Patent ID: 12195188

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account one or more different considerations. For example, the illustrative embodiments recognize and take into account a typical ceiling retainer load is set above any abuse loads a retainer would typically see during installation, service, or day-to-day use to preserve the life of the ceiling retainer which diminishes the effectiveness of the ceiling retainer in certain situations, for example decompression events.

The illustrative embodiments recognize and take into account that typical ceiling retainers currently in use include frangible links that require replacement after a single event such as a decompression event or an accidental trip of the ceiling retainer during maintenance or installation.

The illustrative embodiments also recognize and take into account that after a decompression event or accidental trip of a typical ceiling retainer, tools are required to replace broken frangible links of the ceiling retainer or replacement of the entire ceiling retainer in order to make the ceiling retainer operable again causing the aircraft to be taken out of service for periods of time.

Thus, the illustrative embodiments provide a resettable decompression retainer and roller assembly that allows for a retainer load that is set lower than typical ceiling retainers having frangible links. Thus, the illustrative embodiments provide a resettable decompression retainer that is more effective in more situations. The illustrative embodiments provide a resettable decompression retainer that can be reset by hand back into operational position after an event without having to be replaced and without the use of tools and frangible parts.

The illustrative embodiments provide a resettable decompression retainer that accomplishes at least two functions, hold the ceiling panel closed and allow the ceiling panel to move upward under a decompression load in order to stabilize pressures between two separated compartments like a passenger cabin and a crown space of an aircraft.

With reference now to the figures and, in particular, with reference toFIG.1, an illustration of a block diagram of a platform is depicted in accordance with an illustrative embodiment. Platform100has resettable decompression system102and aircraft104in this illustrative example.

Platform100may take a variety of different forms. For example, without limitation, platform100may be implemented in a mobile platform, a stationary platform, a land-based structure, an aquatic-based structure, or a space-based structure. More specifically, the platform may be an aircraft, a surface ship, a tank, a personnel carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a bridge, a dam, a house, a manufacturing facility, a building, a tool, a mechanical structure, or some other suitable platform or structure where resettable decompression system is desirable.

In this illustrative example, platform100takes the form of aircraft104. In this illustrative example, when platform100takes the form of aircraft104, resettable decompression system102can be installed in aircraft104.

In this illustrative example, aircraft104includes crown space108separated from passenger cabin110by ceiling panel112. Crown space108further includes structures114. Structures114can be any number of support or structural features located in crown space108. Ceiling panel112is connected to structures114. Resettable decompression system102is connected to structures114. Resettable decompression system102is connected to ceiling panel112. Resettable decompression system102holds the ceiling panel closed which separates the passenger cabin from the crown space and provides an aesthetic appearance to the passengers in the passenger cabin of the aircraft.

As used herein, a first component “connected to” or “coupled to” or “associated with” a second component means that the first component can be connected directly or indirectly to the second component. The connection is a physical association. In other words, additional components may be present between the first component and the second component. The first component is considered to be indirectly connected to the second component when one or more additional components are present between the two components. When the first component is directly connected to the second component, no additional components are present between the two components.

For example, a first component can be considered to be physically connected to a second component by at least one of being secured to the second component, bonded to the second component, mounted to the second component, welded to the second component, fastened to the second component, or connected to the second component in some other suitable manner. The first component also can be connected to the second component using a third component. The first component can also be considered to be physically connected to the second component by being formed as part of the second component, an extension of the second component, or both.

In this illustrative example, resettable decompression system102includes resettable decompression retainer106paired with slip fitting118. Typically, more than one resettable decompression retainer106and slip fitting118pair is utilized in resettable decompression system102.

In this illustrative example, slip fitting118is connected to ceiling panel112. Slip fitting118includes slot124.

In this illustrative example, resettable decompression retainer106includes base120and swing arm122. Base120is pivotably124connected swing arm122. Base120is pivotably124connected to swing arm122about axis126. The pivotable connection between base120and swing arm122includes bias130. For example, bias130may be provided by spring132, where spring132is connected to base120and swing arm122. Bias130may be provided by spring132, a shock absorber, a gas or fluid strut, etc. where each is connected to both base120and swing arm122.

In this illustrative example, base120includes cylinder136connected to platform134. Platform134is generally planar and can have constant thickness140or non-constant thickness142. Whether platform134has constant thickness140or non-constant thickness142depends on the location in the aircraft where resettable decompression system102is installed. Space constraints and shape of structures114dictates the thickness of and any angles of non-constant thickness of platform134. Cylinder136surrounds axle144. Axle144provides axis126to which swing arm122is pivotable with respect to base120. Base120includes stop146. Stop146provides a surface where swing arm122abuts base120. Stop146may be angled edge148formed in platform134. Stop146may be notch150formed in cylinder136. Base120includes lag152. Lag152provides a mounting point on base120for spring132or any other device providing bias130.

In this illustrative example, swing arm122includes surface154for abutment with stop146. Surface154may be crossbar166for contact with angled edge148. Surface154may be tab168for contact with notch150. Swing arm122includes lag164. Lag164provides a mounting point on swing arm122for spring132or any other device providing bias130. Swing arm122includes roller156. Roller156further includes sleeve158and axle160. Sleeve158is rotatable about axle160, providing roller axis162. Roller axis162is generally parallel with axis126. Roller156slidably engages slot124of slip fitting118.

Swing arm122is pivotable about axis126with respect to base120. Because of the pivotable connection to base120, swing arm122defines three positions with respect to base120. The three positions of swing arm122with respect to base120are closed position170, over-center position172, and open position174. In normal operation of aircraft104, swing arm122of resettable decompression retainer106is in closed position170and ceiling panel112separates passenger cabin110from crown space108.

If swing arm122is positioned anywhere between closed position170and over-center position172, bias130forces swing arm122into closed position170. When swing arm122is in closed position170, surface154abuts stop146. If swing arm122is positioned anywhere between over-center position172and open position174, bias130forces swing arm122into open position174. When in open position174, swing arm122, thus resettable decompression retainer106, can be manually reset to closed position170without the use of tools and without repairing or replacing any frangible parts. Over-center position172is not a sustainable position. Bias130will always force swing arm122into closed position170or open position174. Swing arm122cannot rest in over-center position172.

During normal operation of the aircraft, the air pressures in the passenger cabin and the crown space are equalized. A decompression event will cause a difference in air pressures between the passenger cabin and the crown space.

During a decompression event, air pressure differences between the passenger cabin and the crown space will create a force on ceiling panel112. Slip fitting118, because it is attached to ceiling panel112and slidably engaged with swing arm122of resettable decompression retainer106, will transmit the force on ceiling panel112to swing arm122. If the force created by the difference in air pressure applied to the swing arm of the resettable decompression retainer is greater than bias130, then swing arm122will rotate with respect to base120and the ceiling panel will move creating an opening between the passenger cabin and the crown space which equalizes the difference in air pressure between the two. In other words, if the force on the ceiling panel is greater than the bias holding the swing arm in a closed position with respect to the base, the swing arm rotates and an air pressure equalizing opening between the passenger cabin and the crown space forms.

Resettable decompression system102will allow ceiling panel112to move to create an opening between crown space108and passenger cabin110. The opening created by resettable decompression system102allows the air pressures between passenger cabin110and crown space108to stabilize. After the decompression event, if the swing arm122has fully rotated from closed position170to open position174, resettable decompression system102can be reset by hand to closed position170without the use of tools and without replacing any frangible pieces in order to get the aircraft back into service as quickly as possible.

Swing arm122will rotate with respect to base120if a force applied to the swing arm is greater than bias130. The force may be the result of, for example, a decompression event or accidental bumping by a technician during installation or routine maintenance. If the force applied to the swing arm is less than bias130, swing arm122does not rotate with respect to base120. If the force applied to the swing arm is greater than bias130, swing arm122will begin to rotate with respect to base120. If at any time the force ceases to overcome bias130and the rotation of swing arm122with respect to base120from the closed position has not reached the over-center position, bias130will automatically force swing arm122back to the closed position without any manual manipulation required. If the force applied to the swing arm is greater than bias130and rotation of the swing arm with respect to the base moves from the closed position to beyond the over-center position, bias130will force the swing arm to the open position regardless of the presence or strength of the force.

As used herein, the phrase “at least one of,” when used with a list of items, means different combinations of one or more of the listed items can be used, and only one of each item in the list may be needed. In other words, “at least one of” means any combination of items and number of items may be used from the list, but not all of the items in the list are required. The item can be a particular object, a thing, or a category.

For example, without limitation, “at least one of item A, item B, or item C” may include item A, item A and item B, or item B. This example also may include item A, item B, and item C or item B and item C. Of course, any combinations of these items can be present. In some illustrative examples, “at least one of” can be, for example, without limitation, two of item A; one of item B; and ten of item C; four of item B and seven of item C; or other suitable combinations.

With reference next toFIGS.2-4, illustrations of a passenger cabin and crown space of an aircraft are depicted in accordance with an illustrative example. In this illustrative example, passenger cabin202of aircraft200is separated from crown space204of aircraft200by ceiling panel206. Structures208may include overhead bins210. Resettable decompression system212includes slip fitting214and resettable decompression retainer216. Slip fitting214is connected to ceiling panel206. Resettable decompression retainer216is connected to structures208. In this illustrative example, aircraft200is an example of one implementation for aircraft104shown in block form inFIG.1. Resettable decompression system212is an example of one implementation for resettable decompression system102shown in block form inFIG.1.

As depicted,FIG.2shows resettable decompression retainer216in a closed position as it would be during normal operating conditions of the aircraft. Ceiling panel206separates passenger cabin202from crown space204. There is generally no opening between passenger cabin202from crown space204. A roller of resettable decompression retainer216is slidably engaged in a slot of slip fitting214.

FIG.3depicts resettable decompression retainer216in an open position as it would be immediately after a decompression event created a force sufficient to overcome the bias of resettable decompression retainer216. The force sufficient to overcome the bias of resettable decompression retainer216has moved ceiling panel206such that slip fitting214has rotated the swing arm of resettable decompression retainer216relative to the base of resettable decompression retainer216to the open position. As a result, opening302exists between passenger cabin202and crown space204. Opening302allows the air pressure differences between passenger cabin202and crown space204resulting from the decompression event to equalize.

FIG.4depicts resettable decompression retainer216in an open position and ready to be manually reset without the use of tools or without the need to repair or replace resettable decompression retainer216. After the air pressure differences between passenger cabin202and crown space204have been equalized, gravity forces slip fitting214attached to ceiling panel206into contact with structures208. Slip fitting214in contact with structures208prevents ceiling panel206from falling into passenger cabin202. The swing arm of the resettable decompression retainer216can be manually reset against the bias of resettable decompression retainer216into the closed position while slidably reengaging slip fitting214with the swing arm of resettable decompression retainer216.

With reference next toFIGS.5-7, illustrations of a resettable decompression system are depicted in accordance with an illustrative example. In this illustrative example, resettable decompression system500is an example of one implementation for resettable decompression system102shown in block form inFIG.1.

In this illustrative example, resettable decompression system500includes slip fitting502and resettable decompression retainer504. Slip fitting502is connected to ceiling panel506. Slip fitting502includes slot508. Resettable decompression retainer504includes swing arm510pivotably connected to base512about axis516. Base512is connected to structures514. Swing arm510includes roller518. Spring520is connected to swing arm510and base512. Spring520imparts bias522on swing arm510with respect to base512.

FIG.5depicts resettable decompression retainer504in a closed position as it would be during normal operating conditions of the aircraft. Ceiling panel506separates the passenger cabin from the crown space. Roller518is slidably engaged in slot508. In the closed position, angle A depicts swing arm510with no rotation with respect to base512. Bias522urges swing arm510into the closed position depicted.

FIG.6depicts resettable decompression retainer504where swing arm510has rotated with respect to base512through angle B. A force, either on swing arm510itself or on ceiling panel506and transmitted to swing arm510, sufficient to overcome bias522, causes swing arm510to move from the closed position and rotate with respect to base512.

FIG.7depicts resettable decompression retainer504in an open position as it would be after a force sufficient to overcome bias522has caused swing arm510to rotate from the closed position to beyond an over-center position. The open position of resettable decompression retainer504depicted inFIG.7shows swing arm510rotated with respect to base512through angle C.

With reference next toFIG.8, illustration of a slip fitting is depicted in accordance with an illustrative example. In this illustrative example, slip fitting800is an example of one implementation for slip fitting118shown in block form inFIG.1. In this illustrative example, slip fitting800is an example of one implementation for slip fitting214shown inFIGS.2-4and slip fitting502shown inFIGS.5-7.

As depicted, slip fitting800includes body802extending from base804. Base804includes mounting holes806for attaching slip fitting800to a ceiling panel. Body802defines slot808. Slot808is sized to slidably receive a roller from a swing arm of a resettable decompression retainer.

With reference next toFIGS.9-11, an illustration of components of a resettable decompression retainer is depicted in accordance with an illustrative example. In the illustrative examples, the same reference numeral may be used in more than one figure. This reuse of a reference numeral in different figures represents the same element in the different figures. The components illustrated inFIGS.9-11are examples of physical implementations of resettable decompression retainer106shown in block form inFIG.1.

As illustrated, resettable decompression retainer900includes swing arm902pivotably connected to base904.FIG.9depicts an exploded view of resettable decompression retainer900in a closed position.FIG.10depicts resettable decompression retainer900in a closed position.FIG.11depicts resettable decompression retainer900in an open position.

Swing arm902is generally “U-shaped” including crossbar906extending between side908and side909. Crossbar906provides surface910for abutment with base904. Side908includes lag912for attachment of spring914. Side909includes lag916for attachment of spring918. Side908and side909define hole920and hole921for housing axle922. Axle922defines axis924. Side908and side909define hole930and hole931for housing axle932. Axle932defines roller axis934. Sleeve936surrounds axle932and rotates with respect to axle932about roller axis934to form roller928. Roller axis934is generally parallel to axis924.

Base904is generally planar including cylinder940extending from platform942. Platform942includes lag944for attachment of spring914and lag946for attachment of spring918. Platform942includes mounting holes948for attachment of base904to aircraft structures. Platform942has a non-constant thickness over width W. Cylinder940defines opening950sized to receive axle922. Platform942includes angled edge952for abutment with surface910of swing arm902.

Retaining rings954secure axle932and axle922within resettable decompression retainer900to pivotably connect swing arm902to base904and to connect roller928to swing arm902. Swing arm902is rotatable with respect to base904about axis924. Sleeve936of roller928is rotatable with respect to axle932about roller axis934.

With reference next toFIGS.12-14, an illustration of components of a resettable decompression retainer is depicted in accordance with an illustrative example. In the illustrative examples, the same reference numeral may be used in more than one figure. This reuse of a reference numeral in different figures represents the same element in the different figures. The components illustrated inFIGS.12-14are examples of physical implementations of resettable decompression retainer106shown in block form inFIG.1.

As illustrated, resettable decompression retainer1200includes swing arm1202pivotably connected to base1204.FIG.12depicts an exploded view of resettable decompression retainer1200in an open position.FIG.13depicts resettable decompression retainer1200in a closed position.FIG.14depicts resettable decompression retainer1200in an open position.

Swing arm1202is generally “U-shaped” including crossbar1206extending between side1208and side1209. Crossbar1206includes tab1210for abutment with base1204. Side1208includes lag1212for attachment of spring1214. Side1209includes lag1216for attachment of spring1218. Side1208and side1209define hole1220and hole1221for housing axle1222. Axle1222defines axis1224. Side1208and side1209define hole1230and hole1231for housing axle1232. Axle1232defines roller axis1234. Sleeve1236surrounds axle1232and rotates with respect to axle1232about roller axis1234to form roller1228. Roller axis1234is generally parallel to axis1224.

Base1204is generally planar including cylinder1240extending from platform1242. Platform1242includes lag1244for attachment of spring1214and lag1246for attachment of spring1218. Platform1242includes mounting holes1248for attachment of base1204to aircraft structures. Platform1242has a constant thickness T over width W. Cylinder1240defines opening1250sized to receive axle1222. Cylinder1240includes notch1252for abutment with tab1210of swing arm1202.

Retaining rings1254secure axle1232and axle1222within resettable decompression retainer1200to pivotably connect swing arm1202to base1204and to connect roller1228to swing arm1202. Swing arm1202is rotatable with respect to base1204about axis1224. Sleeve1236of roller1228is rotatable with respect to axle1232about roller axis1234.

With reference next toFIG.15, an illustration of a flowchart of a process1500for relieving pressure from a passenger cabin of an aircraft during a decompression event. The method depicted inFIG.15may be used in conjunction with resettable decompression retainer depicted inFIGS.1-14.

The process begins by attaching a resettable decompression retainer to a structure of an aircraft (operation1502). The resettable decompression retainer comprises a base configured to be attached to the structure of the aircraft and a swing arm pivotably connected to the base. The swing arm has a bias relative to the base. The process attaches a slip fitting to a panel of the aircraft (operation1504). The slip fitting comprises a slot. The panel separates the passenger cabin from a crown space of the aircraft and the swing arm is slidably engaged with the slot. In response to a force applied to the resettable decompression retainer, the process continues by rotating the swing arm relative to the base against the bias to an open position as the swing arm moves through the slot if the force applied to the resettable decompression retainer is greater than the bias (operation1506).

The process may automatically reset the resettable decompression retainer to a closed position if the force applied to the resettable decompression retainer does not rotate the swing arm beyond an over-center position (operation1508). Automatically resetting the resettable decompression retainer to a closed position occurs without any manual intervention. The bias returns the resettable decompression retainer to a closed position if the rotation of the swing arm has not progressed beyond an over-center position of the swing arm relative to the base. The process may include manually resetting the resettable decompression retainer to a closed position (operation1510). Manually resetting the resettable decompression retainer to a closed position does not require the use of tools and does not require repairing or replacing any frangible parts.

In some alternative implementations of an illustrative example, the function or functions noted in the blocks may occur out of the order noted in the figures. For example, in some cases, two blocks shown in succession may be performed substantially concurrently, or the blocks may sometimes be performed in the reverse order, depending upon the functionality involved. Also, other blocks may be added in addition to the illustrated blocks in a flowchart or block diagram.

The illustrative embodiments of the disclosure may be further described in the context of aircraft manufacturing and service method1600as shown inFIG.16and aircraft1700as shown inFIG.17. Turning first toFIG.16, an illustration of a block diagram of an aircraft manufacturing and service method is depicted in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method1600may include specification and design1602of aircraft1700inFIG.17and material procurement1604.

During production, component and subassembly manufacturing1606and system integration1608of aircraft1700inFIG.17takes place. Thereafter, aircraft1700inFIG.17may go through certification and delivery1610in order to be placed in service1612. While in service1612by a customer, aircraft1700inFIG.17is scheduled for routine maintenance and service1614, which may include modification, reconfiguration, refurbishment, and other maintenance, service, or inspection.

Resettable decompression system102may be installed on an aircraft during component and subassembly manufacturing1606. In addition, Resettable decompression system102may be retrofitted onto aircraft1700inFIG.17during routine maintenance and service1614as part of a modification, reconfiguration, or refurbishment of aircraft1700inFIG.17.

Each of the processes of aircraft manufacturing and service method1600may be performed or carried out by a system integrator, a third party, an operator, or some combination thereof. In these examples, the operator may be a customer. For the purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and major-system subcontractors; a third party may include, without limitation, any number of vendors, subcontractors, and suppliers, and an operator may be an airline, a leasing company, a military entity, a service organization, and so on.

With reference now toFIG.17, an illustration of a block diagram of an aircraft is depicted in which an illustrative embodiment may be implemented. In this example, aircraft1700is produced by aircraft manufacturing and service method1600inFIG.16and may include airframe1702with plurality of systems1704and interior1706. Examples of systems1704include one or more of propulsion system1708, electrical system1710, hydraulic system1712, and environmental system1714. Any number of other systems may be included. Although an aerospace example is shown, different illustrative embodiments may be applied to other industries, such as the automotive industry.

Apparatuses and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and service method1600inFIG.16. In one illustrative example, components or subassemblies produced in component and subassembly manufacturing1606inFIG.16may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft1700is in service1612inFIG.16. As yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production stages, such as component and subassembly manufacturing1606and system integration1608inFIG.16. One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized while aircraft1700is in service1612, during maintenance and service1614, inclusive of inspection, inFIG.16, or both. The use of a number of the different illustrative embodiments may substantially expedite the assembly of aircraft1700, reduce the cost of aircraft1700, or both expedite the assembly of aircraft1700and reduce the cost of aircraft1700.

The description of the different illustrative embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the embodiments in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different illustrative embodiments may provide different features as compared to other desirable embodiments. The embodiment or embodiments selected are chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.