-
公开(公告)号：US5796612A
公开(公告)日：1998-08-18
申请号：US208455
申请日：1994-03-09
申请人： Steven D. Palmer
发明人： Steven D. Palmer
摘要： The present invention relates to a method for three-dimensional flight control based generally upon measuring and comparing actual air pressures at or near various surfaces of an aircraft during flight. Sensors are provided for measuring air pressure acting on the aircraft surface. The method includes measuring air pressure differentials between two or more sensors to evaluate certain critical flight parameters, such as the actual lift being produced, the air direction and speed relative to the aircraft, the air density, and the aircraft position and trajectory. The actual and comparative data provide information about the present flight conditions and performance if the aircraft, such as whether there is ice formed or forming on the wings, the direction and approach of wind shear, whether a stall is approaching, etc. The information can be evaluated by a computer, the aircraft's automatic flight control system ("AFCS"), or flight crew so that appropriate flight control measures can be taken.
摘要翻译： 本发明涉及一种用于三维飞行控制的方法，其基本上通过测量和比较飞行中飞行器各个表面处或附近的实际空气压力。 传感器用于测量作用在飞机表面上的空气压力。 该方法包括测量两个或更多个传感器之间的空气压力差，以评估某些关键飞行参数，例如正在产生的实际升力，相对于飞行器的空气方向和速度，空气密度和飞机位置和轨迹。 实际和比较数据提供有关当前飞行条件和性能的信息，如果飞机是否形成或形成在翅膀上，风切换的方向和接近，失速是否接近等等。信息可以 由飞机的自动飞行控制系统（“AFCS”）或飞行机组进行评估，以便采取适当的飞行控制措施。
-
2.发明授权
公开(公告)号：US6002972A
公开(公告)日：1999-12-14
申请号：US55834
申请日：1998-04-06
申请人： Steven D. Palmer
发明人： Steven D. Palmer
摘要： A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.
摘要翻译： 一种用于测量由飞行器的翼型件产生的升力的方法和装置。 该实时分析通过测量翼型的上升和下升升程表面之间的差压来实现。 该系统包括以下步骤：a）对于给定的飞行速度，测量上升和下升表面之间的实际差压; b）将该实际差压测量传送到计算机; c）将实际差压测量与最佳 相同飞行器速度的压差。 该装置包括用于测量实际压力差的差压传感器机构的固定阵列和用于将最佳压差测量值与实际差压测量值进行比较的计算机。 每个传感器机构优选地包含与上部和下部提升表面连通的压电传感器。
-
公开(公告)号：US06253126B1
公开(公告)日：2001-06-26
申请号：US09076376
申请日：1998-05-12
申请人： Steven D. Palmer
发明人： Steven D. Palmer
IPC分类号： G06F770
摘要： Methods and apparatus are disclosed for three-dimensional flight control based generally upon measuring and comparing actual air pressures at or near various surfaces of an aircraft during flight. Sensors are provided for measuring air pressure acting on an aircraft surface. The methods and apparatus include those for measuring air pressure differentials between two or more sensors to evaluate certain critical flight parameters, such as the actual lift being produced, the air direction and speed relative to the aircraft, the air density, and the aircraft position and trajectory. The actual and comparative data provide information about the present flight conditions and performance of the aircraft, such as whether there is ice formed or forming on the wings, the direction and approach of wind shear, whether a stall is approaching, etc. The information can be evaluated by a computer, the aircraft's automatic flight control system (“AFCS”), or flight crew so that appropriate flight control measures can be taken.
摘要翻译： 公开了用于三维飞行控制的方法和装置，其通常基于在飞行中测量和比较飞行器各个表面处或附近的实际空气压力。 传感器用于测量作用在飞机表面上的空气压力。 这些方法和装置包括用于测量两个或更多个传感器之间的空气压差的那些，以评估某些关键飞行参数，例如正在产生的实际升力，相对于飞行器的空气方向和速度，空气密度和飞机位置， 弹道。 实际和比较数据提供有关当前飞行条件和飞机性能的信息，例如机翼上是否有冰块形成或形成风挡，风切变方向和接近方式，档位是否接近等。信息可以 由飞机的自动飞行控制系统（“AFCS”）或飞行机组进行评估，以便采取适当的飞行控制措施。
-
4.发明授权
公开(公告)号：US5737222A
公开(公告)日：1998-04-07
申请号：US540262
申请日：1995-10-06
申请人： Steven D. Palmer
发明人： Steven D. Palmer
摘要： An apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The apparatus a) measures an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmits this actual differential pressure measurement to a computer, c) compares the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed, and d) evaluates performance of the aircraft based on the result of the comparison. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.
摘要翻译： 一种用于测量由飞行器的翼型件产生的升力的装置。 该实时分析通过测量翼型的上升和下升升程表面之间的差压来实现。 设备a）测量给定飞行器速度的上升和下升表面之间的实际差压，b）将该实际差压测量传输到计算机，c）将实际差压测量与相同的最佳压力差进行比较 飞机速度，以及d）根据比较结果评估飞机的性能。 该装置包括用于测量实际压力差的差压传感器机构的固定阵列和用于将最佳压差测量值与实际差压测量值进行比较的计算机。 每个传感器机构优选地包含与上部和下部提升表面连通的压电传感器。
-
公开(公告)号：US5457630A
公开(公告)日：1995-10-10
申请号：US978347
申请日：1992-11-18
申请人： Steven D. Palmer
发明人： Steven D. Palmer
摘要： A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.
摘要翻译： 一种用于测量由飞行器的翼型件产生的升力的方法和装置。 该实时分析通过测量翼型的上升和下升升程表面之间的差压来实现。 该系统包括以下步骤：a）对于给定的飞行速度，测量上升和下升表面之间的实际差压; b）将该实际差压测量传送到计算机; c）将实际差压测量与最佳 相同飞行器速度的压差。 该装置包括用于测量实际压力差的差压传感器机构的固定阵列和用于将最佳压差测量值与实际差压测量值进行比较的计算机。 每个传感器机构优选地包含与上部和下部提升表面连通的压电传感器。
-
-
-
-
搜索结果
5 条记录 (耗时 0.014 秒)
