...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Aerospace science and technology >Regressor time-shifting to identify longitudinal stability and control derivatives of the Jetstream 3102
【24h】

Regressor time-shifting to identify longitudinal stability and control derivatives of the Jetstream 3102

机译：回归器时移以识别Jetstream 3102的纵向稳定性并控制其导数

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The Jetstream 31 G-NFLA aircraft is used as a national flying laboratory test vehicle for flight dynamics research and teaching purposes. It has been the subject of much theoretical and experimental modelling and therefore, the need for generating validation data through flight testing is critical. In this paper, the aircraft's short period pitch oscillation mode characteristics are identified using data from sixteen flight tests. An identification procedure based on the least squares method and reduced order state space model is used and the need for pre-processing regressors due to the effects of sensor location and instrumentation delays is highlighted. It has been shown that time-shifting the regressors based on relative locations of the angle of attack vanes and the inertial measurement unit results in significant reductions in uncertainty bounds of the estimated aeroderivatives and also a model that provides a closer match to flight test data. The estimated models are validated using separate flight test data and the variations in aeroderivatives over a range of airspeeds and centre of gravity positions are also presented. (C) 2017 Elsevier Masson SAS. All rights reserved.
机译：Jetstream 31 G-NFLA飞机被用作用于飞行动力学研究和教学目的的国家飞行实验室测试工具。它一直是许多理论和实验建模的主题，因此，通过飞行测试生成验证数据的需求至关重要。在本文中，使用来自16次飞行测试的数据来识别飞机的短周期俯仰振荡模式特性。使用了基于最小二乘法和降阶状态空间模型的识别程序，并强调了由于传感器位置和仪器延迟的影响而需要对回归进行预处理的需求。已经表明，基于攻角叶片和惯性测量单元的相对位置对回归器进行时移会显着降低估计的航改航向的不确定性范围，并且还会提供与飞行测试数据更匹配的模型。估计的模型使用单独的飞行测试数据进行了验证，并且还显示了航速衍生物在一系列空速和重心位置上的变化。 （C）2017 Elsevier Masson SAS。版权所有。

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