# US 5,352,529 A · Lightweight thrust vectoring panel > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 5,352,529 A - Document ID: US5352529A - Status: Granted - Kind: A - Application number: 08/025,918 - Filed: 1993-03-03 - Granted: 1994-10-04 - Earliest claimed: 1991-05-13 - Assignees: Auto-Air Composites, Inc. - Inventors: John F. Scanlon; Gary Wigell - Web page: https://patentgrep.com/patent/US5352529A ## CPC - B32B 18/00: Layered products essentially comprising ceramics, e.g. refractory products - C04B 35/63468: {Polyamides} - C04B 37/008: {by means of an interlayer consisting of an organic adhesive, e.g. phenol resin or pitch} - F02K 1/822: {Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors} - C04B 2235/483: Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes - C04B 2235/5228: Silica and alumina, including aluminosilicates, e.g. mullite - C04B 2235/5248: Carbon, e.g. graphite - C04B 2237/34: Oxidic - C04B 2237/341: Silica or silicates - C04B 2237/38: Fiber or whisker reinforced - C04B 2237/62: Forming laminates or joined articles comprising holes, channels or other types of openings - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - Y10T 428/1321: Polymer or resin containing [i.e., natural or synthetic] - Y10T 428/192: Sheets or webs coplanar - Y10T 428/24995: Two or more layers - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract 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. ## Claims ### Claim 1 A thrust vectoring panel for deflecting the thrust of axial turbine engines comprising a face layer comprising a silicon carboxide matrix with ceramic reinforcing fibers, an insulation layer and a skeletal structure, said face layer being of a material capable of withstanding high temperatures in the range of 2200.degree.-2500.degree. F. for an extended period of time and 2800.degree. F. for a short period of time while retaining at least 90% of its room temperature strength during these temperature excursions, said insulation layer being of a fiber reinforced material capable of providing insulation from the extreme heat of the jet engine thrust, and said skeletal structure being of a fiber reinforced material capable of supporting integral interfaces. ### Claim 2 (depends on 1) The thrust vectoring panel of claim 1, wherein said face layer material can withstand temperatures of 2300.degree.-2500.degree. F. for at least 2000 hours and can withstand temperatures of 2800.degree. F. for at least 5 minutes while retaining at least 90% of its room temperature strength during these temperature excursions. ### Claim 3 (depends on 1) The thrust vectoring panel of claim 1 wherein said insulation layer comprises a fiber reinforced ceramic matrix. ### Claim 4 (depends on 1) The thrust vectoring panel of claim 1 wherein the insulation layer is adhesively bonded to the face layer and the skeletal structure. ### Claim 5 The thrust vectoring panel of claim wherein the insulation layer is parasitically bonded to the face layer and the skeletal structure. ### Claim 6 (depends on 1) The thrust vectoring panel of claim 1 wherein the skeletal structure further comprises channels embedded within the skeletal structure for receiving a cooling medium or diagnostic devices. ### Claim 7 A thrust vectoring panel for deflecting the thrust in aircraft engines comprising: a face layer comprising a silicon carboxide matrix with ceramic reinforcing fibers, an insulation layer and a skeletal structure, the face layer being of a silicon carboxide matrix with ceramic reinforcing fibers, the face layer formed and cured from a polymer precursor which is polymerized and then pyrolyzed, the insulation layer being of the same material as the silicon carboxide matrix face layer in its polymerized state before pyrolyzation, the insulation layer providing insulation from the extreme heat of the aircraft engine, and the skeletal structure being of a fiber reinforced material capable of supporting integral interfaces. ### Claim 8 (depends on 7) The thrust vectoring panel of claim 7 wherein said face layer is capable of withstanding high temperatures in the range of 2200.degree.-2500.degree. F. for at least 2000 hours and 2800.degree. F. for at least 5 minutes while retaining at least 90% of its room temperature strength during these temperature excursions. ### Claim 9 (depends on 8) The thrust vectoring panel of claim 8 wherein the insulation layer pyrolyzes when a portion of the face layer covering its wears away or disintegrates thereby exposing the underlying insulation layer, the insulation layer being exposed to the heat of the aircraft engine thrust and pyrolyzing. ### Claim 10 (depends on 8) The thrust vectoring panel of claim 8 wherein said insulation layer comprises a fiber reinforced ceramic matrix. ### Claim 11 (depends on 8) The thrust vectoring panel of claim 8 wherein the insulation layer is adhesively bonded to the face layer and the skeletal structure. ### Claim 12 (depends on 8) The thrust vectoring panel of claim 8 wherein the insulation layer is parasitically bonded to the face layer and the skeletal structure. ### Claim 13 (depends on 8) The thrust vectoring panel of claim 8 wherein the skeletal structure further comprises channels embedded within the skeletal structure for receiving a cooling medium or diagnostic devices.