激光推力器材料耐热性能的数值分析

推力器是激光推进的重要部件,推力器材料的选择需要充分考虑其承受强激光辐射后的耐热性能,避免被熔化破坏。基于激光辐照一维加热熔化模型,提出了高精度和快速的温度场计算方法,研究了强激光辐照推力器材料时的熔化时间,材料表面及内部温度场分布,进一步提出了材料优选的原则:低激光吸收率、高热传导率。以部分典型材料为实例,对耐热性能进行了对比分析,并给出了较好的推力器材料。     

激光成像系统实验研究

为解决激光脚点（laser footprint）在光学图像中的定位问题,建立分析模型,构建了集成激光测距机和CCD摄像机的实验室激光成像系统;通过实验,对采集的数据进行了图像配准和融合,反演出被测目标三维图像,包含了被测目标高程与灰度信息。     

ICAN: A novel laser architecture for space debris removal

The development of a fiber based laser architecture will enable novel applications in environments which have hitherto been impossible due to size, efficiency and power of traditional systems. Such a new architecture has been developed by the International Coherent Amplification Network (ICAN) project. Here we present an analysis of utilizing an ICAN laser for the purpose of tracking and de-orbiting hyper-velocity space debris. With an increasing number of new debris from collisions of active, derelict and new payloads in orbit, there is a growing danger of runaway debris impacts. Due to its compactness and efficiency, it is shown that space-based operation would be possible. For different design parameters such as fiber array size, it is shown that the kHz repetition rate and kW average power of ICAN would be sufficient to de-orbit small 1–10 cm debris within a single instance via laser ablation.     

Hot deformation behavior and microstructure evolution of the laser solid formed TC4 titanium alloy

Hot compressive experiments of the laser solid formed (LSFed) TC4 titanium alloy were conducted at a wide temperature range of 650–950 °C and strain rate of 0.01–10 s⁻¹. The Arrhenius-type constitutive models of the LSFed TC4 alloy were established at the temperature range of 800–950 °C and of 650–800 °C, respectively. The average relative error between the predicted stresses and experimental values in those two temperature ranges are 10.4% and 8.3%, respectively, indicating that the prediction models constructed in this paper are in a good agreement with experimental data. Processing maps were established by the principle of dynamic materials modeling on the basis of the data achieved from the hot compression experiments. The processing parameters corresponding to the stable and unstable regions of material deformation can be determined from the processing maps. The microstructure evolution of the stable and unstable regions of the samples after tests were observed. Finally, the effect of hot compressive parameters on the microstructure were investigated to research the dynamic recrystallization and the texture of the deformed LSFed TC4 alloy.     

不完全角度CT图像重建的模型与算法

为了提升不完全角度计算机断层成像(CT)图像的重建精度和重建效率,研究了有限角度和稀疏角度下的CT图像重建问题,提出新的全变差最小化目标函数,通过将上一步迭代重建的图像作为反馈加入到新的迭代之中,不断更新目标函数的已知项。在算法求解时,采用增广Lagrangian罚函数方法,将约束问题非约束化,并将之转化为等价的3个子问题,通过在交替方向上求解子问题来获得优化问题的最优解。实验结果表明,该算法重建出的图像信息完整,细节清晰,重建精度高,与Split Bregman算法相比,本文算法结果的相对均方误差可下降42.1%~98.5%,条纹指标可下降42.8%~98.5%。     

工业总线标准电容层析成像系统设计

为保证电容层析成像(ECT)系统满足航空航天领域多相流参数测试的要求,开发了一套基于CPCI工业总线标准的ECT系统。采用高性能现场可编程门阵列(FPGA)芯片作为主控芯片,实现信号激励模块、多路复用开关模块、数据处理模块、数据解调和传输模块的集成式设计,将采集信号进行预处理,实现信号的滤波、放大和相敏解调,并通过CPCI工业总线接口把解调后的电容数据传送至系统上位机,完成图像重建。实验测试结果表明:系统采用1 MHz激励信号和8电极传感器的工作模式下,采用10周期的测试信号解调时,图像采集速度可达1 785幅/s,信号的信噪比高于60 d B,成像结果具有良好的空间分辨率。     

基于激光测距的飞艇净重在线计算方法研究

通过对三维建模软件CATIA中的飞艇副气囊模型进行切片分割,获得了不同副气囊高度下的对应体积值,使用最小二乘法建立了副气囊中心点高度与副气囊体积的三次曲线拟合公式,采用相位式激光测距仪对副气囊中心高度测量,使用该公式可以估算出副气囊的实时体积大小,从而推算飞艇净重大小,掌握飞艇的压力高度和起降能力。使用某次飞行试验对副气囊高度测量的数据计算出的飞艇净重值,与多次地面称重数据一致性较好,验证了使用激光测距仪对大型飞艇净重进行在线评估的可行性,并使用该方法对某飞艇某次飞行试验过程中的净重进行了分析,对飞艇的压力高度进行了核算。     

Laser joining of CFRTP to titanium alloy via laser surface texturing

Grid pattern was textured on Ti-6Al-4V alloy (TC4) substrate surface by nanosecond laser system. Laser joining of carbon fiber reinforced thermoplastic composite (CFRTP) to TC4 joints were performed, and the effect of texture grid depth was investigated. The contact angle of molten CFRTP on textured TC4 surface was measured and the tensile-shear force was tested. The fracture surface and interface morphology were observed. The results indicated that the wettability of molten CFRTP on TC4 surface improved remarkably after laser textured TC4. Shear force of CFRTP/TC4 joints was increased by 156% after laser textured TC4 surface. When the depth of grid was deeper than 100 μm, contact angle increased and incomplete filling of molten CFRTP in grid occurred, the shear force thus decreased gradually. Resin-carbon fibers mixture was adhered on the fracture surface of TC4, and the variation tendency of adhesion ratio was consistent with that of shear force. TC4 matrix was exfoliated from substrate and adhered at the fracture surface of CFRTP, indicating stronger mechanical interlocking occurred at the joining interface after laser textured TC4 surface. Beside mechanical interlocking, compound layer consisted of CTi_0.42V_1.58 carburization phase was also confirmed at interface, suggesting that chemical bonding also occurred at the joining interface.     

Brazing diamond grits onto AA7075 aluminium alloy substrate with Ag–Cu–Ti filler alloy by laser heating

The brazing of diamond is a promising way to fabricate grinding wheels for efficient machining and precision grinding. This work investigated the feasibility of bonding diamond grits onto Aluminium Alloy 7075 (AA7075) substrate with a Ag–Cu–Ti filler alloy via laser fusion brazing. The interfacial microstructures and the strength of the brazed diamond joints were studied. The cross-section of the brazed diamond joint consists of a molten filler alloy layer, a molten pool, a heat effect zone, a columnar crystal zone and an equiaxed crystal zone. Within the interface of the filler alloy/substrate metal, microstructures observed possibly were Ag(s.s), Al(s.s), TixAl, Al2Cu and Mg intermetallic compounds. A layer of TiC with a thickness of about 30–50 nm was found at the bonding interface of the diamond/filler alloy. The averaged peak shear force of the brazed joints was found to be approximately 39.8 N. The abrasion grinding test indicated that the diamond/AA7075 brazed joint was adequate for grinding. However, the pulled-off of grit was found to be the primary failure of this type of brazed joint. This work broadened the brazing diamond technique and the range of applications of brazed diamond wheels for efficient grinding.     

Spin axis orientation of Ajisai determined from Graz 2 kHz SLR data

The Graz 2 kHz Satellite Laser Ranging (SLR) measurements allow determination of the spin axis orientation of the geodetic satellite Ajisai. The high repetition rate of the laser makes it possible to determine the epoch time when the laser is pointing directly between two corner cube reflector (CCR) rings of the satellite. Identification of many such events during a few (up to 3) consecutive passes allows to state the satellite orientation in the celestial coordinate system. Six years of 2 kHz SLR data (October 2003–October 2009) delivered 331 orientation values which clearly show precession of the axis along a cone centered at 14^h56^m2.8^s in right ascension and 88.512° in declination (J2000.0 celestial reference frame) and with an half-aperture angle θ of 1.405°. The spin axis precesses with a period of 117 days, which is equal to the period of the right ascension of the ascending node of Ajisai’s orbit. We present a model of the axis precession which allows prediction of the satellite orientation – necessary for the envisaged laser time transfer via Ajisai mirrors.