-
公开(公告)号：US12054266B2
公开(公告)日：2024-08-06
申请号：US17571800
申请日：2022-01-10
Applicant: Aurora Flight Sciences Corporation
IPC: B64D27/24 , H01M10/613 , H01M10/625 , H01M10/6552
CPC classification number: B64D27/24 , H01M10/613 , H01M10/625 , H01M10/6552 , H01M2220/20
Abstract: The present disclosure relates to propulsion system for an aircraft. The propulsion system comprises a motor, a battery bank, a thermal management system, and a controller. The motor being configured to rotate a rotor via a rotor shaft and to drive the thermal management system. The thermal management system configured to urge fluid through a fluid pathway defined by the battery bank. The controller configured to drive the motor and/or control charge and discharge of the battery bank.
-
公开(公告)号：US20140166191A1
公开(公告)日：2014-06-19
申请号：US13715325
申请日：2012-12-14
Applicant: AURORA FLIGHT SCIENCES CORPORATION
Inventor： Daniel Benjamin Cottrell
IPC: B29C70/84
CPC classification number: B29C70/84 , B29C70/443 , B29L2031/772 , B32B37/06 , B32B37/142 , B32B37/24 , B32B2305/28 , B32B2309/02 , B32B2313/04 , B32B2315/085
Abstract: The present invention provides a method of fabricating a composite structure from components of varying stages of cure while reducing the steps associated with the fabrication process of infusing, curing, and bonding composite materials to form a hybrid unitized structure. The method provides a pre-cured stiffener and a pi-preform having a clevis and a base portion. The pre-cured stiffener may be inserted into the clevis of the pi-preform to form a composite structure assembly. The composite structure assembly may be infused with a resin system at the time of cure and bonded to a second composite structure to form a hybrid unitized structure.
Abstract translation: 本发明提供了一种从不同固化阶段的组分制造复合结构的方法，同时减少了与复合材料的注入，固化和粘合的制造过程相关的步骤以形成混合组合结构。 该方法提供了预固化的加强件和具有U形夹和基部的pi预制件。 预固化的加强件可以插入到pi预成型件的U形夹中以形成复合结构组件。 复合结构组件可以在固化时用树脂体系注入，并结合到第二复合结构以形成混合组合结构。
-
公开(公告)号：US20220306305A1
公开(公告)日：2022-09-29
申请号：US17571800
申请日：2022-01-10
Applicant: Aurora Flight Sciences Corporation
IPC: B64D27/24 , H01M10/613 , H01M10/625 , H01M10/6552
Abstract: The present disclosure relates to propulsion system for an aircraft. The propulsion system comprises a motor, a battery bank, a thermal management system, and a controller. The motor being configured to rotate a rotor via a rotor shaft and to drive the thermal management system. The thermal management system configured to urge fluid through a fluid pathway defined by the battery bank. The controller configured to drive the motor and/or control charge and discharge of the battery bank.
-
公开(公告)号：US10807325B2
公开(公告)日：2020-10-20
申请号：US14677435
申请日：2015-04-02
Applicant: AURORA FLIGHT SCIENCES CORPORATION
Inventor： Daniel Benjamin Cottrell
Abstract: The present disclosure relates to a method of fabricating a composite structure using a pre-cured composite stiffener and a dry fabric component. In one example, the method includes the steps of: wrapping an adhesive film and a resin film around an edge of said pre-cured composite stiffener; inserting the edge of said pre-cured composite stiffener into a clevis of a dry fabric component to form a composite structure assembly; securing the pre-cured composite stiffener substantially perpendicularly to the base portion of the dry fabric component; and starting a consolidated infusion and cure process. The consolidated infusion and cure process applies a first temperature to the composite structure assembly for a first predetermined period of time to infuse the dry fabric component, and the increases the first temperature to a second temperature for a second predetermined period of time to cure the composite structure assembly.
-
-
-
Search Results
4
records
(took 0.011 seconds)
