首页> 外文会议>AIAA SciTech forum and exposition >Flight Simulator Investigation of Continuously Moving Highlift Devices During Landing Approaches
【24h】

Flight Simulator Investigation of Continuously Moving Highlift Devices During Landing Approaches

机译:着陆进近过程中连续移动高举设备的飞行模拟器研究

获取原文
获取外文期刊封面目录资料

摘要

This paper describes a flight simulator investigation in which airline pilots evaluated the effects of a high-lift system with continuously moving slats and flaps. Focus is on landing approach. Five pilots participated in the investigation, which was performed on the SEPHIR flight simulator at TU Berlin. The investigation included various high-lift control laws and different wind conditions. The traditional approach where most commercial transport aircraft configure the high-lift setting stepwise represents the reference. Here, the airspeed is reduced to the maximum allowable speed of the next slat/flap configuration, and then the pilot commands the next higher slat/flap setting. Thus, most of the time the aircraft does not fly in its optimal aerodynamic configuration, when it maneuvers in the terminal area during approach. The investigated high-lift system with continuously moving high-lift devices automatically adapts the slat/flap setting based on the airspeed and aircraft mass and enables the aircraft to fly in an optimal aerodynamic configuration, either for minimal drag or for minimal power. In the flight simulator, the pilots easily handled the new function. They suggested further investigations of the continuously moving slats and flaps system (CMSFS). Additionally, the simulator tests affirmed, that the system improves aircraft performance.
机译:本文描述了一个飞行模拟器调查,在该调查中,航空公司飞行员评估了具有连续移动的板条和襟翼的高升力系统的效果。重点是着陆方式。五名飞行员参加了调查,该调查是在柏林工业大学的SEPHIR飞行模拟器上进行的。调查包括各种高升力控制规律和不同的风况。大多数商用运输飞机逐步配置高升力设置的传统方法代表了参考。在这里,空速降低到下一个板条/襟翼配置的最大允许速度,然后飞行员命令下一个更高的板条/襟翼设置。因此,当飞机在进近过程中在终端区域进行操纵时,大多数时候飞机都不会以其最佳的空气动力学配置飞行。所研究的具有连续移动的高升力装置的高升力系统会根据空速和飞机的质量自动调整板条/襟翼的设置,并使飞机以最佳的空气动力学配置飞行,从而实现最小的阻力或最小的功率。在飞行模拟器中,飞行员可以轻松地处理新功能。他们建议对连续运动的板条和襟翼系统(CMSFS)进行进一步研究。此外,仿真器测试确认该系统可提高飞机性能。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号