A thermal blanket system is provided on an aircraft component to protect the component, for example, from engine heat. The component has a latch half attached thereto, which is also covered by the thermal blanket system. In some scenarios, the latch half may need to be detached from the component be
A thermal blanket system is provided on an aircraft component to protect the component, for example, from engine heat. The component has a latch half attached thereto, which is also covered by the thermal blanket system. In some scenarios, the latch half may need to be detached from the component because the latch was stuck closed. The thermal blanket system includes a portion thereof which overlaps the latch half and breaks away from the remainder of the thermal blanket system when the latch half is detached.
대표청구항▼
1. A system, comprising: an inner fixed structure (IFS) including a first IFS panel and a second IFS panel;a thermal protection system layer (TPS layer) having an overlying, attached relationship to the IFS and including a first TPS layer portion, the TPS layer configured to provide thermal insulati
1. A system, comprising: an inner fixed structure (IFS) including a first IFS panel and a second IFS panel;a thermal protection system layer (TPS layer) having an overlying, attached relationship to the IFS and including a first TPS layer portion, the TPS layer configured to provide thermal insulation protection for the IFS;a latch system disposed intermediate the first IFS panel and the second IFS panel and including a first latch half and a second latch half, the first latch half being attached to the first IFS panel and the second latch half attached to the second IFS panel so that the first IFS panel has structural communication with the second IFS panel via the first latch half being latched to the second latch half, the first TPS layer portion being attached to the first latch half;a break-away joint disposed in the system in a manner that connects the TPS layer to the first TPS layer portion, the disposed break-away joint being configured to break when the attached first latch half is detached from the first IFS panel in the assembled system;wherein when the attached first half latch is detached from the first IFS panel in the assembled system the disposed break-away joint breaks so that the first TPS layer portion is detached from the TPS layer and the first IFS panel separates so that the structural communication of the first IFS panel with the second IFS panel does not occur. 2. The system of claim 1, wherein the break-away joint is created with a material having adhesive properties. 3. The system of claim 2, wherein the material is room temperature vulcanizing silicone. 4. The system of claim 1, wherein the break-away joint is created with a spot weld. 5. The system of claim 1, wherein the first latch half is coupled to the first IFS panel with a plurality of fasteners. 6. The system of claim 5, wherein the first latch half is removably coupled to the first IFS panel with the plurality of fasteners. 7. The system of claim 6, wherein the first TPS layer portion is re-attachable to the TPS layer by at least one of a material having adhesive properties or a spot weld. 8. The system of claim 1, further comprising a second TPS layer portion attached to the second latch half. 9. The system of claim 1, further comprising a gas turbine engine, the IFS surrounding the gas turbine engine and the system comprising a propulsion system. 10. A propulsion system, comprising: a gas turbine engine;a first panel and a second panel adapted to be moveable between an open position in which maintenance access is granted to the gas turbine engine and a closed position in which the first panel and the second panel substantially surround and enclose at least a portion of the gas turbine engine;a first latch half connected to the first panel;a second latch half connected to the second panel, the first latch half and the second latch half adapted to latch together when the first panel and the second panel are in the closed position to hold the first panel and the second panel in the closed position;a thermal protection system layer (TPS layer) having an overlying, attached relationship to the first panel and including a first TPS layer portion, the TPS layer configured to provide thermal insulation protection for the first panel, and the first TPS layer portion being attached to the first latch half; anda break-away joint disposed intermediate the first TPS layer portion and the TPS layer, wherein the first TPS layer portion is coupled to the TPS layer via the break-away joint, the disposed break-away joint being configured to allow the first TPS layer portion to separate from the TPS layer when the attached first latch half is detached from the first IFS panel in the assembled system;wherein when the attached first half latch is detached from the first IFS panel in the assembled system the disposed break-away joint breaks so that the first TPS layer portion is detached from the TPS layer. 11. The propulsion system of claim 10, wherein the first panel and the second panel are portions of an inner fixed structure. 12. The propulsion system of claim 10, wherein the break-away joint constitutes a frangible joint. 13. The propulsion system of claim 10, wherein the break-away joint is made from at least one of: an overlapping fold between the first TPS layer portion and the TPS layer;an interference between the first TPS layer portion and the TPS layer;a spot weld; anda room temperature vulcanizing silicone. 14. A thermal protection system, comprising: a first blanket portion attached to an inner fixed structure (IFS) of a thrust reverser;a second blanket portion; anda break-away joint disposed in the thermal protection system in a manner that connects the first blanket portion to the second blanket portion, the break-away joint providing substantially permanent attachment of the second blanket portion to the first blanket portion, and the break-away joint allows the second blanket portion to non-destructively separate from the first blanket portion in response to the first blanket portion and the second blanket portion being pulled away from each other,wherein the break-away joint is a frangible joint made from at least one of a spot weld or a room temperature vulcanizing silicone. 15. The thermal protection system of claim 14, wherein the frangible joint is defined by overlapping folds between the first blanket portion and the second blanket portion. 16. The thermal protection system of claim 14, wherein the break-away joint between the first blanket portion and the second blanket portion is an overlapping fold between the first blanket portion and the second blanket portion. 17. The thermal protection system of claim 14, wherein the break-away joint between the first blanket portion and the second blanket portion is an interference between the first blanket portion and the second blanket portion. 18. The thermal protection system of claim 14, wherein the thermal protection system is for thermally insulating the IFS from an engine.
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이 특허에 인용된 특허 (6)
Dudley Wayne C. (Parkersburg IA), Break away joint boom assembly.
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