航天器部件真空检漏试验管理系统的设计

航天器部件真空检漏试验管理系统是航天器件特殊环境试验管理系统的一个重要组成部分。文章根据航天器部件真空检漏试验管理的需求,结合软件设计开发流程规范,对试验技术流程进行了分析,设计出系统总体框架和功能模块:系统总体框架分为数据资源层、业务逻辑层和客户层;功能模块分为试验任务管理模块、个人任务管理模块、试验数据管理模块、试验归档管理模块、试验资源管理模块、基础配置管理模块和系统管理模块。该试验管理系统将使航天器部件真空检漏试验管理工作更加高效、合理。     

Buoyancy effects on smoldering combustion

A theoretical and experimental study is carried out to determine the effect of buoyancy on the rate of spread of a cocurrent smolder reaction through a porous combustible material. Since buoyant forces are proportional to the product g(_gi − _g), they can be controlled experimentally by varying either the gravitational acceleration, g, or the density difference, _gi − _g. The latter approach was followed in the present work. Measurements are performed of the smolder spread rate through porous α-cellulose (0.83 void fraction) as a function of the ambient air pressure. The experiments are carried out in a pressure vessel for ambient pressures ranging from 0.5 to 1.2 atm. The rate of spread was obtained from the temperature histories of thermocouples placed at fixed intervals along the fuel centerline. The smolder velocity was found to increase as the ambient pressure was increased. Extinction was found to occur when the buoyancy forces could not overcome the drag forces, indicating that at least for the present experimental conditions transport by diffusion cannot, by itself, support the spread of a smolder reaction. This conclusion is particularly important for outer space conditions where gravity and consequently buoyancy could be negligible. In the analysis, which assumes one-dimensional processes, the transport equations are solved to give the smolder spread rate as a function of the inlet oxygen mass flux. This mass flux is then estimated by balancing buoyancy and drag forces. Assuming that the smolder chemical reaction is only weakly dependent on pressure, the analysis finally predicts a smolder velocity dependence of the form v Y_oig²_gi Pa², i.e. is proportional to the ambient pressure squared. Good qualitative agreement is found between the theoretical predictions and the experimental results.     

弹道式飞行器再入高度惯性控制方案

弹道式飞行器再入时，常常要求在规定高度上发出开伞信号，目前用的过载延时控制方法误差太大。本文以飞行器轴向视速度及其积分为控制信号，用共扼方程法设计了一种惯性高度控制方案。计算结果表明，该方案的控制误差小于１００ｍ。     

The ASTROD I charging simulation and disturbances due to solar energetic particles at 0.5 AU

The electrostatic charging of ASTROD I test mass (the Astrodynamical Space Test of Relativity using Optical Devices I) will disturb its pure geodesic motion due to spurious Coulomb and Lorentz forces. The three main disturbances associated with the charging are the acceleration noise of the test mass, the coupling between the test mass and the spacecraft, the appearance of unwanted coherent Fourier components in the measurement bandwidth. By implementing the same geometry and physics models in our previous work, a positive charging rate of 9369 e⁺/s for the solar energetic particles (SEPs) event on October 19th 1989 is predicted. Based on these charging rates, we calculated the acceleration noise and stiffness associated with charging. We also compared the acceleration noises arising from Coulomb and Lorentz effects using different discharge characteristics. Although the noise due to charging exceeds the ASTROD I budget for the two events at 0.5 AU, it can be suppressed through continuous discharging. In addition to Monte Carlo uncertainty, an error of ±30% in the net charging rates was added to account for uncertainties in the primaries spectra, physics and geometry models.     

Design and testing of a roto-translational shutter mechanism for planetary operation

This work describes the design and testing of a shutter mechanism for a miniaturized infrared spectrometer developed for the ESA ExoMars Pasteur mission. Unlike most usual cover mechanisms, the conceived one provides a roto-translational motion. This feature allows the sealing of the interferometer main entrance window from dust contamination, in addition to the usual function of shuttering the instrument field of view. Although this characteristic is strongly desired because it avoids dust deposition and optics contamination while the instrument is not operating, it makes the mechanism design significantly more complex. Moreover, challenging design constraints were faced: the mass budget allowed for no more than 30 g allocation, the expected working thermal range extended down to −80 °C and high vibration levels with an acceleration peak of 670 m/s² were predicted during Mars landing. To complete the picture, the mechanism cover was required to provide also a calibration target for the 2–25 μm spectral range of the spectrometer. The resulting system is made by a calibrating/shutter cover moved by a purposely designed out of plane cams system which provides the desired motion. A mechanism mockup was assembled and successfully tested in the predicted thermal and mechanical environments.     

加速度-气动力综合试验系统研制

加速度-气动力综合试验系统主要用来考核飞行器结构强度和内装物的环境适应性。LJ-1离心机半径10.8 m,适合开展大尺寸、危险品加速度试验,但是其吊篮只能固定在水平或竖直方向上,也不具有与加速度协调施加气动外压的控制系统。文章采用新颖的胀套锁紧结构,实现了吊篮在任意角度固定,并且抗翻转力矩达到13000N·m。气动力控制电路和气路安装在离心机上,上位机将转速通过光纤以太网发送给离心机上的PLC,PLC根据加速度控制气囊压力。试验验证LJ-1离心机具有对试件施加加速度载荷和气动力的综合试验能力。     

真空出气对星用聚酰亚胺材料电导率的影响

卫星介质材料在真空环境下的出气有可能对材料本身的介电性能产生显著影响,增加长期服役卫星寿命末期的充放电风险。文章以卫星上常用的聚酰亚胺材料为对象,通过地面90Sr-90Y辐照源加速辐照试验研究了在材料真空出气后其表面充电平衡负电位的变化,并据此计算出材料电导率的变化规律。结果显示,在5 pA/cm2电子辐照强度下,聚酰亚胺样品的电导率随着出气量的增加而明显下降,在总质量损失达到0.5%时,电导率减小一半左右。初步分析了出气导致电导率下降的物理机制。研究结果对卫星寿命末期充放电防护设计有指导意义。     

Exobiology, SETI, von Neumann and geometric phase control

The central difficulties confronting us at present in exobiology are the problems of the physical forces which sustain three-dimensional organisms, i.e., how one dimensional systems with only nearest interaction and two dimensional ones with its regular vibrations results in an integrated three-dimensional functionality. For example, a human lung has a dimensionality of 2.9 and thus should be measured in m2.9. According to thermodynamics, the first life-like system should have a small number of degrees of freedom, so how can evolution, via cycles of matter, lead to intelligence and theoretical knowledge? Or, more generally, what mechanisms constrain and drive this evolution? We are now on the brink of reaching an understanding below the photon level, into the domain where quantum events implode to the geometric phase which maintains the history of a quantum object. Even if this would exclude point to point communication, it could make it possible to manipulate the molecular level from below, in the physical scale, and result in a new era of geometricised engineering. As such, it would have a significant impact on space exploration and exobiology.     

真空室压升法测量液态工质漏率可行性分析

文章旨在探讨压升法测量液态工质漏率的可行性,研究液体泄漏的试验方法。首先根据液体饱和蒸气压的理论分析,得出液体挥发引起的定容压力增量;之后通过微进样系统,采用真空室静态升压方法,分别以全氟三乙胺和乙二醇水溶液为研究对象进行试验分析,研究得出漏入液体量V与压力变化ΔP成线性关系,与理论分析计算结果相符合,证明了压升法测液态工质漏率的可行性;最后提出了微量采样系统进行比对测量液态工质漏率的压升试验方法及计算公式。研究结果表明,压升法可有效地测量液态工质漏率,为液体的流动试验研究提供参考依据。     

Modeling the benefits of an artificial gravity countermeasure coupled with exercise and vibration

The current, system-specific countermeasures to space deconditioning have limited success with the musculoskeletal system in long duration missions. Artificial gravity (AG) that is produced by short radius centrifugation has been hypothesized as an effective countermeasure because it reintroduces an acceleration field in space; however, AG alone might not be enough stimuli to preserve the musculoskeletal system. A novel combination of AG coupled with one-legged squats on a vibrating platform may preserve muscle and bone in the lower limbs to a greater extent than the current exercise paradigm. The benefits of the proposed countermeasure have been analyzed through the development of a simulation platform. Ground reaction force data and motion data were collected using a motion capture system while performing one-legged and two-legged squats in 1-G. The motion was modeled in OpenSim, an open-source software, and inverse dynamics were applied in order to determine the muscle and reaction forces of lower limb joints. Vibration stimulus was modeled by adding a 20 Hz sinusoidal force of 0.5 body weight to the force plate data. From the numerical model in a 1-G acceleration field, muscle forces for quadriceps femoris, plantar flexors and glutei increased substantially for one-legged squats with vibration compared to one- or two-legged squats without vibration. Additionally, joint reaction forces for one-legged squats with vibration also increased significantly compared to two-legged squats with or without vibration. Higher muscle forces and joint reaction forces might help to stimulate muscle activation and bone modeling and thus might reduce musculoskeletal deconditioning. These results indicate that the proposed countermeasure might surpass the performance of the current space countermeasures and should be further studied as a method of mitigating musculoskeletal deconditioning.     

飞船返回舱高超声速气动特性的风洞实验分析

在返回舱再入过程中,高超声速配平升阻比是一个十分重要的参数。文章介绍球冠倒锥外形返回舱模型在φ0．5m高超声速风洞中气动力的测量结果,给出Ma=4．94、5．96、7．96,相应的Re=3×10^6、6×10^6、2×10^6（以最大横截面直径为特征长度）气流条件下,攻角从2°～-27°变化范围内返回舱的气动力特性,讨论重心位置纵移与横偏变化对配平升阻比和纵向稳定性的影响。     

前庭功能试验加速度环境模拟技术

文章介绍了用于航天员前庭功能测试的多功能转椅和四柱电动秋千。前者采用液压控制,可产生不同位置下水平旋转的角加速度,利用20对引电环记录生理测试信号；后者通过内外框架和吊篮舱的自然摆动进行线加速度测试,摆杆长度以0．5m为档差,分为3．5m、4m、4．5m、5m、5．5m、6m六档可调。     

采用超声波电机的空间飞网自适应收口机构设计

介绍了一种采用超声波电机作为驱动源的空间飞网自适应收口机构（质量块）的设计及实现方法。通过分析捕获过程中质量块运动情况,研究超声波电机电流与负载的关系,确定以加速度信号和电流信号作为电机启动和停止的触发信号,在此基础上设计并实现了质量块的驱动控制系统。通过在电机输出轴与卷筒间加入差动轮系构成双卷筒机构,力学分析证实了该机构在负载不均衡情况下的自适应性。分析证明该机构使飞网的捕获操作对捕获平台的精度要求降低,有容错能力。同时使收口机构在部分质量块故障时也能完成捕获任务。     

Exploitation of new materials processing in a mega-gravity field

A strong acceleration field (mega-gravity) can cause the sedimentation of even atoms and is expected to create an unique one-dimensional crystal strain state, i.e. an instability in molecular or crystalline state in multi-component condensed matter. However, materials science research under the mega-gravity field has now remained unexploited, while microgravity has been much used in many fields. We developed a self-consistent theory for sedimentation of atoms in condensed matter, and an ultracentrifuge apparatus to generate an acceleration of over 1 million (1×10⁶)g at high temperature. Recently, we for the first time formed an atomic-scale-graded structure by the sedimentation of atoms, and observed crystal growth in an alloy under a mega-gravity field. It is expected that the availability of mega-gravity may offer us new and powerful options in materials processing in terms of controlling compositions even of isotopes, of forming atomic-scale-graded structure or nonstoichiometric structure, and of controlling the ordering of atoms or molecules.     

基于分频段加权的加速振动试验方法

振动环境工程研究现行采用的加速试验方法中,都只考虑了加速因子与频率无关这种情形,这不仅提高了试验设备的推力要求,也增加了位移指标要求。文章提出了一种分频段加权的加速振动试验方法,即通过对低频段加速因子的权重的优化设计,实现较小的位移指标要求,且疲劳损伤累积等效。给出了基于Dirlik方法和TB方法疲劳损伤等效的加速试验设计方法和工程实现流程。针对该方法开展了应用实例的计算,结果表明:在疲劳损伤等效的前提下,显著降低了振动台的位移,且推力基本维持不变。     

Design and on-orbit performance of the attitude determination and control system for the ZDPS-1A pico-satellite

The ZDPS-1A pico-satellite, developed by the Zhejiang University, is featured with a three-axis stabilizing capability. It is 15×15×15 cm³ cube-shaped satellite with a total mass of 3.5 kg. ZDPS-1A is the first pico-satellite that has been launched successfully in China. The mission of ZDPS-1A is on-orbit system verification of student-build pico-satellite and wide range earth observation with a micro panoramic camera. A miniature momentum wheel is employed to offer gyro stiffness stability in the pitch (orbit normal) axis. Magnetic coils are employed to generate control torques to achieve the three-axis stabilization of nadir-pointing. The attitude sensors employed in the design include two three-axis magnetometers (TAMs), a three-axis gyro, and two sun sensors. Both ground simulations and on-orbit testing are conducted to verify the feasibility of the given attitude determination and control system (ADCS).     

滚控发动机燃气引流方案研究

依据某型滚控发动机实际结构,设计了3种燃气引流方案,方案1采用喷管与引射直筒留有间隙的布局形式,方案2采用喷管嵌入引射筒、引射筒后部接弯管的布局形式,方案3采用喷管直接排入引射筒的布局形式.采用商业软件对3种方案的引流效果进行了数值仿真,仿真结果表明方案1结构简单、易于实施,能够满足燃气顺利排放条件;方案2能够满足燃气引流,但会产生较大轴向力;方案3也可满足燃气引流,但引射筒与喷管间隙较难控制;综合分析得到方案1适合该滚控发动机燃气引流.     

小型热真空试验设备网络化集群测控技术

随着航天器部组件试验任务的日益增多,在人员少的情况下,高效率地完成型号任务的需求十分迫切。文章介绍了小型热真空试验设备网络化集群测控的方法与技术,以某小型热真空试验设备群为例,针对其接口复杂、数据量大、地理位置分散且要求集中管理的特点,详细阐述了采用混合B/S模式与C/S模式的网络化测控技术来实现小型热真空试验设备群集群测控的功能。该技术已在小型热真空试验设备的集群控制中得到了成功的应用。     

精密离心机误差对石英加速度计误差标定精度分析

分析了离心机各个误差源,用齐次变换法精确地计算了产生的向心加速度,给出了向心加速度、重力加速度和哥氏加速度在加速度计坐标系下的分量,推导了被试加速度计输入加速度的精确表达式。在给出石英摆式加速度计在精密离心机上标定时的误差模型的基础上,着重讨论了误差模型系数的计算值与离心机误差之间的关系。根据仿真结果找出了某些离心机误差对加速度计误差系数标定的影响关系,为按照加速度计的标定精度来确定离心机的精度打下了理论基础。     

R-PP改性沥青侧缠绕管道防腐作业线的研制与应用

本文着重介绍R-PP改性沥青侧缠绕管道防腐作业线的工作原理及研制过程。通过防腐实验，对作业线存在的若干技术问题进行了改进和调整，为作业线应用于管道防腐提供了必要的技术依据。