Patent Description:
Cargo may be transported to its destination using one or more of several different types of vehicles, including, for example, ships, trains, aircraft, and trucks, Such cargo is transported while located in the interior of cargo areas. In some cases, cargo may include hazardous, easily flammable, and/or easily combustible materials that may render transport dangerous to the cargo itself, as well as to the vehicle transporting the cargo and operators of the vehicle.

In many instances, cargo may be carried in an area separated from an operator controlling the vehicle. As a result, an operator may be unaware of a fire or explosion that has occurred within a cargo container or within the cargo area. In addition, there is often more than one cargo container located in any given cargo area. This may render it difficult to determine which containers are on fire, even if it has been determined that there is a fire occurring within a given cargo area.

Due to the nature of a cargo vehicle, there may be a limited supply of fire suppressant available. For example, aboard a cargo aircraft, the weight of any fire suppressant may limit the amount of fire suppressant that may be carried for suppressing fires. Therefore, it may be desirable to limit the amount of fire suppressant used to extinguish a fire in order to reduce the weight carried by the aircraft by focusing any release of fire suppressant on the particular area in need of fire suppressant, rather than merely releasing a large enough amount of suppressant to flood the entire cargo area. Furthermore, the fire suppressant itself may be harmful to some types of cargo. Therefore, it may be desirable to limit the release of fire suppressant to the location in need of fire suppression, so as to limit the spoilage of cargo not in need of fire suppressant. As a result, it may be desirable to provide a fire detection system that can determine the approximate location of a fire, so that an appropriate amount of fire suppressant can be directed solely to the location experiencing the fire.

Because cargo areas experiencing a fire may be located remotely from cargo vehicle operators (i.e., the cargo may be located in an unoccupied and/or difficult to access portion of the vehicle), it may be more difficult to provide fire suppressant to an area experiencing a fire in a timely manner. Therefore, it may be desirable to provide a system for supplying fire suppressant remotely and in a timely manner.

One example of a cargo vehicle having an operator located relatively remotely from the cargo area is an aircraft. The majority of cargo carried by modern aircraft is transported in cargo containers or on cargo pallets. The containers are generally referred to generically as Unit Load Devices ("ULDs"). For safety considerations, ULDs must often be configured to engage an aircraft cargo locking system in order to restrain the cargo containers under various flight, ground load, and/or emergency conditions. Under federal air regulations, ULDs are considered aircraft appliances, are Federal Aviation Administration (FAA)-certified for a specific type of aircraft, and are typically manufactured to specifications contained in National Aerospace Standard (NAS) <NUM>.

In the cargo aircraft example, while some cargo areas may be conventionally equipped with fire extinguishing bottles intended for manual operation, very few cargo containers may be accessible to flight crews during a flight, thereby rendering it difficult to manually extinguish a fire located in an aircraft cargo area using fire extinguishing bottles. In addition, fires may occur inside cargo containers, and if those fires are not suppressed or extinguished, they could breach the walls of the container and spread throughout the cargo area. However, it may be difficult, if not impossible, to suppress or extinguish a fire inside a container without discharging fire suppressant into the interior of the container.

Thus, it may be desirable to provide a system for detecting a fire in a cargo container of a vehicle cargo area. Further, it may be desirable to provide a system for suppressing a fire associated with a container for which a fire has been detected. In addition, it may be desirable to provide a system for supplying fire suppressant inside the container. Further, it may be desirable to provide a system that has reduced weight for suppressing a fire associated with a container.

In order reduce the labor and time associated with loading and unloading cargo from a cargo area, it is desirable to minimize impediments to crews responsible for loading and unloading cargo. Thus, it may be desirable to provide a system for suppressing a fire that does not provide unnecessary impediments to loading and unloading cargo from a cargo area.

Problems associated with detecting and/or suppressing fires are not limited to the cargo transportation industry. Similar problems may arise, for example, wherever cargo and/or other articles are stored in a location that is remote from a person supervising the cargo or other articles, such as, for example, a storage facility. Thus, in a broad variety of situations, it may be desirable to remotely detect and/or remotely suppress a fire.

A system for fire suppressing fires in cargo bays of vehicles is known from <CIT>.

In the following description, certain aspects and embodiments will become evident. It should be understood that the aspects and embodiments, in their broadest sense, could be practiced without having one or more features of these aspects and embodiments. It should be understood that these aspects and embodiments are merely exemplary.

According to an aspect, there is provided a system as set forth in the appended claims. Other features will be apparent from the dependent claims, drawings and the description which follows.

As used herein, the term "fire" is not necessarily limited to a fire having visible flames. Rather, the term "fire" is used in a broad sense and may be used to describe situations in which an object and/or surface is exhibiting a higher temperature than desired or considered to be unsafe to a person having skill in the art, such as, for example, a situation in which an object and/or surface is smoldering, smoking, and/or is hot to the touch.

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate several exemplary embodiments of the invention and together with the description, may serve to explain the principles of the invention. <FIG> illustrate embodiments according to the claimed invention, and <FIG> illustrate non-claimed combinations of features that may be implemented in conjunction with the embodiments and therefore may be useful for implementing the claimed invention.

Reference will now be made in detail to exemplary embodiments of the invention, which are illustrated in the accompanying drawings.

<FIG> and <FIG> depict an exemplary cargo aircraft <NUM>, which is merely one example of an environment in which the exemplary systems for suppressing a fire inside a container disclosed herein may be used. Use in other environments is also possible and contemplated, such as, for example, in ships, trucks, trains, other types of vehicles, and/or storage facilities.

As shown in <FIG>, exemplary aircraft <NUM> includes a body <NUM> (i.e., a fuselage) defining an interior <NUM> of aircraft <NUM>. Interior <NUM> may includes a cargo area <NUM> having a deck <NUM> and a ceiling <NUM> spaced above deck <NUM>. Deck <NUM> may be configured to support one or more cargo containers <NUM> configured to contain items for transport aboard aircraft <NUM>. For example, deck <NUM> may include rollers and/or fixtures (not shown) configured to facilitate ease of movement of containers <NUM> within cargo area <NUM> and/or to secure containers <NUM> in a fixed position on deck <NUM>.

Referring to <FIG>, exemplary deck <NUM> of aircraft <NUM> is divided into a number of cargo positions <NUM> to guide placement of containers <NUM>. For example, the exemplary deck <NUM> shown in <FIG> is divided into two longitudinally-extending rows defining cargo positions <NUM> for placement of containers <NUM>. The number and configuration of cargo positions <NUM> is exemplary and other numbers and configurations are contemplated.

Referring to <FIG>, containers 22a and 22b located at cargo positions 24a and 24b, respectively, may be cargo containers, such as, for example, ULDs. Such containers may have differing dimensions. For example, a very commonly used industry ULD is the "SAA" designated container, which measures about <NUM> inches wide by about <NUM> inches long, with an arched roof about <NUM> inches high. Another example of a ULD is the "AMJ" designated container, which measures about <NUM> inches wide by about <NUM> inches long, with a maximum height of about <NUM> inches. ULDs may have walls formed of, for example, one or more of aluminum, steel, composites, fiberglass, and LEXAN. Containers <NUM> may be any containers known to those skilled in the cargo container art. For example, containers <NUM> may be any containers certified by the FAA and/or may be manufactured to specifications contained in NAS <NUM>.

As shown in <FIG>, exemplary aircraft <NUM> may be provided with a system <NUM> for suppressing a fire associated with (e.g., within) one or more of containers <NUM>. For example, exemplary system <NUM> shown in <FIG> includes a control system <NUM> and a fire suppression system <NUM>. Control system <NUM> may be configured to receive signals from one or more sensors <NUM> for detecting a temperature associated with one or more of containers <NUM>, and determine whether the detected temperature is greater than a predetermined temperature, and if so, either activate fire suppression system <NUM> or activate a warning signal. In some embodiments, control system <NUM> activates both a fire suppression system <NUM> and a warning signal. Such signals may be transmitted via hard-wire, wireless systems, and/or infrared systems known to those skilled in the art. For example, infra-red transmission systems may be used in order to reduce interference with, for example, signals associated with operation of aircraft <NUM>.

Control system <NUM> may include a switch (not shown), such that an operator of the aircraft <NUM> may manually activate fire suppression system <NUM>. Fire suppression system <NUM> is configured such that when activated, fire suppressant is supplied to the container <NUM> (e.g., into the interior of the container <NUM>) associated with the sensor <NUM> that detects a temperature greater than the predetermined temperature. As explained in more detail below, exemplary system <NUM> for suppressing a fire may be capable of detecting a fire inside a container, deploying a penetrator system to the container, piercing the container, and/or supplying fire suppressant into the interior of the container.

As shown in <FIG>, exemplary control system <NUM> includes at least one control module <NUM> configured to control exemplary system <NUM> and one or more sensors <NUM> in communication with control module <NUM> for detecting a temperature associated with one or more of containers <NUM>. Exemplary control module <NUM> may be a microprocessor-based controller, such as, for example, a programmable or preprogrammed controller that operates digitally according to logic and/or program instructions stored either within controller <NUM> or downloaded remotely via physical connection and/or wireless communication link.

In exemplary control system <NUM>, one or more sensors <NUM> may be mounted in cargo area <NUM> in relation to one or more of respective cargo positions <NUM>, such that the sensors <NUM> are able to detect a temperature associated with a container <NUM> located at, or in the vicinity of, the respective cargo positions <NUM>. For example, one or more sensors <NUM> may be mounted above (e.g., via ceiling <NUM>) and/or to the side of (e.g., adjacent to) a cargo position <NUM>, such that the one or more sensors <NUM> can detect a temperature associated with a container <NUM> positioned at the corresponding cargo position <NUM>. Sensors <NUM> may be, for example, thermopiles, optical pyrometers, and/or infrared sensors. Any temperature sensors known to those skilled in the art are contemplated and may be used. According to some embodiments, signals may be sent to a warning system, including, for example, warning lights and/or audible messages for warning an operator or system supervisor. Some embodiments may include a manual switch that may be triggered by an operator to activate the exemplary system <NUM> upon receipt of warning signals.

Exemplary fire suppression system <NUM> shown in <FIG> includes a fire suppression system <NUM>, including one or more fire suppressant devices <NUM> configured to suppress a fire associated with (e.g., inside) one or more of containers <NUM> and a fire suppressant delivery system <NUM> configured to supply fire suppressant to fire suppressant devices <NUM>. For example, fire suppressant delivery system <NUM> may include one or more tanks <NUM> containing fire suppressant and a manifold system <NUM>, including conduit <NUM> and associated fittings (not shown) for providing flow communication between the tank(s) <NUM> and one or more devices <NUM> for suppressing a fire. Conduit <NUM> and related fittings may be any suitable conduit and/or fittings known to those skilled in the art. Manifold system <NUM> may be configured to selectively supply fire suppressant to one or more of individual fire suppressant devices <NUM>. In particular, manifold system <NUM> may include a number of valves (not shown) configured to direct flow to any one or more of fire suppressant devices <NUM> in response to signals received from control module <NUM>. As a result, if a fire associated with one of containers <NUM> is detected, control module <NUM> is configured to send a signal to appropriate valves of manifold system <NUM>, such that fire suppressant is supplied only to the container <NUM> associated with the detected fire.

For example, as shown in <FIG>, exemplary system <NUM> includes three tanks 44a, 44b, and 44c. Tanks 44a, 44b, and 44c may each contain the same fire suppressant, different fire suppressants, or different components that are combined to form a single fire suppressant. For example, tank 44a and 44b may contain gas, and tank 44c may contain foam solution, such that when the gas and foam solution is combined at a fire suppressant device <NUM>, fire suppressant foam is created for discharging into the container <NUM>, as explained in more detail herein. For example, the gas may include oxygen, nitrogen, or any inert gas (i.e., helium, neon, argon, krypton, xenon, and radon). The foam solution may be, for example, CARGO FOAM marketed by ANSUL, or any other solution that becomes foam when combined with gas. Other fire suppressant agents and/or components known to those skilled in the art are contemplated and may be used.

Referring to <FIG>, exemplary fire suppressant device <NUM> includes a support structure <NUM> configured to be mounted inside, for example, aircraft <NUM>, a deployment structure <NUM>, and a penetrator assembly <NUM>. As shown in <FIG>, exemplary support structure <NUM> is configured to provide mounting points for various components of fire suppressant device <NUM>, as explained in more detail below.

Exemplary support structure <NUM> shown in <FIG> includes four frame members 56a-56d coupled to one another to form a generally rectangular frame <NUM> (e.g., a generally square frame). Exemplary frame <NUM> is configured to be attached to the interior of a vehicle, for example, cargo area <NUM> of aircraft <NUM>, via known attachment devices (e.g., bolts, screws, welded joints, etc.). For example, as shown in <FIG> and <FIG>, exemplary frame <NUM> is attached to ceiling <NUM> of aircraft <NUM>, so that frame <NUM> is oriented in a substantially horizontal plane and is positioned along a center line of aircraft <NUM>. Other locations and/or orientations are contemplated.

As used herein, the terms "horizontal" and "vertical," and derivatives thereof, may be used to describe positions and orientations in a relative sense, such as, for example, in a sense relative to a structure to which frame <NUM> may be mounted. Thus, to the extent that, for example, a vehicle in which frame <NUM> is mounted is level, frame <NUM> is mounted such that it lies in a horizontal plane. However, if the vehicle in which frame <NUM> is mounted is not level, frame <NUM> would not be horizontal in a global sense, but rather in a relative sense, such that frame <NUM> would lie in a plane substantially parallel to, for example, a plane in which deck <NUM> and/or ceiling <NUM> of aircraft <NUM> lies, at least in the exemplary embodiments disclosed herein. However, the terms "horizontal" and "vertical," with respect to each other, are generally orthogonal to one another, regardless of whether those terms are used in a global or relative sense.

As shown in <FIG> and <FIG>, exemplary frame <NUM> further includes two brace members 60a and 60b, which both extend from a generally central point of frame member 56a to a generally central point of frame members 56b and 56c, respectively. Brace members 60a and 60b provide support for frame <NUM> and deployment structure <NUM>. Exemplary support structure <NUM> may be formed of one or more of aluminum, titanium, steel, composite material, such as, for example, carbon fiber, and/or any other suitable materials known to those skilled in the art. In addition, exemplary frame members 56a-56d and brace members 60a and 60b may have any cross-sectional shape, such as, for example, C-shaped, channel-shaped, I-shaped, L-shaped, Z-shaped, circular, and/or box-shaped. Other cross-sectional shapes known to those skilled in the art are contemplated and may be used.

Exemplary support structure <NUM> further includes a pivot mount <NUM> configured to provide an attachment point for deployment structure <NUM>. As shown in <FIG> and <FIG>, exemplary pivot mount <NUM> includes a first plate 64a coupled to an underside of brace members 60a and 60b and frame member 56a, and a second plate 64b (see <FIG> and <FIG>) coupled to an upper side of brace members 60a and 60b and frame member 56a, at a point where brace members 60a and 60b meet at the generally central point of frame member 56a. Exemplary plates 64a and 64b provide a pivot point defining a vertical axis V for receiving deployment structure <NUM> and providing a vertical hinge <NUM>, which enables deployment structure <NUM> to swing in a pivoting manner in a first plane P<NUM> (e.g., a horizontal plane) (see, e.g., <FIG>).

Exemplary support structure <NUM> also includes a stow mount <NUM> configured to support a latch assembly, which maintains deployment structure <NUM> in a stowed condition when exemplary fire suppressant device <NUM> is not in use. By virtue of maintaining this stowed condition, fire suppressant device <NUM> does not interfere with, for example, the loading and unloading of containers <NUM> into and from cargo area <NUM>. Exemplary stow mount <NUM> includes a support bracket <NUM> mounted to frame <NUM>.

Exemplary deployment structure <NUM> shown in <FIG> and <FIG> includes an arm <NUM> coupled at one end to support structure <NUM> and at the opposite end to penetrator assembly <NUM>. More specifically, exemplary deployment structure <NUM> includes a pivot member <NUM> coupled to hinge <NUM>, and exemplary pivot member <NUM> includes a hinge <NUM> to which one end of arm <NUM> is coupled. Hinge <NUM> provides a pivot point defining a horizontal axis H (<FIG>), which enables arm <NUM> to swing in a pivoting manner in a second plane P<NUM> (e.g., a vertical plane), which is generally orthogonal with respect to the first plane P<NUM>. (See, e.g., <FIG>). Thus, by virtue of exemplary arm <NUM> of deployment structure <NUM> being coupled to support structure <NUM> via hinges <NUM> and <NUM>, arm <NUM> may be pivoted in two generally orthogonal planes (e.g., a horizontal plane and a vertical plane, respectively).

As shown in <FIG> and <FIG>, exemplary arm <NUM> includes two lower links 82a and 82b and two upper links 82c and 82d. More specifically, links 82a-82d are coupled at one end to pivot member <NUM>, such that lower links 82a and 82b are coupled to a lower portion of pivot member <NUM>, and upper links 82c and 82d are coupled to an upper portion of pivot member <NUM>. Links 82a-82d are also coupled at the opposite end to penetrator assembly <NUM>, such that lower links 82a and 82b are coupled to a lower portion of penetrator assembly <NUM>, and upper links 82c and 82d are coupled to an upper portion of penetrator assembly <NUM>. Lower and upper links 82a-82d are coupled to pivot member <NUM> and penetrator assembly <NUM> in a manner that permits each of links 82a-82d to pivot relative to pivot member <NUM> and penetrator assembly <NUM>.

In the exemplary embodiment shown, lower links 82a and 82b are generally parallel to upper links 82c and 82d. By virtue of this exemplary arrangement, as arm <NUM> pivots in second plane P<NUM> (e.g., a vertical plane), penetrator assembly <NUM> maintains a substantially constant orientation relative to support structure <NUM>. In particular, frame <NUM> of support structure <NUM> is shown lying in an exemplary horizontal plane, and as arm <NUM> pivots in a plane orthogonal to the horizontal plane, penetrator assembly <NUM>, although moving vertically in relation to frame <NUM>, does not rotate relative the horizontal plane, thus maintaining its orientation relative to frame <NUM>.

Exemplary penetrator assembly <NUM> is configured to receive fire suppressant from fire suppressant delivery system <NUM>, pierce a barrier, such as, for example, a wall of a container <NUM> (e.g., an upper wall of container <NUM>), and direct fire suppressant into the interior of container <NUM>. Referring to <FIG>, exemplary penetrator assembly <NUM> includes a housing <NUM>, a fire suppressant receiving chamber <NUM>, a nozzle <NUM>, and a puncture actuator <NUM>. Fire suppressant receiving chamber <NUM>, nozzle <NUM>, and a puncture actuator <NUM> are coupled to one another via housing <NUM>.

Exemplary fire suppressant receiving chamber <NUM> includes a tubular structure <NUM>, which is in flow communication with fire suppressant delivery system <NUM> via conduits 48a and 48b. In the exemplary embodiment shown, conduits 48a and 48b are coupled to one end of tubular structure <NUM> and provide flow communication via manifold system <NUM> to tanks 44a-44c (see <FIG>, <FIG>, and <FIG>).

During activation of exemplary system <NUM>, control system <NUM> operates to open appropriate valves in manifold system <NUM>, so that conduits 48a and 48b supply fire suppressant to receiving chamber <NUM>. Tanks 44a-44c may supply the same fire suppressant to receiving chamber <NUM>. However, according to some embodiments, tanks 44a and 44b and tank 44c may contain different components of a fire suppressant, and conduits 48a and 48b may supply first and second fire suppressant components, respectively, to receiving chamber <NUM>. For example, tanks 44a and 44b may supply gas to receiving chamber <NUM>, and tank 44c may supply foam solution to receiving chamber <NUM>. Receiving chamber <NUM> may include a foam generator (not shown) in tubular structure <NUM>, with the foam generator being configured to receive gas and foam solution, and combine the gas and foam solution to form fire suppressant foam.

Exemplary receiving chamber <NUM> is in flow communication with housing <NUM>, which includes a chamber <NUM> defined therein. Exemplary nozzle <NUM> includes a tubular member <NUM>, which is coupled to housing <NUM>, thereby providing flow communication between tubular member <NUM> and receiving chamber <NUM> via chamber <NUM> of housing <NUM>. Thus, fire suppressant supplied to receiving chamber <NUM> via fire suppressant delivery system <NUM> flows through chamber <NUM> and into tubular member <NUM> of nozzle <NUM>.

Tubular member <NUM> of exemplary nozzle <NUM> extends from housing <NUM> and ends in a tip <NUM> configured to pierce a barrier, such as a wall of container <NUM>. Tip <NUM> may be configured with a scalloped edge or other characteristic for facilitating the piercing of a barrier. Tubular member <NUM>, although shown as having a circular cross-section, may have any one of a number of cross-sections, such as, for example, square-shaped, triangular-shaped, etc. The tubular configuration of exemplary tubular member <NUM> provides flow communication between chamber <NUM> of housing <NUM> and the tip-end of nozzle <NUM>, so that fire suppressant may flow from housing <NUM> and out tip <NUM> and behind a barrier pierced by tip <NUM> (e.g., a wall of container <NUM>). Exemplary tip <NUM> may be formed from one or more of steel, cutting steel, stainless steel, titanium, ceramics, composites, or any other material(s) known to those skilled in the art for piercing materials, such as, for example, aluminum, steel, composites, carbon fiber, LEXAN, fiberglass, and/or any other material of which a barrier (e.g., a wall of container <NUM>) may be formed. According to some embodiments, tip <NUM> may be frangible, so that once it has penetrated a barrier, it may be disassociated from a portion of the remainder of nozzle <NUM> and/or housing <NUM>.

As shown in <FIG>, exemplary puncture actuator <NUM> includes a cylinder portion <NUM> and a piston portion <NUM>. <FIG> shows exemplary puncture actuator <NUM> in an extended configuration, with piston portion <NUM> extending from cylinder portion <NUM>. Cylinder portion <NUM> includes bosses <NUM>, which facilitate the coupling of links 82a-82d to penetrator assembly <NUM>, such that links 82a-82d are permitted to pivot with respect to bosses <NUM>. In addition, cylinder portion <NUM> may include a catch (not shown) for cooperating with a stow actuator, as explained in more detail below. For embodiments of puncture actuator <NUM> that are pneumatic or hydraulic actuators, cylinder portion <NUM> includes a fitting <NUM> for receipt of pressurized air or hydraulic fluid, respectively, such that upon supply of pressurized fluid to cylinder portion <NUM>, piston portion <NUM> extends from cylinder portion <NUM>. In the exemplary embodiment shown, one end of piston portion <NUM> is coupled to a flange <NUM> of housing <NUM>. Thus, upon extension of piston portion <NUM> from cylinder portion <NUM>, housing <NUM>, receiving chamber <NUM>, and nozzle <NUM> are extended from penetrator assembly <NUM>. As a result, tip <NUM> of nozzle <NUM> is extended, thus piercing a barrier adjacent to, or against which, tip <NUM> may be positioned prior to extension. Thus, if tip <NUM> is adjacent a barrier (e.g., the wall of a container <NUM>), piston portion <NUM> drives tip <NUM> into and through the barrier, thereby providing flow communication between nozzle <NUM> and the other side of the barrier. As a result, fire suppressant may be supplied behind the barrier (e.g., into a container <NUM>) via penetrator assembly <NUM>. (See <FIG>. ) According to some embodiments, puncture actuator <NUM>, rather than being a pneumatic or hydraulic actuator, may be an electrically-driven and/or spring-loaded actuator.

Exemplary deployment structure <NUM> also includes a number of actuators configured to control and drive movement of arm <NUM> relative to frame <NUM>, so that penetrator assembly <NUM> can be positioned to facilitate delivery of fire suppressant to an appropriate container <NUM>. For example, deployment structure <NUM> includes a stow actuator <NUM> mounted to stow mount <NUM> (see <FIG> and <FIG>). In particular, stow actuator <NUM>, when actuated, either manually or via control system <NUM>, retracts from a catch on, for example, cylinder portion <NUM> of puncture actuator <NUM>, so that deployment structure <NUM> is released from its stowed condition (see <FIG>) to a condition for being deployed (see <FIG>). Upon release of stow actuator <NUM>, arm <NUM> of deployment structure drops below the horizontal level of frame <NUM> and into an intermediate position (<FIG>), so that arm <NUM> may be manipulated to move penetrator assembly <NUM> to be positioned to pierce a container <NUM> for receipt of receive fire suppressant.

In order to move penetrator assembly <NUM> to the desired position, deployment structure <NUM> further includes a swing lock actuator (not shown) and a swing actuator (not shown) including, for example, a linear actuator configured to pivot penetrator assembly <NUM>. The swing lock actuator is configured to prevent a swinging or pivoting motion of arm <NUM> about hinge <NUM>, so that penetrator assembly <NUM> does not move within first plane P<NUM> (e.g., a horizontal plane) (see <FIG>) relative to the stowed position of deployment structure <NUM>. More specifically, in the stowed position (see <FIG>), arm <NUM> is positioned next to brace member 60b. Thus, the swing lock actuator prevents arm <NUM> from moving in plane P<NUM>, so that when arm <NUM> is deployed, it moves only in plane P<NUM> (e.g., a vertical plane) (see <FIG>). Thus, in the exemplary embodiment shown, penetrator assembly <NUM> moves only vertically, so that a container <NUM> below brace member 60b is pierced upon activation of penetrator assembly <NUM>.

The swing actuator is configured to drive arm <NUM>, so that penetrator assembly <NUM> moves in first plane P<NUM> when the swing lock actuator is disengaged to permit such movement. The swing actuator is mounted on frame <NUM> adjacent hinge <NUM> with its piston coupled to arm <NUM>, such that upon extension of the piston of the swing actuator, arm <NUM> pivots on hinge <NUM>, so that penetrator assembly <NUM> moves in plane P<NUM>. As a result, rather than tip <NUM> of nozzle <NUM> piercing a container <NUM> located under brace member 60b, tip <NUM> pierces a container <NUM> located underneath brace 60a. Thus, by virtue of the ability of exemplary deployment structure <NUM> to swing penetrator assembly <NUM> from a position above a first one of containers <NUM> to a position above a second one of containers <NUM>, a single one of exemplary fire suppressant devices <NUM> is able to selectively discharge fire suppressant into more than one container <NUM>.

Deployment structure <NUM> is configured such that when tip <NUM> of nozzle <NUM> drops via gravity and presses against the upper wall of container <NUM> and resistance is provided against the force created by puncture actuator <NUM> when piston portion <NUM> of puncture actuator <NUM> is extended to pierce the upper wall of container <NUM>. For example, a ratcheting catch (not shown) associated with deployment structure <NUM> adjacent hinge <NUM> holds arm <NUM> in a stable condition so that when tip <NUM> presses against the upper wall of container <NUM>, the upper wall is punctured.

According to the exemplary embodiment of system <NUM> shown in <FIG> and <FIG>, a single device <NUM> is able to supply fire suppressant into two different containers <NUM>. In particular, as shown in <FIG> exemplary devices 40a, 40b, and 40c are mounted above respective pairs of cargo positions 24a and 24b, 24c and 24d, and 24e and 24f, at which respective pairs of containers 22a and 22b, 22c and 22d, and 22e and 22f are positioned. Arms 76a, 76b, and 76c of respective devices 40a, 40b, and 40c are able to swing in first plane P<NUM> from a position (see <FIG>), such that respective penetrator assemblies 54a, 54b, and 54c are positioned over containers 22a, 22c, and 22e (see <FIG>) to a position, such that respective penetrator assemblies 54a, 54b, and 54c are positioned over containers 22b, 22d, and 22f (see <FIG>). Exemplary control system <NUM> is able to either activate penetrator assemblies <NUM> to pierce containers <NUM> located under the penetrator assembly <NUM> in the stowed condition (<FIG>) or activate penetrator assemblies <NUM> to pierce containers <NUM> on the opposite side of the center line C of exemplary aircraft <NUM> (<FIG>). By virtue of a single device <NUM> being able to supply fire suppressant to more than one container <NUM>, the number of devices <NUM> required to supply fire suppressant to all of the containers <NUM> in the cargo area <NUM> may be reduced, thereby reducing the weight of the overall system <NUM>. According to some embodiments (not shown), device <NUM> may be configured to penetrate more than two containers <NUM>, such as, for example, four containers, by modifying frame <NUM> to permit arm <NUM> to swing through a greater range on angles, such as about <NUM> degrees.

Referring to <FIG>, exemplary system <NUM> is able to deliver fire suppressant to containers <NUM> having different heights. As shown in <FIG>, containers 22a and 22b are positioned at respective cargo positions 24a and 24b. If there is a fire associated with container 22a, device <NUM> is able to lower arm <NUM> through second plane P<NUM> (<FIG>) to a point at which tip <NUM> of nozzle <NUM> is just above or in contact with the upper surface of container 22a. Alternatively, if there is a fire associated with container 22b, device <NUM> is able to swing arm <NUM> through first plane P<NUM> to a point at which tip <NUM> of nozzle <NUM> is just above or in contact with the upper surface of container 22b, for example, as shown in <FIG>. Thus, the operation of some embodiments of system <NUM> is flexible enough to provide fire suppressant to containers of different heights.

According to some examples, nozzle <NUM> may be frangible, so that once the tip <NUM> has penetrated the upper surface of a container <NUM> and fire suppressant has been discharged into container <NUM>, tip <NUM> of nozzle <NUM> may be disassociated from a portion of nozzle <NUM> and/or housing <NUM>. Alternatively, or in addition, nozzle <NUM> may be easily removable from housing <NUM> via a quick-disconnect coupling, such as, quick-access fasteners and latches. This may be desirable because it facilitates ease of removal of the container <NUM> from cargo area <NUM> without disassembly or retraction of the device <NUM>, thereby reducing inconvenience and time for removal of cargo from aircraft <NUM>.

For the purpose of describing exemplary operation, operation of the exemplary embodiment of system <NUM> has been described in relation to exemplary aircraft <NUM>. However, exemplary system <NUM> may be used in association with different vehicles and/or storage areas, with the operation tailored to those environments.

During operation of exemplary system <NUM>, sensors <NUM> detect the temperatures associated with containers <NUM> (<FIG>). For example, referring to <FIG>, which provides a block diagram of exemplary control steps of exemplary control module <NUM>, at step <NUM>, control module <NUM> receives signals from the temperature sensors <NUM> indicative of the temperatures associated with respective containers <NUM>. At step <NUM>, control module <NUM> compares the indicated temperatures with a predetermined temperature. According to some embodiments, the predetermined temperature may differ for different containers <NUM>, and/or the predetermined temperature may be dynamic. For example, the predetermined temperature may change with changing parameters, such as, for example, the ambient temperature outside aircraft <NUM> and/or the operation of aircraft <NUM> (e.g., whether aircraft <NUM> is flying, taxiing, or being loaded or unloaded).

At step <NUM>, if no temperatures are greater than the predetermined temperature, control module <NUM> continues receiving and comparing temperatures, unless the system <NUM> is deactivated. However, if at step <NUM>, a temperature associated with one of containers <NUM> is greater than the predetermined temperature, at step <NUM>, control module <NUM> determines the cargo position <NUM> of the container <NUM> with which the high temperature is associated. At step <NUM>, control module <NUM> activates the fire suppressant device <NUM> corresponding to the sensor <NUM> with which the high temperature is associated. For example, at step <NUM>, control module <NUM> activates stow actuator <NUM>, so that deployment structure <NUM> drops to an intermediate level. At step <NUM>, control module <NUM> activates appropriate ones of the swing lock actuator and the swing actuator to deploy the penetrator assembly <NUM> to a position for piercing the appropriate container <NUM>. At step <NUM>, control module <NUM> activates a stabilizing actuator or mechanism (e.g., a ratcheting catch passively locks arm <NUM> into a stabilized position), so that tip <NUM> of nozzle <NUM> is positioned above or in contact with the upper surface of the container <NUM>. At step <NUM>, control module <NUM> activates puncture actuator <NUM>, such that the upper surface of container <NUM> is pierced via tip <NUM> to provide flow communication between nozzle <NUM> and the interior of the container <NUM>.

At step <NUM>, after delaying a sufficient amount time for the nozzle <NUM> of penetrator assembly <NUM> of the appropriate fire suppressant device <NUM> to pierce the upper wall of the container <NUM>, control module <NUM> activates appropriate valves associated with tanks 44a-44c and manifold system <NUM>, so that gas and foam solution is supplied to the corresponding fire suppressant device <NUM>. As a result, gas and foam solution are supplied to receiving chamber <NUM> of penetrator assembly <NUM>, wherein the foam generator combines the gas and foam solution, and fire suppressant foam is generated, flows through chamber <NUM> of housing <NUM>, into tubular member <NUM> of nozzle <NUM>, and into the container <NUM> (<FIG>).

Claim 1:
A system (<NUM>) for suppressing fire inside a first and second container (<NUM>), the system comprising:
a support structure (<NUM>) configured to be mounted inside a vehicle (<NUM>);
a deployment structure (<NUM>) coupled to the support structure;
a penetrator assembly (<NUM>) coupled to the deployment structure, the penetrator assembly being configured to pierce the first and second container and direct fire suppressant into the first and second container, the penetrator assembly comprising:
a nozzle having a tip configured to pierce the first and second container,
an actuator associated with the nozzle wherein the actuator is configured to extend the tip of the nozzle such that it pierces the first and second container; and
a fire suppressant delivery system (<NUM>) associated with the penetrator assembly (<NUM>),
wherein the support structure (<NUM>) and the deployment structure (<NUM>) are configured such that the penetrator assembly (<NUM>) is moveable in at least one plane with respect to the support structure,
wherein the support structure (<NUM>) includes a pivot mount (<NUM>) configured to provide an attachment point for the deployment structure (<NUM>), and the deployment structure (<NUM>) includes an arm (<NUM>) coupled at one end to the support structure (<NUM>) and at an opposite end to the penetrator assembly (<NUM>),
wherein the arm (<NUM>) is moveable in a first plane from a first position such that the penetrator assembly (<NUM>) is positioned over one of the first and second containers to a second position such that the penetrator assembly (<NUM>) is positioned over the other of the first and second containers, and
wherein the fire suppressant delivery system (<NUM>) is configured to supply fire suppressant to the nozzle (<NUM>) associated with the actuator (<NUM>).