Characteristics of pulse detonation engine versus ramjet characteristics

We discuss the method of comparing pulse detonation engines (PDE) and engines with combustion in subsonic flow (ramjet) by means of their specific impulse used by the “Center of Pulse-Detonation Combustion” (CPDC). We demonstrate that the method used by CPDC to calculate the performance of PDE overstates the value of specific impulse relative to its actual value by a factor of at least two. In contrast, the values of specific impulse for ramjet are understated. As a result, the specific impulse of PDE significantly exceeds that of ramjet or is close to it. We investigate these misleading conclusions, and demonstrate their complete failure.     

Exergy analysis of ramjet

An exergy analysis of possible regimes of energy supply to the air flow in the ramjet duct is carried out. A condition for the supply of a given heat amount to supersonic flow and a condition of the passage across the sound velocity are obtained for a duct with variable cross-sectional area. An analysis of the flow in a model ramjet duct at a pulsed-periodic energy supply is carried out. For a clear demonstration of possible schemes of heat supply in such a duct, a diagram in the temperature-exergy coordinates is proposed. A duct configuration in which the heat supply to supersonic flow is realized with regard for the limitation of the gas static temperature is proposed.     

Exergy method for estimating the ramjet specific impulse

The exergy method is developed for computing the ramjet thrust-economic characteristics with regard for real thermodynamic properties of combustion products when using as fuel the hydrogen and hydrocarbon fuel for the freestream Mach numbers M = 4 ÷ 14. The estimates for the specific impulse of the given engine using the presented technique are shown to agree with the estimates computed by other authors. The computational method is intended for obtaining the ramjet characteristics and conduction of the parameter analysis at the research initial stage as well as for its use at the conceptual developments of hypersonic flying vehicles.     

Testing of solid fuel ramjet with measurement of thrust characteristics in aerodynamic facilities

A design of an axisymmetric solid fuel ramjet consisting of a multi wedges nose air intake, solid fuel gas gene-rator, combustion chamber, and a nozzle, was developed. According to this design, a ramjet model for tests in the ground wind-tunnel facilities was fabricated. Experiments with solid fuel combustion were carried out in the Transit-M and T-313 wind tunnels, ITAM SB RAS, at air-flow Mach numbers М = 2.5?5.0. High values of the internal and net excess thrust were obtained.     

Investigations of three-dimensional flow characteristics in a liquid ramjet combustor using the PIV method

Three-dimensional flow characteristics in a liquid fuel ramjet combustor were investigated using the PIV method. The combustor had two rectangular inlets that form a 90-degree angle with each other, with intake angles of 30 degrees. Three guide vanes were installed in each rectangular inlet to improve flow stability. The experiments were performed in a water tunnel test with the same Reynolds number as Mach 0.3 at the inlet. PIV software was developed to measure the characteristics of the flow field in the combustor. Accuracy of the developed PIV program was verified with a rotating disk experiment and standard data. The experimental results showed that the two main streams from the rectangular intakes collided near the plane of symmetry and generated two large longitudinal vortices, which was in agreement with three dimensional computational results. A large and complex threedimensional recirculating flow was measured behind the intakes.     

Investigation of the efficiency of regenerative cooling of the ramjet combustor by gasification products of energy-intensive material

The results of mathematical modeling of the thermal state of combustion chambers with regenerative cooling for ramjet engines of promising flying vehicles are presented. The cooling of combustion chambers by the gasification products of a combined charge of the energy-intensive material is considered, where the polyethylene is used as a stuff, and the HMX-based compounds are used as the active substance. The flow rates of the cooling eneregy-intensive material are determined, which provide acceptable levels of temperatures of combustion chambers at various modes of engines operation are determined.     

Three-dimensional numerical simulation of the characteristics of a ramjet power plant with a continuous-detonation combustor in supersonic flight

Multi-variant three-dimensional numerical simulations demonstrate the feasibility of the continuous- detonation process in an annular combustor of a ramjet power plant operating on hydrogen as fuel and air as oxidant in conditions of flight at a Mach number of M ₀ = 5.0 and an altitude of 20 km. Conceptual schemes of an axisymmetric power plant, 400 mm in external diameter and 1.3 to 1.5 m in length, with a supersonic intake, divergent annular combustor, and outlet nozzle with a frusto-conical central body are proposed. Calculations of the characteristics of the internal and external flows, with consideration given to the finite rate of turbulent-molecular mixing of the fuel mixture components with each other and with the combustion products, as well as the finite rate of chemical reactions and the viscous interaction of the flow with the bounding surfaces, have shown that, in these flight conditions, the engine of such a power plant has the following performance characteristics: the thrust, 10.7 kN; specific thrust, 0.89 (kN s)/kg; specific impulse, 1210 s; and specific fuel?consumption 0.303 kg/(N h). In this case, the combustor can operate with one detonation wave traveling in the annular channel at an average velocity of 1695 m/s, which corresponds to a detonation wave rotation frequency of 1350 Hz. It is shown that, an operating combustor has regions with subsonic flow of detonation products, but the flow is supersonic throughout its outlet section.     

Influence of resonators on the acoustic and propulsion performance characteristics of a ramjet ejector chamber under conditions with vibration hydrogen combustion

The influence of acoustic resonators on the acoustic and propulsion performance characteristics of a ramjet ejector chamber under conditions with vibration hydrogen combustion was experimentally examined. In the study, resonators having identical throats and different cavity diameters were used. For fixed-volume resonators the best propulsion performance characteristics were achieved in the case in which the cavity diameter differed little from the resonator throat diameter.     

Characteristics of double-pomeron exchange

A detailed kinematic study is made of the cross section for double-pomeron exchange. We consider reactions of the type a + b → c + d + (h₁ + h₂ + …) where a → c and b → d are quasi-elastic transitions with limited momentum transfer and (h₁ + h₂ + …) is a centrally produced hadron cluster. The dependence of the cross section on the relative azimuthal angle φ between the final hadrons c and d provides an important test for double-pomeron exchange. We calculate this φ-dependence for all cases of interest, using a model in which pomeron exchange is represented by an effective current-current interaction. For limited momentum transfer, where the pomeron spin is nearly equal to one, this model is equivalent to Reggeized pomeron exchange. We give a complete formalism for the partial-wave analysis of the double-pomeron reaction ab → cd + h₁₂ which differs from the one given by Rushbrooke and Webber. Furthermore, we discuss the two-pomeron vertex, and the construction of detailed and realistic models for double-pomeron reactions.     

Characteristics of Exploding-Wire Plasmas

The phenomenon of exploding wire has been investigated in the energy range E < Ee to E > a few Ee, where Ee is the energy density required for complete evaporation of the wire. For E < Ee, macroscopic fragmentation (size ~ tens of micrometers) of wire takes place. As E is increased above Ee, the fragment size tends to atomic dimensions, and for E >> Ee explosive vaporization occurs resulting in high-temperature plasma. The study indicates that during the explosion, plasma is in a nonequilibrium state with temperatures as high as 10 eV or more. This plasma attains equilibrium in tens of nanoseconds. The free-expansion velocity of this plasma is of the order 105-106 cm/s and increases with increasing E. Consequently, the plasma density decreases for E >> Ee. After about 100 ns, the resulting plasma densities are in the region of 1018-1020 cm-3. Such plasmas have significant interest in the development of particle beams, laser, and fast switching systems.     

光纤Bragg光栅水听器探头的特性及实验研究

论述了FBG水听器探头基元——光纤Bragg光栅(FBG)的传感特性,分析了FBG的耦合系数、反射率、反射带宽和栅长对FBG水听器传感特性的影响。通过改进FBG水听器探头封装结构,增加了其压力敏感系数。并将实验结果与标准水听器(压电型)比较,标定出FBG的声压灵敏度,在1～25KHz的声波检测范围,其响应平坦度好、信号输出稳定,改进措施是有效的。     

（LaO）3BO3基质中Tb^3的发光特性

在254nm紫外光（UV）激发下,研究了（LaO)3BO3基质中Tb^3 的激发光谱、发射光谱、发光寿命与Tb^3 浓度的关系,并探讨了Tb^3 的^5D3→^7D3→F4。跃迁发射的自身浓度猝灭机理,在阴极射线（CD）激发下,研究了（LaO)3BO3:Tb^3 的发光强度与Tb^3 浓度、加速电压及电流密度的关系,发现在UV事CR两种激发条件下,试样均能发出明亮的绿色荧光,有望成为一种有发展前途的绿粉。     

含氧化合物的红外光谱特征

总结了含氧化合物的主要红外光谱特征,讨论了其红外特征与结构之间的规律,结果表明,所有含氧化合物,无论是有机物还是无机物,其红外活性都是很大的,表现为强宽的吸收峰,这为判定化合物是否含氧提供了有力的分析检测依据。     

理想波导短程透镜的研究

报道无曲率奇点，无像差光波导短程透镜的研究。在透镜面型设计上，应用前文提出的过渡区母线函数形式，有效地消除了透镜卷边两端的曲率奇点，具体设计和研制了理想光波导短程透镜。     

Characteristics of Bifilar Helix Circuit

The characteristics of two kinds of bifilar helix circuit are discussed in this paper. One is alike wound bifilar helix and another is contrawound bifilar helix. Alike wound bifilar helix is often used in O-type backward wave tube (BWO). Owing to wider operating bandwidth, higher interaction impedance and large dimensions, the contrawound helix is suitable for broadband millimeter wave traveling wave tube (MMW TWT).     

Morphological Characteristics of Composite Films

For the testing of methods for morphological analysis of composite films, a computer experiment was suggested. Two models were prepared to study the possibility of at least partial reconstruction of 3D structures from their 2D projections or sections. The importance of some morphological characteristics for the reconstruction of size and/or spatial distribution of objects is shown in the paper. It illustrates the usage and significance of the integral transform method for the unfolding of the structures, too.     

Internal-Field Characteristics of Spherical Particles

The finely stratified sphere model was used to calculate electromagnetic fields inside homogeneous and radially inhomogeneous spheres which are illuminated by electromagnetic plane waves. A complete picture of the internal fields is given for spheres whose diameters are comparable to the wavelength (α = 1.5 and 5, where α = 2 πa/γs is the size parameter of the sphere) and spheres whose diameters are much larger than the, wavelength (α as high as 150), for coated spheres (spheres composed of a homogeneous core and a homogeneous shell) and gradient-index spheres (spheres with a continuous of refractive index), for spheres at states of morphology-dependent resonances (MDRs) and those at non-resonant states.