Experimental study on rotary ultrasonic vibration assisted drilling rock

Traditional rotary ultrasonic vibration drilling rock (f_z < 2A) is an effective drilling rock method, but its feed rate is limited by the ultrasonic vibration amplitude, resulting in lower drilling efficiency. In this paper, based on the requirements of drilling efficiency in the asteroid sampling mission, the process method of rotary ultrasonic vibration assisted drilling rock (f_z > 2A) was proposed. The mechanism of ultrasonic vibration assisted drilling rock was analyzed, and the propagation of ultrasonic energy in the process of ultrasonic vibration assisted drilling rock was analyzed. Using the small diameter cemented carbide triangular bit as the drilling tool, the comparative test of ultrasonic vibration assisted drilling and traditional drilling of sandstone, marble, and basalt was carried out. The experimental results showed that there was a specific feed rate range for each type of rock, so that the weight on bit required for ultrasonic vibration assisted drilling was less than that of traditional drilling. With the increase of firmness coefficient of sandstone, marble, and basalt, the ratio of weight on bit to feed rate was increased, and the effective feed rate range of ultrasonic vibration assisted drilling was reduced. The ultrasonic vibration assisted drilling rock (f_z > 2A) was one of the alternative methods for drilling rock on the asteroid surface.     

Fuel-optimal and Energy-optimal guidance schemes for lunar soft landing at a desired location

Two guidance schemes (i) fuel-optimal (ii) energy-optimal to realize soft landing at a desired location on the moon are developed using the optimal control laws. The optimal control laws are obtained by solving a two-point boundary value problem formulated based on Pontryagin’s principle. The guidance laws, adapted from the optimal control laws, are obtained as a function of unknown co-state variables. Differential Transformation (DT) technique is employed to determine the unknown co-states at each time instant of landing trajectory using the information on the current vehicle state, target landing site (loaded on-board apriori) and the time-to-go. The numerical integration of co-state dynamics is avoided due to the DT based approach. The time-to-go, a critical parameter for any guidance scheme, is computed and updated real time using a simple strategy which uses the current and end states. The simple strategy for time-to-go works well even when the shape of the trajectory is nonlinear. Extensive analysis is carried out to evaluate and compare the proposed guidance schemes. Further, the proposed schemes are compared with other popular guidance schemes. The DT based proposed schemes help quantify the landing masses for fuel-optimal and energy-optimal objectives. Other features of the proposed schemes are that they do not assume constant gravity field and independent of reference trajectory.     

Impacts of the PAH size and the radiation intensity on the IR features of illuminated dust within the reflection nebulae

Interstellar dust grains are illuminated in the reflection nebulae. Under conditions of the PAH size and the intensity of the interstellar radiation field, we follow their impact on the PAH aromatic infrared bands using the numerical DustEM code. For a dust model consisting of PAH, amorphous C and amorphous silicate, the PAH size varies in a range from 0.31 to 4.9 nm while the radiation intensity varies by a scale factor from 0.1 to 10⁴. Various trends of the results show the effect of varying both the PAH size and the radiation intensity on the strength of the aromatic mid-IR bands. Through small PAH sizes less than 0.7 nm, the grain temperature distribution of PAHs shows a small variation within 2–3 K at low radiation intensity while it increases to 15 and 8 K for PAH⁰ and PAH⁺, respectively, at higher radiation intensity. In final the variability in these results reveals the evolution of the dust grains under the physical space conditions of the reflection nebulae. In the mid-IR region, the contributions of PAH⁰ and PAH⁺ in the total SED intensity agree with the proportions of these PAHs observed in some reflection nebulae having higher radiation intensities.     

氧气/煤油发动机燃气热物理参数及输运系数计算

为了给氧气/煤油发动机设计和热防护设计提供必要的设计参数,针对氧气/煤油燃气进行热力学计算。运用吉布斯最小自由焓计算模型得到燃气平衡组成,通过拟合公式的方法得到燃气的热物理参数及输运系数。通过计算,得到氧气/煤油燃气的组分及比焓、密度、比熵、粘性系数等热物理参数和输运系数随温度和压力的变化特性。分析结果表明:水离解对氧气/煤油燃气组分变化存在显著影响,压力增大会导致水离解起始温度升高;氧气/煤油燃气比焓、比熵、定压比热、粘性系数、热传导系数变化在温度较低时受压力影响较小,当水开始离解后,压力的影响显著增强;组分在燃气中的扩散系数同时受到了温度和组分摩尔分数的影响;燃气普朗特数变化受热传导系数变化的影响较大,水离解后,热传导系数的迅速增大使燃气的普朗特数迅速减小。     

自然形高空气球上升过程形状预测

为研究高空气球在上升过程中的形状变化以及蒙皮应力分布情况，并给气球的结构设计以及强度设计提供一定依据，本文建立了气球上升过程中的热力学模型，同时基于高空气球蒙皮材料具有非线性、黏弹性、各向异性和不能抗压等特点，通过简化气球几何模型，采用最小势能法预测自然形高空气球上升过程中的形状，并分析了气球上升过程中的应力分布情况，气球的应力极值出现在气球顶部和底部，而经向应力的数量级远大于纬向应力；还对比了不同充气量下、不同时刻下气球形状及应力分布情况，为气球设计及工程应用提供了有效计算 方法。     

大飞机货舱地板下部结构有限元建模与适坠性分析

为了研究大飞机坠撞特性及数值分析方法，选取大飞机货舱地板下部结构为研究对象，建立其有限元模型，实现显式动力学的求解与分析。考察倒置、固支的货舱地板下部结构在200 kg落重以7 m/s垂直冲击下的结构响应、吸能与失效的动态行为，识别落重冲击过程中结构变形与失效模式、冲击响应特性及能量吸收与耗散机理。仿真结果表明，货舱地板下部结构的机身框组件、支撑件组件是主要吸能结构，冲击能量的吸收主要依靠上述结构的塑性变形与失效，紧固件的吸能贡献仅占1%左右。     

Depth dependency of neutron density produced by cosmic rays in the lunar subsurface

Depth dependency of neutrons produced by cosmic rays (CRs) in the lunar subsurface was estimated using the three-dimensional Monte Carlo particle and heavy ion transport simulation code, PHITS, incorporating the latest high energy nuclear data, JENDL/HE-2007. The PHITS simulations of equilibrium neutron density profiles in the lunar subsurface were compared with the measurement by Apollo 17 Lunar Neutron Probe Experiment (LNPE). Our calculations reproduced the LNPE data except for the 350–400 mg/cm² region under the improved condition using the CR spectra model based on the latest observations, well-tested nuclear interaction models with systematic cross section data, and JENDL/HE-2007.     

任意多面体网格上的欧拉方程数值算法

发展并验证了一种新的支持多面体网格的欧拉方程离散算法,采用Fortran 95编写了支持任意网格拓扑及三维复杂外形的通用求解器.在空间离散上,基于径向基函数理论提出了一种新的梯度计算方法,并采用动能通量分裂格式来得到准确并且稳定的二阶精度重构.该方法不依赖于网格几何形状,因此对网格质量不敏感.由于在时间方向采用了点隐松...     

平面磨削石英陶瓷比磨削能正交试验研究

通过大量的正交试验,研究陶瓷材料在低速下的磨削性能,优化陶瓷磨削参数,对于丰富陶瓷磨削理论,指导实际生产实践具有重要的现实意义.     

基于能量法的舰载机拦阻着舰动力学分析及建模仿真

针对舰载机拦阻着舰过程,采用能量法分析了任意着舰姿态和位置下的拦阻力响应,建立了全机六自由度动力学模型,考虑了航母甲板风的影响以及航母纵摇和升沉运动。通过MATLAB／SIMULINK建立数学模型,并以一种偏心非垂直着舰拦阻状态为算例进行了仿真分析。