基于混合星座的卫星导航系统功率增强服务性能分析

在导航战中,卫星功率增强技术是提高战区卫星导航系统生存能力的重要措施.针对导航战背景下如何保持Compass系统对我国领土及周边区域导航服务能力的问题进行了研究,提出了一种基于混合星座和最优GDOP值准则的卫星导航系统功率增强方案,并就功率增强覆盖区域在不同实现方式条件下的覆盖性、可用性和实现复杂度等性能进行了对比分析.分析结果表明,采用“5GEO +4MEO”的功率增强组合形式,可以实现对我国领土及近海区域的全天时覆盖,可用性水平达到100％( GDOP ＜6.3),同时具有实现复杂度低和系统稳定性好等特点,可作为我国区域功率增强的备选方案.     

具有优先级消息的AFDX建模与性能分析

以Petri网为工具,建立了基于具有优先级消息传输的AFDX(航空电子全双工以太网)网络模型,通过仿真,求解出消息发送时的平均等待时间,得到的指标结果验证了高优先级数据消息帧发送等待延时明显小于低优先级数据消息帧的发送等待延时,充分说明了优先级对紧急数据传输的重要性。模型有助于进一步理解航电系统不同优先级消息在AFDX网络中的传输机制,为以AFDX为总线的综合航电系统的设计和完善提供重要的理论依据。     

一种新的雷达抗干扰技术

提出了一种新的雷达抗干扰技术,即波形选择处理技术,指的是从接收的回波中分析出哪些脉冲未受干扰或受干扰程度较小,从而可以有选择地将这些脉冲信号进行相应的信号处理。分析结果表明,通过对回波进行波形选择处理,可以进一步增强雷达的抗干扰能力。     

不完备检测下视情维修的多级劣化系统性能评估

视情维修是改善多级劣化系统性能表现的重要措施,然而在实际中检测不完备问题会制约视情维修的有效开展,从而影响劣化系统性能评估结果。针对这一问题,将多级劣化系统检测维修马尔科夫链模型中的状态转移进行调整,建立其在不完备检测下进行视情维修的性能评估模型,给出系统性能参数的求解方法。实例验证表明:在实际工作中,虚警和漏检对于系统瞬态可用度的影响是随时间变化而不定的,但对于系统可靠度的影响则是确定的,即在任意时刻虚警提高系统可靠度,而漏检降低系统可靠度。     

润滑油基础油黏度调和模型的优化选择

通过测定46#机械油基础油与PAO8（8#聚α-烯烃油）不同比例混合后油品的黏温性能,研究了黏度偏差率随测量温度的变化规律．通过实验发现：国际通用黏度调和计算模型能较好预测混合基础油的高温运动黏度,黏度偏差率最大值为3．56％;而美国标准局的黏度调和计算模型在混合基础油的低温运动黏度计算上精确度更高．     

大气气溶胶对激光制导探测作用距离影响的数值分析

针对大气气溶胶辐射传输衰减效应是影响1.06μm激光武器系统性能的重要因素,探讨了大气气溶胶对1.06μm激光探测作用距离的影响,构建了激光制导波段探测作用距离模型,并在此基础上进行激光探测作用距离的大气气溶胶影响数值仿真。试验表明,基于该模型计算的大气透过特性准确度基本符合国际公认理论分析值,对作用距离的评估结果与客观实际基本相符,对最大限度分析利用战场气象环境以确保武器作战性能的充分发挥具有重要价值,可为激光探测作用距离的气象环境影响后续发展奠定一定基础。     

Influence of propagation direction on operation performance of rotating detonation combustor with turbine guide vane

Due to the pressure gain combustion characteristics, the rotating detonation combustor (RDC) can enhance thermodynamic cycle efficiency. Therefore, the performance of gas-turbine engine can be further improved with this combustion technology. In the present study, the RDC operation performance with a turbine guide vane (TGV) is experimentally investigated. Hydrogen and air are used as propellants while hydrogen and air mass flow rate are about 16.1 g/s and 500 g/s and the equivalence ratio is about 1.0. A pre-detonator is used to ignite the mixture. High-frequency dynamic pressure transducers and silicon pressure sensors are employed to measure pressure oscillations and static pressure in the combustion chamber. The experimental results show that the steady propagation of rotating detonation wave (RDW) is observed in the combustion chamber and the mean propagation velocity is above 1650 m/s, reaching over 84% of theoretical Chapman-Jouguet detonation velocity. Clockwise and counterclockwise propagation directions of RDW are obtained. For clockwise propagation direction, the static pressure is about 15% higher in the combustor compared with counterclockwise propagation direction, but the RDW dominant frequency is lower. When the oblique shock wave propagates across the TGV, the pressure oscillations reduces significantly. In addition, as the detonation products flow through the TGV, the static pressure drops up to 32% and 43% for clockwise and counterclockwise propagation process respectively.     

Supercritical carbon dioxide as a new working medium for pneumatic launch: A theoretical study

Compared with the conventionally gaseous or liquid working media, the specific internal energy of supercritical carbon dioxide (SCD) is higher at the same temperature and pressure, and the critical temperature of carbon dioxide is close to room temperature, making SCD a potential new working medium for pneumatic launch. To analyze the feasibility of this conception, an analytical model of a pneumatic catapult is established on basis of the conservations of mass and energy. The model consists of a high-pressure chamber and a low-pressure chamber connected by multiple valves, and there is a movable piston in the low-pressure chamber that can push an aircraft to accelerate. The effects of the launch readiness state of SCD in the high-pressure chamber, the initial volume of the low-pressure chamber and the valve control on the movement of the aircraft are analyzed. It is found that there is a restrictive relation between the temperature and pressure of the launch readiness state of SCD, i.e., there is a maximum allowable launch readiness pressure when the launch readiness temperature is fixed. If this restrictive relation is not satisfied, the working medium in the low-pressure chamber will drop to its triple point within a few milliseconds, leading to a launch failure. Owing to this restrictive relation, there is an optimal launch readiness state of SCD with the highest working capacity for any allowable launch readiness temperature. The pressure of the low-pressure chamber will decrease significantly as the initial volume increases, leading to a decreased acceleration of the aircraft. The ac-celeration can be controlled below a critical value by a designed sequential blasting technique of multiple valves. The calculated results show that a 500 kg aircraft can be accelerated from 0 to 58 m/s in 0.9 s with 36 kg of carbon dioxide. This research provides a new technique for the controllable cold launch of an aircraft.     

耐1200℃陶瓷瓦重复使用性能

针对目前比较成熟的耐1 200℃陶瓷瓦开展了1 200℃多次重复热处理,研究了陶瓷瓦的结构和性能演变行为和重复使用性能。结果表明:1 200℃热处理20次后,耐1 200℃陶瓷瓦表现出良好的宏观热稳定性;重复热处理过程中,纤维间烧结,黏接熔融和石英纤维析晶及晶粒长大,使纤维直径发生变化,出现缩颈,进而导致了Z向收缩,收缩率达14%,从而使得压缩强度略有增大,隔热性能降低;经过1 260℃、11次单面辐射加热后,Z向收缩率为5.58%,隔热效果降低了7.59%,但隔热材料能够在6次重复加热后保持材料隔热性能不降低。     

MPI并行程序中通信等待问题的诊断方法及其应用

随着并行规模的扩大,现有通信等待问题的诊断方法存在内存开销大、测量时间开销大等问题。通过对现有通信等待问题诊断方法的深入分析,同时考虑测量开销可控的实际需求,建立基于热点函数的通信等待问题诊断模型。基于上述模型,总结出一种更精简、更实用的通信等待问题诊断方法。将该诊断方法分别应用到二维LARED集成、LARED-S、LAP3D等大规模MPI并行程序的通信等待问题诊断过程,应用效果表明本诊断方法可精确定位导致通信等待问题的关键代码段,给出的优化方案及性能提升空间对于后续的程序改进具有参考价值,其中根据诊断结果优化后的LARED-S程序性能提升32%,通信等待时间减少44%。