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1. 发明公开

US20240018903A1 SUPERSONIC SPEED ATTENUATOR OF AN AIR INTAKE OF AN AIRCRAFT PROPULSION ASSEMBLY COMPRISING A DE-ICING DEVICE AND DE-ICING METHOD 审中-公开
公开(公告)号：US20240018903A1
公开(公告)日：2024-01-18
申请号：US18247052
申请日：2021-10-01
申请人： SAFRAN NACELLES
发明人： Jean-Philippe Joret , Damien Lemoine , Charles-Antoine Lampaert , Hazem Kioua
IPC分类号： F02C7/047 , B64D33/02
CPC分类号： F02C7/047 , B64D33/02 , B64D2033/0233 , B64D2033/026 , F05D2220/80
摘要： Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.

2. 发明授权

US11752899B2 High efficiency hydrogen fueled high altitude thermodynamic fuel cell system and aircraft using same 有权
公开(公告)号：US11752899B2
公开(公告)日：2023-09-12
申请号：US17973539
申请日：2022-10-26
申请人： Joby Aero, Inc.
发明人： Gregor Veble Mikic , JoeBen Bevirt , Robert Gulliver Lynn , Alex Stoll
IPC分类号： H01M8/04 , B60L58/33 , B64D27/24 , B64C29/00 , H01M8/04701 , H01M8/04029 , H01M8/04119 , H01M8/04014 , B64D33/02
CPC分类号： B60L58/33 , B64C29/0016 , B64D27/24 , H01M8/04014 , H01M8/04029 , H01M8/04164 , H01M8/04738 , B60L2200/10 , B64D2033/024 , B64D2033/026 , B64D2033/0266 , H01M2250/20
摘要： A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

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. 发明授权

US09758253B2 Swept gradient boundary layer diverter 有权
公开(公告)号：US09758253B2
公开(公告)日：2017-09-12
申请号：US14750718
申请日：2015-06-25
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： Trajaen J. Troia , John F. Mangus
IPC分类号： B64D33/02 , B64C21/10 , B64C23/06 , B64C23/04 , B64D47/08
CPC分类号： B64D33/02 , B64C21/10 , B64C23/04 , B64C23/06 , B64D47/08 , B64D2033/0226 , B64D2033/026 , Y02T50/162 , Y02T50/166
摘要： A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.

5. 发明申请

US20160362176A1 Shock Wave Modification Method and System 审中-公开
公开(公告)号：US20160362176A1
公开(公告)日：2016-12-15
申请号：US14452113
申请日：2014-08-05
申请人： Kevin Kremeyer
发明人： Kevin Kremeyer
IPC分类号： B64C23/04 , B64D33/02 , B64G1/62 , F15D1/00 , B64C30/00
CPC分类号： B64C23/04 , B64C23/005 , B64C30/00 , B64D33/02 , B64D2033/026 , B64G1/62 , F15D1/0065 , F17D1/02 , Y02T50/166 , Y10T137/0391
摘要： A shock wave in a gas is modified by emitting energy to form an extended path in the gas; heating gas along the path to form a volume of heated gas expanding outwardly from the path; and directing a path. The volume of heated gas passes through the shock wave and modifies the shock wave. This eliminates or reduces a pressure difference between gas on opposite sides of the shock wave. Electromagnetic, microwaves and/or electric discharge can be used to heat the gas along the path. This application has uses in reducing the drag on a body passing through the gas, noise reduction, controlling amount of gas into a propulsion system, and steering a body through the gas. An apparatus is also disclosed.

6. 发明申请

US20160273452A1 SUPERSONIC CARET INLET SYSTEM 有权
标题翻译：超声心脏入口系统
公开(公告)号：US20160273452A1
公开(公告)日：2016-09-22
申请号：US14603666
申请日：2015-01-23
申请人： The Boeing Company
发明人： Thuy Huynh
IPC分类号： F02C7/042 , B64D33/02 , F02C7/057
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , B64D2033/0273 , F02C7/057 , F05D2220/80 , F05D2250/11
摘要： An engine inlet for efficient operation in both subsonic and supersonic flight wherein the inlet has a caret configuration is rotatable about an off-body axis for compression ramp angle and capture area variation and a diffuser is engaged to the inlet in a scrubbing relationship to maintain a seal upon rotation of the inlet.
摘要翻译：用于在亚音速和超音速飞行中有效操作的发动机入口，其中入口具有插入符号构型可以围绕离体轴线旋转以便压缩斜坡角度和捕获区域变化，并且扩散器以洗涤关系接合到入口以保持在入口旋转时密封。

7. 发明授权

US09353704B2 Air inlet arrangement and method of making the same 有权
标题翻译：进气口布置及其制作方法
公开(公告)号：US09353704B2
公开(公告)日：2016-05-31
申请号：US13541482
申请日：2012-07-03
申请人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , F02C7/045 , B64D33/02 , F02K7/10 , F02K7/16 , F02K7/20 , F02K1/04 , F02K1/46 , F02C7/00 , F02K7/00 , F02K3/02
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.
摘要翻译：本文公开了一种与超音速喷气发动机一起使用的入口装置，其构造成当超音速喷气发动机以预定的功率设定运行并以预定的马赫速度运动时以预定的质量流量消耗空气。空气入口装置包括但不限于具有整流罩和与整流罩同轴对准的中心体的整流罩。中心体的突出部分在前罩的上游延伸的长度大于传统的尖钉长度。突出部分构造成将在突出部分上流动的空气从入口的路径转移到超音速喷气发动机，使得接近并进入入口的剩余气流与预定质量流量匹配。

8. 发明申请

US20150344158A1 SPACE AIRCRAFT 审中-公开
标题翻译：空中飞机
公开(公告)号：US20150344158A1
公开(公告)日：2015-12-03
申请号：US14763299
申请日：2014-01-17
申请人： AIRBUS DEFENCE AND SPACE SAS
发明人： Eugénio Ferreira , Marco Prampolini , Yohann Coraboeuf
IPC分类号： B64G1/40 , B64G1/14
CPC分类号： B64D33/02 , B64D2033/0253 , B64D2033/026 , B64G1/14 , B64G1/40 , F02C7/042 , F02C7/05
摘要： According to the invention, said space aircraft comprises, at the front of each of the air inlets of the turbo engines, a mobile flap that can move, in both directions, between a first position for which said flap opens said air inlet and a second position for which said flap prevents air from entering said air inlet.
摘要翻译：根据本发明，所述太空飞行器在涡轮发动机的每个空气入口的前部包括可移动的翼片，其能够在两个方向上在所述翼片打开所述空气入口的第一位置和第二位置之间移动，所述挡板防止空气进入所述空气入口的位置。

9. 发明申请

US20150315966A1 Hypersonic Vehicle Base Drag Reduction and Improved Inlet Performance Through Venting Forebody Bleed Air to Base Area Using Open Core Ceramic Composites 审中-公开
标题翻译：超音速车辆底座通过使用开放式核心陶瓷复合材料通过排气孔将基础空气排放到底座，减少阻尼和改进的入口性能
公开(公告)号：US20150315966A1
公开(公告)日：2015-11-05
申请号：US14267716
申请日：2014-05-01
申请人： The Boeing Company
发明人： Todd Magee , Ben Y. Won
IPC分类号： F02C7/04
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/026 , F02K7/14 , F05D2220/80 , F05D2250/50 , Y10T137/0536
摘要： A system and method of air routing for an air-breathing engine is disclosed. Air enters the front of a scramjet engine via an inlet region. The inlet region is connected to a duct, which extends to the aft region of the scramjet engine where a base area of the air-breathing engine is located. The duct walls are formed using a porous structure fluidly coupled to apertures in both the inlet region and the base area. The air that enters the inlet region is routed through the porous walls of the duct and expelled at the base area. This expulsion of air through apertures in the base area causes base pressure to increase, which reduces base drag. Additionally, pulling air through perforations in the inlet region reduces the amount of low momentum flow entering the engine, which improves engine performance.
摘要翻译：公开了一种用于空气呼吸发动机的空气路径的系统和方法。空气通过入口区域进入冲击式发动机的前部。入口区域连接到管道，该管道延伸到空气呼吸发动机的基座所在的冲击式发动机的后部区域。导管壁使用流体耦合到入口区域和基部区域中的孔的多孔结构形成。进入入口区域的空气穿过管道的多孔壁，并在基部区域排出。通过基部区域中的孔的这种排出导致基础压力增加，这降低了基础阻力。此外，通过入口区域中的穿孔拉动空气减少了进入发动机的低动量流量，这提高了发动机性能。

10. 发明申请

US20150232204A1 AEROSPACE PLANE SYSTEM 审中-公开
标题翻译：航空平面系统
公开(公告)号：US20150232204A1
公开(公告)日：2015-08-20
申请号：US14390470
申请日：2013-04-04
申请人： Commercial Aerospace Plane Pty Limited
发明人： Nick Alexander
IPC分类号： B64G1/40 , B64D37/00 , B64C3/10
CPC分类号： B64G1/40 , B64C3/10 , B64C15/00 , B64C17/10 , B64D33/02 , B64D37/00 , B64D37/34 , B64D2033/026 , B64G1/002 , B64G1/14 , B64G1/405 , B64G1/58 , B64G1/62 , Y02T50/44
摘要： An aerospace plane (1) having an elongate body (2) supports a pair of wings (3). The wings are adapted to extend away from said body in opposing directions. A landing gear assembly is operatively associated with said body to be moveable from a retracted position where said assembly is substantially locatable within said body and an extended position were said assembly extends at least partially away from said body. At least one engine (10) is adapted to generate thrust. At least one stabilizer is adapted to assist with movement of said aerospace plane. The at least one engine is locatable at least partially within an intake housing (14) to direct air into said at least one engine. The intake housing having at least one door portion to open or close the intake housing to moderate the amount of air flowing into said intake housing and thereby said engine.
摘要翻译：具有细长主体（2）的航空航天飞机（1）支撑一对翼（3）。翼适于在相反方向上远离所述身体延伸。起落架组件可操作地与所述主体相关联，以便可从所述组件基本上定位在所述主体内的缩回位置移动，并且所述组件的延伸位置至少部分地远离所述主体延伸。至少一个发动机（10）适于产生推力。至少一个稳定器适于协助所述航空航天飞机的运动。所述至少一个发动机至少部分地位于进气室（14）内以将空气引导到所述至少一个发动机中。进气室具有至少一个门部分，用于打开或关闭进气室，以缓和流入所述进气室的空气量，从而抑制所述发动机。

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