公开(公告)号：US5897078A

公开(公告)日：1999-04-27

申请号：US756154

申请日：1996-11-26

申请人： Robert W. Burnham ,  Michael F. Fitzpatrick ,  Dennis A. Muilenberg ,  Joseph K. Schoebelen ,  Laurence B. Trollen

发明人： Robert W. Burnham ,  Michael F. Fitzpatrick ,  Dennis A. Muilenberg ,  Joseph K. Schoebelen ,  Laurence B. Trollen

IPC分类号： B64C20060101 ,  B64C1/00 ,  B64C1/06 ,  B64C29/00

CPC分类号： B64C1/0009 ,  B64C1/061 ,  B64C29/00 ,  B64C29/0066 ,  B64C2039/105

摘要： A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing; a forebody section, including a cockpit, which is mounted to the front of the wing; and a propulsion system support frame mounted beneath the forebody section and the underside of the wing. The propulsion system is supported within this frame. The aircraft can also include an aftbody section mounted to the aft end of the wing, which includes a 2-D variable thrust vectoring nozzle and a pair of canted vertical tails. The forebody section includes a chin inlet below the cockpit. The wing is preferably constructed using thermoplastic welding.

摘要翻译： 制造高性能军用飞机的模块化方法使不同的飞机能够以合理的成本制造，并且具有高的部件号通用性。 这样构造的飞机包括三角翼; 前身部分，包括安装在机翼前部的驾驶舱; 以及安装在机翼前部和下侧的推进系统支撑框架。 在此框架内支持推进系统。 飞机还可以包括安装在机翼的后端的船体部分，其包括2-D可变推力矢量喷嘴和一对倾斜的垂直尾部。 前身部分包括驾驶舱下方的下巴入口。 翼优选地使用热塑性焊接构造。