火箭导弹工程图管理系统

提出对火箭导弹的工程图纸，照片等进行管理的方法，并进行了软件实现。     

顺逆流向喷流干扰下二体分离气动力风洞实验研究及前体轴向力特性

本文概述了具有顺，逆流向喷流干扰的二体分离气动力风洞实验技术研究。对有喷流干扰引起的前体轴向气动力特性，作了简单的介绍。最后对有顺、逆流向喷流干扰的前体底部流动模型作了定性的描绘，可供理论研究时参考。     

DATH在CMDB推进剂中应用研究

对ＤＡＴＨ在复合改性双基推进剂中应用及配装浇 出工艺制ＤＡＴＨ－ＣＭＤＢ推进剂药柱过程中出现的较强固化放气问题做了探讨，得出了若干结论。     

“大涡破碎”的紊流减阻实验研究

本文对当今国外曾提出的紊流表面摩擦减阻新概念——“大涡破碎”(LEBU)进行了初步的风洞实验探索。将具有对称流线型剖面的二元小肋,沿垂直于气流的方向安置在平板表面的紊流附面层内某一高度处,收到了不同程度的减阻效果。实验中分别考察了小肋的安置位置L,安置高度H,迎角θ及相对厚度b等参数对减阻效果的不同影响。从紊流附面层涡结构的观点出发,提出紊流的“细化”作用是小肋对平扳减阻的根本原因,并认为改善紊流附面层的速度型是研究紊流减阻的一种手段。实验使用自制的高灵敏度摩擦天平,测得的减阻效果与Ludwieg—Tillman公式的计算结果基本一致。     

失速改出伞阻力特征面积估算方法

研究了高平尾布局飞机的气动特性。使用失速改出伞是飞机改出深失速的重要途径,但如何确定失速改出伞的关键参数(阻力面积等)却没有现成的方法。以ARJ21-700飞机为例,分别使用公式分析法、类比法综合估算出失速改出伞的关键参数,通过模型自由飞和模拟仿真分析验证其具有足够效能将飞机改出深失速状态。形成了一套新机失速改出伞的设计方法和关键数据图表,可供其他型号飞机失速改出伞的设计研制使用。     

Real-time fault detection method based on belief rule base for aircraft navigation system

Real-time and accurate fault detection is essential to enhance the aircraft navigation system’s reliability and safety. The existent detection methods based on analytical model draws back at simultaneously detecting gradual and sudden faults. On account of this reason, we propose an online detection solution based on non-analytical model. In this article, the navigation system fault detection model is established based on belief rule base (BRB), where the system measuring residual and its changing rate are used as the inputs of BRB model and the fault detection function as the output. To overcome the drawbacks of current parameter optimization algorithms for BRB and achieve online update, a parameter recursive estimation algorithm is presented for online BRB detection model based on expectation maximization (EM) algorithm. Furthermore, the proposed method is verified by navigation experiment. Experimental results show that the proposed method is able to effectively realize online parameter evaluation in navigation system fault detection model. The output of the detection model can track the fault state very well, and the faults can be diagnosed in real time and accurately. In addition, the detection ability, especially in the probability of false detection, is superior to offline optimization method, and thus the system reliability has great improvement.     

Low-cost solutions for Martian base

Technical and architectural problems of a Martian base have been arised in many publications. Usually there is one solution described in detail or general classification is presented. In this paper, a recognition of low-cost solutions for Martian architecture is analyzed. The overview through various building techniques based on previous concepts of extraterrestrial architecture is summarized. Several solutions taking advantages of the shape of terrain, aiming for cost decreasing of human settlement on Mars are proposed.     

某型飞机起落架故障诊断专家系统设计研究

给出了飞机起落架故障诊断专家系统的构成、体系结构以及功能,引入了正向推理、不精确推理两种推理机制,研究了基于数据库技术的知识库构建方法,并用此构建方法完成了软件测试.仿真试验表明,应用此系统可以提高起落架故障智能诊断的效率和准确性,具有较强的实用性.     

Deorbiting spacecraft with passively stabilised attitude using a simplified quasi-rhombic-pyramid sail

This paper studies deorbiting using an analogue to the quasi-rhombic-pyramid concept for planar motion. The focus is on maintaining a stable (meaning oscillatory) attitude close to the direction of the velocity of the spacecraft relative to the atmosphere. The study consists of a massive computation of deorbit times chosen in a region of the phase space where atmospheric drag plays a leading role. Here, no damping effects are considered. Thus, any passive stabilisation observed is either due to solar radiation pressure or atmospheric drag. The results show that such stable deorbiting is feasible up to a threshold that depends upon the physical parameters of the sail. This threshold is around 500 km of altitude. Stable deorbiting is also shown to reduce the unpredictability that appears due to tumbling.     

基于声学黑洞效应的直升机驾驶舱宽带降噪

声学黑洞（ABH）效应是利用结构阻抗的变化，使结构中传播的波相速度和群速度发生变化，在结构局部区域实现波的聚集，进而通过少量阻尼将能量耗损。该方法具有高效、轻质、宽频等优点，为结构振动噪声控制提供了新的思路，具有较强的潜能和应用前景。本文针对直升机驾驶舱复杂的噪声问题，根据噪声源和传递路径，提出基于ABH效应的内嵌式和附加式2种减振降噪设计方案。利用有限元软件建立了结构声振耦合模型，分析了直升机驾驶舱模型的声振特性，解释了ABH效应有助于降低舱室噪声的机理，并搭建了实验平台，开展了效果测试和性能评估。结果表明，内嵌式ABH结构可以有效降低舱内的中高频噪声，而低频控制能力略显不足。附加式ABH结构可以弥补这一局限性，拓宽有效频带。结合内嵌式和附加式ABH 2种控制方案，相比传统结构在总质量不增加甚至略有降低的前提下，舱室平均噪声水平在1/3倍频程内降低3~10 dB。该研究成果有助于推进ABH新技术在未来直升机工程减振降噪中的应用。