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1. 发明申请

WO2008041964A8 INFRARED SUPPRESSION SYSTEM 审中-公开
标题翻译：红外抑制系统
公开(公告)号：WO2008041964A8
公开(公告)日：2008-08-14
申请号：PCT/US2006029419
申请日：2006-07-27
申请人： SIKORSKY AIRCRAFT CORP
发明人： CHAPKOVICH JOHN S III , FITTS RICHARD ALAN , ZACK DAVID
IPC分类号： F02C7/00
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , F05D2210/42 , F05D2220/329 , Y02T50/671
摘要： An InfraRed Suppression System (IRSS) includes an exhaust manifold and a high aspect ratio exhaust duct along a longitudinal length thereof. The IRSS minimizes impingement of engine exhaust onto adjacent aircraft structure by discharging the flow upwardly and/or outwardly, away from the fuselage at relatively high velocity to reduce fuselage heating due to plume impingement in both hover and forward flight thus minimizing fuselage IR signature contributions. Furthermore, by directing the exhaust stream upward, a direct line of sight to the exhausted IR energy is masked from ground threats. The high aspect ratio exhaust duct and exhaust manifold are also preferably shrouded by an aerodynamic fairing which provides an aerodynamic contour to minimize aerodynamic impact to the aircraft and defines an air-cooled ejector gap to augment airflow to further insulate and obscure the high temperature exhaust gas exhausted through the exhaust duct.
摘要翻译：红外抑制系统（IRSS）包括沿其纵向长度的排气歧管和高纵横比排气管。 IRSS通过向上和/或向外，以相对较高的速度离开机身排出气流，将发动机排气冲击最小化，从而减少由于在悬停和向前飞行中的羽流撞击而导致的机身加热，从而使机身IR签名贡献最小化。此外，通过将排气流向上引导，红外线能量的直接视线被地面威胁所掩盖。高纵横比排气管和排气歧管最好还被空气动力学整流罩覆盖，该空气动力整流罩提供空气动力学轮廓以最小化对飞机的空气动力学冲击，并限定空气冷却喷射器间隙以增大气流以进一步隔离和遮蔽高温排气通过排气管排出。

2. 发明申请

WO2008041964A3 INFRARED SUPPRESSION SYSTEM 审中-公开
标题翻译：红外抑制系统
公开(公告)号：WO2008041964A3
公开(公告)日：2008-10-02
申请号：PCT/US2006029419
申请日：2006-07-27
申请人： SIKORSKY AIRCRAFT CORP
发明人： CHAPKOVICH JOHN S III , FITTS RICHARD ALAN , ZACK DAVID
IPC分类号： F02C7/08 , F02G1/00 , F02G3/00
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , F05D2210/42 , F05D2220/329 , Y02T50/671
摘要： An InfraRed Suppression System (IRSS) includes an exhaust manifold and a high aspect ratio exhaust duct along a longitudinal length thereof. The IRSS minimizes impingement of engine exhaust onto adjacent aircraft structure by discharging the flow upwardly and/or outwardly, away from the fuselage at relatively high velocity to reduce fuselage heating due to plume impingement in both hover and forward flight thus minimizing fuselage IR signature contributions. Furthermore, by directing the exhaust stream upward, a direct line of sight to the exhausted IR energy is masked from ground threats. The high aspect ratio exhaust duct and exhaust manifold are also preferably shrouded by an aerodynamic fairing which provides an aerodynamic contour to minimize aerodynamic impact to the aircraft and defines an air-cooled ejector gap to augment airflow to further insulate and obscure the high temperature exhaust gas exhausted through the exhaust duct.
摘要翻译：红外线抑制系统（IRSS）包括沿其纵向长度的排气歧管和高纵横比排气管道。 IRSS通过以相对较高的速度将机身向上和/或向外排放离开机身，将发动机排气的冲击最小化，以减少由于在悬停和向前飞行中的羽流撞击造成的机身加热，从而使机身IR特征贡献最小化。此外，通过向上引导排气流，对被耗尽的IR能量的直接视线被地面威胁掩蔽。高纵横比排气管道和排气歧管还优选地由空气动力学整流罩覆盖，空气动力学整流罩提供空气动力学轮廓以最小化对飞行器的空气动力学冲击，并限定空气冷却喷射器间隙以增加气流以进一步绝热和模糊高温废气通过排气管排出。

3. 发明公开

EP1943419A4 INFRARED SUPPRESSION SYSTEM 失效
标题翻译：红外抑制系统
公开(公告)号：EP1943419A4
公开(公告)日：2009-04-15
申请号：EP06851667
申请日：2006-07-27
申请人： SIKORSKY AIRCRAFT CORP
发明人： CHAPKOVICH JOHN S III , FITTS RICHARD ALAN , ZACK DAVID
IPC分类号： F02C7/08 , B64D33/04
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , F05D2210/42 , F05D2220/329 , Y02T50/671
摘要： An InfraRed Suppression System (IRSS) includes an exhaust manifold and a high aspect ratio exhaust duct along a longitudinal length thereof. The IRSS minimizes impingement of engine exhaust onto adjacent aircraft structure by discharging the flow upwardly and/or outwardly, away from the fuselage at relatively high velocity to reduce fuselage heating due to plume impingement in both hover and forward flight thus minimizing fuselage IR signature contributions. Furthermore, by directing the exhaust stream upward, a direct line of sight to the exhausted IR energy is masked from ground threats. The high aspect ratio exhaust duct and exhaust manifold are also preferably shrouded by an aerodynamic fairing which provides an aerodynamic contour to minimize aerodynamic impact to the aircraft and defines an air-cooled ejector gap to augment airflow to further insulate and obscure the high temperature exhaust gas exhausted through the exhaust duct.

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