Patent Application
20160138301
This disclosure relates generally to a self-contained electronic stowage bin system for use in an aircraft.
Traditionally, the contents within overhead stowage bins in an aircraft are secured within such bin by a purely mechanical latch system mounted to the door. This mechanical system includes a handle mechanism connected to latching mechanisms by torque tubes. This requires a number of mechanical elements which add weight, require adjustment, and are subject to wear and limited lifetime.
An electronic stowage bin latch system includes a latch handle coupled to a switch which sends an electronic signal to electronically activated end latches to cause the stowage bin door to open. Traditional electronic stowage bin latch systems are connected to an aircraft's internal power system and cabin management system via long cable runs, adding cost and weight to the aircraft.
Accordingly, there is a need for a stowage bin latching system which is not subject to the problems of the conventional mechanical and electronic stowage bin systems.
In one aspect, a self-contained electronic latching system for a stowage bin is disclosed. The system includes an energy storage device, an electronic latch device, a latch button, and one or more energy harvesting systems. The electronic latch device is for opening a door of a stowage bin and is configured to open the door upon receipt of a signal on an input. The electronic latch device is coupled to the energy storage device and is configured to receive electrical power only from the energy storage device. The latch button is for activating an electronic switch coupled to the input of the electronic latch device. The one or more energy harvesting systems are coupled to the energy storage device. Each of the one or more energy harvesting systems is configured to generate electricity and to provide the generated electricity to the energy storage device.
In a further embodiment, the electronic latch device may further comprise an element for securing the door in a closed position. Also, the one or more energy harvesting systems may generate electricity based upon cabin vibrations, based upon motion supplied to a piezoelectric device, or based upon motion supplied to an electromechanical device. Alternatively, the one or more energy harvesting systems may generate electricity using a photovoltaic device and/or using a thermoelectric device.
In a still further embodiment, one of the one or more energy harvesting systems may be incorporated into the latch button and be configured to generate electricity using a piezoelectric device and/or electromechanical device.
The energy storage devices may be either a capacitor or a battery. Further, a low-energy bi-stable display may be mounted on a surface of the latch button which provides an indication of the latching status of the door.
In another aspect, an electronic latching system for a stowage bin is disclosed. The system includes a first energy storage device, an electronic latch device, a latch button, and one or more first energy harvesting systems. The electronic latch device is for opening a door of a stowage bin and is configured to open the door upon receipt of a signal on an input. The electronic latch device is coupled to the first energy storage device and is configured to receive electrical power from the first energy storage device. The latch button is for activating an electronic switch coupled to the input of the electronic latch device. The one or more first energy harvesting systems are coupled to the energy storage device. Each of the one or more first energy harvesting systems is configured to generate electricity and to provide the generated electricity to the energy storage device. Each of the one or more first energy harvesting systems is incorporated into the latch button and is configured to generate electricity based upon piezoelectric and/or electromechanical action.
In a further embodiment, the system includes a second energy storage device and one or more second energy harvesting systems which are coupled to the second energy storage device. Each of the one or more second energy harvesting systems is configured to generate electricity and to provide the generated electricity to the second energy storage device. Each of the one or more second energy harvesting systems is incorporated into the stowage bin. In this further embodiment, the electronic latch device is also coupled to the second energy storage device and is also configured to receive electrical power from the second energy storage device. Each of the one of the one or more second energy harvesting systems may be configured to generate electricity using a piezoelectric device and/or electromechanical device.
In a still further embodiment, the system includes a third energy storage device and one or more third energy harvesting systems coupled to the third energy storage device. Each of the one or more third energy harvesting systems is configured to generate electricity and to provide the generated electricity to the energy storage device. Each of the one or more third energy harvesting systems is mounted outside of the stowage bin. The electronic latch device is also coupled to the third energy storage device and is also configured to receive electrical power from the third energy storage device.
In one alternative further embodiment, the one or more third energy harvesting systems may be configured to generate electricity using piezoelectric device and/or electromechanical device. In another alternative further embodiment, the one or more third energy harvesting systems may be configured to generate electricity using a photovoltaic device and/or a thermoelectric device. In a still further alternative embodiment, the stowage bin may be mounted within an aircraft and at least one of the one or more third energy harvesting systems may be configured to generate electricity by harvesting aircraft cabin vibrations.
In yet another aspect, a method of operating a self-contained electronic latching system for a stowage bin is disclosed. Electricity is generated in one or more energy harvesting systems. The generated electricity is provided to an energy storage device. Upon activation of a latch button, a signal is generated in an electronic switch that is coupled to an input of an electronic latch device. Finally, upon receipt of the signal at the input of the electronic latch device, a door of the stowage bin is caused to open by activating the electronic latch device which is configured to receive electrical power only from the energy storage device.
The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments, further details of which can be seen with reference to the following description and drawings.
The following detailed description, given by way of example and not intended to limit the present disclosure solely thereto, will best be understood in conjunction with the accompanying drawings in which:
In the present disclosure, like reference numbers refer to like elements throughout the drawings, which illustrate various exemplary embodiments of the present disclosure.
Referring now to
Devices used to capture energy may be vibration, piezoelectric, electromechanical (microgenerator), photovoltaic, thermoelectric, or some combination thereof, depending on the type of energy source identified for use. Examples of energy sources include, but are not limited to one or more of the following: (1) rotation of internal latch components; (2) additional linear motion capture of the latch strike interface; (3) rotation at pivot points (e.g., door hinges); (4) linear dampers; (5) motion capture; (6) cabin or external light; (7) thermal gradients; and (8) cabin vibration. In a further embodiment, particularly for new installations, the energy harvesting system 140 may also include a direct connection to the aircraft power system that can provide power to supplement the power generated by the energy capture devices.
In one embodiment, energy storage device 130 may be a rechargeable battery, so that the energy locally generated by energy harvesting systems 140 may be used to continually maintain the energy storage level within such battery. In a further embodiment, the rechargeable battery is replaceable. In another embodiment, energy storage device 130 may be a capacitor (and associated electronic circuitry) that is charged by the energy locally generated by energy harvesting systems 140. In some embodiments, a number of different energy sources are combined to comprise energy harvesting systems 140, as necessary to maintain the required energy level in energy storage device 130 that is necessary to operate latch mechanism 120 and any optionally added ancillary equipment such as lighting/communications devices 150.
In the embodiment shown in
Referring now to
Referring now to
By using a self-contained power generating source, the system disclosed herein combines the best features of mechanical latches (i.e., an independent design) and of electronic latches (i.e., lighter weight and feedback displays). The independent nature of this system allows use in both new aircraft (during construction) and existing aircraft (via retrofit of existing mechanical latch systems).
Although the present disclosure has been particularly shown and described with reference to the preferred embodiments and various aspects thereof, it will be appreciated by those of ordinary skill in the art that various changes and modifications may be made without departing from the spirit and scope of the disclosure. It is intended that the appended claims be interpreted as including the embodiments described herein, the alternatives mentioned above, and all equivalents thereto.
