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1. 发明授权

US08442705B2 Method and device for determining aerodynamic characteristics of an aircraft 有权
标题翻译：用于确定飞行器的空气动力特性的方法和装置
公开(公告)号：US08442705B2
公开(公告)日：2013-05-14
申请号：US12704661
申请日：2010-02-12
申请人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
发明人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
IPC分类号： G06F19/00
CPC分类号： G01M9/06
摘要： The present invention provides a device and method for determining aerodynamic characteristics of an aircraft, in particular a pitch moment coefficient at an ascending force of the aircraft without a horizontal tail plane of zero and an aerodynamic neutral point of the aircraft without a horizontal tail plane. In the method according to the invention, forces and mechanical flight parameters on aerofoils and a horizontal tail plane of the aircraft are detected at various detection instants during at least one non-stationary flight maneuvre of the aircraft. In this case, a linear system of equations is formed, which comprises a pitch movement moment balance equation for each detection instant, the pitch movement moment balance equation having the detected forces and mechanical flight parameters. This linear system of equations is evaluated to calculate the aerodynamic characteristics.
摘要翻译：本发明提供一种用于确定飞行器的空气动力学特性的装置和方法，特别是在没有水平尾翼平面的情况下飞行器的上升力的俯仰力矩系数和没有水平尾翼平面的飞机的空气动力学中性点。在根据本发明的方法中，在飞行器的至少一个非固定飞行操作期间，在各种检测时刻检测飞机上的机翼和水平尾翼的力和机械飞行参数。在这种情况下，形成线性方程式，其包括每个检测时刻的俯仰运动力矩平衡方程，具有检测力的俯仰运动力矩平衡方程和机械飞行参数。评估该线性方程组以计算空气动力特性。

2. 发明申请

US20100222945A1 METHOD AND DEVICE FOR DETERMINING AERODYNAMIC CHARACTERISTICS OF AN AIRCRAFT 有权
标题翻译：用于确定飞机航行特征的方法和装置
公开(公告)号：US20100222945A1
公开(公告)日：2010-09-02
申请号：US12704661
申请日：2010-02-12
申请人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
发明人： Hans-Gerd Giesseler , Wilfried Stegelmeier , Chloé Tauzin
IPC分类号： G06F19/00
CPC分类号： G01M9/06
摘要： The present invention provides a device and method for determining aerodynamic characteristics of an aircraft, in particular a pitch moment coefficient at an ascending force of the aircraft without a horizontal tail plane of zero and an aerodynamic neutral point of the aircraft without a horizontal tail plane. In the method according to the invention, forces and mechanical flight parameters on aerofoils and a horizontal tail plane of the aircraft are detected at various detection instants during at least one non-stationary flight manoeuvre of the aircraft. In this case, a linear system of equations is formed, which comprises a pitch movement moment balance equation for each detection instant, the pitch movement moment balance equation having the detected forces and mechanical flight parameters. This linear system of equations is evaluated to calculate the aerodynamic characteristics.
摘要翻译：本发明提供一种用于确定飞行器的空气动力学特性的装置和方法，特别是在没有水平尾翼平面的情况下飞行器的上升力的俯仰力矩系数和没有水平尾翼平面的飞机的空气动力学中性点。在根据本发明的方法中，在飞行器的至少一次非平稳飞行操作期间，在各种检测时刻检测飞行器的机翼和水平尾翼面上的力和机械飞行参数。在这种情况下，形成线性方程式，其包括每个检测时刻的俯仰运动力矩平衡方程，具有检测力的俯仰运动力矩平衡方程和机械飞行参数。评估该线性方程组以计算空气动力特性。

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