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2. 发明授权

US06164563A Converging exhaust nozzle fitted with translating cold flaps 有权
标题翻译：融合排气喷嘴配有翻转冷襟翼
公开(公告)号：US06164563A
公开(公告)日：2000-12-26
申请号：US356321
申请日：1999-07-16
申请人： Philippe Pierre Vincent Bouiller , Pierre-Yves Bourquin , Fabrice Michel Olivier Cot , Daniel Kettler , Jean-Pierre Ruis
发明人： Philippe Pierre Vincent Bouiller , Pierre-Yves Bourquin , Fabrice Michel Olivier Cot , Daniel Kettler , Jean-Pierre Ruis
IPC分类号： F02K1/11 , F02K1/82 , B05B12/00
CPC分类号： F02K1/11 , F02K1/825 , F05D2250/323 , F05D2250/34
摘要： A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).
摘要翻译：一种用于飞行器的喷射推进系统的气体流动排气组件，其中会聚的排气喷嘴（4）装配有平移的冷襟翼（21,22）。主排气喷嘴（4）包括位于由飞行器整流罩（2）包围的主管道（1）之外的两个热襟翼（5,6）。整流罩（2）由辅助排气喷嘴（20）延伸，二次排气喷嘴（20）由主管道（1）支撑，并可由控制机构（27a，27b）平移。二次排气喷嘴（20）包括与另一个控制机构（29a，29b）驱动的冷襟翼（21,22），独立于热襟翼（5,6）的角位置。优选地，在水平横向轴（23a，23b）上铰接并支撑有两个眼睑形冷舌片（21,22）。轴（23a，23b）优选地固定在两个横向滑动件（24a，24b）上，滑动件（24a，24b）在主导管（1）上滑动，并可通过使辅助排气喷嘴（20）平移的控制机构（27a，27b）移动。

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