宏指令在变螺距螺旋轨迹编程中的应用

以一个现实的零件,表述了宏指令在变螺距螺旋加工中的运用,利用函数的合成,循环语句的运用,细致而详细地描述了程序编制的整个过程。对于复杂空间曲线,若能建立函数的关系,通过宏指令的运用,也能手动编制出简洁的复杂轨迹,且应用面广,程序段直观而清晰,更具可读性。     

多臂空间机器人的视觉伺服与协调控制

针对多臂空间机器人自主目标抓捕任务,首先建立多臂空间机器人的运动模型和其与目标的相对运动模型,采用Kane方法建立多臂空间机器人的动力学模型;其次,研究基于视觉伺服的机械臂在线轨迹规划算法,并引入零反作用机动,消除机械臂运动对平台姿态的扰动;再次,在不使用零反作用机动功能时,分别使用基于角动量前馈补偿的协调控制算法和逆动力学方法设计了协调控制器,在机械臂运动时保持平台姿态和相对目标的位置。最后,开发了基于Matlab的仿真软件MASS（多臂空间机器人仿真）,仿真结果校验了上述方法的有效性。     

熔融沉积成型连续碳纤维增强尼龙蜂窝芯材的压缩特性

采用熔融沉积成型方法成形了连续碳纤维增强尼龙复合材料蜂窝芯材,并对不同测试方向的静态单轴压缩特性进行了表征分析,着重关注不同测试方向熔融沉积成形蜂窝芯材平面静态压缩破碎行为和能量吸收行为,并与纯聚合物基体进行对比。结果表明:X_1方向的压缩平台区域的力-位移曲线更加平滑稳定,且载荷值稍高于X_2方向,因此X_1方向更适用于能量吸收应用;此外,连续纤维的增强作用可使蜂窝芯材的平台载荷值得到明显提升。研究结果为连续纤维增强聚合物复合材料的空间增材制造提供理论基础。     

一种针对局部结构的有限元模型修正方法

针对实际结构有限元模型（FEM）的建模误差通常仅存在于局部区域,提出了一种对局部结构单独进行模型修正的方法。首先,根据频响函数（FRF）解耦理论得到由残余结构频响函数与包含待修正参数的局部结构动刚度所重构的整体结构频响函数的拟合值,然后通过迭代优化使其与测量值的残差最小化,从而得到参数的极大似然估计。在此基础上,将残差关于参数的灵敏度以局部结构动力学矩阵表示,建立了模型修正的基本方程,利用整体结构的测试数据即可直接对分离出来的局部结构进行模型修正。最后,对喷气式飞机和三角机翼飞机分别进行了数值模拟和实验研究,验证了所提方法的可行性和有效性。结果表明,所提方法可以成功地用于仅局部区域含有建模误差的实际结构有限元模型的修正,修正后的有限元模型的动态特性与实际结构有较好的一致性。     

大跨时空任务背景下的太阳能无人机任务规划技术研究进展

通过任务规划技术合理的优化太阳能无人机的飞行轨迹和动力学参数,能够有效提高太阳能无人机的能量利用率,使其胜任许多大范围跨时间跨空间飞行任务。从能量建模、续航评估和能量管理策略3个方面对大跨时空任务背景下太阳能无人机任务规划技术的研究进展进行了综述。在能量建模方面,介绍了当前主流的太阳辐射模型和能量生产基本框架;在续航评估方面,分析了目前的指标设计和应用方法;在能量管理策略方面,从能量综合应用、风力滑翔机制、轨迹优化方法和面向特定任务的应用4个角度,梳理了当前的研究现状。最后,对该领域未来可能的研究方向进行了展望。     

多状态空间信息网络拓扑生成优化算法

依据空间信息网络（SIN）高动态性的特点,并考虑卫星工作的多状态特性,兼顾星间通信时延和拓扑抗毁性的要求,研究了多状态下空间信息网络拓扑生成及动态优化的问题。根据卫星星座的周期性,建立了一种卫星网络的拓扑周期表。综合卫星的可视性和连接度等约束条件,以网络平均和最大时延作为通信性能的优化目标,建立拓扑的多目标优化模型。提出一种改进的多目标模拟退火（IMOSA）算法,求解全局时延最优的卫星拓扑,并在考虑多状态情况下对链路进行优化,以满足网络高动态性。最后基于具有66颗低轨（LEO）的铱星星座进行仿真,研究表明：针对多状态条件下的铱星星座,该算法最大化减小了通信时延,得到抗毁性良好的拓扑结构,通信性能较之原有静态拓扑明显得到改善。     

Shock protection of penetrator-based instrumentation via a sublimation approach

It is often necessary for space-borne instrumentation to cope with substantial levels of shock acceleration both in the initial launch phase, as well as during entry, descent and landing in the case of planetary exploration. Current plans for a new generation of penetrator-based space missions will subject the associated on-board instrumentation to far greater levels of shock, and ways must therefore be found to either ruggedize or else protect any sensitive components during the impact phase. In this paper, we present an innovative method of shock protection that is suited for use in a number of planetary environments, based upon the temporary encapsulation of said components within a waxy solid which may then be sublimated to return the instrument back to its normal operation. We have tested this method experimentally using micromachined silicon suspensions under applied shock loads of up to 15,000g, and found that these were able to survive without incurring damage. Furthermore, quality factor measurements undertaken on these suspensions indicate that their mechanical performance remains unaffected by the encapsulation and subsequent sublimation process.     

Using the radial basis function neural network to predict ionospheric critical frequency of F2 layer over Wuhan

Neural networks (NNs) have been applied to ionospheric predictions recently. This paper uses radial basis function neural network (RBF-NN) to forecast hourly values of the ionospheric F₂ layer critical frequency(f_oF₂), over Wuhan (30.5N, 114.3E), China. The false nearest neighbor method is used to determine the embedding dimension, and the principal component analysis (PCA) is used to reduce noise and dimension. The whole study is based on a sample of about 26,000 observations of f_oF₂ with 1-h time resolution, derived during the period from January 1981 to December 1983. The performance of RBF-NN is estimated by calculating the normalized root-mean-squared (NRMSE) error, and its results show that short-term predictions of f_oF₂ are improved.     

A high-performance ground-based prototype of horn-type sequential vegetable production facility for life support system in space

Vegetable cultivation plays a crucial role in dietary supplements and psychosocial benefits of the crew during manned space flight. Here we developed a ground-based prototype of horn-type sequential vegetable production facility, named Horn-type Producer (HTP), which was capable of simulating the microgravity effect and the continuous cultivation of leaf–vegetables on root modules. The growth chamber of the facility had a volume of 0.12 m³, characterized by a three-stage space expansion with plant growth. The planting surface of 0.154 m² was comprised of six ring-shaped root modules with a fibrous ion-exchange resin substrate. Root modules were fastened to a central porous tube supplying water, and moved forward with plant growth. The total illuminated crop area of 0.567 m² was provided by a combination of red and white light emitting diodes on the internal surfaces. In tests with a 24-h photoperiod, the productivity of the HTP at 0.3 kW for lettuce achieved 254.3 g eatable biomass per week. Long-term operation of the HTP did not alter vegetable nutrition composition to any great extent. Furthermore, the efficiency of the HTP, based on the Q-criterion, was 7 × 10⁻⁴ g² m⁻³ J⁻¹. These results show that the HTP exhibited high productivity, stable quality, and good efficiency in the process of planting lettuce, indicative of an interesting design for space vegetable production.     

空间稳定型捷联惯导系统静态误差分析

定量分析空间稳定型捷联惯导系统的误差传播特性,以便实现惯导系统对战术技术指标及元部件对自身精度指标的设定要求.首先设计了一种用于地球表面导航的船用空间稳定型捷联惯导系统方案,然后通过求解静基座状态下的该种捷联惯导系统误差方程,分析了陀螺常值漂移以及加速度计零偏对空间稳定型捷联惯导系统的影响.理论分析以及实物试验表明陀螺常值漂移会造成经度误差随时间线性增长,其它导航信息按舒勒频率和地球频率等幅振荡传播.