Auto Air Composites, Inc.

Sundstrand Corporation

Gary W Wigell

John F Scanlon

John S Church

Scott M Thomson

Eugene V Czerniewski

James L Kasarsky

David A Stark

Timothy A Davis

Duncan Lawrie

A thrust vectoring panel which is a hybrid ceramic/ceramic composite consisting of three layers of lightweight materials, the anisotropic properties of which are manipulated such that the properties of the materials, i.e., the coefficient of thermal expansion, the strain energy release rate, and the tensile and flexure modules, either match or gradually transition from material to material. The three layers include a face layer which is of a high temperature capable material that can withstand temperatures within a range of 2300.degree.-25000.degree. F. for an extended period of time and a temperature as high as 28000.degree. F. for a short period of time. The middle layer simply is an insulating layer for providing adequate thermal insulation for the activator mechanism for the thrust panel. The third layer is a skeletal structure or layer which is of a lightweight material having sufficient strength to support all the integral interfaces, such as the activator mounts and the like.

Lightweight thrust vectoring panel

A hybrid metal/composite spinner cone used in aircraft applications and a method of manufacturing the same. The spinner cone has a metal outer shell which is bonded during the molding process to an inner structural member of thermoplastic composite. The metal shell imparts several desirable characteristics to the spinner cone such as impact resistance, erosion resistance, appearance, and supplying a lightning strike material to protect the composite structure. The thermoplastic composite has significant property advantages over metal or thermoset systems. The hybrid metal/composite spinner cone is manufactured using a ceramic mold which is less expensive and more readily available than a steel mold. The metal shell provides a barrier between the thermoplastic composite and the ceramic mold and allows the finished spinner cone to be easily released from the mold.

Method of manufacturing a metal/composite spinner cone

A hybrid metal/composite spinner cone used in aircraft applications. The spinner cone has a metal outer shell which is bonded during the molding process to an inner structural member of thermoplastic composite. The metal shell imparts several desirable characteristics to the spinner cone such as impact resistance, erosion resistance, appearance, and supplying a lightning strike material to protect the composite structure. The thermoplastic composite has significant property advantages over metal or thermoset systems. The hybrid metal/composite spinner cone is manufactured using a ceramic mold which is less expensive and more readily available than a steel mold. The metal shell provides a barrier between the thermoplastic composite and the ceramic mold and allows the finished spinner cone to be easily released from the mold.

Metal/composite spinner cone

A generator housing including a housing module having at least one relatively complex internal passage formed therein and housing flow control components for circulating a fluid coolant through the generator. The housing module is formed by forming a plurality of sub-components each having at least one relatively simple passage formed therein for defining part of the at least one relatively complex internal passage. The sub-components are combined together as by bonding to form the housing module with at least one relatively complex internal passage. The flow control components are contained in bores within the housing module in fluid communication with the relatively complex internal passage therein. The housing module if formed of a relatively lightweight, non-metallic material to enable reduction in the weight of the generator housing in cost-effective and technically accepted manner thereby providing an improved generator which can be used in aircraft.

Composite center module housing using specifically shaped segments to

A self-locking retention system is provided for a composite rotor blade supported on a rotor hub. A radially extending, stud-like retention member is provided on the rotor hub. A composite thickness projects radially inwardly from the rotor blade and substantially surrounds the retention member. The composite thickness is woven in a pattern which grips the retention member in response to outward forces applied to the rotor blade and the woven composite thickness.

Growing community of inventors

Lansing, MI, United States of America

Gary W Wigell