门及控制装置等组成。文中重点介绍了高温催化氧化装置实验样机的结构设计和控制方法，在搭建的实验平台上对该净化样机进行了各种工作性能实验研究。实验结果表明：温度控制器控制精度高、装置工作性能稳定、净化效率较高。     

Comparison of computational and experimental results in vibroacoustic active control using piezoelectric film technology

The present investigation concerns control of far-field acoustic radiation generated by a thin plate in a broad frequency band using piezoelectric films. System dynamics is of modal nature.This paper describes a comparison of numerical and experimental results for a closed loop type control. This comes from Optimal Control Theory via radiation filter causal transformation based on a dissipative criterion.     

地球卫星星光折射导航量测量及其性能对比

星光折射天文导航是一种重要的地球卫星自主导航方式,量测量是影响其导航精度的重要因素。在地球卫星星光折射导航中,折射视高度、星光折射角、折射星像素坐标（折射星矢量）是3种常用的量测量,结合星光折射导航的基本原理重点介绍了这3种量测量的获取方法和量测模型,通过仿真和可观性分析比较了相同条件下3种量测量的导航性能。仿真结果表明,由于折射星像素坐标可以同时反映星光折射的大小和方向可观性高,而星光折射角和折射视高度仅能反映星光折射的大小,无法反映其方向可观性低,因此折射星像素坐标的导航性能优于星光折射角和折射视高度。此外,本文也对星敏感器精度、卫星轨道高度、星敏感器安装夹角3种因素对3种方法导航性能的影响进行了分析。