公开(公告)号：US20160297679A1

公开(公告)日：2016-10-13

申请号：US14682245

申请日：2015-04-09

Applicant: The Boeing Company

Inventor： John J. Vajo ,  Adam Franklin Gross ,  Shanying Cui

IPC: C01B21/06 ,  B01J8/02

CPC classification number: C01B21/0622 ,  B01J3/02 ,  B01J3/04 ,  C01P2004/16 ,  C01P2004/32 ,  C01P2004/54 ,  C01P2004/64

Abstract: Provided is a method and system for making powdered Fe16N2. The method can include sealing iron powder and a fixed amount of ammonia (NH3) gas within a pressure vessel. The pressure of the fixed amount of ammonia gas in the pressure vessel can be elevated so that Fe16N2 can be formed from the iron powder. Use of a pressure vessel and a fixed amount of ammonia gas can provide economic and environmental benefits such as higher conversion rates of iron powder into Fe16N2, reduced ammonia gas use, and reclamation of used ammonia gas.

Abstract translation: 提供了制备粉末状Fe16N2的方法和系统。 该方法可以包括在压力容器内密封铁粉和固定量的氨（NH 3）气体。 可以提高压力容器中固定量的氨气的压力，从而可以由铁粉形成Fe16N2。 使用压力容器和固定量的氨气可以提供经济和环境方面的好处，例如铁粉转化成Fe16N2，降低氨气使用量和回用氨气。

公开(公告)号：US20160229552A1

公开(公告)日：2016-08-11

申请号：US14614656

申请日：2015-02-05

Applicant: THE BOEING COMPANY

Inventor： Adam Franklin Gross ,  Darrin M. Hansen ,  Shahriar Khosravani

IPC: B64D45/02 ,  F16B1/00

CPC classification number: B64D45/02 ,  B22F7/062 ,  B22F7/064 ,  B29C65/562 ,  B29C66/112 ,  B29C66/131 ,  B29C66/474 ,  B29C66/54 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73141 ,  B29C66/73161 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/742 ,  B29C70/882 ,  B29L2031/3002 ,  B29L2031/3076 ,  B64D37/32 ,  F16B1/00 ,  F16B2001/0064 ,  Y02T50/43 ,  B29K2307/04

Abstract: A structural assembly of an aircraft which includes a structural element constructed of a composite material which includes a matrix material and plurality of fibers positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers are accessible from a surface of the structural element. A fastener secures the structural element to a structural component. A metal structure comprising gallium is positioned in contact with a surface of the fastener. The metal structure extends from the surface of the fastener and contacts at least a portion of the at least a portion of the plurality of fibers. Also included is a method for assembling a structure.

Abstract translation: 一种飞行器的结构组件，其包括由复合材料构成的结构元件，所述复合材料包括基体材料和定位成延伸穿过基体材料的多根纤维，其中所述多根纤维的至少一部分可从 结构元素。 紧固件将结构元件固定到结构部件。 包含镓的金属结构被定位成与紧固件的表面接触。 金属结构从紧固件的表面延伸并接触多根纤维的至少一部分的至少一部分。 还包括组装结构的方法。