3株乳酸芽孢杆菌的筛选、初步鉴定及应用试验

通过对41株产酸芽孢杆菌Bacillus培养物的HPLC分析及抑菌活性和芽孢形成检测,筛选出3株能产生乳酸、有抑菌活性、易形成芽孢的乳酸芽孢杆菌.通过形态染色特性观察、Biolog系统鉴定及16S rDNA 碱基序列分析,初步鉴定3株菌为芽孢杆菌SC Bacillus sp.SC、芽孢杆菌TR B.sp.TR和蜡状芽孢杆菌SL1 B.cereus strain SL1.动物饲养试验显示,乳酸芽孢杆菌益生素能提高三黄鸡血清钙、磷、总蛋白、球蛋白、溶菌酶、IgG、IgA含量及脾脏、胸腺和法氏囊指数;饲料中添加5 g/kg 的乳酸芽孢杆菌益生素,可使56日龄三黄鸡的平均日增质量提高13.61%,料质量比降低18.37%.     

苜蓿内生菌中高效AHL降解菌的筛选和鉴定

从中国新疆、内蒙古和墨西哥等地分离苜蓿内生菌133株,平板筛选到8株细菌具有N-酰基高丝氨酸内酯(N-Acyl-L-homoserinelactone,AHL)降解活性,其中活性较强的菌株有r-12、r-9和R1.5.对8株AHL降解菌做AHL唯一碳源试验,结果发现菌株S35和N46在液体AHL唯一碳源培养基中生长情况较好,D_(600 nm)分别为0.415和0.386,菌株r-9的生长情况最差,D_(600 nm)为0.015.菌株R1.5还具有耐高温、耐盐碱、能分解无机磷、在无氮培养基上生长等优点.经细菌形态学观察、生理生化试验以及16S rDNA序列分析,初步确定菌株R1.5为1株地衣芽孢杆菌.     

利用PCR-DGGE技术快速检测鉴定饲用微生物

针对目前国内外对饲用微生物添加剂中多种微生物的检测缺乏简捷有效手段这一现实状况,通过PCR-DGGE方法建立了地衣芽孢杆菌Bacillus licheniformis、粪肠球菌Enterococcus faecalis、植物乳杆菌Lactobacillus plantarum、干酪乳杆菌Lactobacillus casei 4种标准菌株的分子指纹图谱,建立了一套这4种微生物的快速同步检测技术,并用该检测技术对市场上一种饲用微生物添加剂进行分析,结果判定其含有6种优势菌群,包括植物乳杆菌和干酪乳杆菌.本技术还可以推广应用到目前国家允许添加的其他16种饲用微生物的检测,为饲用微生物添加剂产品质量监控提供了技术支撑.     

ZH_(205)~(204)B压力校测仪与ZHR_(533)B信号源通过鉴定

由北京航空航天大学中航机电所研制的ZH204B、ZH205B电脑压力校验测量仪和ZHR553B多功能信号源于1994年9月通过国家鉴定。ZH204B、ZH205B以微电脑为基础，具有手动泵产生精确压力信号，进行高精度压力测量，电流、电压测量，采集存储测量数据，重显数据，配有打印机和RS232接口等多种功能。可为被校表提供DC24V电源。量程齐全，精度：0．05％FS，0．1％FS。ZHR553B是为现场校验工业自动化仪表，如变送器、控制器、调节器、记录仪、接受机等而研制的1种新型数字式仪表。是1种便携式、交直流两用、高精度、数字显示的多用途信号源…     

影响农杆菌介导草菇遗传转化的因素研究

以草菇Volvariella volvacea菌株V51为受体材料,用农杆菌Agrobacterium tumefaciens介导法转入抗冷冻蛋白基因(afp),探索不同的转化受体、农杆菌种类、乙酰丁香酮(AS)的浓度、共培养的温度、时间等因素对转化效率的影响,并采用PCR及Southern杂交检测afp基因是否整合到草菇的基因组中.结果表明:以D_(660 nm)为0.15的EHA105为侵染的农杆菌菌株,加入200 μmol/L AS进行预培养,侵染菌丝球后转入含有AS为200 μmol/L的IMA培养基上,28 ℃,共培养60 h为最佳转化条件.PCR与Southern杂交结果证明afp基因已整合到草菇的基因组中.     

舰载机服役环境中微生物的提取及其对 7B04铝合金腐蚀行为的影响

舰载机服役环境恶劣,容易遭受微生物腐蚀。从舰载机油箱和电子元件材料腐蚀产物中取样,进行微生物的分离、提取与鉴定,筛选出 7种典型菌株。通过开路电位(OCP)、电化学阻抗谱(EIS)和动电位极化曲线等电化学测试,初步研究了其中 3种菌对 7B04铝合金腐蚀行为的影响。试验结果表明,假丝酵母菌对 7B04铝合金腐蚀有抑制作用,而鲁氏不动杆菌和副干酪乳酸菌具有促进腐蚀的作用。     

双股同轴中心旋流-突扩燃烧室试验研究

本文对双股同轴中心旋流-突扩燃烧室模型进行了冷态气模试验.发现有收扩挡块的旋流室出口扩张角大于8°时,在突扩燃烧室内可形成中心回流区;当旋流室长径比L_i/D_i为1.3时,除了出现中心旋流回流区外,同时,紧接在该回流区后形成另一个较大的无切向速度分量的回流区.在无旋流室收扩挡块的情况下,只能形成一个中心旋流回流区,不可能在该回流区后再产生无切向速度分量的中心回流区.     

神舟十号飞船下行菌株Microbacterium sp. LCT-H2的基因组测序及分析

神舟十号飞船返回舱内表面分离得到一株下行菌株LCT-H2,显微观察和革兰氏染色结果为短杆状的革兰氏阳性菌,利用葡萄糖、纤维二糖等多种碳源,对该菌进行16S rRNA测序,鉴定其为微杆菌属成员,并命名为Microbacterium sp.LCT-H2。对该下行菌进行了全基因组测序和基因功能注释分析,其基因组大小为3.36 M,包括3235个编码序列和53个RNA基因,COG数据库比对共注释到21组COG功能分类。可对研究密闭飞行器内微生物种类分布等提供一定帮助。     

毒死蜱降解菌枝孢霉菌的紫外诱变和筛选

通过紫外诱变毒死蜱降解菌枝孢霉菌Cladosporium cladosporioides Hu-01,利用高效液相色谱(HPLC)检测,筛选获得12株突变菌株,其中突变株Hu-01-4和Hu-01-6的降解效果明显高于初始菌株Hu-01.突变株Hu-01-4和Hu-01-6经过加药斜面传种10代,Hu-01-6的降解率比初始菌株提高11.74%,并且保持良好的稳定性.突变菌株Hu-01-6在28 ℃、pH6.5培养条件下的生长量最大,降解率最高,且均明显高于初始菌株Hu-01.     

一株神舟十号飞船分离少动鞘氨醇单胞菌基因组测序结果及分析

在神舟十号飞船中检测出一株下行菌,16 S r DNA鉴定后命名为少动鞘氨醇单胞菌LCTSP1。通过对该菌基因组进行二代测序及基因注释,发现该菌包含3884个蛋白编码基因、3个rRNA编码基因和47个tRNA编码基因。通过对该菌基因组进行COG、GO分析及注释,完善了该菌的遗传信息,并建立了该菌的系统发育树。分析发现该菌包含腐蚀相关基因并可适应恶劣的生存环境。通过基因注释发现该菌包含574个毒力相关基因以及57个耐药相关基因,提示该菌存在潜在的致病性。     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

ν-gap度量及其在飞行控制律评估中的应用

 传统控制律评估方法主要用于单输入单输出（SISO）系统，且对模型参数摄动考虑不够全面,针对这些不足，研究了ν-gap度量方法。在介绍系统广义稳定裕度相关概念的基础上，给出了ν-gap度量的定义、特点和性质以及近似摄动模型的计算，提出ν-gap度量评估控制律的步骤。实例结果表明，该方法不仅克服了上述传统评估方法的缺陷，而且还有根据所求的各摄动影响情况忽略影响小的元素，以减少计算量及可以找到最坏情况下的参数摄动组合等优点。     

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Integrated Entry Guidance for Reusable Launch Vehicle

A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor, and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty. Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertain-ties are presented to demonstrate the capacity and reliability of this method.     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。