公开(公告)号：WO2008054521A2

公开(公告)日：2008-05-08

申请号：PCT/US2007/010193

申请日：2007-04-26

Applicant: THE BOEING COMPANY ,  MILLER, Gerald, D. ,  ATREYA, Shailesh ,  BIGBEE-HANSEN, William, J. ,  VIISOREANU, Adrian ,  OLSEN, Albert ,  MOORE, Wesley, F. ,  DAVIDSON, Ronald, W. ,  MORRIS, Russell, W.

Inventor： MILLER, Gerald, D. ,  ATREYA, Shailesh ,  BIGBEE-HANSEN, William, J. ,  VIISOREANU, Adrian ,  OLSEN, Albert ,  MOORE, Wesley, F. ,  DAVIDSON, Ronald, W. ,  MORRIS, Russell, W.

IPC: B64D27/02 ,  B64D37/30

CPC classification number: B64D37/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T10/16 ,  Y02T50/44 ,  Y02T90/44

Abstract: Hydrogen powered air vehicles that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 60,000 ft carrying pay loads of up to 2,000 pounds. Embodiments may include features such as large wingspan relative to fuselage and an all composite or partial composite structure for light weight and strength. The aircraft of the invention use one or more internal combustion engines adapted for hydrogen combustion, each engine driving propellers. The hydrogen fuel is stored on board in containers, located within the fuselage, as a cryogenic liquid, and is vaporized in a heat exchanger before delivery to the internal combustion engine.

Abstract translation: 在一些实施例中的氢动力空中飞行器可以在高达60,000英尺的高度上以非常长的耐久性（10或更多天）飞行，承载高达2,000磅的负载。 实施例可以包括相对于机身的大翼展以及用于轻量化和强度的全复合或部分复合结构的特征。 本发明的飞机使用一个或多个适于氢燃烧的内燃机，每个发动机都驱动螺旋桨。 氢燃料被储存在位于机身内的容器中，作为低温液体，并且在输送到内燃机之前在热交换器中蒸发。

公开(公告)号：WO1997015778A1

公开(公告)日：1997-05-01

申请号：PCT/US1996016894

申请日：1996-10-22

Applicant: STANLEY AVIATION CORPORATION ,  EYSTER, Todd, A. ,  OLSEN, Albert, B.

Inventor： STANLEY AVIATION CORPORATION

IPC: F16L23/04

CPC classification number: F16L23/04 ,  F16L21/06 ,  F16L21/08 ,  F16L25/01 ,  Y10S285/921 ,  Y10T24/45581

Abstract: A coupling assembly (A), for connecting adjacent ends of conduits, primarily used for aircraft fuel, water and oxygen lines having redundant locking features is provided. This coupling can be manipulated with one hand and includes laterally spaced locking tines (44, 46, 48, 50) which engage a mating channel for locking the coupling in secured relationship. The coupling assembly (A) can be manipulated with one hand and has viewing ports to ensure that all parts are in place. A pivotal locking member (L) is provided to supply additional redundancy. The locking member (L) has at least one fin (94, 96) which is received between the locking tines (44, 46, 48, 50) and snaps into locking position when the coupling is securely fastened. If the coupling is not securely fastened, the fin (94, 96) will not fit between the tines (44, 46, 48, 50) thereby preventing the locking member (L) from snapping into the locked position. Thus, the mechanic will know that the coupling is not securely fastened and will take steps to remedy the problem. When snapped into locked position, the pivotal locking member (L) also serves to prevent the locking tines (44, 46, 48, 50) from accidental disengagement. The pivotal locking member provides full redundancy so that if the locking tines (44, 46, 48, 50) are damaged or broken, the pivotal locking member (L) provides full strength in locking the coupling halves (2, 4) together.

Abstract translation: 提供了用于连接主要用于具有冗余锁定特征的飞机燃料，水和氧气管线的管道的相邻端的联接组件（A）。 该联接器可以用一只手来操纵并且包括侧向间隔开的锁定齿（44,46,48,50），其接合用于以固定关系锁定联接器的配合通道。 联轴器组件（A）可以用一只手操纵，并具有观察端口，以确保所有部件就位。 提供枢转锁定构件（L）以提供额外的冗余。 锁定构件（L）具有至少一个翅片（94,96），其被接收在锁定齿（44,46,48,50）之间并且当联接器被牢固地固定时卡入锁定位置。 如果联接器未牢固地固定，则翅片（94,96）将不会配合在尖齿（44,46,48,50）之间，从而防止锁定构件（L）卡入锁定位置。 因此，技工将知道联轴器没有牢固固定，并采取措施来弥补问题。 当锁定在锁定位置时，枢转锁定构件（L）还用于防止锁定齿（44,46,48,50）意外脱开。 枢转锁定构件提供完全的冗余度，使得如果锁定齿（44,46,48,50）被损坏或断裂，则枢转锁定构件（L）提供了将联接器半部（2,4）锁定在一起的全部强度。

公开(公告)号：WO2008054521B1

公开(公告)日：2008-09-25

申请号：PCT/US2007010193

申请日：2007-04-26

Applicant: BOEING CO ,  MILLER GERALD D ,  ATREYA SHAILESH ,  BIGBEE-HANSEN WILLIAM J ,  VIISOREANU ADRIAN ,  OLSEN ALBERT ,  MOORE WESLEY F ,  DAVIDSON RONALD W ,  MORRIS RUSSELL W

Inventor： MILLER GERALD D ,  ATREYA SHAILESH ,  BIGBEE-HANSEN WILLIAM J ,  VIISOREANU ADRIAN ,  OLSEN ALBERT ,  MOORE WESLEY F ,  DAVIDSON RONALD W ,  MORRIS RUSSELL W

IPC: B64D27/02 ,  B64D37/30

CPC classification number: B64D37/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T10/16 ,  Y02T50/44 ,  Y02T90/44

Abstract: Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features such as large wingspan relative to fuselage (110) and an all composite or partial composite structure for light weight and strength. The aircraft of the invention use one or more internal combustion engines (122) adapted for hydrogen combustion, each engine driving propellers (123). The hydrogen fuel is stored on board in containers (300), located within the fuselage, as a cryogenic liquid, and is vaporized in a heat exchanger (320) before delivery to the internal combustion engine.

Abstract translation: 氢动力飞行器（100）在一些实施例中可以在高度超过18288米（60,000英尺）的海拔高度（10或更多天）飞行，携带高达907.2千克（2,000磅）的工作负荷。 实施例可以包括诸如相对于机身（110）的大翼展以及用于轻重量和强度的全部复合或部分复合结构的特征。 本发明的飞机使用一个或多个适用于氢燃烧的内燃机（122），每个发动机驱动螺旋桨（123）。 氢燃料作为低温液体在船上储存在位于机身内的容器（300）中，并在输送到内燃机之前在热交换器（320）中汽化。

公开(公告)号：WO1990007076A1

公开(公告)日：1990-06-28

申请号：PCT/US1989005522

申请日：1989-12-06

Applicant: STANLEY AVIATION CORPORATION ,  GALE, Edwin, J. ,  OLSEN, Albert, B. ,  DINSMOOR, John, C.

Inventor： STANLEY AVIATION CORPORATION

IPC: F16L19/00

CPC classification number: F16L25/01 ,  F16L19/005 ,  H01R13/639

Abstract: A bonding jumper (74) is mounted on one facing surface of first (38) and second coupling means (40) which are threadably interconnected. The bonding jumper (74) has a plurality of resilient detent members (92) for bearing against the facing surface of the other coupling means to establish a redundant electrical bond between the first (38) and second coupling means (40) when the facing surfaces are axially drawn toward each other. A plurality of recesses (72') is provided in the second surface for coacting with the detent means (92) to yieldably resist opposing relative rotation in the unthreading direction.

公开(公告)号：WO2008054521A3

公开(公告)日：2008-08-07

申请号：PCT/US2007010193

申请日：2007-04-26

Applicant: BOEING CO ,  MILLER GERALD D ,  ATREYA SHAILESH ,  BIGBEE-HANSEN WILLIAM J ,  VIISOREANU ADRIAN ,  OLSEN ALBERT ,  MOORE WESLEY F ,  DAVIDSON RONALD W ,  MORRIS RUSSELL W

Inventor： MILLER GERALD D ,  ATREYA SHAILESH ,  BIGBEE-HANSEN WILLIAM J ,  VIISOREANU ADRIAN ,  OLSEN ALBERT ,  MOORE WESLEY F ,  DAVIDSON RONALD W ,  MORRIS RUSSELL W

IPC: B64D27/02 ,  B64D37/30

CPC classification number: B64D37/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T10/16 ,  Y02T50/44 ,  Y02T90/44

Abstract: Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features such as large wingspan relative to fuselage (110) and an all composite or partial composite structure for light weight and strength. The aircraft of the invention use one or more internal combustion engines (122) adapted for hydrogen combustion, each engine driving propellers (123). The hydrogen fuel is stored on board in containers (300), located within the fuselage, as a cryogenic liquid, and is vaporized in a heat exchanger (320) before delivery to the internal combustion engine.

Abstract translation: 在一些实施例中，能够以高达907.2kg（2,000磅）的高度运行的高度在18288m（60,000ft）的高度的非常长的耐久性（10或更多天）飞行的氢动力空中飞行器（100）。 实施例可以包括相对于机身（110）的大翼展以及用于轻量化和强度的全复合或部分复合结构的特征。 本发明的飞行器使用适于氢燃烧的一个或多个内燃机（122），每个发动机驱动螺旋桨（123）。 氢燃料被储存在位于机身内的容器（300）中作为低温液体，并且在输送到内燃机之前在热交换器（320）中蒸发。