中国空间探测领域40年发展

中国空间科学学会成立的40年，是中国空间探测逐渐走进世界舞台的40年，空间探测极大推动了空间科学和相邻学科的发展，也影响到经济、军事和日常生活诸多方面.本文简要回顾了从空间探测专业委员会成立的1980年至今，中国空间探测领域的主要发展历程，包括探空火箭、高空气球、科学卫星、月球与行星探测、载人航天空间探测、遥感卫星地面站等主要项目、进展和所取得的成果，对未来若干年空间探测的发展进行了展望.      

期望状态序列导向的深空探测器规划修复方法

Aiming at the challenges caused by the persistence, concurrency and energy consumption of probe actions, a plan repair method of deep space probe based on the expected state sequence is proposed. In this method, the expected state sequence is formed of the expected effect of the unfinished action and the expected precondition of the unexecuted action in the pre designed plan, according to the execution status of the action. The expected state sequence is an ordered set of states with mixed logic and energy, providing subgoals for plan repair and also transforming the plan repair problem into the state transition path searching problem. During the search, the plan repair strategy with energy supply priority is proposed, which separates the logic repair from energy repair to reduce the difficulty of solving the problem. And this method enables the probe to recover from plan failure autonomously. Finally, the effectiveness and rationality of the proposed method are verified through simulation by taking the Mars Orbiter as an example.     

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。     

行星着陆大气进入段自适应滑模抗扰控制方法

针对行星探测器着陆过程可能存在的干扰影响着陆精度问题，提出了一种抗干扰控制方法。首先建立行星探测器着陆控制模型，利用非线性干扰观测器实现对系统外部干扰的估计；在此基础上提出一种自适应滑模控制律，使得系统状态快速收敛到平衡点附近。最后，将该方法应用于火星着陆场景进行仿真。结果表明，提出的自适应滑模控制方法能够在未知扰动存在的情况下，有效实现行星探测器安全着陆，提高着陆任务的成功率。     

半球谐振子疲劳寿命分析与仿真

半球谐振子的寿命和损伤是直接影响高精度半球谐振陀螺使用时长和安全性的重要因素。目前国内加工的半球谐振子所用的熔融石英玻璃材料主要依靠进口，采用传统的疲劳寿命实验确定方法成本过于昂贵，因此需要利用疲劳分析软件对半球谐振子的疲劳寿命进行分析。文章通过半球谐振陀螺应力分析，采用ANSYS软件对熔融石英半球谐振子进行应力分析仿真，确定因残余应力所引起的疲劳危险部位，并在疲劳部位进行裂纹扩展分析，得到 、 和 型应力强度因子，以使在半球谐振子结构设计和使用过程中对易疲劳的部位进行有效监控和预防。     

航天器时态规划技术研究进展

结合航天器自主运行的迫切需求,阐述了航天器任务规划问题给智能规划技术带来的挑战,并重点分析了具有时间属性的规划方法研究必要性。给出航天器时态规划定义,分别总结了状态空间时态规划建模方法和基于时间线的时态规划建模方法,并给出时态规划知识模型关键元素定义。根据规划方法发展现状,归纳总结前向链、模型转换、规划空间规划和分层任务网络四种方法在时态规划技术方面的特点和研究进展,着重描述各种方法对规划中时间要素的处理。在对目前的航天器时态规划技术发展趋势总结分析基础上,给出了未来航天器时态规划技术的发展建议。     

Controller development of photo bioreactor for closed-loop regulation of O2 production based on ANN model reference control and computer simulation

When Bioregenerative Life Support System (BLSS) is used for long-term deep space exploration in the future, it is possible to perform closed-loop control on growth of microalgae to effectively regulate O₂ production process in emergencies. However, designing controller of microalgae cultivating device (MCD) by means of traditional methods is very difficult or even impossible due to its highly nonlinearity and large operation scope. In our research, the Artificial Neural Network Model Reference Control (ANN-MRC) method was therefore utilized for model identification and controller design for O₂ production process of a specific MCD prototype—photo bioreactor (PBR), based on actual experiment and computer simulation. The results demonstrated that the ANN-MRC servo controller could robustly and self-adaptively control and regulate the light intensity of PBR to make O₂ concentrations in vent pipe be in line with step reference concentrations with prescribed dynamic response performance.     

Reachable domain of spacecraft with a single tangent impulse considering trajectory safety

The reachable domain of the two-body transfer orbit with a single upper-bounded tangent impulse is studied. Three cases are analyzed for either the magnitude of the tangent impulse or the initial impulse point being free, or both being free. For a fixed impulse magnitude and a free initial impulse point, the initial orbit is proved to be one of the envelopes of the reachable domain. Moreover, the trajectory safety for the transfer orbit requires a lower bound on the perigee altitude and an upper bound on the apogee altitude. Then the ranges of the impulse magnitude and the initial true anomaly can be obtained by solving quadratic and cubic inequalities, respectively. If both constraints are required for an arbitrary impulse point, the range of the impulse magnitude is obtained with impulses at the perigee and the apogee. Several numerical examples with different eccentricities are provided to show the geometry of the reachable domain and to verify the proposed method.     

Optimal guidance for reentry vehicles based on indirect Legendre pseudospectral method

Development of a feasible guidance scheme for reentry vehicles is a challenge because of its significant nonlinearity and multi-constraints. A method for the implementation of three-degree-of-freedom guidance for constrained reentry vehicle is presented in the paper. First, the constrained trajectory is generated by Legendre pseudospectral method (LPM) and then the feasibily of the trajectory is validated. Based on the obtained reference trajectory, the guidance problem is converted into a trajectory state regulation problem which is a linear time varying system. A robust state feedback guidance law is generated in real time using indirect Legendre pseudospectral feedback method. Finally, simulation results illustrate that the overall guidance scheme can lead to a very accurately controlled flight with all the constraints satisfied even in the presence of initial state uncertainty.     

Adaptive sliding mode control for six-DOF relative motion of spacecraft with input constraint

This paper addresses the synchronized control problem of relative position and attitude for spacecraft with input constraint. First, using dual quaternion, the kinematic and dynamic models of the six-degree-of-freedom relative motion of spacecraft are introduced. Second, a new adaptive sliding mode control scheme is proposed to guarantee the globally asymptotic convergence of relative motion despite the presence of control input constraint, parametric uncertainties and external disturbances. A detailed stability analysis of the resulting closed-loop system is included. Finally, simulation results are presented to illustrate the validity and effectiveness of the proposed controller, which has the following properties: (1) explicit accounting for the problem of input constraint, (2) fast convergent rate and accurate results can be obtained, (3) no chattering phenomenon is present in the control torque and control force, (4) self-adaptive regulation law is dynamically adjusted to ensure the tracking errors tend to zero asymptotically, (5) the upper bounds of unknown variables are estimated dynamically.