大推力氢氧发动机瞬态特性研究

以大推力氢氧火箭发动机为研究对象,对其瞬态特性进行了研究。根据模块化的建模和仿真思想,建立了发动机各组件的动态数学模型,开发了发动机系统各组件的仿真模块,开展了发动机动态特性仿真分析与起动时序试验研究。仿真结果表明,推力室氧阀采用25%初级与100%全开的双开度形式,氧涡轮侧设置10%分流流量的燃气分流阀,燃气发生器在火药启动器工作至70%~80%时间段点火的系统优化配置方案,有利于控制发动机点火起动混合比,提高起动可靠性。通过添加故障因子,当涡轮效率由于故障从0.29降至0.19时,发动机工况降至故障前的78%工况,当效率降至0.06时,发动机工况降至故障前20%工况,发动机故障仿真结果与地面试验故障结果吻合较好,有利于故障分析定位。     

一种全数字GMSK解调方法

文章提出一种用于GMSK解调的全数字中频接收机方案,并重点讨论了载波同步和位同步两个部分。载波同步选用了判决反馈环,可实现特定BT范围内的载波恢复。又根据GMSK信号线性近似后与OQPSK形式一致这一特点,借鉴OQPSK位同步中用到的数据转换跟踪环（DTFL）,设计了适用于GMSK的位同步环路。仿真和硬件实现结果均表明该方案是一种简单而又行之有效的方法。     

飞控系统实时仿真算法分析

采用改进的双线性变换方法－临界频率预翘曲方法,对双线性变换方法引起的偏差进行预补偿,从而减小飞控系统的实时仿真误差。以频带较宽的典型环节为例,对系统频率特性进行了分析,同时,将其与双线性变换及四阶龙格－库塔法的计算结果进行了比较。结果表明：该方法能较好地补偿双线性变换所引起的误差,满足飞机飞控系统的实时仿真要求。     

Basic belief assignment approximations using degree of non-redundancy for focal element

Dempster-Shafer evidence theory, also called the theory of belief function, is widely used for uncertainty modeling and reasoning. However, when the size and number of focal elements are large, the evidence combination will bring a high computational complexity. To address this issue, various methods have been proposed including the implementation of more efficient combination rules and the simplifications or approximations of Basic Belief Assignments (BBAs). In this paper, a novel principle for approximating a BBA into a simpler one is proposed, which is based on the degree of non-redundancy for focal elements. More non-redundant focal elements are kept in the approximation while more redundant focal elements in the original BBA are removed first. Three types of degree of non-redundancy are defined based on three different definitions of focal element distance, respectively. Two different implementations of this principle for BBA approximations are proposed including a batch and an iterative type. Examples, experiments, comparisons and related analyses are provided to validate proposed approximation approaches.     

非线性热传导方程混合问题插值逼近

以Legendre-Gauss-type积分节点为插值节点,构造插值基函数展开数值解,逼近有界杆上的非线性热传导方程Dirichlet边界条件的正确解。给出算法格式和相应的数值算例,表明所提算法格式的有效性和高精度。所给算法适合于非线性问题求解。     

CFD predictions of LBO limits for aero-engine combustors using fuel iterative approximation

Lean blow-out (LBO) is critical to operational performance of combustion systems in propulsion and power generation. Current predictive tools for LBO limits are based on decadesold empirical correlations that have limited applicability for modern combustor designs. According to the Lefebvre’s model for LBO and classical perfect stirred reactor (PSR) concept, a load parameter (LP) is proposed for LBO analysis of aero-engine combustors in this paper. The parameters contained in load parameter are all estimated from the non-reacting flow field of a combustor that is obtained by numerical simulation. Additionally, based on the load parameter, a method of fuel iterative approximation (FIA) is proposed to predict the LBO limit of the combustor. Compared with experimental data for 19 combustors, it is found that load parameter can represent the actual combustion load of the combustor near LBO and have good relativity with LBO fuel/air ratio (FAR). The LBO FAR obtained by FIA shows good agreement with experimental data, the maximum prediction uncertainty of FIA is about ±17.5%. Because only the non-reacting flow is simulated, the time cost of the LBO limit prediction using FIA is relatively low (about 6 h for one combustor with computer equipment of CPU 2.66 GHz · 4 and 4 GB memory), showing that FIA is reliable and efficient to be used for practical applications.     

Weibull分布更新函数的指数近似算法

针对Weibull分布的更新函数较难确定的问题,研究了在平均寿命相等情况下指数分布与Weibull分布之间的贴近性.在此基础上,提出利用指数分布的更新函数模型计算Weibull分布的更新函数,能够比较方便有效地得到近似解.通过实例计算,分别比较了指数方法(直接利用指数分布的更新函数)、线性加权模型以及几何加权模型等三种方法的精度.结果表明:当时间较短时,线性加权和几何加权模型比指数方法精确度有所提高;当时间较长时,几何加权模型的精度较高.利用该结论能够为工程应用提供方便.     

A novel cooperative mid-course guidance scheme for multiple intercepting missiles

In the interception engagement,if the target movement information is not accurate enough for the mid-course guidance of intercepting missiles,the interception mission may fail as a result of large handover errors.This paper proposes a novel cooperative mid-course guidance scheme for multiple missiles to intercept a target under the condition of large detection errors.Under this scheme,the launch and interception moments are staggered for different missiles.The earlier launched missiles can obtain a relatively accurate detection to the target during their terminal guidance,based on which the latter missiles are permitted to eliminate the handover error in the mid-course guidance.A significant merit of this scheme is that the available resources are fully exploited and less missiles are needed to achieve the interception mission.To this end,first,the design of cooperative handover parameters is formulated as an optimization problem.Then,an algorithm based on Monte Carlo sampling and stochastic approximation is proposed to solve this optimization problem,and the convergence of the algorithm is proved as well.Finally,simulation experiments are carried out to validate the effectiveness of the proposed cooperative scheme and algorithm.     

核心机驱动风扇级在非设计模式下的匹配方法研究

核心机驱动风扇级(CDFS)是双涵道变循环发动机的关键部件之一。为了开展CDFS在非设计模式下(双涵道模式)的匹配分析,利用速度三角形建立了CDFS在双涵道模式下的匹配特性图,该图能够正确反映双涵道模式下CDFS的工作特点和主要气动参数的变化趋势。结果表明:给定CDFS在双涵道模式下流量时,随着压比下降,需要降低CDFS在双涵道模式下的转速才能保证转子进口相对气流角不变;给定双涵道模式的流量和压比时,若要使转子进口相对气流角下降,需要增加CDFS在双涵道模式下的转速。     

立体构成中的能力培育、创造力育成

立体构成学习不再是简单的技能培训，也不是模仿性的学习，重点在于创造意识、创造能力的培养。本文阐述了立体构成中能力的培育、创造力的育成的新观点、新认识。