航天器轨道交会迭代制导算法

针对航天器轨道交会的脉冲推力模型与实际发动机连续推力模型不相符的问题,研究一种脉冲变轨策略的工程实现方法,使脉冲变轨策略可应用于工程实际.基于Lambert飞行时间定理和遗传算法,研究航天器最优脉冲变轨策略.根据脉冲变轨优化的结果,采用迭代制导算法研究脉冲变轨工程化问题.仿真结果验证了迭代制导算法在航天器轨道交会中的有效性.     

冲击噪声环境下基于任意阵列流形的空时二维DOA估计方法

 针对冲击噪声环境中信号源的高分辨二维波达方向(DOA)估计问题,提出了一种适合任意阵形的基于联合对角化分数低阶空时(ST)相关矩阵的二维DOA估计方法。该方法先对分数低阶空时矩进行采样构建伪快拍数据矩阵,然后对两个时延分数低阶空时矩阵进行联合对角化处理。其无需二维谱峰搜索和参数配对,在低信噪比下对强冲击噪声具有更好的抑制作用,适合存在一维角度兼并的情况。仿真结果证明了该方法的有效性。     

异构多星编队的脉冲构型保持控制方法

近地轨道的双星编队通常设计具有自稳定性的编队构型参数初值,通过保持编队构型参数形成长期稳定的相对周期运动。针对编队中卫星数量增多产生的相对运动耦合问题,提出了基于Hill坐标和三角函数公式的多星相对运动分析方法。基于SAR载荷测量基线定义,结合多星编队构型参数的相对运动特性,提出了编队构型参数的设计方法,能够实现多星编队的最大有效基线组合。通过分析J2项摄动和大气阻力摄动的长期影响,研究了异构多星编队的相对运动衍化规律,提出了主从形式的脉冲偏置控制,能够有效保持针对异构多星编队设计的编队构型。通过面质比异构的四星编队控制仿真,验证了脉冲偏置控制形式下异构多星编队构型保持控制方法的有效性。     

中国运载火箭地面系统发展方向研究

地面系统用于支持和保障火箭的发射与试验,对火箭的使用性能、发射能力、发射场配置及工作流程等有重要的影响。调研了国外运载火箭地面系统发展现状,总结了国外运载火箭地面系统发展趋势。从快速发射、简易发射、安全发射、自动发射和通用发射等方面提出了地面系统发展思路和主要关键技术,为我国后续运载火箭地面系统发展提供参考。     

圆轨道欠驱动航天器编队重构脉冲控制

针对圆轨道径向或迹向欠驱动航天器编队重构控制问题,提出了欠驱动脉冲控制方法。首先,基于圆轨道欠驱动航天器相对运动动力学模型,分析了两类欠驱动条件下的系统可控性和重构可行性。然后,解析推导了两类欠驱动条件下实现重构所需的最少脉冲次数以及对应的速度增量消耗。最后,设计数值仿真算例,验证了本文提出的欠驱动脉冲控制方法的正确性。仿真结果表明:径向和迹向欠驱动条件下均可实现圆轨道编队重构。与全驱动控制方法相比,欠驱动控制方法可有效避免由推力器故障引起的重构任务失效,故而提高了控制系统的灵活性与可靠性。     

太阳微波脉冲事件的时变特性

本文利用瑞士Berne大学1988年1月-1989年12月发布的15个太阳微波脉冲事件的观测资料，分析其时间轮廓的3个主要特征：脉冲度、不对称性和半功率宽度频率响应．这些特性，可以定性地用非热电子的连续注入模，和不均匀的源模型给出较合理的解释．     

Optimal station-keeping near Earth–Moon collinear libration points using continuous and impulsive maneuvers

In this study the gravitational perturbations of the Sun and other planets are modeled on the dynamics near the Earth–Moon Lagrange points and optimal continuous and discrete station-keeping maneuvers are found to maintain spacecraft about these points. The most critical perturbation effect near the L₁ and L₂ Lagrange points of the Earth–Moon is the ellipticity of the Moon’s orbit and the Sun’s gravity, respectively. These perturbations deviate the spacecraft from its nominal orbit and have been modeled through a restricted five-body problem (R5BP) formulation compatible with circular restricted three-body problem (CR3BP). The continuous control or impulsive maneuvers can compensate the deviation and keep the spacecraft on the closed orbit about the Lagrange point. The continuous control has been computed using linear quadratic regulator (LQR) and is compared with nonlinear programming (NP). The multiple shooting (MS) has been used for the computation of impulsive maneuvers to keep the trajectory closed and subsequently an optimized MS (OMS) method and multiple impulses optimization (MIO) method have been introduced, which minimize the summation of multiple impulses. In these two methods the spacecraft is allowed to deviate from the nominal orbit; however, the spacecraft trajectory should close itself. In this manner, some closed or nearly closed trajectories around the Earth–Moon Lagrange points are found that need almost zero station-keeping maneuver.     

Extensions in adaptive model tracking with mitigated passivity conditions

Feasibility of nonlinear and adaptive control methodologies in multivariable linear timeinvariant systems with state space realization {A, B, C} has apparently been limited by the standard strict passivity (or positive realness) conditions that imply that the product CB must be positive definite symmetric. More recently the symmetry condition has been mitigated, requiring instead that the not necessarily symmetric matrix CB be diagonalizable and with positive real eigenvalues. However, although the mitigated conditions are useful in proving pure stabilizability with Adaptive Controllers, the Model Tracking question has remained open and counterexamples seem to demonstrate total divergence of standard model reference adaptive controllers when the regular passivity conditions are not fully satisfied. Therefore, this paper further extends the previous results, showing that the new passivity conditions do guarantee stability with adaptive model tracking. Examples show how the new conditions solve the case of flexible structures with unknown parameters when perfect collocation is not possible. Also, the so-called counterexamples become simple, well-behaved, examples.     

Evolution of an electron beam pulse influenced by coulomb collision effects in the solar corona

Electrons accelerated in the corona during solar activity give rise to radio emission events that can be observed over a wide range of frequencies. Among different finer-scale structures in the dynamic spectra observed in the radio range, fast transients with extents of some milliseconds known as solar radio spikes are observed accompaning the background continuum emission. Fundamental to the generation of radio spikes is a propagating electron beam and following its evolution allows us to understand the physical processes occurring in the solar corona. With the use of a numerical Fokker–Planck code we follow a previous numerical study to simulate the propagation of an electron beam pulse injected in a small region at the top of a magnetic field and outwards the solar corona under typical flare conditions. It was found that in large ambient densities of ${10}^{10}$ cm⁻³ at the injection point, Coulomb collision effects have an important effect on the propagation of the electrons, causing that the injected electrons thermalize faster in a time of $0.1$ and $0.4$ s for an electron distribution with a low-energy cut off of 16 and 7 keV respectively and a spectral index of 3. For a tenous ambient medium of density ${10}^9$ cm⁻³ thermalization occurs only for an electron distribution with smaller low-energy cut off (7 keV) with a duration of $\approx$1.5 s, while for a larger low-energy cut off (16 keV) the loss of accelerated electrons is very slow, regardles of the spectral index ($3,7$). The electron loss time by Coulomb collisions, which depends on the low boundary ambient density, might be an important parameter that influences the generation of radio spikes due to the formation of instabilities in the corona.     

介绍一种校准加速度计的新装置

混合摆是由单摆与复摆构成的新型摆。它克服了单摆与复摆的缺点,兼有二者的优点。介绍了这种摆的结构原理、性能特点和没计依据,阐明了其冲击加速度的计算与测试方法。这种装置避免了地球重力加速度的影响,适合于中低档g值加速度计的校准工作,其准确度优于5％。