公开(公告)号：US5273237A

公开(公告)日：1993-12-28

申请号：US970747

申请日：1992-11-02

申请人： Robert W. Guyton ,  Jon A. Tinapple ,  Kenneth C. Cornelius

发明人： Robert W. Guyton ,  Jon A. Tinapple ,  Kenneth C. Cornelius

IPC分类号： B64C15/14 ,  F41G7/00 ,  F42B10/60

CPC分类号： F42B10/663 ,  B64C15/14

摘要： A system for augmenting yaw control in an aircraft is described which comprises first and second thrust nozzles disposed on the upper surface of the aircraft forebody aft of the forebody nose apex a distance of about 0.5 times the forebody diameter at about 45.degree. to either side of the symmetry plane of the forebody, each thrust nozzle oriented to direct a fluid jet at an angle of about 10.degree. from the surface of the forebody and generally rearwardly toward the symmetry plane at about 60.degree. .+-.10.degree. to the symmetry plane, and a source of pressurized fluid operatively connected to the thrust nozzles for generating the jets.

摘要翻译： 描述了一种用于增加飞行器中的偏航控制的系统，其包括设置在飞行器的上表面上的第一和第二推力喷嘴的前身前部顶点的后部约为前体直径的约0.5倍的距离， 前体的对称平面，每个推力喷嘴定向成以与前体表面大约10°的角度引导流体射流，大致向对称平面向对称平面向对称面约60°+/- 10°， 以及可操作地连接到推力喷嘴以产生射流的加压流体源。