1. An electrical power generation device for arrangement in an aircraft seat, the electrical power generation device comprising:

an elastomeric lattice insert defining one or more thermoelectric generator grooves;

one or more thermoelectric generators; and

an electricity storage device for storing electricity,

wherein:

the one or more thermoelectric generator recesses are configured to place a hot side of the one or more thermoelectric generators proximate to a human body in an aircraft seat and a cold side of the one or more thermoelectric generators proximate to a ventilation portion of the elastomeric lattice insert.

2. The apparatus of claim 1, wherein the elastomeric lattice insert is configured for insertion into a void disposed in a surface of a cushion proximate to a person in the aircraft seat.

3. The device of claim 1, wherein the elastomeric lattice insert defines an unobstructed airflow path through the seat cushion.

4. The apparatus of claim 1, wherein the elastomeric lattice insert is configured for insertion into a void disposed in a surface of a seat back proximate a human body in the aircraft seat.

5. The apparatus of claim 4, further comprising:

an elastomeric dot matrix seat insert defining one or more thermoelectric generator grooves, wherein the elastomeric dot matrix seat insert is configured for insertion into a void in a surface of a seat cushion disposed proximate a human body in an aircraft seat.

6. The apparatus according to claim 1, further comprising a USB power connection connected to the power storage device, the USB power connection being provided in a rear surface of the aircraft seat.

7. The apparatus of claim 6, further comprising an LED configured to indicate that the power storage device is charged.

8. An aircraft seat, comprising:

an elastomeric lattice insert defining one or more thermoelectric generator grooves;

one or more thermoelectric generators; and

an electricity storage device for storing electricity,

wherein:

the one or more thermoelectric generator recesses are configured to place a hot side of the one or more thermoelectric generators proximate to a human body in an aircraft seat and a cold side of the one or more thermoelectric generators proximate to a ventilation portion of the elastomeric lattice insert.

9. The aircraft seat of claim 8, further comprising a seat cushion defining a void configured to receive the elastomeric lattice insert, the void disposed in a surface of the seat cushion proximate to a human body in the aircraft seat.

10. The aircraft seat of claim 9, wherein the seat cushion defines one or more lateral openings configured to facilitate ambient air flow.

11. The aircraft seat of claim 9, wherein the seat cushion defines one or more rear openings configured to facilitate ambient air flow.

12. The aircraft seat of claim 8, further comprising a seat back defining a void configured to receive the elastomeric dot matrix insert, the void disposed in a surface of the seat back proximate to a human body in the aircraft seat.

13. The aircraft seat of claim 12, further comprising:

an elastomeric dot matrix seat insert defining one or more thermoelectric generator grooves; and

a seat cushion defining a void configured to receive the elastomeric dot matrix seat insert, the void disposed in a surface of the seat cushion proximate to a human body in an aircraft seat.

14. The aircraft seat of claim 8, further comprising a USB power supply connection to the power storage device, the USB power supply connection being disposed in a rear surface of the aircraft seat.

15. The aircraft seat of claim 14, further comprising an LED configured to indicate that the power storage device is charged.

Background

Passengers on aircraft often use portable electronic devices. These portable electronic devices require a power source and are typically charged through a low voltage USB power connection. Providing power to the occupant in the seat is problematic; typically, aircraft are designed without consideration of electrical outlets for each passenger, and retrofitting each seat using existing technology requires extensive modification of the electrical system within the aircraft.

It would be advantageous if there were a system that could efficiently deliver low voltage power to individual aircraft passengers without requiring significant structural or electrical changes to the aircraft.

Disclosure of Invention

In one aspect, embodiments of the inventive concepts disclosed herein relate to a power generation system in an aircraft seat having thermoelectric generators in an elastomeric lattice to maintain the hot side of the thermoelectric generators near the passenger's body and the cold side of the thermoelectric generators in ambient air, away from the insulating properties of the aircraft seat.

In another aspect, the elastomer lattice and the thermoelectric generator are disposed in both the seat cushion and the seat back. The power conditioner and storage device store power from the thermoelectric generator and discharge over time as needed.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the claims. The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments of the inventive concepts disclosed herein and, together with the general description, serve to explain the principles.

Drawings

The numerous advantages of embodiments of the inventive concepts disclosed herein may be better understood by those skilled in the art by reference to the accompanying drawings in which:

FIG. 1 illustrates an environmental diagram of a power generation system according to an exemplary embodiment;

FIG. 2 illustrates an aircraft seat suitable for practicing the exemplary embodiments;

FIG. 3 illustrates an environmental diagram of an aircraft seat according to an exemplary embodiment;

FIG. 4 illustrates an environmental diagram of an aircraft seat according to an exemplary embodiment;

FIG. 5A illustrates an exemplary embodiment of an aircraft seat cushion suitable for implementing the exemplary embodiment;

FIG. 5B illustrates an exemplary embodiment of an aircraft seat cushion suitable for implementing the exemplary embodiment;

FIG. 6 shows an exploded side view of a power generation system according to an exemplary embodiment;

figure 7 shows a perspective view of a seat cushion suitable for implementing an exemplary embodiment; and

FIG. 8 shows a block diagram of a power generation system according to an example embodiment.

Detailed Description

Before explaining at least one embodiment of the inventive concepts disclosed herein in detail, it is to be understood that the inventive concepts are not limited in their application to the details of construction and the arrangement of the components and steps or methods set forth in the following description or illustrated in the drawings. In the following detailed description of embodiments of the inventive concept, numerous specific details are set forth in order to provide a more thorough understanding of the inventive concept. However, it will be apparent to one having ordinary skill in the art having had the benefit of the present disclosure that the inventive concepts disclosed herein may be practiced without these specific details. In other instances, well-known features may not have been described in detail to avoid unnecessarily complicating the disclosure. The inventive concepts disclosed herein are capable of other embodiments or of being practiced or carried out in various ways. Also, it is to be understood that the phraseology and terminology employed herein is for the purpose of description and should not be regarded as limiting.

As used herein, letters following reference numerals are intended to denote embodiments of features or elements that may be similar to, but not necessarily identical to, previously described elements or features bearing the same reference numerals (e.g., 1a, 1 b). Such shorthand notations are used merely for convenience and should not be construed to limit the inventive concepts disclosed herein in any way unless explicitly stated to the contrary.

Further, unless expressly stated to the contrary, "or" refers to an inclusive "or" and not to an exclusive "or". For example, one of the following conditions satisfies condition a or B: a is true (or present) and B is false (or not present); a is false (or not present) and B is true (or present); and both a and B are true (or present).

Also, the use of "a" or "an" is used to describe elements and components of embodiments of the inventive concepts. This is done merely for convenience and to give a general sense of the inventive concept and "a" and "an" are intended to include one or at least one and the singular also includes the plural unless it is obvious that it is meant otherwise.

Finally, as used herein, any reference to "one embodiment" or "some embodiments" means that a particular element, feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the inventive concept. Disclosed herein. The appearances of the phrase "in some embodiments" in various places in the specification are not necessarily all referring to the same embodiment, and embodiments of the disclosed inventive concept may include one or more features expressly described or inherently present herein, or any combination of two or more such features, and any other features which may not necessarily be expressly described or inherently present in the disclosure.

Broadly, embodiments of the inventive concepts disclosed herein relate to a power generation system in an aircraft seat with thermoelectric generators in an elastomeric lattice to maintain the hot side of the thermoelectric generators close to the body of a passenger and the cold side of the thermoelectric generators in ambient air, away from the insulating properties of the aircraft seat.

Referring to FIG. 1, an environmental diagram of a power generation system according to an exemplary embodiment is shown. The aircraft seat 100 includes one or more thermoelectric generators 102, 104. The thermoelectric generators 102, 104 may be disposed in the seat cushion 106, the seat back 108, or both. The thermoelectric generators 102, 104 generate direct current through a temperature difference; in the case of aircraft seats, the temperature difference is produced by the passengers (about 37 ℃) in contact with the hot side and the ambient cabin air (about 25 ℃) in contact with the cold side. The power generated by the thermoelectric generators 102, 104 can be stored in a regulator 110 having a battery. Such a temperature difference may be sufficient to power a low voltage USB power connection 112 provided in the rear surface of the aircraft seat 100. Since the availability of the power source is based on the regulator 110, which is conventionally modified by the passenger in the aircraft seat 100, the power to the USB power source connection 112 may be inconsistent. In at least one embodiment, the LED indicator may provide a colored indication of whether power is available at the USB power connection 112.

Referring to FIG. 2, an aircraft seat 200 suitable for implementing the exemplary embodiment is shown. The aircraft seat 200 includes a seat cushion 202 having a unit of an insulation pad 204 and one or more elastomeric lattice materials 206 disposed in one or more corresponding voids of the insulation pad 204, the seat cushion 202.

In at least one embodiment, the aircraft seat 200 further includes a seat back 208 having an insulation pad and one or more units of elastomeric lattice material disposed in one or more corresponding voids of the insulation pad.

Because the thermoelectric generator operates with a temperature differential, the insulation mat 204 tends to reduce the efficiency of the thermoelectric generator because it normalizes the temperature and reduces the temperature differential. The elastomeric lattice material 206 creates channels for air flow to maintain the temperature differential.

Referring to fig. 3, an environmental view of an aircraft seat 300 is shown according to an exemplary embodiment. The aircraft seat 300 may include thermoelectric generators 302, 304 disposed in the seat cushion and seat back. The thermoelectric generators 302, 304 are arranged to be in maximum contact with the passenger in the seat.

Referring to fig. 4, an environmental view of an aircraft seat 400 according to an exemplary embodiment is shown. In the case where one or more thermoelectric generators are included in the seat cushion of the aircraft seat 400, a power conditioner 404 disposed in the seat receives power and raises or lowers a corresponding voltage as needed to provide a standard voltage to a USB power supply connection 402 disposed in the rear surface of the aircraft seat 400. In at least one embodiment, the USB power connector 402 may include an LED that indicates whether the USB power connector 402 is powered.

Referring to fig. 5A-5B, an exemplary embodiment of an aircraft seat cushion 500, 502 suitable for implementing an exemplary embodiment is shown. In at least one embodiment, the seat cushion 500 can include a solid foam member 504 (e.g., open cell foam) and a plurality of elastomeric lattice inserts 506. In at least one embodiment, the seat cushion 500 can include open cell foam disposed at least at the top surface of the seat cushion 500 and optionally closed cell foam at the depth of the seat cushion for floatation. The elastomeric dot matrix insert 506 may be generally concentrated in the area or portion of the seat cushion 500 that experiences the highest load bearing requirements when an occupant is seated. Where the elastomeric dot matrix insert 506 is concentrated near the rear and sides of the seat bottom, the elastomeric dot matrix insert 506 is disposed at the point of maximum occupant contact, and thus at the maximum temperature differential.

Alternatively or additionally, the seat cushion 502 includes a plurality of elastomeric lattice inserts 508 disposed in a plurality of voids or grooves formed in the solid foam member 504, wherein the plurality of elastomeric lattice inserts 506 are disposed in the load bearing area of the solid foam member 504. The cushion 502 may have fewer but larger elastomeric dot matrix inserts 506. The gas permeability of the elastomeric lattice insert 508 facilitates ventilation of the enclosed thermoelectric generator.

Referring to FIG. 6, an exploded side view of a power generation system 600 according to an exemplary embodiment is shown. The aircraft cushion 602 defines one or more voids 612 or grooves configured to receive corresponding elastomeric dot matrix inserts 604. The elastomeric dot matrix insert 604 allows ambient air to circulate around the void 612 even when an occupant is seated.

The elastomeric dot matrix insert 604 also defines a thermoelectric generator groove 614 to keep the thermoelectric generator 606 with its hot side 608 near the top surface of the aircraft seat cushion 602 on which a passenger will sit. Furthermore, the thermoelectric generator recesses 614 hold the cold side 610 of the thermoelectric generator 606 in the void 612 so that ambient air flow can effectively cool the cold side 610.

Referring to fig. 7, a perspective view of a seat cushion 700 suitable for implementing an exemplary embodiment is shown. The seat cushion 700 defines a void 702 having lateral openings 704 to facilitate ambient air flow. In at least one embodiment, the void 702 may further define one or more rear openings 706 to further facilitate ambient air flow.

Referring to FIG. 8, a block diagram of a power generation system according to an exemplary embodiment is shown. A system disposed in an aircraft seat cushion 802 includes an elastic lattice insert 802 having lateral and aft openings to facilitate ambient air flow around a cold side of a thermoelectric generator 804 disposed in the elastic lattice insert 802.

The system includes a regulator/battery 806 to receive power from the thermoelectric generator 804 and discharge power to a USB power connection 808. The regulator/battery 806 may step up or down the voltage as needed to comply with the USB standard.

It is believed that the inventive concepts disclosed herein and many of its attendant advantages will be understood by the foregoing description of embodiments of the disclosed inventive concepts, and it will be apparent that changes may be made in the form, construction and arrangement of the parts thereof without departing from the broad scope of the inventive concepts disclosed herein or without sacrificing all of its material advantages; various features from the various embodiments may be combined to yield yet further embodiments. The form herein before described being merely an explanatory embodiment thereof, it is the intention of the appended claims to encompass and include such changes. Furthermore, any feature disclosed in relation to any single embodiment may be incorporated into any other embodiment.