公开(公告)号：WO2015048695A1

公开(公告)日：2015-04-02

申请号：PCT/US2014/058145

申请日：2014-09-29

Applicant: LONG RANGE AG ,  KIRK, Philip ,  PRAKASH, Om ,  SWIFT, Peter

Inventor： KIRK, Philip ,  PRAKASH, Om ,  SWIFT, Peter

IPC: B64C1/20 ,  B64D37/00 ,  B64D37/04 ,  B64D37/20

CPC classification number: B60K15/06 ,  B60K15/035 ,  B60K15/067 ,  B60K2015/03144 ,  B60K2015/03164 ,  B60K2015/03217 ,  B60K2015/03447 ,  B64C1/20 ,  B64D37/00 ,  B64D37/04 ,  B64D37/20 ,  Y10T137/6906 ,  Y10T137/86187 ,  Y10T137/86196

Abstract: An aircraft auxiliary fuel tank system comprising a master tank and a plurality of slave tanks connectable to the master tank. The slave tanks can be easily added or removed to adjust fuel capacity. A rail assembly is provided to assist in the easy installation and removal of the slave and master fuel tanks. Methods are provided for using the auxiliary fuel tanks system and for providing a service for slave tank distribution, reservation and installation.

Abstract translation: 一种飞机辅助油箱系统，包括主油箱和可连接到主油箱的多个从油箱。 可以方便地添加或移除子液箱以调节燃油容量。 提供了一种轨道组件，以帮助容易地安装和拆卸从动和主燃料箱。 提供了使用辅助燃料箱系统和提供从罐分配，预约和安装的服务的方法。

公开(公告)号：WO2014126860A1

公开(公告)日：2014-08-21

申请号：PCT/US2014/015600

申请日：2014-02-10

Applicant: GULFSTREAM AEROSPACE CORPORATION ,  FREUND, Donald

Inventor： FREUND, Donald

IPC: B64C30/00

CPC classification number: B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

Abstract: A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.

Abstract translation: 用于控制由超音速飞行器的脱离设计操作引起的声音吊杆的大小的系统包括被配置为检测超音速飞行器的状况的传感器。 该系统还包括安装在超音速飞行器的机翼上的控制表面。 系统还包括通信地耦合到传感器并且与控制表面可操作地耦合的处理器。 处理器被配置为（1）从传感器接收指示超音速飞行器的状况的信息，（2）基于该信息确定升力分布与设计状况提升分布之间存在偏差，并且（3 ）控制控制面以减少偏差的方式移动。 当偏差减小时，声音臂的大小减小。

公开(公告)号：WO2014126858A1

公开(公告)日：2014-08-21

申请号：PCT/US2014/015591

申请日：2014-02-10

Applicant: GULFSTREAM AEROSPACE CORPORATION ,  FREUND, Donald

Inventor： FREUND, Donald

IPC: B64C30/00

CPC classification number: B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2010058147A1

公开(公告)日：2010-05-27

申请号：PCT/GB2008/051084

申请日：2008-11-19

Applicant: AIRBUS UK LIMITED ,  SJUNGARGÅRD, Petter

Inventor： SJUNGARGÅRD, Petter

IPC: B64C17/10 ,  B64D37/14

CPC classification number: B64C17/10 ,  B64D37/00

Abstract: A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks (2, 4, 6, 10, 12), the fuel monitoring system comprises a fuel quantity sensor (14) arranged to measure the quantity of fuel in a first fuel tank (10) and a data processor (16) arranged to receive a fuel quantity measurement from the sensor, wherein in response to receiving a command to transfer fuel from the first fuel tank to one or more further fuel tanks (12) the data processor is arranged to determine the rate of change of fuel quantity in the first tank from the received fuel quantity measurement and if the rate of change of fuel quantity is less than a threshold value and the received fuel quantity measurement is greater than an expected value then the data processor is further arranged to provide an output indicating that the commanded fuel transfer has failed.

Abstract translation: 一种用于自动监测飞行器燃料系统中的燃料转移的燃料监测系统，所述燃料系统包括多个燃料箱（2,4,6,10,12），所述燃料监测系统包括燃料量传感器（14），其布置 测量第一燃料箱（10）和布置成从传感器接收燃料量测量的数据处理器（16）中的燃料量，其中响应于接收到将燃料从第一燃料箱转移到一个或 更多的燃料箱（12），数据处理器被布置成从接收的燃料量测量中确定第一罐中的燃料量的变化率，并且如果燃料量的变化率小于阈值，并且接收的燃料 数量测量值大于期望值，则数据处理器进一步被布置成提供指示所指示的燃料转移失败的输出。

公开(公告)号：WO2008011217A3

公开(公告)日：2008-03-06

申请号：PCT/US2007069134

申请日：2007-05-17

Applicant: INSITU GROUP INC ,  JOHNSON ROGER F

Inventor： JOHNSON ROGER F

IPC: G01F23/292 ,  B64D37/02

CPC classification number: B64D37/00 ,  G01F23/292 ,  G01N21/41 ,  G01N2021/5957

Abstract: Fluid sensing systems and methods, including sensors used to sense various fluid levels in vehicles, are disclosed herein. One aspect of the invention is directed toward a method for sensing a fluid that includes passing electromagnetic radiation through a receptacle positioned to hold a fluid. The receptacle can be configured so that electromagnetic radiation that passes through portions of the receptacle containing fluid is focused. The method can further include determining (a) whether fluid is located in a selected portion of the receptacle based on an amount of electromagnetic radiation that impinges on at least one radiation sensor, (b) a characteristic of fluid located in the passageway of the selected portion based on a pattern of the electromagnetic radiation that is created on the at least one radiation sensor, or (c) both (a) and (b).

Abstract translation: 本文公开了包括用于感测车辆中的各种液位的传感器的流体感测系统和方法。 本发明的一个方面涉及一种用于感测流体的方法，该方法包括使电磁辐射穿过定位成容纳流体的容器。 容器可以被配置为使得穿过容纳流体的容器的部分的电磁辐射被聚焦。 该方法可以进一步包括基于撞击在至少一个辐射传感器上的电磁辐射的量来确定（a）流体是否位于容器的选定部分中，（b）位于选定的通道中的流体的特性 基于在所述至少一个辐射传感器上创建的电磁辐射的图案的部分，或（c）（a）和（b）两者。

公开(公告)号：WO2008011217A2

公开(公告)日：2008-01-24

申请号：PCT/US2007/069134

申请日：2007-05-17

Applicant: THE INSITU GROUP, INC. ,  JOHNSON, Roger, F.

Inventor： JOHNSON, Roger, F.

IPC: B64D37/02

CPC classification number: B64D37/00 ,  G01F23/292 ,  G01N21/41 ,  G01N2021/5957

Abstract: Fluid sensing systems and methods, including sensors used to sense various fluid levels in vehicles, are disclosed herein. One aspect of the invention is directed toward a method for sensing a fluid that includes passing electromagnetic radiation through a receptacle positioned to hold a fluid. The receptacle can be configured so that electromagnetic radiation that passes through portions of the receptacle containing fluid is focused. The method can further include determining (a) whether fluid is located in a selected portion of the receptacle based on an amount of electromagnetic radiation that impinges on at least one radiation sensor, (b) a characteristic of fluid located in the passageway of the selected portion based on a pattern of the electromagnetic radiation that is created on the at least one radiation sensor, or (c) both (a) and (b).

Abstract translation: 本文公开了流体感测系统和方法，包括用于检测车辆中的各种液位的传感器。 本发明的一个方面涉及一种用于感测流体的方法，该方法包括使电磁辐射通过定位成保持流体的容器。 容器可以被配置成使得通过包含流体的容器的部分的电磁辐射被聚焦。 该方法还可以包括：（a）基于撞击在至少一个辐射传感器上的电磁辐射的量，确定流体是否位于容器的选定部分中，（b）位于所选择的通道中的流体的特性 基于在至少一个辐射传感器上产生的电磁辐射的图案的部分，或（c）（a）和（b）两者。

公开(公告)号：WO2007008185A3

公开(公告)日：2007-04-12

申请号：PCT/US2004043618

申请日：2004-12-29

Applicant: GULFSTREAM AEROSPACE CORP ,  WOZNIAK GREGG ,  LAMB DAVID ,  LE DUNG

Inventor： WOZNIAK GREGG ,  LAMB DAVID ,  LE DUNG

IPC: B64D37/00 ,  B64C17/10

CPC classification number: B64C17/10 ,  B64D37/00

Abstract: Method and arrangement for dispersing fuel (62) within a fuel containment system (60) of an aircraft (30) including utilizing a fuel containment system on an aircraft that is located at least partially within a wing (34) of the aircraft and defines a reservoir portion (42) and a remote portion (44). Fuel is pumped during aircraft flight from the reservoir portion to the remote portion at a pumped rate (80), while simultaneously fuel that is contained in the remote portion of the fuel containment system is permitted to drain to the reservoir portion at a drainage rate (82). The drainage rate is less than the pumped rate. A fuel mass (64) is accumulated in the remote portion of the fuel containment system because of a difference between the pumped rate and the drainage rate and as a result, a counteractive moment (49) is induced in the aircraft that is opposingly directed to a lift moment (46) caused by wing-lift (45) during aircraft flight.

Abstract translation: 用于将燃料（62）分散在飞机（30）的燃料容纳系统（60）内的方法和装置，包括利用飞机上的燃料容纳系统，该飞机至少部分地位于飞机的机翼（34）内并限定 储存器部分（42）和远程部分（44）。 燃料在飞机飞行期间以泵送速率（80）从储存器部分泵送至远程部分，同时允许容纳在燃料容纳系统的远程部分中的燃料以排出速率排出至储存器部分（ 82）。 排水率低于抽水率。 由于泵送速率与排放速率之间的差异，燃料容积（64）积聚在燃料容纳系统的远端部分中，并且因此在飞机中引起反作用力矩（49），该力矩相反地指向 在飞机飞行期间由机翼升力（45）引起的升力矩（46）。

公开(公告)号：WO99032857A1

公开(公告)日：1999-07-01

申请号：PCT/US1998/015134

申请日：1998-07-22

IPC: B64D37/00 ,  G01F23/00 ,  G01F23/18 ,  G01F23/296 ,  G01F17/00 ,  G01F23/16

CPC classification number: G01F23/296 ,  B64D37/00 ,  G01F23/0069 ,  G01F23/0076 ,  G01F23/18

Abstract: Liquid gauging system for liquid in a container includes a plurality of sensors; each of the sensors measuring a respective parameter of the liquid in the container and producing a sensor output related to its measured parameter; there being at least two sensors that measure different parameters of the liquid; and a processor that receives the sensor outputs and determines, based on the sensor outputs, a quantity of the liquid in the container; the processor determining the quantity by executing at least one sensor fusion algorithm that is based on a set of relationships between the measured parameters and the quantity. The gauging system can also include a data fusion process for determining quantity based on a plurality of quantity measurements.

Abstract translation: 用于容器中的液体的液体测量系统包括多个传感器; 每个传感器测量容器中的液体的相应参数，并产生与其测量参数相关的传感器输出; 至少有两个测量液体不同参数的传感器; 以及处理器，其接收所述传感器输出并基于所述传感器输出确定所述容器中的液体的量; 所述处理器通过执行至少一个传感器融合算法来确定所述数量，所述至少一个传感器融合算法基于所述测量参数与所述量之间的一组关系。 测量系统还可以包括用于基于多个量测量来确定数量的数据融合过程。

公开(公告)号：WO2016154414A1

公开(公告)日：2016-09-29

申请号：PCT/US2016/023975

申请日：2016-03-24

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： CIRIOLI, Adriano ,  SHIELDS, Daniel John ,  MEYER, Alex

IPC: F02C7/22 ,  F02M37/18 ,  F02C7/236 ,  B64D37/04 ,  B64D37/02 ,  B64D37/00

CPC classification number: B64D37/10 ,  B64D37/00 ,  F02C7/236 ,  F02M37/10 ,  F02M37/103 ,  F02M37/18 ,  Y02T50/44

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract translation: 用于飞行器的燃料供应系统包括：燃料箱，其配置成将燃料供应到飞行器的发动机;与所述燃料箱运行连通的升压泵，其中所述增压泵构造成控制燃料液位和 燃料箱中的燃料压力以及与升压泵连通并被配置为控制升压泵的电子控制器。 电子控制器被配置为接收包括（i）燃料信息，（ii）飞行信息和（iii）飞机信息）的接收信息，并且被配置为基于接收的信息来控制升压泵。

公开(公告)号：WO2016046485A1

公开(公告)日：2016-03-31

申请号：PCT/FR2015/052532

申请日：2015-09-22

Applicant: ZODIAC AEROTECHNICS

Inventor： DUMAS, Florian ,  TRAVERS, Nicolas

IPC: F04B43/00 ,  B64D37/00

CPC classification number: B64D37/005 ,  B64D37/00 ,  B64D37/16 ,  B64D41/00 ,  F04B43/02 ,  Y02T50/44

Abstract: La présente invention concerne un procédé de circulation de carburant dans un aéronef, remarquable en ce qu'il consiste à utiliser d'au moins une pompe à membrane ondulante (1) apte à onduler, sous l'action de moyens d'actionnement, entre deux flasques pour faire circuler ledit carburant entre une conduite d'admission (4) de la pompe (1) jusqu'à une conduite d'échappement (5) de la pompe (1).

Abstract translation: 本发明涉及一种用于在飞行器中循环燃料的方法，其特征在于，其包括使用至少一个隔膜泵（1），该隔膜泵（1）具有波动隔膜，其可在致动装置的作用下在两个凸缘之间波动，以便循环 所述燃料在所述泵（1）的进入管线（4）和所述泵（1）的排气管线（5）之间。