Predicting lean blow-off of bluffbody stabilized flames based on Damköhler number

Lean Blow-Off(LBO) prediction is important to propulsion system design. In this paper,a hybrid method combining numerical simulation and Da(Damk?hler) model is proposed based on bluffbody stabilized flames. In the simulated reacting flow, Practical Reaction Zone(PRZ) is built based on OH radical concentration, and it is considered to be the critical zone that controls LBO.Da number is obtained based on the volume-averaged parameters of PRZ. The flow time scale(s_f)indicates the residence time of the fresh mixture flowing through the PRZ. It is obtained based on the characteristic length and volume-averaged axial velocity of the PRZ. The chemical time scale(s_c) indicates the shortest time needed to trigger the reaction of the mixture. It is obtained by commercial software CHEMKIN through monitoring the transient variation of the reactor temperature. The result shows that the average Da number under different LBO conditions is 1.135(the Da number under each LBO condition ranges from 0.673 to 1.351). This indicates that the flow time scale and chemical time scale are comparable. The combustion is in a critical state where LBO is easy to occur. With the increase of the fuel mass flow rate(the global fuel/air ratio increases from 0.004761 to 0.01095), s_f increases from 0.001268 s to 0.007249 s, and s_c decreases from 0.00124 s to0.00089 s. Accordingly, Da number increases from 1.023 to 8.145, which shows that the combustion becomes more stable. The above results show that the method proposed in the present study can properly predict the LBO limits of combustors, which provides important technical supports for combustor design and optimization.     

大型水陆两栖飞机抗浪能力研究

阐述了大型灭火/水上救援水陆两栖飞机高抗浪船体设计方法，对飞机起飞过程中的水阻力、滑行稳定性和波浪运动响应进行了研究。通过对比分析，发现断阶喷溅形态是影响水阻力出现第2峰值的关键因素，提出了水阻力曲线出现第2峰值的条件；分析了在纵倾角-速度图中不同区域滑行时飞机纵倾角响应特性，明确了飞机在典型状态的稳定边界；通过研究波长、速度对飞机纵倾角、飞高和机身垂向过载的影响，确定了飞机在波浪水面发生剧烈运动响应时对应的波长范围。     

中继卫星系统仿真软件设计与应用*

设计开发中继卫星系统仿真软件,并针对理想信道条件、I/Q幅相不平衡、幅频特性、群时延、相位噪声、功放饱和条件、非线性信道条件这七种信道,仿真16QAM和16APSK的误码率性能,并对仿真结果进行分析。利用仿真平台得出的非线性信道条件下误码率需求与所需信噪比之间的关系,可以作为完善系统技术指标的重要依据,为中继卫星系统后续建设和应用提供重要参考。     

Guidepost-based autonomous orbit determination method for GEO satellite

Guidepost-based navigation system is a novel autonomous orbit determination method for the GEO satellite. The system is achieved by using the camera imaging function to obtain the guidepost images and the GNSS signal receiver to obtain the pseudoranges between the GEO and the navigation satellites. Due to the high altitude of GEO satellite and the time-varying sunlight condition in the space environment, it may be difficult to obtain object image points and the distance measurements of GNSS because of the weak visibility of the guideposts. To deal with the problem, a novel integrated orbit determination system is presented. The Earth landmarks, the in-orbit spacecraft and GNSS navigation satellites whose line-of-sights and the distance can be easily obtained are used at the same time as information for the GEO satellite navigation based on the observability conditions analysis. The observability of the GEO satellite navigation system is analyzed through the physical observability, the mathematical observability and the engineering observability through the observing geometry, the rank of observability matrix and the Cramer-Rao lower bound (CRLB) respectively. Besides, the maximum correntropy unscented Kalman filter (MCUKF) algorithm is applied to improve the estimation stability of the system in the presence of non-Gaussian noises. The simulation indicates the feasibility of the proposed scheme.     

叠氮交联层技术

介绍了叠氮交联层候选叠氮有机化合物的类别、合成、应用及其工艺；分析了叠氮交联层的粘结机理、适用性；着篝讨论了叠氮交联层用于绝热层／复合固化推进剂界面的制造工艺和性能。     

液体火箭发动机燃烧室工作过程仿真软件──CAFILRE的设计与实现

描述了液体火箭发动机燃烧室内喷雾燃烧与流动过程仿真软件CAFILRE(Combus-tion and Flow in Liquid Rocket Engine）的结构和功能。CAFILRE程序是采用模块化方法编制和发展的二维通用软件，具有模拟发动机燃烧室内推进剂雾化过程、液雾蒸发过程、湍流混合与燃烧过程的能力。用此软件可以对发动机内部进行详细的性能分析和参数优化。