应用气动谐振的气氧、煤油点火器的方案研究

为了实现液体推进剂火箭发动机的多次可靠起动,将气动谐振点火技术应用于气氧煤油的点火.提出了两种应用气动谐振的气氧煤油点火器方案:直接点火方案和间接点火方案.在直接点火方案中对气氧与煤油同轴喷入和煤油由顶部喷入两种不同的点火方式进行了分析比较.在间接点火方案中对点火火炬为富燃和富氧两种情况进行了对比分析.试验研究表明两种方案均实现了多次可靠的点火并生成了稳定的点火火炬.通过对两种方案的优缺点、工程上应用的技术可行性和存在的技术难点的分析,认为富燃情况的间接点火方案具有明显的优势并有望在短期内达到工程应用要求.      

新颖机动变轨化学火箭发动机头部研究

为研究轻型、可靠、环保的空间站机动变轨发动机,在氢/氧液体火箭发动机头部设计中引入了新型气动谐振点火技术.结合发动机推力室设计以及同轴氢氧谐振点火器研究,确定了用富燃的谐振点火火炬与剩余主体氧气再燃烧的发动机头部整体方案.通过对几种主氧喷嘴下发动机头部结构方案研究,选定了主氧喷嘴结构形式.针对发动机要求快速起动、点火响应时间短的关键技术,提出了几种研究实现途径,包括谐振加热装置的结构形式优化、参数匹配优化、材料改进以及点火组元进入时序研究等,以提高气动谐振装置的加热速度及点火能量集聚效率,最终实现了发动机起动时间达到0.2?s以内.     

气氧酒精多管点火器试验研究

多管同步点火是塞式喷管的一项关键技术,介绍了气氧酒精多管点火器的设计和试验情况.研究了推进剂的混合比、点火器的工作时间、燃气导管的材料和几何尺寸、点火器的冷却方式,以及补氧燃烧措施对多管点火性能的影响,同时对高空情况下的点火方法进行了初步探讨.最后确定了多管点火器的工作参数,实现了可靠的多管同步点火.      

氢氧谐振点火器多室同步点火研究

将气动谐振点火技术应用于塞式喷管发动机多推力室的多次同步点火,研制了新型的氢氧谐振点火器. 通过对点火器的点火响应时间、点火延迟时间、多次点火的重复性以及点火器寿命等方面进行试验研究,验证了新研制的点火器具有起动快、点火延迟时间短、多次点火重复性好、寿命长等特点.采用2个点火器联试的方式进行了5次同步点火试验,研究了连接管路对同步性的影响,并提出了进一步缩短同步性时差的方法,结果表明氢氧谐振点火器完全可以满足塞式喷管发动机多推力室同步点火的要求.     

塞式喷管热试实验和数值模拟

以气氢／气氧为推进剂,对三单元直排塞式喷管发动机进行了热试实验和数值模拟研究.介绍了实验系统及实验发动机主要零部件的结构和设计参数,给出了实验参数测量结果、实验照片和数据分析.数值模拟研究了塞式喷管的流场特点,数值预示了实验塞式喷管发动机的高度特性曲线.无再生冷却塞式喷管发动机采用耐烧蚀材料钨渗铜加工内喷管和燃烧室内衬,碳钢材料加工塞锥.使用爆震波点火器点燃多个单元推力室,成功进行了热试实验.在2个压比下获得了塞式喷管性能数据,实验表明,塞式喷管具有良好的高度补偿能力和较高的喷管效率.在C_NPR=50附近,效率达到92％~93.5％;在C_NPR=350附近,效率达到95％~96％.预计在设计点的效率不低于98％.      

超燃燃烧室等离子体点火和火焰稳定性能

为了研究热等离子点火器在超燃冲压发动机中的应用,在来流马赫数2.0工况下,针对乙烯和氢气两种燃料,进行了超燃环境中等离子体点火的试验和仿真研究.在来流总温1 500~1 950 K,燃料当量比0.1~0.55范围内对等离子点火器的点火和改善燃烧性能的性质进行了详细分析.结果显示:对于氢气和乙烯燃料,等离子体点火器使两种燃料的点火性能均得到明显改善,点火延迟时间大大缩短,燃料着火范围扩大、贫燃极限当量比降低.但未观察到其在加速掺混以及改善燃烧性能方面的明显作用.进行了与乙烯燃烧试验对应的数值仿真工作,选用了两种乙烯化学反应模型进行对比研究.仿真结果显示:8步9组分反应模型与试验结果符合较好,而3步6组分反应模型过高的估计了反应剧烈程度,燃烧室压力值偏高,压力起始上升位置偏向上游.所用的8步模型比3步模型更适合于超燃燃烧室中乙烯反应的模拟.     

中性气体释放人工产生气辉

电离层中分子性的离子与电子的复合要比氧离子与电子的辐射性复合快得多,因此火箭发动机产生的尾气和空间等离子体主动实验中主动释放的中性气体会对电离层有很大的影响,这么大的电离层扰动现象在过去的实验中经常可以观测到.根据中性气体在热层背景中的扩散方程,考虑电离层F区主要的离子化学反应,研究了H2,H2O和CO2气体在电离层高度上的扩散过程和电离层对所释放气体的响应,计算了气辉的体发射系数和发射强度.结果表明,中性气体在电离层高度上扩散非常迅速,在F区的一些高度上,主要正离子成分由O+转变为其他分子离子,且在释放过程中伴随气辉发射,发射气辉的波长和特征与释放物质的种类有关.      

利用WACCM-3模式对平流层动力、热力场及微量化学成分季节变化的数值模拟研究

利用美国NCAR最新的化学-气候耦合模式WACCM-3对平流层风场、温度场以及平流层臭氧等多种微量气体成分(O3, CH4, N2O, H2O, HCl, HNO3)的季节变化进行了数值模拟, 并使用ECMWF再分析资料与美国UARS卫星 搭载的HALOE, MLS, CLAES等探测器的观测资料, 对模式输出的动力、热力及化学成分浓度的气候平均值进行了验证. 结果表明, 在气候平均海表温度值驱动下, WACCM-3模式能够很好地再现ECMWF资料中平流层纬向平均风场与温度场的季节变化. 模拟结果中平流层化学成分的经向-垂直分布及其季节变化与卫星观测结果基本一致. 模式的动力、热力场在极地平流层以及热带对流层顶等区域存在一定的偏差. 这些偏差对于微量气体成分分布 的模拟具有一定影响, 特别是南半球冬(7月)、春(10月)季节南极平流层低层极夜 急流偏强, 造成极地地区附近的输送障碍增强, 从而导致CH4, N2O, H2O浓度比观测偏低. 此外, WACCM-3缺少热带平流层风场的准两年振荡(QBO) 机制, 这对于热带平流层东风急流以及低纬度平流层O3, CH4, N2O, H2O等成分经向输送的模拟结果也有一定影响.      

液体火箭发动机爆震波点火技术初步研究

对液体火箭发动机各种点火技术优缺点进行了对比分析,探讨了各种点火技术方案应用于未来先进推进系统的多管多次点火系统的可行性,讨论了各种点火技术应用方案的结构形式.对爆震波点火技术进行了初步研究,建立了气氢气氧爆震波点火的简化理论分析模型,对其在实际液氢液氧发动机中应用的具体方案进行了分析.分析结果表明,爆震波点火技术可以由低压混合气体产生高温高压的爆震产物,爆震波以高马赫数速度传播,迅速到达各点火位置.爆震波点火技术具备良好的同步性能和简单的结构方案形式,适用于液体火箭发动机多管多次同步点火.     

直线电机气浮精密定位平台设计与控制

为了掌握光刻机工件台的设计和控制技术,建立了双边直线电机驱动的H型气浮精密定位平台,对该精密定位系统的气浮导轨设计方法、双边直线电机同步运动控制等关键技术进行了研究.利用有限元计算方法分析设计了气浮导轨,采用预加载技术提高气浮导轨的承载能力和刚度.实验结果表明:气浮导轨具有较高的承载能力和刚度, X和Y 导轨的竖直方向静刚度为276.9N/μm和333.3N/μm.H型工作台的双边直线电机需要高精度的同步运动控制,传统的串、并联同步控制不能满足精度要求,设计了基于同步速度偏差的改进型并联结构同步控制器,采用模糊控制实现PID参数的自适应整定.实验表明:采用改进的控制器将速度同步精度提高了3倍多,适合于具有强机械耦合的多电机同步运动控制.H直线电机气浮定位平台具有承载能力强(40kg)、精度高(<2μm)的优点,可用于精密工程领域.      

Plasma chemical reactions in C2H2/N2, C2H4/N2, and C2H6/N2 gas mixtures of a laboratory dielectric barrier discharge

Plasma chemical reactions in C₂H₂/N₂, C₂H₄/N₂, and C₂H₆/N₂ gas mixtures have been studied by means of mass spectrometry at a medium pressure of 300 mbar in a laboratory dielectric barrier discharge. A major reaction scheme is production of larger hydrocarbons like C_nH_m with n up to 12 including formation of functional CN groups.     

Rotational constants of linear and/or bent Cn+1H and CnN(n = 1–6): A DFT study

The geometries, dipole moments, and rotational constants for the linear and/or bent cations, C_n+1H⁺ and C_nN⁺(n = 1–6), were studied by the B3LYP method with the modest basis sets. For C_nH⁺(n = odd; 3, 5, 7) and C_nN⁺(n = even; 2, 4, 6), the theoretical rotational constants (B_es) of closed-shell singlet C₃H⁺, C₅H⁺, C₇H⁺, CCN⁺, C₄N⁺, and C₆N⁺ were calculated to be about 11,244, 2420, 885.2, 11,970, 2439, and 880.8 MHz, respectively. By contrast, the triplets are stable than the corresponding singlets for C_nH⁺(n = odd; 2, 4, 6) and C_nN⁺(n = even; 3, 5) except CN⁺.     

Quantitative determination of the outgassing water vapor concentrations surrounding space vehicles from ion mass spectrometer measurements

Outgassing from materials as well as deliberate gaseous and liquid releases create contaminant clouds around spacecraft that can degrade both instrumentation and measurements. This paper describes a new method for estimating outgassing water vapor concentrations around space vehicles. Water vapor ions measured in the course of a rocket experiment performed at Eglin AFB, Florida, on December 12, 1980 at 2311 UT are utilized to demonstrate the technique. The H₂O concentration near the payload's surface is calculated using the rate coefficient for the fast charge transfer process, O⁺ + H₂O + H₂O⁺ + O, the source of the observed water vapor ions. It is found that the measured H₂O⁺ ions were produced within 3–4 cm of the sampling plate's surface and that the average H₂O pressure over this distance was relatively constant on ascent at 8 × 10^?6 torr, within a factor two, implying a steady outgassing rate.     

基于支板燃烧室的喷管化学非平衡效应

采用有限体积法全隐式格式和代用燃料C₁₂H₂₃的10组元13步化学反应Arrhenius有限速率模型研究煤油燃料超燃冲压发动机单边膨胀喷管(SERN, Single Expansion Ramp Nozzle)内的化学非平衡流动,通过建立支板燃烧室——喷管模型有效解决了单边膨胀喷管模型的"入口薄层"问题.计算结果表明,整个单边膨胀喷管内,流动呈现化学非平衡效应,喷管入口附近区域尤其显著;非平衡流动喷管性能明显高于冻结流动,随发动机当量混合比 ε增加,非平衡流动的喷管推力系数和升力系数相对冻结流动的百分比增量 δ不断升高,当 ε=0.8时,推力系数百分比增量 δ_CF达到9.41%,升力系数百分比增量 δ_CY达到16.39%,化学非平衡效应对煤油燃料超燃冲压发动机尾喷管性能的影响不可忽略.     

Positive ion composition and electron density in a combined auroral and NLC event

The positive ion composition and electron density were measured in the lower ionosphere above Kiruna in salvo A of CAMP (Cold Arctic Mesopause Project). The CAMP/P (S37/P) payload carrying a magnetic ion spectrometer, positive ion and electron probes, and propagation experiments was launched on 3 August 1982 2332 UT during extended Noctilucent Clouds (NLC) and auroral activities over Kiruna. The measured electron density was 5×10³cm^?3 at 80 km and 2.5×10⁵cm^?3 at 90 km. The increase of ion and electron densities in the D- and E-region during twilight was caused by precipitating auroral particles. The height distribution of the positive ions measured by the mass spectrometer in the mass range 19–280 amu is different from a winter flight with similar auroral conditions. Below 85.5 km proton hydrates H⁺(H₂O)₃ ? H⁺(H₂O)₈ were the dominant ions. The heaviest proton hydrates H⁺(H₂O)₇ and H⁺(H₂O)₈ were most abundant at 82–85.5 km, the altitude of visible NLC. Above 85.5 km O₂⁺ and NO⁺ became dominant. A small metal ion layer was observed between 90.5–93 km with a maximum ion density of 10% of the total positive ion density at 91 km altitude. The metal ion density disappeared within about a km below 90.5 km.     

An icy mineralogy package (IMP) for in-situ studies of Titan’s surface

We describe the scientific case for and preliminary design of an instrument whose primary goal is to determine the chemistry (element abundance) and mineralogy (compound identity and abundance) of Titan’s surface using a combination of energy dispersive X-ray fluorescence spectroscopy (EDXRF) and X-ray diffraction (XRD). XRD is capable of identifying any crystalline substance present on Titan’s surface at relative abundances greater than ∼1 wt%, allowing unambiguous identification of, for example, structure I and II clathrates (even in the presence of ice), and various organic solids, which may include C₂H₂, C₂H₄, C₄H₂, HCN, CH₃CN, HC₃N, and C₄N₂). The XRF component of the instrument will obtain elemental abundances for 16 < Z < 60 with minimum detection limits better than 10 ppm (including detection of atmospheric noble gas isotopes), and may achieve detection limits of 0.01–1% for lighter elements down to Z = 6 (carbon). The instrument is well suited to integration with other analytical tools as part of a light-weight surface chemistry and mineralogy package. Although considerably less sensitive to elemental abundance than GC–MS (10⁻² vs. 10⁻⁸) it is likely to be significantly lighter (<0.5 kg vs. 10 kg).     

Mesospheric H2O and H2O2 densities inferred from in situ positive ion composition measurement

The measurements of positive ion composition in the high latitude D-region have revealed an excess of 34⁺ under distrubed conditions which has been interpreted as H₂O₂⁺. At the same altitude range near the transition height oxonium ions were measured as well. This paper presents a new model for the production and loss of oxonium ions with their production from H₂O₂⁺ + H₂O → H₃O⁺ + HO₂ and their loss by attachment of N₂ and/or CO₂. A reaction constant of 8.5×10^?28 (300/T)⁴ cm⁶s^?1 has been obtained for the three body attachment H₃O⁺ + CO₂ + M → H₃O⁺.CO₂ + M from the measured density profile of 63⁺ in flight 18.1020. Mesospheric H₂O and H₂O₂ densities are inferred from measurements of four high latitude ion compositions based on the oxonium model. The mixing ratios of hydrogen peroxide are up to two orders of magnitude higher compared to previous model calculations. In order to explain the missing production of odd hydrogen, we consider larger O(¹D) densities, surface reactions of O(³P) on particles, and cathalytic photodissociation of water vapor on aerosol particles.