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    Tow Line Tension Management Systems for Aircraft
    4.
    发明公开
    Tow Line Tension Management Systems for Aircraft 审中-公开

    公开(公告)号：US20240051661A1

    公开(公告)日：2024-02-15

    申请号：US17885053

    申请日：2022-08-10

    申请人： Textron Innovations Inc.

    发明人： Russell C. Peters ,  John Robert Wittmaak, JR. ,  Alyssa Berta Armendariz ,  Christopher John Stroncek

    IPC分类号： B64C29/00 ,  B64D3/00

    CPC分类号： B64C29/0091 ,  B64D3/00

    摘要： A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.

    Aircraft control methods
    7.
    发明授权
    Aircraft control methods 失效
    飞机控制方法

    公开(公告)号：US3831887A

    公开(公告)日：1974-08-27

    申请号：US37442973

    申请日：1973-06-28

    申请人： ROCKWELL INTERNATIONAL CORP

    发明人： FOSNESS J

    IPC分类号： F02K1/78 ,  B64C15/14 ,  B64C29/00 ,  B64C9/38

    CPC分类号： B64C29/0091

    摘要： Method of apparatus operation are disclosed for advantageously developing fluid-reaction lift control and also attitude control in improved manners in aircraft systems of the type capable of vertical, hovering, transitional, and conventional modes of flight operation. The apparatus consists of an aircraft system having an airframe with right and left primary airfoils and right and left canard airfoils, spaced-apart forward and after rotatable flap members in each airfoil which define a lift ejector diffuser section having a divergence angle, an engine operable at different rotational speeds to produce different corresponding high-energy primary fluid flows and a duct system for selectively distributing the total primary fluid flow from the engine to the lift ejector diffuser sections in each airfoil. The method of operating the control system comprises the steps of: operating the engine at a constant rotational speed and output power to produce a total primary fluid flow; distributing the total primary fluid flow to the lift ejector diffuser sections in proportions divided equally between said right and left airfoils; and changing the altitude or attitude of the aircraft by rotating the forward and after flap members in opposite directions with respect to each other in each of the airfoils to change the lift ejector divergence angles while the rotational speed, output power and total primary fluid flow of the engine and the proportional distribution of the total primary fluid flow remains constant.

    摘要翻译： 公开了装置操作的方法，以有利地开发流体反作用提升控制以及在能够垂直，悬停，过渡和常规飞行操作的类型的飞机系统中以改进的方式进行姿态控制。 该装置包括具有机身的飞机系统，其具有右和左主要翼型件以及左右翼型翼型件，每个机翼中间隔开的前后可旋转的翼片构件，其限定具有发散角的提升喷射器扩散器部分，发动机可操作 在不同的转速下产生不同的相应的高能量主流体流和用于选择性地将来自发动机的总主要流体流分配到每个翼型中的提升喷射器扩散器部分的管道系统。 操作控制系统的方法包括以下步骤：以恒定的转速操作发动机并输出功率以产生总的初级流体流; 将总主要流体流分配到升降喷射器扩散器部分，其比例在所述右翼型和左翼型之间平均分配; 并且通过在每个翼型件中相对于彼此相反的方向旋转前翼和后翼片构件来改变飞行器的高度或姿态，以改变升降喷射器发散角，同时转动速度，输出功率和总主流体流量 发动机和总的初级流体流量的比例分布保持恒定。