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1. 发明公开

US20230249837A1 INLET ARRANGEMENT, A PROPULSION SYSTEM, AND AN AIRCRAFT 审中-公开
公开(公告)号：US20230249837A1
公开(公告)日：2023-08-10
申请号：US17650318
申请日：2022-02-08
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund , Derek Muzychka , Douglas Klutzke
IPC分类号： F01D25/24 , B64D27/26 , B64D27/02 , B64D29/06
CPC分类号： F01D25/24 , B64D27/26 , B64D27/02 , B64D29/06
摘要： An inlet arrangement for a propulsion system includes an actuator, a linkage and an inlet assembly. The inlet assembly includes (1) a lip, (2) a cowl extending downstream from the lip, the cowl defining an external surface of the inlet assembly, (3) an inlet duct extending downstream from the lip, the inlet duct disposed radially inward of the cowl, and (4) a movable component associated with the lip, the cowl, or the inlet duct. An outer surface of the inlet duct and an inner surface of the cowl define a gap therebetween. The linkage is disposed in the gap and coupled with the moveable component. The linkage is configured to move within the gap and to move the moveable component when the linkage moves. The actuator is coupled with the linkage and moves the linkage when the actuator is actuated. The actuator is mounted remotely from the inlet assembly.

2. 发明申请

US20140224926A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 有权
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：US20140224926A1
公开(公告)日：2014-08-14
申请号：US14176865
申请日：2014-02-10
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund
IPC分类号： B64C23/00 , B64C3/38 , B64C3/42 , B64C30/00
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.
摘要翻译：用于控制声波起重臂的大小的系统包括被配置为检测超音速飞行器的第一状态的第一传感器。该系统还包括一对构造成前后移动的翼。所述系统还包括处理器，其与所述传感器通信地耦合并且与所述一对机翼可操作地耦合。处理器被配置为（1）从第一传感器接收指示第一条件的第一信息，（2）基于第一信息计算超音速飞机的升力分布，（3）确定存在基于飞行条件从所需的升力分布提升分配，以及（4）控制所述一对翼移动以以更符合期望的升力分布的方式重新分配升力。当偏差减小时，声音臂的大小减小。

3. 发明授权

US11686246B2 Propulsion system for an aircraft 有权
公开(公告)号：US11686246B2
公开(公告)日：2023-06-27
申请号：US17451137
申请日：2021-10-15
申请人： Gulfstream Aerospace Corporation
发明人： Shawn Bennett , Joe Gavin , Nicholas Powell , Donald Freund , Derek Muzychka , John Louis
IPC分类号： F02C7/042 , F02C7/057 , F02K1/16 , B64D33/02
CPC分类号： F02C7/042 , F02C7/057 , F02K1/165 , B64D2033/0206 , B64D2033/026 , B64D2033/0226 , F05D2220/323 , F05D2270/122
摘要： An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.

4. 发明申请

US20140224925A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 有权
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：US20140224925A1
公开(公告)日：2014-08-14
申请号：US14176843
申请日：2014-02-10
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund
IPC分类号： B64C23/00 , B64D37/00 , B64C30/00
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation.
摘要翻译：本文公开了用于控制由超音速飞行器超超速度的偏离设计条件操作引起的声波起重量的方法和系统。该方法包括但不限于用处理器监测超音速飞机的重量和超音速飞机上的燃料分配。该方法还包括但不限于与处理器确定超音速飞机的重量与设计条件权重的偏差。该方法还包括但不限于与处理器一起控制超音速飞机上的燃料的重新分配，以调节存储在机翼内的燃料量，以最小化由偏差引起的机翼扭转。这种重新分配将减少由偏差引起的声波爆震的大小。

5. 发明公开

US20240280065A1 NOZZLE ASSEMBLY FOR USE WITH A PROPULSION SYSTEM AND SLEEVE ASSEMBLY FOR USE WITH THE NOZZLE ASSEMBLY 审中-公开
公开(公告)号：US20240280065A1
公开(公告)日：2024-08-22
申请号：US18646133
申请日：2024-04-25
申请人： Gulfstream Aerospace Corporation
发明人： Derek Muzychka , Donald Freund , Andrew Clemens , John Louis , Joseph Gavin , Till Gerhardt , William Mcfarland , Benjamin Walke
IPC分类号： F02K1/76 , B64C7/02 , F02K1/72
CPC分类号： F02K1/763 , B64C7/02 , F02K1/72 , F05D2220/323
摘要： Various non-limiting embodiments of a nozzle assembly for use with a propulsion system and a sleeve assembly for use with the nozzle assembly are disclosed herein. In a non-limiting embodiment, the nozzle assembly includes, but is not limited to, a nacelle. The nozzle assembly further includes, but is not limited to, a sleeve assembly mounted within the nacelle downstream of the engine. The sleeve assembly is configured to receive the mass flow from the engine and to guide the mass flow to an exit of the propulsion system. The sleeve assembly is comprised of a plurality of sleeve segments arranged in a circumferential configuration. Each sleeve segment of the plurality of sleeve segments has an elongate body that is longitudinally aligned with a longitudinal axis of the sleeve assembly.

6. 发明公开

US20240059421A1 EXHAUST NOZZLE ASSEMBLY, PROPULSION SYSTEM EMPLOYING THE EXHAUST NOZZLE ASSEMBLY, AND AIRCRAFT EMPLOYING THE PROPULSION SYSTEM 审中-公开
公开(公告)号：US20240059421A1
公开(公告)日：2024-02-22
申请号：US18494181
申请日：2023-10-25
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund , Derek Muzychka
IPC分类号： B64D33/04 , B64D27/16 , B64D29/02 , B64D29/04 , B64D29/06 , F02K1/56 , F02K1/76
CPC分类号： B64D33/04 , B64D27/16 , B64D29/02 , B64D29/04 , B64D29/06 , F02K1/56 , F02K1/763
摘要： An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

7. 发明申请

US20220009645A1 PROPULSION SYSTEM, AIRCRAFT HAVING A PROPULSION SYSTEM, AND METHOD OF MANUFACTURING AN AIRCRAFT 有权
公开(公告)号：US20220009645A1
公开(公告)日：2022-01-13
申请号：US17302325
申请日：2021-04-30
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund , Derek Muzychka , Douglas Klutzke
IPC分类号： B64D27/26 , B64D29/04 , B64D29/02 , B64D27/18 , B64D27/20
摘要： A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine. The propulsion system further includes, but is not limited to, an outer cover associated with the engine. The engine and the outer cover are configured for coupling to the aircraft. The propulsion system further includes, but is not limited to, an external engine component. The propulsion system still further includes, but is not limited to, a coupler that operatively couples the external engine component to the engine. The external engine component is configured to be coupled to the aircraft at a location spaced apart from the engine.

8. 发明公开

US20240125286A1 NOZZLE ASSEMBLY FOR USE WITH A PROPULSION SYSTEM 审中-公开
公开(公告)号：US20240125286A1
公开(公告)日：2024-04-18
申请号：US18307162
申请日：2023-04-26
申请人： Gulfstream Aerospace Corporation
发明人： Derek Muzychka , Donald Freund , Andrew Clemens , John Louis , Joseph Gavin , Till Gerhardt , William Mcfarland , Benjamin Walke
IPC分类号： F02K1/76 , B64C7/02 , F02K1/72
CPC分类号： F02K1/763 , B64C7/02 , F02K1/72 , F05D2220/323
摘要： A nozzle assembly includes a sleeve defining a pathway, the sleeve disposed within a nacelle. The pathway and an internal surface of the nacelle guides a mass flow from an engine to an exit of the propulsion system. The sleeve is configured to move between a forward position an aft position within the nacelle aft of the engine. The sleeve has a protruding portion that extends towards a center of the pathway and that defines a smallest internal diameter of the sleeve. The sleeve includes a plurality of sleeve segments that are longitudinally aligned and circumferentially arranged to form the sleeve. The sleeve segments are configured to move circumferentially closer as the sleeve moves in a first direction within the nacelle and to move circumferentially further apart as the sleeve moves in a second direction within the nacelle. An actuator is coupled with, and is configured to move the sleeve.

9. 发明申请

US20230120249A1 PROPULSION SYSTEM FOR AN AIRCRAFT 有权
公开(公告)号：US20230120249A1
公开(公告)日：2023-04-20
申请号：US17451137
申请日：2021-10-15
申请人： Gulfstream Aerospace Corporation
发明人： Shawn Bennett , Joe Gavin , Nicholas Powell , Donald Freund , Derek Muzychka , John Louis
IPC分类号： F02C7/042 , B64D27/20 , F02K1/72 , F02K1/76 , F02K1/12 , F02C7/057
摘要： An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.

10. 发明申请

US20210316875A1 EXHAUST NOZZLE ASSEMBLY, PROPULSION SYSTEM EMPLOYING THE EXHAUST NOZZLE ASSEMBLY, AND AIRCRAFT EMPLOYING THE PROPULSION SYSTEM 有权
公开(公告)号：US20210316875A1
公开(公告)日：2021-10-14
申请号：US17301239
申请日：2021-03-30
申请人： Gulfstream Aerospace Corporation
发明人： Donald Freund , Derek Muzychka
IPC分类号： B64D33/04 , B64D27/16 , B64D29/06 , B64D29/02 , B64D29/04 , F02K1/56 , F02K1/76
摘要： An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

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