有限推力下时间最优轨道转移

研究了一种有限推力作用下的时间最优轨道转移计算方法。以非奇异根素形式的高斯行星摄动方程为基础,由庞德里亚金极小值原理导出正则方程组,通过将最优控制问题转化为协状态初值为待优化参数的参数优化问题,并通过非线性规划求解得到的参数优化问题,从而避开求解两点边值问题的困难。文章最后给出2个算例,分别计算了零倾角零偏心率最优轨道转移和大倾角改变最优轨道转移。计算过程及结果表明本文所用方法对协状态初值猜测敏感性小,收敛迅速;零倾角零偏心率情况下无奇异;所得控制轨线光滑。     

基于局部Neymark分解的混沌信号与噪声的分离方法

从动力系统和几何的观点出发,提出了基于局部Ｎｅｙｍａｒｋ分解的混沌信号与噪声的分离方法。该方法在一个局部的轨道空间内进行Ｎｅｙｍａｒｋ分解,重构时消除由噪声引起的在某些方向上的错误分量,接着进行反嵌入,使得这一由于噪声影响而发生畸变的局部轨道得以纠正,达到混沌信号与噪声分离（以下简称混沌滤波）的目的,并对其中的反嵌入问题作了较为深入的讨论,仿真实验表明了本方法的有效性。     

运动的核弹比静止的核弹威力小?——多普勒效应、红移、光行差和动体的质能当量关系

证明爱因斯坦立足于光速不变假设和长度收缩假设的洛伦茨变换未能正确地解释多普勒效应、红移和光行差现象;他也未能给出正确的动体的质能当量关系.作者立足于完全符合相对性原理的伽利略变换,成功地解决了上述问题.     

The gas pixel detector as a solar X-ray polarimeter and imager

The Sun is the nearest astrophysical source with a very intense emission in the X-ray band. The study of energetic events, such as solar flares, can help us to understand the behaviour of the magnetic field of our star. There are in the literature numerous studies published about polarization predictions, for a wide range of solar flares models involving the emission from thermal and/or non-thermal processes, but observations in the X-ray band have never been exhaustive.The gas pixel detector (GPD) was designed to achieve X-ray polarimetric measurements as well as X-ray images for far astrophysical sources. Here we present the possibility to employ this instrument for the observation of our Sun in the X-ray band.     

某型教练机起落架信号电路改进设计

针对某型教练机存外场使用时出现起落架未放到位，而飞行员却没能及时发现的问题，本文对飞机起落架信号电路进行了分析，并提出了相应的改进措施。     

Fast Probabilistic Particle Identification algorithm using silicon strip detectors

Active detectors used as radiation monitors in space are not usually able to perform Particle Identification (PID). Common techniques need energy loss spectra with high statistics to estimate ion abundances. The ALTEA-space detector system is a set of silicon strip particle telescopes monitoring the radiation environment on board the International Space Station since July 2006 with real-time telemetry capabilities. Its large geometrical factor due to the concurrent use of six detectors permits the acquisition of good energy loss spectra even in a short period of observation. In this paper we present a novel Fast Probabilistic Particle Identification (FPPI) algorithm developed for the ALTEA data analysis in order to perform nuclear identification with low statistics and, with some limitations, also in real time.     

Experimental and theoretical burning of solid rocket propellants near the pressure deflagration limit

Burning of composite solid rocket propellants near the pressure deflagration limit (PDL) was studied experimentally in two different test chambers. The propellant tested was a nonmetallized ammonium perchlorate-based composite propellant (AP 84/CTPB 16). Measurements were taken of the regression rate, oscillations frequency and flame luminosity. Self-sustained oscillations were detected near the PDL that matched reasonably well the predictions of the analytical nonlinear stability theory and of the numerically solved nonlinear mathematical model. Both experimental and numerical results show the burning rate oscillations near the PDL due to statically unstable burning, that is the only combustion regime possible below a certain pressure. When pressure is further reduced the amplitude of the oscillations increases and their frequency decreases, until extinction follows abruptly below a pressure that corresponds to the PDL.     

An approach to the dynamics of modular repetitive structures

The dynamics of modular structures is approached in this paper by means of the discrete Fourier transform. This method, applied to a structure with N bays and ring type boundary conditions, leads to N uncoupled systems of the size of a single bay. For other boundary conditions, it leads to a “spectrally resolved” eigenproblem, that is a form whose dominant terms in each field of frequency are evidenced. Approximate reduced models in narrow frequency fields can therefore be generated by using the “spectral condensation” technique. The method can be applied with general boundary conditions, but the present paper deals mostly with the “clamped edges” boundary condition and shows that numerical advantages can be obtained, particularly for the large space structures.     

Zenith Pass Problem of Inter-satellite Linkage Antenna Based on Program Guidance Method

While adopting an elevation-over-azimuth architecture by an inter-satellite linkage antenna of a user satellite, a zenith pass problem always occurs when the antenna is tracing the tracking and data relay satellite （TDRS）. This paper deals with this problem by way of, firstly, introducing movement laws of the inter-satellite linkage to predict the movement of the user satellite antenna followed by analyzing the potential pass moment and the actual one of the zenith pass in detail. A number of specific orbit altitudes for the user satellite that can remove the blindness zone are obtained. Finally, on the base of the predicted results from the movement laws of the inter-satellite linkage, the zenith pass tracing strategies for the user satellite antenna are designed under the program guidance using a trajectory preprocessor. Simulations have confirmed the reasonability and feasibility of the strategies in dealing with the zenith pass problem.