Abstract:
The disclosure provides systems and methods for a heating system with a seat having a first heating element, a floor heating panel located at least partially under the seat, and a controller operatively coupled to the first heating element and the floor heating panel and configured to implement control logic that receives at least one input and thereby control the first heating element and the floor heating panel.

Description:
FIELD OF THE DISCLOSURE 
       [0001]    This disclosure relates to heating systems for occupant comfort on an aircraft. In particular, the disclosure relates to supplemental heating systems for use with an attendant jump seat located in the door and galley areas of aircraft. 
       BACKGROUND 
       [0002]    Certain aircraft, such as commercial airplanes, often include environmental control systems, such as air conditioners and heaters, in order to keep the cabin temperature in a range comfortable for the occupants of the airplane. Although existing systems are effective in achieving cabin temperatures within an acceptable comfort range, temperature gradients within the cabin often exist, particularly for larger cabins, and occupants may experience “hot” or “cold” spots in some areas of the cabin. 
         [0003]    In particular, some larger aircraft often have cold spots in the area around the doors or galleys of the airplane where factors such as heat loss due to airplane structure, insufficient insulation in and around the doors, and insufficient heat addition may contribute to the creation of a cold spot. Other factors may also contribute to the creation of temperature gradients in the cabin of an aircraft. 
         [0004]    Such a cold spot can be particularly uncomfortable for persons that spend any appreciable time in the doorway or galley areas. For example, flight attendants or crew on a commercial aircraft are often seated in a jump seat in the doorway or galley area, and situations such as long duration night time flying with low activity in the cabin or turbulence may cause the crew to remain seated for extended periods. 
         [0005]    Prior solutions to alleviate cold areas have included adding one or more of an electrical door air heater to flow warm air across the base of exit door bustles, electrically heated floor panels, heated sidewall panels, and heated door liner surface panels to address the temperature loss in door and galley areas. One drawback of these existing solutions is that because they heat the air, or the surfaces near the floor or door, they are less effective in providing direct thermal comfort to the persons located in the cold area. 
         [0006]    Furthermore, these surface and air heaters are typically designed to be constantly powered on in order to sufficiently heat the cold space. Therefore, without proper operational control, adding these supplemental heating systems in areas such as doorways and galleys where occupancy is often transitory and temporary can be expensive and inefficient. Other drawbacks of existing solutions also exist. 
       SUMMARY 
       [0007]    Accordingly, the present disclosure provides systems and methods for providing thermal comfort to persons in cold areas of aircraft cabins. 
         [0008]    In addition, the disclosure provides systems and methods for a heating system comprising a seat having a first heating element, a floor heating panel located at least partially under the seat, and a controller operatively coupled to the first heating element and the floor heating panel and configured to implement control logic that receives at least one input and thereby control the first heating element and the floor heating panel. 
         [0009]    In addition, some embodiments of the controller may further comprise an input indicative of an in-flight condition of the aircraft within which the heating system is located. In still further embodiments, the in-flight condition may further comprise an indication of the status of the aircraft landing gear. 
         [0010]    In addition, some embodiments of the controller may further comprise an input indicative of an environmental control system parameter for the aircraft within which the heating system is located. In still further embodiments, the environmental control system parameter may comprise an indication of the status of the aircraft air conditioning packs. 
         [0011]    In addition, some embodiments of the controller may further comprise an input indicative of a temperature of the seat, or an input indicative of ambient temperature of the aircraft within which the heating system is located. 
         [0012]    Also disclosed is a method of making a heating system comprising coupling a seat into a vehicle, the seat having a first heating element, coupling a floor heating panel into the vehicle, the floor heating panel being located at least partially under the seat, and coupling a controller into the vehicle, the controller operatively coupled to the first heating element and the floor heating panel and configured to implement control logic that receives at least one input and thereby control the first heating element and the floor heating panel. 
         [0013]    In addition, in some embodiments, the method comprises coupling an in-flight sensor to the vehicle wherein the in-flight sensor provides the controller with an input indicative of an in-flight condition of the aircraft within which the heating system is located. In still further embodiments, the input indicative of an in-flight condition further comprises an indication of the status of the aircraft landing gear. 
         [0014]    In addition, in some embodiments, the method further comprises coupling an environmental control system sensor to the vehicle wherein the environmental control system sensor provides the controller an input indicative of an environmental control system parameter for the aircraft within which the heating system is located. In still further embodiments, the input indicative of an environmental control system parameter comprises an indication of the status of the aircraft air conditioning packs. 
         [0015]    In addition, some embodiments of the method further comprise coupling a temperature sensor to the seat to provide the controller an input indicative of a temperature of the seat, or coupling an ambient temperature sensor to the vehicle to provide the controller an input indicative of ambient temperature of the aircraft within which the heating system is located. 
         [0016]    Other advantages and features of the disclosed systems and methods will be apparent from the following detailed description. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0017]      FIG. 1  is an exemplary representation of a doorway or galley area inside an aircraft in accordance with some embodiments of the disclosure. 
           [0018]      FIG. 2  is a schematic representation of some embodiments of control logic for operation of the jump seat supplemental heat system. 
       
    
    
       [0019]    While the disclosure is susceptible to various modifications and alternative forms, specific embodiments have been shown by way of example in the drawings and will be described in detail herein. However, it should be understood that the disclosure is not intended to be limited to the particular forms disclosed. Rather, the intention is to cover all modifications, equivalents and alternatives falling within the spirit and scope of the invention as defined by the appended claims. 
       DETAILED DESCRIPTION 
       [0020]      FIG. 1  is an exemplary representation of a doorway or galley area inside an aircraft in accordance with some embodiments of the disclosure. As shown, a doorway or galley area  5  may be included at various locations within an aircraft. Typically, a doorway or galley area  5  may also include a door  10  suitable for ingress and egress from the aircraft at appropriate times. Lavatory  20  may also be located near doorway or galley area  5 . Not pictured, but also often present in doorway or galley area  5  may be a food storage and preparation area. Other common items located in doorway or galley area  5  may include a communication device, such as a telephone  30 , and other aircraft controls  40  to operate such systems as cabin temperature control, cabin lights, video displays, safety signs, or the like. Other doorway or galley area  5  configurations are also possible. 
         [0021]    As shown in  FIG. 1 , a doorway or galley area  5  may also include a jump seat  50 . As shown, some embodiments of jump seat  50  may comprise a folding or otherwise stowable seat  52  and a seat backrest  54 . Numerous other configurations for jump seat  50  are also possible. 
         [0022]    As shown in  FIG. 1 , some embodiments may include a region underneath the jump seat  50  equipped with a floor heating panel  56 . The panel  56  may be placed in a location so that when jump seat  50  is occupied, the occupant&#39;s feet rest on or near the panel  56 . In some embodiments, floor heating panel  56  may be heated by electric-resistance heating coils. Other heating elements are also possible. 
         [0023]    As also shown in  FIG. 1 , some embodiments may include heating elements in jump seat  50 . For example, stowable seat  52  may have a heating element  60  integrated within and seat backrest  54  may also have a heating element  62  integrated within. 
         [0024]    Heating elements  60 ,  62  may comprise any suitable system for heating a seat, such as electric resistance heating coils, heating pads, or the like. Other heating elements are also possible. 
         [0025]      FIG. 2  is a schematic representation of some embodiments of control logic for operation of the supplemental heat system. In general, the control logic  200  for the jump seat supplemental heat system may comprise part of the control logic for the door heat control logic and may operate through existing environmental controls and systems. 
         [0026]    As shown in  FIG. 2 , some embodiments of the jump seat supplemental heat system may include control logic  200  that comprises receiving input from the aircraft landing gear systems  202 . For example, landing gear systems  202  may be queried to determine if the aircraft is in flight by reading an AIR/GND signal at  204  that specifies whether the aircraft is airborne. In some embodiments, when an aircraft is airborne, a RLY-GND SAFETY relay  206  will energize and may be used to provide power to energize the jump seat supplemental heat system. For example, the energizing of RLY-GND SAFETY relay  206  may switch on jump seat control relays  208  that provide power to the jump seat heating elements (e.g., floor panel  56 , seat element  60 , and backrest element  62 ). 
         [0027]    In some embodiments, additional input for the control logic of the jump seat supplemental heat system may be provided by the aircraft environmental control systems (ECS)  210 . For example, the ECS  210  may provide, as indicated at  212 , an analog discreet signal (e.g., from an ECS  210  MISC PCA card, or the like) that indicates that a predetermined number of air conditioning packs are operating. That signal may then be used to energize the heated jump seat control relays  208 . In some embodiments, the predetermined number of air conditioning packs may be one, or two, or more packs. 
         [0028]    In some embodiments it may be preferable to also include other control logic criteria  214  as part of control logic  200 . Embodiments may include some or all of the following criteria  214 . In addition, other control logic criteria  214  are possible. 
         [0029]    For example, some embodiments may comprise checking at  216  an internal temperature set point of the heated seat to ensure that the seat is operating within design parameters. Temperatures within the set point may result in a jump seat on signal, and temperatures outside the set point may result in a jump seat off signal. For example, in some embodiments the seat internal temperature set point may be set to 100° F., and for internal seat temperatures below that set point the control logic process  216  will deliver a seat on signal. Other set points are possible. 
         [0030]    Another control logic criterion  214  may comprise checking at  218  an overheat temperature set point. For this parameter, temperatures above the set point may result in a jump seat off signal and temperatures below the set point may result in a jump seat on signal. For example, in some embodiments the overheat temperature set point may be set to 120° F., and for internal seat temperatures above that set point control logic process  218  will deliver a seat off signal. Other set points are possible. 
         [0031]    Another control logic criterion  214  may comprise checking at  220  an ambient temperature set point of the aircraft cabin. Temperatures above the ambient set point may result in a seat off signal and temperatures below the ambient set point may result in a seat on signal. For example, in some embodiments the ambient temperature set point may be set to 80° F., and for internal seat temperatures above that set point control logic process  220  will deliver a seat off signal. Other set points are possible. 
         [0032]    Another control logic criterion  214  may comprise some sort of user input  222 . For example, user input may comprise an on/off switch, an adjustable temperature setting, any of floor, back, or seat on/off or temperature settings, or the like to enable the user to customize or adjust the settings, and thus comfort level, of the jump seat  50 . 
         [0033]    As shown in  FIG. 2 , when all the various control logic  200  routines are performed, and the various set points and on signals received, then the jump seat  50  will be powered and functional as indicated at  224 . Other control logic flows are also possible. 
         [0034]    While the above disclosure has been primarily directed to an attendant&#39;s jump seat  50 , other applications of the disclosed concepts are also possible. For example, the above-disclosed concepts could be applied to a pilot&#39;s seat or a passenger&#39;s seat. Furthermore, other set points or control logic criteria  214  may be implemented. 
         [0035]    Although various embodiments have been shown and described, the present disclosure is not so limited and will be understood to include all such modifications and variations as would be apparent to one skilled in the art.