公开(公告)号：US10000281B2

公开(公告)日：2018-06-19

申请号：US15417702

申请日：2017-01-27

Applicant: AIRBUS HELICOPTERS

Inventor： Louis Delorme ,  Didier Bertin

IPC: B64C25/56 ,  G06F17/11 ,  B64C27/04

CPC classification number: B64C25/56 ,  B64C27/04 ,  G06F17/11

Abstract: The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (MOD1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (STP1) of predicting a forthcoming impact. During a step (STP2) of characterizing said impact, at least one predicted component of a ditching speed is determined. During an automatic inflation step (STP3), each float is automatically inflated in flight when at least said ditching condition is true and when each determined predicted component is less than a corresponding speed threshold.

公开(公告)号：US09533757B2

公开(公告)日：2017-01-03

申请号：US14513508

申请日：2014-10-14

Applicant: AIRBUS HELICOPTERS

Inventor： Louis Delorme ,  Nicolas Lamarche ,  David Ayache ,  Bernard Certain

IPC: B64C25/56 ,  B64D25/00 ,  B64C25/32

CPC classification number: B64C25/56 ,  B64C2025/325 ,  B64D25/00 ,  B64D2201/00

Abstract: A buoyancy system (10) for an aircraft (1), the buoyancy system (10) being provided with at least one inflatable float (15). The buoyancy system (10) has at least one inflator (25) and at least one actuator (30) interposed between the inflator (25) and a float (15), the actuator (30) having a cylinder (35) and a rod (40) partially received in the cylinder (35). The rod (40) is secured to a piston (50) defining a first chamber (61) within the cylinder (35) and in fluid flow communication with the inflator (25), and a second chamber (62) within the rod (40) and in fluid flow communication with the float (15), and the piston (50) has a channel (63) to put the first chamber (61) into fluid flow communication with the second chamber (62), the deployment device (20) having a shutter (70) for shutting the channel (63).

Abstract translation: 一种用于飞机（1）的浮力系统（10），所述浮力系统（10）设置有至少一个可充气浮子（15）。 浮力系统（10）具有至少一个充气机（25）和置于充气机（25）和浮子（15）之间的至少一个致动器（30），所述致动器（30）具有气缸（35）和杆 （40）部分地容纳在气缸（35）中。 所述杆（40）固定到限定所述气缸（35）内并与所述充气机（25）流体连通的第一室（61）的活塞（50），并且所述杆（40）内的第二室（62） ）并且与所述浮子（15）流体连通，并且所述活塞（50）具有通道（63）以使所述第一室（61）与所述第二室（62）流体连通，所述展开装置（20） ）具有用于关闭通道（63）的快门（70）。

公开(公告)号：US11584518B2

公开(公告)日：2023-02-21

申请号：US17174388

申请日：2021-02-12

Applicant: AIRBUS HELICOPTERS

Inventor： Louis Delorme ,  Pierre Prud'homme Lacroix

IPC: B64C25/56 ,  B64C25/54 ,  B64C27/04 ,  B64C25/32 ,  G05D7/06

Abstract: A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.

公开(公告)号：US11027829B2

公开(公告)日：2021-06-08

申请号：US15987122

申请日：2018-05-23

Applicant: AIRBUS HELICOPTERS

Inventor： Louis Delorme ,  Pierre Prud'Homme Lacroix

IPC: B64C25/56 ,  B64C25/54 ,  B64C27/04 ,  B64C25/32 ,  G05D7/06

Abstract: A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.