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Validation of Simulated Dynamic Interface Testing as a Tool in the Forecasting of Air Vehicle Deck Limits and Deck Landing Aids

机译:验证模拟动态接口测试作为空气车辆甲板限制和甲板着陆辅助工具的工具

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Validation results are discussed and compared in confirming the tendency of certain parameters being well represented by simulation with the actual at-sea result. The use of 6 degree-of-freedom motion flight simulator to forecast physical deck motion and deck motion limits, is discussed. Full flight test programs using the Merlin CAE Trainer System at RNAS Culdrose and the Manned Flight Simulator at Naval Air Test Center, Aircraft Division (Patuxent River, Maryland), are described. Using a real-time ship motion-based helicopter recovery monitoring system, pilots perform flight-testing evolutions (DLQ) just as they would at sea. The simulated flight test has 5 (five) essential objectives: assess the capabilities of the Cockpit Dynamic Simulator (CDS) to support or conduct SHOL/NATOPS limits; demonstrate High Level Architecture (HLA) federation along with selected modules e.g. air wake; evaluate recovery safety improvements offered by experimental systems, such as the Landing Period Designator; and determine feasibility of applying these simulators in support of dynamic interface at sea testing. The method, which has been implemented at both centers, gives good performance and correlation with apparent quiescent windows of deck motion. The theoretical approach is described. Results are presented in relation to the stability issues normally confronted by a helicopter at the instant of recovery in progressively difficult conditions. A brief synopsis of several of the integrated HLA modules representing various aspects of the maritime environment, is presented. The summaries include development, simulation and testing of various helicopter recovery aids which were applied during the simulator test. Measurements of instantaneous degree-of-freedom velocity and acceleration are reported, and preliminary comparisons are made with, and between, aided launch and recovery and non-aided evolutions.
机译:讨论了验证结果,并在确认通过模拟与实际的海拔结果表示的某些参数的趋势进行比较。讨论了使用6自由度运动飞行模拟器来预测物理甲板运动和甲板运动限制。描述了使用Merlin Cae教练系统的完整飞行测试程序,在RNAS Culdrose和Manned飞行模拟器,飞机部(Patuxent River,Maryland),Marned Simulidator,飞机部(Patuxent River,Maryland)。使用基于实时船舶运动的直升机恢复监控系统,飞行员在海上时执行飞行测试演变(DLQ)。模拟飞行试验有5(五)个基本目标:评估驾驶舱动态模拟器(CDS)的能力,以支持或进行避免/ NATOP限制;展示高级架构(HLA)联合以及选定的模块。空气苏醒;评估实验系统提供的回收安全改进,如着陆期指定器;并确定应用这些模拟器以支持海上测试动态接口的可行性。在两个中心实施的方法,具有良好的性能和与甲板运动的明显静止窗口相关性。描述了理论方法。结果在逐步困难的条件下在恢复的瞬间施加直升机时呈现出稳定性问题。提出了代表海上环境各个方面的几个集成HLA模块的简要概述。摘要包括在模拟器测试期间应用的各种直升机恢复助剂的开发,仿真和测试。报告了瞬时自由度和加速度的测量,并进行了初步比较,以及之间,辅助发射和恢复和非辅助演变。

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