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AP/HTPB推进剂凝聚相反应对燃速的影响 总被引:1,自引:0,他引:1
W.G.Schmidt[1]和K.Kishore等人[2、3]从推进剂实际燃烧过程发生在气相,而推进剂组分相对又不挥发的观点出发,得出在固相中必定要先发生一系列产生气态产物的凝聚相反应的结论。由于气相反应比凝聚相反应快得多,因而得出凝聚相反应是推进剂燃烧过程的主要控制步骤。 相似文献
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O. Alexandrova C. H. K. Chen L. Sorriso-Valvo T. S. Horbury S. D. Bale 《Space Science Reviews》2013,178(2-4):101-139
Solar wind is probably the best laboratory to study turbulence in astrophysical plasmas. In addition to the presence of magnetic field, the differences with neutral fluid isotropic turbulence are: (i) weakness of collisional dissipation and (ii) presence of several characteristic space and time scales. In this paper we discuss observational properties of solar wind turbulence in a large range from the MHD to the electron scales. At MHD scales, within the inertial range, turbulence cascade of magnetic fluctuations develops mostly in the plane perpendicular to the mean field, with the Kolmogorov scaling $k_{\perp}^{-5/3}$ for the perpendicular cascade and $k_{\|}^{-2}$ for the parallel one. Solar wind turbulence is compressible in nature: density fluctuations at MHD scales have the Kolmogorov spectrum. Velocity fluctuations do not follow magnetic field ones: their spectrum is a power-law with a ?3/2 spectral index. Probability distribution functions of different plasma parameters are not Gaussian, indicating presence of intermittency. At the moment there is no global model taking into account all these observed properties of the inertial range. At ion scales, turbulent spectra have a break, compressibility increases and the density fluctuation spectrum has a local flattening. Around ion scales, magnetic spectra are variable and ion instabilities occur as a function of the local plasma parameters. Between ion and electron scales, a small scale turbulent cascade seems to be established. It is characterized by a well defined power-law spectrum in magnetic and density fluctuations with a spectral index close to ?2.8. Approaching electron scales, the fluctuations are no more self-similar: an exponential cut-off is usually observed (for time intervals without quasi-parallel whistlers) indicating an onset of dissipation. The small scale inertial range between ion and electron scales and the electron dissipation range can be together described by $\sim k_{\perp}^{-\alpha}\exp(-k_{\perp}\ell_{d})$ , with α?8/3 and the dissipation scale ? d close to the electron Larmor radius ? d ?ρ e . The nature of this small scale cascade and a possible dissipation mechanism are still under debate. 相似文献
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Moongeun Hong 《Aerospace Science and Technology》2012,16(1):56-60
Solid propellant gas generators play a role as a turbo-pump starter in liquid propellant propulsion systems by supplying pressurized gas to power turbines for engine start. Among the required combustion gas properties provided by solid propellant gas generators, the combustion gas temperature should not exceed a certain temperature which may damage the turbine blades. For such purposes, phase stabilized ammonium nitrate (AN)-based propellants have been widely used with a low combustion temperature. However, gas generator propellants with ammonium nitrate have historically exhibited incomplete combustion resulting in increased flame temperatures differing significantly from equilibrium values. In consideration of design requirements, an engineering model of solid propellant gas generator was manufactured using the combustion gas properties calculated by a chemical equilibrium code and then hot-fire tests were performed. Procedures for the correction of , k and of the combustion gas from the experimental results are introduced and the following effects on the design of the solid propellant gas generator are presented. From the experimental correction of the combustion gas properties, it is found that the amount of the propellant could be reduced while providing the same amount of available power to the turbines and consequently, the size of the gas generator could also be decreased. 相似文献
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We present observations of stratosphere NO y species from 2002 to 2010 taken by the Michelson Interferometer for Passive Atmospheric Sounding (MIPAS) and by the Global Ozone Monitoring by Occultation of Stars (GOMOS) instruments on board ENVISAT. We jointly used observations of MIPAS NO2, HNO3, N2O5, ClONO2 and N2O, and GOMOS NO2 and NO3. MIPAS results are part of the MIPAS2D database retrieved adopting a full 2D tomographic approach. We describe the mean distribution and variability of NO y species in the stratosphere, identifying changes induced by plasma processes. Beside enhancements due to sporadic solar proton events, we show that winter polar NO2 has an almost linear relationship with the geomagnetic activity index Ap down to about 10?hPa. This indicates a dominant role of energetic precipitating particles in the production of upper atmosphere NO y . The correlation has clear signatures extending to mid latitudes. Partitioning of the NO y reservoir species are also traced, with HNO3 and N2O5 showing a correlation with Ap extending to lower altitude within the polar regions. We found no large signatures of an impact of thunderstorm-induced plasma processes onto monthly means of NO y species in the stratosphere. 相似文献
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《Aerospace Science and Technology》2007,11(1):13-17
The hydrazinium nitrate (N2H41HNO3HN) can be considered as a candidate for using instead of ammonium perchlorate (AP) in eco-friendly solid propellant formulations. In combination with energetic binder it provides reasonably high energetic parameters of solid propellant. In addition, the substitution of AP by HN leads to decrease in the combustion temperature. The combustion of the HN based metallized propellants containing energetic binder has been investigated. The effect of partial substitution of commercial Al powder by Alex on the propellant combustion characteristics has been examined. The burning law was measured in the pressure range 20–80 atm, the ignition delay time and temperature profile were measured at atmospheric pressure. Some qualitative observations on the combustion behavior of the propellants under study have been made by analyzing the video camera and recoil force transducer records. 相似文献
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《中国航空学报》2021,34(12):17-27
Ammonia (NH3) is considered as a potential alternative carbon free fuel to reduce greenhouse gas emission to meet the increasingly stringent emission requirements. Co-burning NH3 and H2 is an effective way to overcome ammonia’s relative low burning velocity. In this work, 3D Reynolds Averaged Navier-Stokes (RANS) numerical simulations are conducted on a premixed NH3/H2 swirling flame with reduced chemical kinetic mechanism. The effects of (A) overall equivalence ratio Φ and (B) hydrogen blended molar fraction XH2 on combustion and emission characteristics are examined. The present results show that when 100%NH3-0%H2-air are burnt, the NO emission and unburned NH3 of at the swirling combustor outlet has the opposite varying trends. With the increase of Φ, NO emission is found to be decreased, while the unburnt ammonia emission is increased. NH2 → HNO, NH → HNO and HNO → NO sub-paths are found to play a critical role in NO formation. Normalized reaction rate of all these three sub-paths is shown to be decreased with increased Φ. Hydrogen addition is shown to significantly increase the laminar burning velocity of the mixed fuel. However, adding H2 does not affect the critical equivalence ratio corresponding to the maximum burning velocity. The emission trend of NO and unburnt NH3 with increased Φ is unchanged by blending H2. NO emission with increased XH2 is increased slightly less at a larger Φ than that at a smaller Φ. In addition, reaction rates of NH2 → HNO and HNO → NO sub-paths are decreased with increased XH2, when Φ is larger. Under all tested cases, blending H2 with NH3 reduces the unburned NH3 emission, especially for rich combustion conditions. In summary, the present work provides research finding on supporting applying ammonia with hydrogen blended in low-emission gas turbine engines. 相似文献
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Patrick Petitjean Raghunathan Srianand Hum Chand Alexander Ivanchik Pasquier Noterdaeme Neeraj Gupta 《Space Science Reviews》2009,148(1-4):289-300
We summarize the attempts by our group and others to derive constraints on variations of fundamental constants over cosmic time using quasar absorption lines. Most upper limits reside in the range 0.5–1.5×10?5 at the 3σ level over a redshift range of approximately 0.5–2.5 for the fine-structure constant, α, the proton-to-electron mass ratio, μ and a combination of the proton gyromagnetic factor and the two previous constants, g p(α 2/μ) ν , for only one claimed variation of α. It is therefore very important to perform new measurements to improve the sensitivity of the numerous methods to at least <0.1×10?5 which should be possible in the next few years. Future instrumentations on ELTs in the optical and/or ALMA, EVLA and SKA pathfinders in the radio will undoutedly boost this field by allowing to reach much better signal-to-noise ratios at higher spectral resolution and to perform measurements on molecules in the ISM of high redshift galaxies. 相似文献
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《中国航空学报》2021,34(3):105-117
Swirl-Loop Scavenging (SLS) improves the performance of 2-stroke aircraft diesel engine because the involved swirl may not only benefit the scavenging process, but also facilitate the fuel atomization and combustion. The arrangement of scavenge port angles greatly influences in-cylinder flow distribution and swirl intensity, as well as the performance of the SLS engine. However, the mechanism of the effect and visualization experiment are rarely mentioned in the literature. To further investigate the SLS, Particle Image Velocimetry (PIV) experiment and Computational Fluid Dynamics (CFD) simulation are adopted to obtain its swirl distribution characteristics, and the effect of port angles on scavenging performance is discussed based on engine fired cycle simulation. The results illustrate that Reynolds Stress Turbulence model is accurate enough for in-cylinder flow simulation. Tangential and axial velocity distribution of the flow, as well as the scavenging performance, are mainly determined by geometric scavenge port angles αgeom and βgeom. For reinforcement of scavenging on cross-sections and meridian planes, αgeom value of 27° and βgeom value of 60° are preferred, under which the scavenging efficiency reaches as high as 73.7%. Excessive swirl intensity has a negative effect on SLS performance, which should be controlled to a proper extent. 相似文献
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固体推进剂铝团聚模型 总被引:1,自引:0,他引:1
综述了固体推进剂铝团聚研究进展,对现有研究中存在的局限性进行了讨论,并分析了未来团聚模型的趋势.铝团聚物理过程可抽象为堆积、聚集和团聚3个阶段.现有团聚模型可分为5类,分别是经验模型、口袋模型、物理模型、随机装填模型和凝相边界层模型.目前缺乏高精度、宽适用性的模型来准确预测铝的团聚过程.团聚模型未来发展的趋势应具备能够预测团聚物粒度分布和计算量小两大优势.由于能描述团聚过程的本质,物理模型具有很好的研究前景.开展了5MPa下含铝推进剂燃烧实验,采用高速显微拍摄技术获得推进剂燃面处铝颗粒的团聚直径,与Hermsen模型和Salita模型预测数据进行了比较,对于燃速分别为5.1mm/s和8.0mm/s的推进剂,Salita模型对于团聚直径的预示误差分别为8.7%和9.6%,而Hermsen模型对于高燃速推进剂的预示误差为19.2%.总体看来,Salita模型预示精度更为合理. 相似文献
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The kinematic characteristics of flexible membrane wing have vital influences on its aerodynamic characteristics. To deeply explore the regularities between them, time-resolved aerodynamic forces and deformations at different aeroelastic parameters and angles of attack(α) were measured synchronously by wind tunnel experiments. The membrane motion can be mainly divided into two states at α > 0° with various lift-enhancement regularities: Deformed-Steady State(DSS)at pre-stall, and Dynamic Bala... 相似文献
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Rainer Schwenn 《Space Science Reviews》1983,34(1):85-99
Major interplanetary shock waves have often been successfully associated with major solar flares. The interplanetary response to weaker solar events, e.g., eruptive prominences (EP) and slow coronal transients, is far less pronounced. Recently, progress has been made by combining the newly-available data of white-light-coronagraph measurements from the earth-orbiting satellite P78/1 (these data show the development of coronal transients between 2.5 and 10 R bd, in-situ plasma measurements from the HELIOS solar probes positioned mostly above the Sun's limb at solar distances between 60 and 200 R bd (showing the reactions of the interplanetary plasma), ground based Hα-coronagraphs (showing in a few cases the evolution of EP's from the Sun's limb up to 1.5 Abd). In the years 1979 to 1981 about 25 uniquely associated events were identified, 19 of which allow some detailed analysis. The events can be sorted into three main categories: The ‘flare-type’: 13 events, probably all of them flare-related, transient speeds v t from 560 to 1460 km s?1, no evidence for post-acceleration of the transient (indicating impulsive injection), all transients followed by drastic interplanetary shock waves, some of them probably involving magnetic clouds. The ‘EP-type’: 4 events, none of them flare-related, at least one was observed as an Hα-EP, transient speed from 200 to 410 km s-1, all post-accelerated (indicating ‘driven’ injection), all followed by shocks with at least one magnetic cloud, one showing presence of He+ and O2+ behind the shock. The ‘NCDE-type’: 2 events, one observed as an Hα-EP, the other without known solar source, v t , = 130 and 470 km s?1, one post-accelerated, the other one not, considerable density increase in interplanetary plasma (however, in pressure equilibrium with surroundings), one event including shock, the other not. These two events may not belong to the same category. Our results are not completely consistent with previous work which is mainly based on data from the Skylab era, 1973/74. This could be due to the different phase in the solar cycle. The study is being continued. 相似文献
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螺旋管内超临界航空煤油流动阻力特性 总被引:1,自引:0,他引:1
研究了系统压力、质量流速及螺旋管结构形式对超临界压力下航空煤油RP-3在螺旋管内的流动阻力特性.实验结果表明:螺旋管局部阻力系数变化曲线由螺旋管内流体临界雷诺数、拟临界温度分为明显的3个部分:工质温度低于拟临界温度且管内雷诺数小于螺旋管临界雷诺数时,局部损失系 数与雷诺数和螺旋直径与管径比D/din相关;流体温度低于拟临界温度且雷诺数大于临界雷诺数时,局部阻力系数只与D/din相关; 流体温度大于拟临界温度时,局部阻力系数除与雷诺数和D/din相关外,同时还与密度、黏性的大幅变化相关.另外,基于实验结果,提出了一种用压力、温度和螺旋直径与管径比进行修正的局部阻力系数关联式,拟合结果与实验结果相比,具有较好的一致性. 相似文献
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Significant springback occurs after tube rotary-draw-bending (RDB), especially for a high-strength Ti-3A1-2.5V tube (HSTT) due to its high ratio of yield strength to Young's modulus. The combination scheme of explicit and implicit is preferred to predict the springback. This simulation strategy includes several numerical parameters, such as element type, number of elements through thickness (NEL), element size, etc. However, the influences of these parameters on spring- back prediction accuracy are not fully understood. Thus, taking the geometrical specification 9.525 mm × 0.508 mm ofa HSTT as the objective, the effects of numerical parameters on prediction accuracy and computation efficiency of springback simulation of HSTT RDB are investigated. The simulated springback results are compared with experimental ones. The main results are: (1) solid and continuum-shell elements predict the experimental results well; (2) for C3DSR elements, NEL of at least 3 is required to obtain reliable results and a relative error of 29% can occur as NEL is varied in the range of 1-3; (3) specifying damping factor typically works well in Abaqus/Emplicit simulation of springback and the springback results are sensitive to the magnitude of damping factor. In addition, the explanations of the effect rules are given and a guideline is added. 相似文献