Patent Publication Number: US-9884215-B2

Title: Fire suppression system actuation apparatus and system

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     This application is a division of application U.S. Ser. No. 14/261,312 filed Apr. 24, 2014 for FIRE SUPPRESSION SYSTEM ACTUATION APPARATUS AND SYSTEM. 
    
    
     FIELD 
     The present disclosure relates to fire suppression systems, and more specifically, to an actuation system for a fire suppression system that makes use of shape memory alloys. 
     BACKGROUND 
     Fire suppression systems have typically employed electro-explosive devices to actuate the fire suppression systems. For example, in a typical system, an electro-explosive device may be detonated causing a shockwave inside a discharge portion of the fire suppression system. The detonation and/or shockwave may rupture and/or deform the disk that restrains the fire suppression agent. The pressure of the fire suppression agent may further rupture and/or deform the disk, allowing the fire suppression agent to be discharged into an aircraft structure. 
     SUMMARY 
     In various embodiments, a fire suppression system may comprise a vessel, a disk, a plug, a retainer, and a flow control element. The vessel may be configured to contain a fire suppression agent. The disk may be configured to seal the vessel and retain the fire suppression agent. The plug may be configured to support and retain the disk. The retainer may be configured to constrain the plug. The retainer may also be configured to non-destructively change shape. The exhaust port may be configured to direct the fire suppression agent in response to the fire suppression system being activated. 
     In various embodiments, a fire suppression pressure vessel may comprise a vessel, a disk, and a shape memory plug. The vessel may be configured to hold pressurized fire suppression agent. The disk may be configured to hermetically seal an exhaust port of the vessel. The shape memory plug may be installable in the exhaust port. The shape memory plug may also be configured to support the disk. 
     The forgoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated herein otherwise. These features and elements as well as the operation of the disclosed embodiments will become more apparent in light of the following description and accompanying drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the drawing figures, wherein like numerals denote like elements. 
         FIG. 1  is a block diagram of fire suppression system components, in accordance with various embodiments; 
         FIG. 2  illustrates a portion of a fire suppression system including a discharge head, in accordance with various embodiments; 
         FIG. 3A  illustrates a portion of a fire suppression system comprising a first shape memory alloy actuation system in a stowed configuration, in accordance with various embodiments; 
         FIG. 3B  illustrates a portion of a fire suppression system comprising a first shape memory alloy actuation system in a deployed configuration, in accordance with various embodiments; 
         FIG. 4A  illustrates a portion of a fire suppression system comprising a second shape memory alloy actuation system in a stowed configuration, in accordance with various embodiments; 
         FIG. 4B  illustrates a portion of a fire suppression system comprising a second shape memory alloy actuation system in a deployed configuration, in accordance with various embodiments; 
         FIG. 5A  illustrates a portion of a fire suppression system comprising a third shape memory alloy actuation system in a stowed configuration, in accordance with various embodiments; 
         FIG. 5B  illustrates a portion of a fire suppression system comprising a third shape memory alloy actuation system in a deployed configuration, in accordance with various embodiments; and 
         FIGS. 6A-6B  illustrate a retaining disk comprising design rupture patterns, in accordance with various embodiments. 
     
    
    
     DETAILED DESCRIPTION 
     The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it should be understood that other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this invention and the teachings herein. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation. The scope of the invention is defined by the appended claims. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials. 
     In various embodiments and with reference to  FIG. 1 , aircraft structure  100  may comprise a fire extinguishing system  110 . Fire extinguishing system  110  may be configured to provide a fire suppression agent  125  to aircraft structure  100 . In this regard, fire extinguishing system  110  may be configured to disperse fire suppression agent  125  into aircraft structure  100  in response to detecting heat, smoke, a flame, particulates, and/or any other suitable indicator of a fire in aircraft structure  100 . 
     In various embodiments, fire extinguishing system  110  may comprise a vessel  120  (e.g., bottle, a pressure vessel, fire suppression agent storage tank, and/or the like), a disk  130 , a plug  140 , a retainer  150 , and an exhaust port  160  (e.g., a flow control mechanism, nozzle, orifice, and/or the like). Vessel  120  may comprise and/or contain fire suppression agent  125  (e.g., an inert gases and/or chemical agents used to extinguish fire such as, for example, HALON®). Disk  130  may be configured to partially retain and/or restrain fire suppression agent  125  in vessel  120 . In this regard, fire suppression agent  125  may be under pressure in vessel  120 . Plug  140  may be configured to block the opening of vessel  120  and partially retain and/or restrain disk  130 . Retainer  150  may be configured to restrain and/or retain plug  140  and/or fire suppression agent  125 . Exhaust port  160  may be configured to conduct fire suppression agent  125  from vessel  120  into aircraft structure  100 . 
     In various embodiments, retainer  150  may be comprised of a shape memory material. A shape memory material may be any material that is configured to change shape and/or phase in response to a predetermined stimulus (e.g., heat, electrical stimulation, and/or the like). For example, the shape memory material may be configured with a transition temperature. In response to increasing the heat of retainer  150  and/or the shape memory material past a transition temperature, retainer  150  and/or the shape memory alloy may change shape and/or phase. In this regard, retainer  150  and/or the shape memory alloy may reversibly change shape and/or phase. Retainer  150  may be any suitable shape memory alloy such as for example, Nitinol (Nickel-Titanium alloys), and the like. 
     In various embodiments and with reference to  FIG. 2 , retainer  250  may also be configured to restrain, retain, and/or hold plug  240  in a position adjacent to disk  230 . Disk  230  may be hermetically sealed to vessel  220 . In this regard, disk  230  and the corresponding hermetic seal may reduce, minimize, and/or eliminate leakage of fire suppression agent  225  from vessel  220 . Disk  230  may be designed to rupture at a pressure less than the internal pressure of fire suppression agent  225  in vessel  220 . 
     In various embodiments and in operation, retainer  250  may be actuated in response to detection of a fire event. The heating of retainer  250  past the transition temperature may cause retainer  250  to change shape, releasing plug  240 . The internal pressure of fire suppression agent  225  may cause disk  230  to rupture. Fire suppression agent  225  may further push plug  240  from the mouth of vessel  220  releasing fire suppression agent  225  to exhaust port  260 . 
     In various embodiments and with reference to  FIGS. 3A and 3B , in a stowed position as shown in  FIG. 3A , retainer  350  may be configured to contain, restrain, and/or otherwise hold plug  340  and/or disk  330  in a position to retain fire suppression agent in vessel  320 . For example, retainer  350  may be configured to mate to an outer diameter of exhaust port  360 . Fire suppression system  310  may be configured to transition from a stowed position as shown in  FIG. 3A  to a deployed position as shown in  FIG. 3B  in response to a fire being detected. The transition from the stowed position to the deployed position may include retainer  350  changing shape in response to a stimulus, causing at least a portion of retainer  350  to release from exhaust port  360 . 
     In various embodiments, shape change and/or actuation of retainer  350  between a first configuration and a second configuration may be electrical. In this regard, actuation of retainer  350  may be commanded via ohmic heating and/or electrical resistance heating of retainer  350 . This may cause the temperature of retainer  350  to increase past the transition temperature (e.g., the temperature at which the shape memory alloy transitions, changes phase, and/or changes shape). In this regard, retainer  350  and/or the shape memory alloy used to make retainer  350  may be designed to transition at a temperature corresponding to a desired thermal relief temperature so that the pressure is safely relieved from vessel  320  in the event of an extreme high temperature environment. Moreover, retainer  350  and/or the shape memory alloy used to make retainer  350  may be designed and/or may vary depending on the specific application where the fire extinguishing system is deployed. 
     In various embodiments and with reference to  FIGS. 4A and 4B , fire suppression system  410  may be sealed by any suitable shape memory structure. More specifically, disk  430  may be hermetically sealed to vessel  420 . Disk  430  may be retained and/or supported by any suitable shape memory structure. For example, where fire extinguishing system  410  is in a stowed position as shown in  FIG. 4A , disk  430  may be supported by shape memory plug  455 . Shape memory plug  455  may be installed in a portion of exhaust port  460 . In response to fire extinguishing system  410  being commanded to a deployed position, shape memory plug  455  may change shape (e.g., contract) and discharge from exhaust port  460 . In response to discharge of shape memory plug  455 , disk  430  may rupture, allowing a fire suppression agent to discharge from vessel  420 . 
     In various embodiments and with reference to  FIGS. 5A and 5B , fire extinguishing system  510  may comprise a clip  570  that is configured to retain plug  555  in exhaust port  560 . Clip  570  may be a shape memory material. Clip  570  may be retained in groove  562 , which may be formed in exhaust port  560 . In response to clip  570  be exposed to a trigger temperature, clip  570  may change shape and may be discharged from exhaust port  560 . In this regard, clip  570  may shrink or otherwise change shape such that it is not retained within groove  562 . This may also allow plug  555  to be discharged from exhaust port  560 . 
     In various embodiments and with reference to  FIGS. 6A and 6B , disk  630  may comprise and/or be designed to rupture in a specific fashion. For example, disk  630  may comprise one or more stress concentrations, scores, and/or design rupture pattern  632 A. Moreover, disk  630  may comprise multiple design rupture points including, for example, design rupture pattern  632 B and design rupture pattern  634 B. In this regard, disk  530  may be configured to rupture in a specific way to provide sufficient flow, and/or activation in response to the retainer and/or plug being discharged from the bottle of a fire extinguishing system. A disk having a configuration of stress concentrations, scores, and/or design rupture pattern may be referred to as having a “designed rupture pattern.” 
     In various embodiments, the fire extinguishing systems described herein may be deployed in any suitable aircraft structure. For example, the fire extinguishing systems described herein may be deployed and/or used in cargo bays, engine nacelles, in auxiliary power unit bays, as part of any suitable fire protection system in an aircraft, structure, and/or vehicle. 
     Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the inventions. The scope of the inventions is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. 
     Systems, methods and apparatus are provided herein. In the detailed description herein, references to “various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments. 
     Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f) unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.