Insulation Blanket Assemblies and Methods

An insulation blanket assembly for use on an aircraft includes a cover. The cover has an inboard material and an outboard material. The insulation blanket assembly also includes an insulation material between the inboard material and the outboard material. The insulation blanket assembly also includes one or more support rails attached to at least one of the cover or the insulation material. When the insulation blanket assembly is attached to the aircraft, the one or more support rails are configured to provide separation between an aircraft structure and the insulation material to reduce or eliminate moisture from transferring to the insulation material.

FIELD

The present disclosure generally relates to insulation, and more particularly, to support rails for aircraft insulation blankets.

BACKGROUND

This background description is provided for the purpose of generally presenting the context of the disclosure. Unless otherwise indicated herein, material described in this section is neither expressly nor impliedly admitted to be prior art to the present disclosure or the appended claims.

Aircrafts use thermal and acoustic insulation for different purposes. For example, thermal and acoustic insulation can be used to reduce noise transfer and thermal conduction with outside elements of an aircraft. Additionally, thermal and acoustic insulation can be used to channel moisture generated in an upper lobe cabin of the aircraft down to drains in a lower lobe structure of the aircraft, where the moisture exits the aircraft. However, thermal and acoustic insulation can become saturated from the moisture and can block water on its way along a drain path.

SUMMARY

The present application is directed to reducing a rate at which an insulation blanket becomes saturated on an aircraft. In particular, according to the present application, one or more support rails are attached to, or embedded within, the insulation blanket to provide separation between an insulation material of the insulation blanket and an aircraft structure, such as a fuselage panel, to reduce or eliminate moisture associated with the aircraft structure from saturating the insulation material.

Moisture generated in an upper lobe of the aircraft is typically channeled down to drains in a lower lobe structure of the aircraft, from which the moisture exits the aircraft. Thus, moisture typically collects near a lower lobe cheek and bilge of the aircraft before exiting the aircraft. As a result, the lower lobe cheek and bilge of the aircraft can be a relatively wet environment. Along with reducing noise transfer with a surrounding environment of the aircraft, reducing thermal conduction with the surrounding environment of the aircraft, and acting as a barrier against other external hazards, the insulation blanket can be used to channel moisture from the upper lobe of the aircraft down to the drains in the lower lobe structure of the aircraft.

To reduce the likelihood or risk of the insulation blanket blocking water on its way down drain paths, one or more support rails are attached to, or embedded within, the insulation blanket to provide separation between the insulation material and different aircraft structures (e.g., to prevent the insulation material from laying flush against skin and structure in the lower lobe structure of the aircraft). The one or more support rails can be made of a foam material. The foam support rails allow water drainage above and below the surface of the insulation blanket. In particular, the one or more support rails may be comprised of a closed cell foam to reduce or eliminate moisture absorption. Additionally, the increased gap between the insulation material and the lower lobe structure of the aircraft can prevent the insulation material within the insulation blanket from becoming saturated with moisture, thus increasing the in-service performance of the insulation blanket.

In one aspect, the present application discloses an insulation blanket assembly for use on an aircraft includes a cover. The cover has an inboard material and an outboard material. The insulation blanket assembly also includes an insulation material between the inboard material and the outboard material. The insulation blanket assembly also includes one or more support rails attached to at least one of the cover or the insulation material. When the insulation blanket assembly is attached to the aircraft, the one or more support rails are configured to provide separation between an aircraft structure and the insulation material to reduce or eliminate moisture from transferring to the insulation material.

In another aspect, the present application discloses an aircraft. The aircraft includes a fuselage. The fuselage includes a plurality of frame structures and a plurality of stringers attached to the plurality of frame structures. The plurality of stringers extend laterally along a length of the fuselage. The aircraft also includes an insulation blanket assembly attached to at least one frame structure of the plurality of frame structures or to at least one stringer of the plurality of stringers. The insulation blanket assembly includes one or more support rails that extend transverse relative to the plurality of stringers.

In another aspect, the present application discloses a method of making an insulation blanket assembly for an aircraft. The method includes providing an insulation material. The method also includes forming a cover. The method also includes, prior to or after forming the cover, attaching one or more support rails to at least one of the cover or the insulation material such that, when installed on the aircraft, the one or more support rails provide separation of the insulation material from an outer panel of the aircraft for moisture management.

In another aspect, the present application discloses a method of installing an insulation blanket assembly on an aircraft. The method includes applying (i) first hook tape to a first inner mold line of a first aircraft frame structure and (ii) second hook tape to a second inner mold line of a second aircraft frame structure. The first hook tape and the first hook tape are double-sided tapes. The method also includes applying (i) first loop tape to a first group of blanket tabs attached to a first edge of an outboard material of an insulation blanket assembly and (ii) second loop tape to a second group of blanket tables attached to a second edge of the outboard material. The first loop tape and the second loop tape are double-sided tapes, and the insulation blanket assembly comprises one or more support rails that extend transverse relative to aircraft stringers. The method also includes attaching (i) the first group of blanket tabs to the first inner mold line by placing the first loop tape on top of the first hook tape and (ii) the second group of blanket tabs to the second inner mold line by placing the second loop tape on top of the second hook tape.

DETAILED DESCRIPTION

Particular implementations are described herein with reference to the drawings. In the description, common features may be designated by common reference numbers throughout the drawings. In some drawings, multiple instances of a particular type of feature are used. Although these features are physically and/or logically distinct, the same reference number is used for each, and the different instances are distinguished by addition of a letter to the reference number. When the features as a group or a type are referred to herein (e.g., when no particular one of the features is being referenced), the reference number is used without a distinguishing letter. However, when one particular feature of multiple features of the same type is referred to herein, the reference number is used with the distinguishing letter. For example, referring toFIGS.1A and1E, insulation blanket assemblies are illustrated and associated with reference number100. When referring to a particular one of the insulation blanket assemblies, such as the insulation blanket assembly100A, the distinguishing letter “A” is used. However, when referring to any arbitrary one of the insulation blanket assemblies or to the insulation blanket assemblies as a group, the reference number100may be used without a distinguishing letter.

As used herein, various terminology is used for the purpose of describing particular implementations only and is not intended to be limiting. For example, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, the terms “comprise,” “comprises,” and “comprising” are used interchangeably with “include,” “includes,” or “including.” Additionally, the term “wherein” is used interchangeably with the term “where.” As used herein, “exemplary” indicates an example, an implementation, and/or an aspect, and should not be construed as limiting or as indicating a preference or a preferred implementation. As used herein, an ordinal term (e.g., “first,” “second,” “third,” etc.) used to modify an element, such as a structure, a component, an operation, etc., does not by itself indicate any priority or order of the element with respect to another element, but rather merely distinguishes the element from another element having a same name (but for use of the ordinal term). As used herein, the term “set” refers to a grouping of one or more elements, and the term “plurality” refers to multiple elements.

Referring toFIG.1A, a diagram of an insulation blanket assembly100A that includes one or more support rails is illustrated, according to an exemplary embodiment. According to some implementations, as described in greater detail with respect toFIG.2, the insulation blanket assembly100A can be installed on an aircraft200.

The insulation blanket assembly100A includes a cover101A having an outboard material102A and an inboard material104A. The insulation blanket assembly100A also includes an insulation material110A between the inboard material104A and the outboard material102A. For example, referring to the cross-sectional view of the insulation blanket assembly100A inFIG.1B, to seal in the insulation material110A, the outboard material102A of the cover101A is wrapped around a first side of the insulation material110A, and the inboard material104A of the cover101A is wrapped around a second side of the insulation material110A. An edge of the inboard material104A is attached to an edge of the outboard material102A via tape103A.

As depicted inFIGS.1A and1B, the insulation blanket assembly100A also includes one or more support rails106A attached to the cover101A. In particular, the one or more support rails106A are attached to the outboard material102A of the cover101A such that the outboard material102A is between the insulation material110A and the one or more support rails106A. The one or more support rails106A may be attached with double-sided tape or a garment tags. As described below, when the insulation blanket assembly110A is attached to an aircraft, such as the aircraft200ofFIG.2, the one or more support rails106A are configured to provide separation between an aircraft structure (e.g., such as an aircraft stringer or an aircraft fuselage structure) and the insulation material110A to reduce or eliminate moisture from transferring to the insulation material110A.

As depicted inFIG.1A, each support rail106A of the one or more support rails106A may include an elongated member that has a length that is less than a length of the cover101A such that ends of the one or more support rails106A are separated laterally from a perimeter of the cover101A. InFIG.1A, the insulation blanket assembly100A includes two (2) support rails106A that extend in a parallel direction relative to each other. However, in other implementations, the insulation blanket assembly100A can include additional (or fewer) support rails106A. As a non-limiting example, in one implementation, the insulation blanket assembly100A can include five (5) support rails106A extended in a parallel direction relative to each other. The support rails106A may be comprised of a flexible material to enable the support rails106A to be flexible. As a non-limiting example, the support rails106A may be comprised of a foam material.

According to one implementation, a first support rail106A of the one or more support rails106A has a first length, and a second support rail106A of the one or more support rails106A has a second length that is less than the first length to provide variable rigidity along the insulation blanket assembly100A. According to one implementation, a first support rail106A of the one or more support rails106has a first width, and a second support rail106A of the one or more support rails106A has a second width that is less than the first width. The first and second support rails106A may be comprised of the same foam material such that the first support rail106A has a different stiffness than the second support rail106A to provide rigidity to the insulation blanket assembly100A.

The insulation blanket assembly100may also include a plurality of attachment portions172. Each attachment portion172includes a hole that extends through the cover101A and the insulation material110A to facilitate attachment of the insulation blanket assembly100A to an aircraft structure with a fastener.

As depicted inFIGS.1A and1C, at least one support rail106A of the one or more support rails106A is an elongated member that includes a beveled edge107A on opposing ends of the elongated member to facilitate sliding the insulation blanket assembly110A into position prior to securing the insulation blanket assembly110A to an aircraft structure. As depicted inFIGS.1A and1D, at least one support rail106A of the one or more support rails106A is an elongated member that includes a straight edge108A. AlthoughFIG.1Aillustrates one support rail106A having the beveled edge107A and one support rail106A having the straight edge108A, in other implementations, the edges of the support rails106A can be consistent for the insulation blanket assembly100A. For example, each support rail106A can have the beveled edge107A or each support rail106A can have the straight edge108A.

Referring toFIG.1E, another diagram of an insulation blanket assembly100B that includes one or more support rails is illustrated, according to an exemplary embodiment. According to some implementations, as described in greater detail with respect toFIG.2, the insulation blanket assembly100B can be installed on the aircraft200.

The insulation blanket assembly100B includes a cover101B having an outboard material102B and an inboard material104B. The insulation blanket assembly100B also includes an insulation material110B between the inboard material104B and the outboard material102B. For example, referring to the cross-sectional view of the insulation blanket assembly100B inFIG.1F, to seal in the insulation material110B, the outboard material102B of the cover101B is wrapped around a first side of the insulation material110B, and the inboard material104B of the cover101B is wrapped around a second side of the insulation material110B. An edge of the inboard material104B is attached to an edge of the outboard material102B via tape103B.

As depicted inFIGS.1Eand IF, the insulation blanket assembly100F also includes one or more support rails106B attached to the insulation material110B. In particular, the one or more support rails106B are attached to the insulation material110B such that the one or more support rails106B are positioned between the outboard material102B and the insulation material110B. The one or more support rails106B may be attached with double-sided tape. As described below, when the insulation blanket assembly110B is attached to an aircraft, such as the aircraft200ofFIG.2, the one or more support rails106B are configured to provide separation between an aircraft structure (e.g., such as an aircraft stringer or an aircraft fuselage structure) and the insulation material110B to reduce or eliminate moisture from transferring to the insulation material110B.

As depicted inFIG.1E, each support rail106B of the one or more support rails106B may include an elongated member that has a length that is less than a length of the cover101B such that ends of the one or more support rails106B are separated laterally from a perimeter of the cover101B. InFIG.1E, the insulation blanket assembly100B includes two (2) support rails106B that extend in a parallel direction relative to each other. However, in other implementations, the insulation blanket assembly100B can include additional (or fewer) support rails106B. As a non-limiting example, in one implementation, the insulation blanket assembly100B can include five (5) support rails106B extended in a parallel direction relative to each other. The support rails106B may be comprised of a flexible material to enable the support rails106B to be flexible. As a non-limiting example, the support rails106B may be comprised of a foam material.

According to one implementation, a first support rail106B of the one or more support rails106B has a first length, and a second support rail106B of the one or more support rails106B has a second length that is less than the first length to provide variable rigidity along the insulation blanket assembly100B. According to one implementation, a first support rail106B of the one or more support rails106B has a first width, and a second support rail106B of the one or more support rails106B has a second width that is less than the first width. The first and second support rails106B may be comprised of the same foam material such that the first support rail106B has a different stiffness than the second support rail106B to provide rigidity to the insulation blanket assembly100B.

The insulation blanket assembly100B may also include a plurality of attachment portions172. Each attachment portion172includes a hole that extends through the cover101B and the insulation material110B to facilitate attachment of the insulation blanket assembly100B to an aircraft structure with a fastener.

As depicted inFIGS.1E and1G, at least one support rail106B of the one or more support rails106B is an elongated member that includes a beveled edge107B on opposing ends of the elongated member to facilitate sliding the insulation blanket assembly110B into position prior to securing the insulation blanket assembly110B to an aircraft structure.

Although rectangular support rails106are illustrated, different patterns of stiffeners (e.g., support rails) may be utilized according to techniques described herein. Additionally, multiple stiffener cross sections can be utilized according to the techniques described herein. A rectangular stiffener may be used for simplicity; however, a triangle stiffener may add rigidity for higher fabrication costs. In some implementations, multiple rectangular stiffeners may be laminated together in a leaf spring pattern and preloaded with curvature for added stiffness with no additional weight expense.

FIG.2illustrates a cross-sectional, schematic view of an aircraft200that includes an insulation blanket assembly, according to an exemplary embodiment. In particular,FIG.2depicts a fuselage230of the aircraft200.

The fuselage230includes a floor204, a ceiling206, and an aesthetic fascia wall or an inner wall208that defines a cabin202, where the ceiling206and/or the inner wall208represents an interior wall of the aircraft200. The floor204of the cabin202may be supported by a plurality of supporting beams260. The inner wall208is a lining that separates a main cabin, cockpit, and/or other areas within the aircraft200from the fuselage230. The inner wall208can be made of plastic, glass-fiber, carbon fiber, glass-reinforced resin, other reinforced polymers, and/or other materials. The inner wall208can be designed to provide thermal and acoustic insulation as well.

Passengers in the aircraft200may congregate in seats210of the cabin202during flight.FIG.2illustrates that, inside of the fuselage230(e.g., in the cabin202), respiration and other sources of water cause a moisture220to enter or form in the air in the cabin202. As a non-limiting example, warm exhaled air includes the moisture220and rises upward through the ceiling206. Some of the warm air rises into a space240between an outer wall216of the aircraft200and the cabin202.

As the outer wall216is cooled by outside air at high altitude during flight, the temperature of the outer wall216eventually decreases to a temperature below a freezing temperature of water. This cooling causes the moisture220(e.g., water) to condense out of the air in the space240and freeze onto an interior surfaces of the outer wall216as ice. As the aircraft200changes to a lower altitude and/or commences descent for landing and the temperature increases, the ice begins to melt causing water droplets225(e.g., liquid) to travel through the space240towards a bottom of the fuselage230.

The space240can include one or more insulation blanket assemblies100to provide thermal and acoustic insulation to the aircraft200. The insulation blanket assemblies100inFIG.2can correspond to the insulation blanket assembly100A ofFIG.1Aor the insulation blanket assembly110B ofFIG.1E. As illustrated inFIG.2, the support rails106of one of the insulation blanket assemblies110are proximate to (e.g., resting on) aircraft stringers250running along the outer wall216of the fuselage230.

The one or more support rails106may extend perpendicular relative to the stringers250such that the one or more support rails106provide a drainage path downwardly towards a lower area of the fuselage230. For example, the orientation of the support rails106is perpendicular to an orientation of the aircraft stringers250such that the support rails106can rest on the aircraft stringers250to provide separation between the insulation material110and an aircraft structure, such as the aircraft stringers250and/or the outer wall216of the fuselage230. The support rails106of the other insulation blanket assembly100is resting flush on the outer wall216of the fuselage230to provide separation between the insulation material110and the outer wall216.

The support rails106reduce an amount of moisture transferred to the insulation material110as the water droplets225(e.g., liquid) travel through the space240towards the bottom of the fuselage230. For example, the separation between the insulation material110and the different aircraft structures caused by the support rails106enable the insulation material110to remain relatively dry, which decreases the rate at which the insulation material110becomes saturated and thus improves (e.g., lengthens) the lifespan of the insulation blanket assembly100. It should also be appreciated that because the support rails106are flexible (e.g., comprised of a foam material), the support rails106can take the shape of the aircraft structures on which the insulation blanket assemblies100rest. For example, because the one or more support rails106are comprised of a flexible foam material, and because the insulation material110and the cover101are flexible, the insulation blanket assembly100may radially conform to a shape of the fuselage230of the aircraft200when installed.

FIG.3illustrates a structural view of the aircraft fuselage230that includes the insulation blanket assembly100, according to an exemplary embodiment.

The aircraft fuselage230includes the floor204that is supported by the plurality of supporting beams260. The supporting beams260can be coupled to (and supported by) a plurality of struts302. The aircraft stringers250run along the side of the aircraft fuselage230and are supported by a plurality of circular frame structures304. For example, the plurality of stringers250may be attached to the plurality of frame structures304and may extend laterally along a length of the fuselage230. The skin306of the aircraft200is coupled to the circular frame structures304and the aircraft stringers250.

As illustrated inFIG.3, the support rails106of the insulation blanket assembly100are positioned perpendicular to the orientation of the aircraft stringers250. As a result, moisture (e.g., the water droplets225) can travel downwardly and be collected at the bottom of the aircraft fuselage230for discharge. Typically, existing insulation blankets become heavily saturated due to the water droplets225; however, the configuration of the support rails106on the insulation blanket assembly100enable the insulation material110to be separated from the water droplets225as the droplets225travel downwardly, which also promotes vertical drainage of the water droplets225.

FIG.4Aillustrates the insulation blanket assembly100A that includes one or more support rails attached to an outboard material, according to an exemplary embodiment. As illustrated inFIG.4A, the support rails106A are attached to the outboard material102A of the cover101A such that the outboard material102A is between the insulation material (not shown inFIG.4A) and the support rails106A.

FIG.4Billustrates an insulation blanket assembly that includes one or more support rails attached to an insulation material, according to an exemplary embodiment. As illustrated inFIG.4B, the support rail106B is attached to the insulation material110B via an adhesive402, such as double-sided tape. The support rail106B is between the insulation material110B and the outboard material102B of the cover101B.

Referring toFIG.5, a diagram500of one or more support rails attached to an insulation blanket is illustrated, according to an exemplary embodiment

The diagram500depicts an insulation blanket550that rests on one or more aircraft stringers250. One or more support rails506A,506B are positioned to elevate the insulation blanket550with respect to the aircraft stringers250. For example, inFIG.5, two (2) support rails506A,506B are positioned to elevate the insulation blanket550with respect to the aircraft stringers250to reduce the rate at which the insulation blanket550becomes saturated with moisture associated with the aircraft stringers250or with aircraft skin. The support rails506A,506B can be comprised of a foam material.

Referring toFIG.6, a diagram600of one or more support rails attached to an insulation blanket is illustrated, according to an exemplary embodiment

The diagram600depicts an insulation blanket650that rests on one or more aircraft stringers250. One or more support rails606A,606B,606C,606D,606E are positioned to elevate the insulation blanket650with respect to the aircraft stringers250. For example, inFIG.6, five (5) support rails606A,606B,606C,606D,606E are positioned to elevate the insulation blanket650with respect to the aircraft stringers250to reduce the rate at which the insulation blanket650becomes saturated with moisture associated with the aircraft stringers250or with aircraft skin. InFIG.6, the support rails606B,606D are longer than the support rails606A,606C,606E. Thus, different support rails606can have different dimensions, as further illustrated inFIG.7. The support rails606A,606B,606C,606D,606E can be comprised of a foam material.

Referring toFIG.7, a diagram700of one or more support rails attached to an insulation blanket is illustrated, according to an exemplary embodiment

The diagram700depicts an insulation blanket750that rests on one or more aircraft stringers250. One or more support rails706A,706B,706C,706D,706E are positioned to elevate the insulation blanket750with respect to the aircraft stringers250. For example, inFIG.7, five (5) support rails706A,706B,706C,706D,706E are positioned to elevate the insulation blanket750with respect to the aircraft stringers250to reduce the rate at which the insulation blanket750becomes saturated with moisture associated with the aircraft stringers250or with aircraft skin. InFIG.7, the support rails706B,706D are shorter than the support rails706A,706C,706E. Thus, different support rails706can have different dimensions. The support rails706A,706B,706C,706D,706E can be comprised of a foam material.

Referring toFIG.8A, a cross-sectional diagram800of portions of an insulation blanket that includes a support rail having a beveled cut is illustrated, according to an exemplary embodiment.

The diagram800depicts portions of an insulation blanket. For example, the diagram800depicts an inboard region803of a cover material, an outboard region804of the cover material, and an insulation material802between the inboard region803of the cover material and the outboard region804of the cover material. The diagram800also depicts a support rail806attached to the outboard region804of the cover material. In particular, an adhesive side890of the support rail806is attached to the outboard region804of the cover material.

Referring toFIG.8B, a diagram of a portion of the support rail with a beveled cut is illustrated, according to an exemplary embodiment. The support rail806can be comprised of a foam material. The support rail806has a beveled cut892towards the non-adhesive side to facilitate sliding the insulation blanket into position.

Referring toFIG.9A, a cross-sectional diagram900of portions of an insulation blanket that includes a support rail having a straight edge is illustrated, according to an exemplary embodiment.

The diagram900depicts portions of an insulation blanket. For example, the diagram900depicts an inboard region903of a cover material, an outboard region904of the cover material, and an insulation material902between the inboard region903of the cover material and the outboard region904of the cover material. The diagram900also depicts a support rail906attached to the outboard region904of the cover material. In particular, an adhesive side990of the support rail906is attached to the outboard region904of the cover material.

Referring toFIG.9B, a diagram of a portion of the support rail with a straight edge is illustrated, according to an exemplary embodiment. The support rail906can be comprised of a foam material. The support rail906has a straight edge992(e.g., a straight 90 degrees cut) between the adhesive side990and the non-adhesive side.

Referring toFIG.10A, a cross-sectional diagram1000of portions of an insulation blanket that includes a support rail having a beveled cut is illustrated, according to an exemplary embodiment.

The diagram1000depicts portions of an insulation blanket. For example, the diagram1000depicts an inboard region1003of a cover material, an outboard region1004of the cover material, and an insulation material1002between the inboard region1003of the cover material and the outboard region1004of the cover material. The diagram1000also depicts support rails1006A,1006B between the outboard region1004of the cover material and the insulation material1002. In particular, an adhesive side1090of the support rail1006A is attached to the outboard region1004of the cover material. The same approach applies to support rail1006B, etc.

Referring toFIG.10B, a diagram of a portion of the support rail with a beveled cut is illustrated, according to an exemplary embodiment. The support rail1006can be comprised of a foam material. The support rail1006has a beveled cut1092towards the adhesive side1090. The same approach applies to support rail1006B, etc.

Referring toFIG.11, a diagram of an insulation blanket assembly installed on the aircraft200is illustrated, according to an exemplary embodiment.

As illustrated inFIG.11, the aircraft200may include an inner mold line1102A and an inner mold line1102B. The inner mold line1102A may be an inner mold line of a first frame structure304depicted inFIG.3, and the inner mold line1102B may be an inner mold line of a second frame structure304depicted inFIG.3. Hook tape1120A (e.g., double-sided tape) may be aligned along the inner mold line1102A, and hook tape1120B may be aligned along the inner mold line1102B. For example, one side of the hook tape1120A,1120B may be attached to the respective inner mold line1102A,1102B, and the other side of the hook tape1120A,1120B may include an adhesive that can adhere to blanket tabs1110A,1110B, as described below.

The insulation blanket assembly100may include (i) a first group of blanket tabs1110A attached to a first edge of the outboard material102of the cover101and (ii) a second group of blanket tabs1110B attached to a second edge of the outboard material102of the cover101. To install the installation blanket assembly100to the aircraft200, the first group of blanket tabs1110A may be attached to the hook tape1120A, and the second group of blanket tabs1110B may be attached to the hook tape1120B.

Referring toFIG.12, a diagram1200of attaching the blanket tabs to an inner mold line of a frame structure of an aircraft is illustrated, according to an exemplary embodiment. According to the diagram1200, the hook tape1120A is aligned along the inner mold line1102A. The first group of blanket tabs1110A is attached to the hook tape1120A to secure the insulation blanket assembly100to the inner mold line1102A.

Referring toFIG.13, a diagram1300of attaching a first blanket tab of a first insulation blanket assembly to a second blanket tab of a second insulation blanket assembly, according to an exemplary embodiment.

In the diagram1300, a plurality of aircraft structures1302are illustrated. In some implementations, the aircraft structures1302can correspond to supports for aircraft flooring, such as the floor204. The diagram1300also includes an insulation blanket assembly100C and an insulation blanket assembly100D. Each insulation blanket assembly110C,110D can correspond to the insulation blanket assembly100A or the insulation blanket assembly100B. The insulation blanket assemblies100C,100D are placed under the aircraft structures1302to provide thermal and acoustic insulation to an aircraft.

To install the installation blanket assemblies100C,100D, tape1310(e.g., hook tape and/or loop tape) attached to a blanket tab of the insulation blanket assembly100C can be placed on tape1320(e.g., double-sided hook tape and/or loop tape) attached to a blanket tab of the insulation blanket assembly100D.

Referring toFIG.14, a cross-sectional diagram1400of an installation blanket assembly installed on an aircraft is illustrated, according to an exemplary embodiment.

In the diagram1400, the stringer250is coupled to the inner mold line1102of a frame structure, such as one of the frame structures304ofFIG.3. Portions of the insulation blanket assembly100are also depicted inFIG.14. For example, the insulation material110and the outboard material102are depicted inFIG.14. The support rails106are attached to the insulation material110to provide separation between the stringers250and the insulation material110, which reduces or eliminates moisture from transferring to the insulation material110.

The hook tape1120is aligned along the mold line1102. The blanket tab1110is attached to the hook tape1120via loop tape1402. For example, the loop tape1402(e.g., double-sided tape) may be attached to blanket tab1110. The loop tape1402is placed on the hook tape1120to provide additional adhesive security when installing the insulation blanket assembly100.

Referring toFIG.15, another cross-sectional diagram1500of an installation blanket assembly installed on an aircraft is illustrated, according to an exemplary embodiment.

In the diagram1500, the stringer250is coupled to the inner mold line1102of the frame structure, such as one of the frame structures304ofFIG.3. Portions of the insulation blanket assembly100are also depicted inFIG.15. For example, the insulation material110and the outboard material102are depicted inFIG.15. The support rails106are attached to the outboard material102to provide separation between the stringers250and the insulation material110, which reduces or eliminates moisture from transferring to the insulation material110.

The hook tape1120is aligned along the mold line1102. The blanket tab1110is attached to the hook tape1120via loop tape1402. For example, the loop tape1402(e.g., double-sided tape) may be attached to blanket tab1110. The loop tape1402is placed on the hook tape1120to provide additional adhesive security when installing the insulation blanket assembly100.

FIG.16illustrates a flow chart of a method1600, according to an exemplary embodiment.

The method1600includes providing an insulation material, at block1602.

The method1600also includes forming a cover, at block1604.

The method1600also includes, prior to or after forming the cover, attaching one or more support rails to at least one of the cover or the insulation material such that, when installed on the aircraft, the one or more support rails provide separation of the insulation material from an outer panel of the aircraft for moisture management, at block1606.

According to one implementation of the method1600, forming the cover includes attaching an inboard material to an outboard material such that the insulation material is between the inboard material and the outboard material.

According to one implementation of the method1600, attaching the one or more support rails includes attaching the one or more support rails to the insulation material such that the one or more support rails are positioned between the outboard material and the insulation material.

According to one implementation of the method1600, attaching the one or more support rails includes attaching the one or more support rails to the outboard material such that the outboard material is between the insulation material and the one or more support rails.

According to one implementation, the method1600may include, prior to attaching the one or more support rails, forming a beveled edge on opposing endos of an elongated member. The elongated member may correspond to at least one support rail of the one or more support rails.

According to one implementation of the method1600, attaching the one or more support rails includes (i) attaching a first support rail of the one or more support rails to at least one of the cover or the insulation material and (ii) attaching a second support rail of the one or more support rails to at least one of the cover of the insulation material. The first support rail and the second support rail may have a parallel orientation.

FIG.17illustrates a flow chart of a method1700, according to an exemplary embodiment.

The method1700includes applying (i) first hook tape to a first inner mold line of a first aircraft frame structure and (ii) second hook tape to a second inner mold line of a second aircraft frame structure, at block1702. The first hook tape and the second hook tape are double-sided tapes.

The method1700also includes applying (i) first loop tape to a first group of blanket tabs attached to a first edge of an outboard material of an insulation blanket assembly and (ii) second loop tape to a second group of blanket tabs attached to a second edge of the outboard material, at block1704. The first loop tape and the second loop tape are double-sided tapes, and the insulation blanket assembly includes one or more support rails that extend transverse relative to aircraft stringers.

The method1700also includes attaching (i) the first group of blanket tabs to the first inner mold line by placing the first loop tape on top of the first hook tape and (ii) the second group of blanket tabs to the second inner mold line by placing the second loop tape on top of the second hook tape, at block1706.

The techniques described with respect toFIGS.1-17reduce the likelihood or risk of an insulation blanket blocking water on its way down drain paths by attaching support rails into the insulation blanket to elevate the insulation blanket (e.g., prevent the insulation blanket from laying flush against skin and structure in the lower lobe structure of the aircraft). The foam support rails allow water drainage above and below the surface of the insulation blanket. Additionally, the increased gap between the insulation blanket and the lower lobe structure of the aircraft can prevent insulation materials within the insulation blanket from becoming saturated with moisture, thus increasing the in-service performance of the insulation blanket.

Although the systems are described herein with specific reference to space systems or aerospace vehicles, in other embodiments, the system can be a vehicle other than a spacecraft without departing from the essence of the present disclosure.

While the systems and methods of operation have been described with reference to certain examples, it will be understood by those skilled in the art that various changes can be made and equivalents can be substituted without departing from the scope of the claims. Therefore, it is intended that the present methods and systems not be limited to the particular examples disclosed, but that the disclosed methods and systems include all embodiments falling within the scope of the appended claims.