Patent Application
20100282897
1. Field of the Invention
The present invention relates to a surveillance device and, more particularly, to a stowable unmanned aerial surveillance device.
2. Description of Related Art
In certain situations, it may be desirable or even necessary to view or survey a scene from above. However, such surveillance may often be difficult to conduct in person due to the limitations of being able to physically obtain the necessary views. As such, various unmanned aerial surveillance devices have been proposed. One such example of a surveillance device is the “Cyber Bug” device produced by Cyber Defense Systems of St. Petersburg, Fla. The Cyber Bug appears to comprise a conventional uni-body or monolithic fuselage, wherein such a “box” design includes access doors or panels placed at strategic locations for receiving various components. The fuselage includes a tail section having a horizontal stabilizer, a vertical stabilizer, a rudder, and an elevator, wherein the vertical stabilizer and the rudder are mirrored below the centerline of the craft. An electric, tractor-configured propulsion system with a folding propeller is located at the nose portion of the fuselage. The fuselage is suspended via a connecting member beneath a delta-shaped hang-glider type canopy or main wing. The main wing includes a delta-shaped frame having a fabric attached to the frame members for forming the wing envelope. Similar to a hang glider, the fabric loosely extends between the frame members and is unsupported at the trailing edge. Autonomous flight and surveillance capabilities appear to be provided.
However, surveillance devices such as the Cyber Bug implement a uni-body or “box” design fuselage that is bulky and that may suffer from poor space management for the payload capacity. The weight of such a fuselage may also be detrimental to the flight efficiency of the craft. Such a configuration may also result in an undesirable bulkiness for storing the craft when not in use. Further, the use of the low aspect ratio control surfaces (rudder and elevator) may not provide sufficient response or authority, even when coupled with the corresponding stabilizers. In addition, the use of an additional vertical stabilizer and rudder may also undesirably increase the weight of the craft. Also, the fabric loosely attached to the delta-shaped frame is dependent on a fixed flight angle to maintain the canopy in the “inflated” shape to provide the necessary lift to keep the craft aloft. However, if the craft is disrupted from the optimum flight angle, and the fabric loses the “inflated” shape, the craft may tend to enter an unrecoverable dive at the risk of catastrophic damage thereto.
Thus, there exists a need for an unmanned aerial surveillance device that is lighter, less bulky, durable, responsive, and stable, wherein such a device should preferably be able to accommodate various components and sub-assemblies, as well as any payload, in an efficient and readily adaptable manner.
The above and other needs are met by the present invention which, in one embodiment, provides an unmanned aerial surveillance device, comprising an image capturing device operably engaged with an airframe structure configured to be capable of supporting the image-capturing device at an above-ground altitude. Such an airframe structure includes an elongate body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion is operably engaged with the body portion along the axis and comprises a rudder control surface and an elevator control surface. A pair of transversely-opposed wing portions is directly and operably engaged with the body portion and each extend substantially transversely thereto. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection disposed distally with respect to the body portion. The spars have a fabric extending therebetween so as to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, wherein the support members are configured to tension and rigidify the respective wing portion so as to provide a positive camber for each wing portion and to form an airfoil.
Embodiments of the present invention thus provide significant advantages as further detailed herein.
Having thus described the invention in general terms, reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and wherein:
The present inventions now will be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the inventions are shown. Indeed, these inventions may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will satisfy applicable legal requirements. Like numbers refer to like elements throughout.
In one embodiment, as shown in
In some embodiments, the airframe structure 200 may also have a propulsion device 600 operably engaged therewith (see, e.g., FIGS. 1 and 2A-2D). For example, the propulsion device 600 may also be housed by or otherwise engaged with the body portion 300, with the propulsion device 600 being configured to provide forward propulsion for the airframe structure 200. In one embodiment, the propulsion device 600 comprises an electrically-driven motor (not shown) configured to rotate a propeller member 650 having a plurality of blades 675. The propulsion device 600 may be configured in a tractor configuration or in a pusher configuration. As discussed further herein, one embodiment of the present invention includes a propeller member 650 having foldable blades 675 that can be folded along the body portion 300, generally parallel to the axis 310, so as to facilitate stowage of the device 100. Further, the airframe structure 200 includes a power source 700 (
In order to provide flight controls for the airframe structure 200, the tail portion 400 comprises a rudder control surface 425 and an elevator control surface 450 (
In one embodiment, each of the rudder control surface 425 and the elevator control surface 450 is comprised of a frame having a plurality of frame members pivotably attached at a leading edge thereof, wherein the trailing edges of the frame members are configured to be pivotable about the leading edge between a stowed position generally parallel to the axis 310 and a deployed position pivoted outwardly from the axis 310 (
Further, the frame of each control surface 425, 450 may also have a fabric extended thereover (either or both of the opposing surfaces of the frame, as shown in
The airframe structure 200 further comprises a pair of transversely-opposed wing portions 800, 850 (FIGS. 1 and 2A-2D) operably engaged directly with the body portion 300 and extending substantially transversely thereto. Each wing portion 800, 850 comprises leading and trailing, or longitudinally-opposed, spars 800A, 800B, 850A, 850B, wherein the respective leading and trailing spars are operably engaged with and disposed in a spaced-apart relation along the axis 310 with respect to the body portion 300. The respective spars 800A, 800B, 850A, 850B extend substantially transversely outwardly of the body portion 300 and are attached at a common connection 800C, 850C (“wingtip”) via a wingtip bracket 825 (
When deployed, the respective spars 800A, 800B, 850A, 850B of the wing portions 800, 850 define the corresponding leading and trailing edges, as well as the frame structure, of that wing portion, wherein the shape of the frame structure is approximately elliptical and is similar in configuration, for example, to a high aspect ratio conventional glider aircraft. The frame structure may be comprised of, for example, rods or tubes of rigid, strong, and durable, but light, material such as, for example, a polymer or a carbon fiber or carbon-fiber composite that may include, in some instances, Kevlar™ or Aramid™ fibers. In some instances, one or more wing spreader members 810 (
In order to provide further stability for the airframe structure 200 and rigidity of the wing portions 800, 850, each wing portion 800, 850 further includes a support member 900, 950 (
In other embodiments, the wing portions 800, 850 may be configured to be operably engaged to form a discrete wing assembly with respect to the remainder of the airframe structure 200, wherein the wing assembly can be removably engaged with the body portion 300 and/or the extension member 500 to form the device 100. For example, the wing portions 800, 850 may be configured such that the respective leading spars 800A, 850A and trailing spars 800B, 850B are first secured together to form the wing assembly. The support members 900, 950 extending from each of the common connections 800C, 850C are then connected together so as to spread the leading spars 800A, 850A and trailing spars 800B, 850B apart about the lateral center of the wing assembly. In some instances, one or more wing spreader members 810 may be operably engaged between the leading and trailing spars of the respective wing portions 800, 850 so as to maintain the approximately elliptical deployed shape of the wing assembly when the leading spars 800A, 850A and trailing spars 800B, 850B are spread apart, wherein such wing spreader members 810 may be configured, for example, with over-the-center hinge mechanisms 815 to facilitate folding of the wing portions 800, 850. The wing assembly, once prepared, can then be operably engaged with the body portion 300 and/or the extension member 500, for example, through a hook member 960 (
In order to further facilitate a surveillance application, the device 100 may also include a controller device (not shown) operably engaged with and configured to control at least one of the image-capturing device 150, the propulsion device 600, the rudder control surface 425, and the elevator control surface 450 (and/or other components of the device 100 as disclosed herein) through appropriate connectivity, whether electrical, mechanical, or otherwise, as will be appreciated by one skilled in the art. Such a controller device may also be operably received by the body portion 300 of the device 100 and powered by the power source 700. In some instances, the controller device may be configured to be remotely actuated, such as by a remote station (not shown) that may be, for example, stationed with an operator on the ground while the device 100 is aloft. Such a remote station (preferably in wireless communication with the controller device) would, for example, allow the device 100 to be remotely controlled and/or operated such that at least one of the image-capturing device 150, the propulsion device 600, the rudder control surface 425, and the elevator control surface 450 (and/or other components of the device 100 as disclosed herein) is remotely controlled as the airframe structure 200 is at the above-ground altitude. In other instances, the controller device may be programmable to execute a particular sequence of operations (including, for instance, flight path, image capture, and landing functions), independently of any remote actuation (though there may be a manual override of that functionality of the controller device via, for example, the remote station), such that, once the device 100 is deployed, the device 100 will autonomously follow that particular sequence of events until the mission is complete.
In any event, the controller device may also include wireless transceiver functionality to allow any images captured by the image-capturing device 150, as well as, for example, any other monitored environmental or equipment parameters, to be wirelessly transmitted to a remote location for monitoring and/or recording. That is, for instance, the device 100 may include any number of components or subassemblies, for monitoring or otherwise, that are necessary for a particular mission, subject to various factors such as, for example, payload capacity of the device 100, the weight of the device 100 itself, power consumption, or other factors. For example, the device 100 may include, in some instances, any number of an audio-capturing device, a chemical sensor, a temperature sensor, a radiation detector, a sound-emitting device, a light-emitting device, a deployable explosive device, a self-destruction device, a radar device, a tracking device, a homing device, or any other device that may be suitable and/or necessary for a particular mission. Accordingly, the examples presented herein are not intended to be limiting in any respect to the functional capabilities of the device 100, whether for surveillance or otherwise.
For instance, the device 100 may also comprise a navigation device (not shown), such as a GPS device or any other suitable navigation device, operably engaged with at least the controller device. In such cases, the controller device may be responsive to the navigational device to, for example, direct the propulsion device 600, the rudder control surface 425, and/or the elevator control surface 450 (and/or other components of the device 100 as disclosed herein) to guide the airframe structure 200 from a first location to a second location, and then direct the image-capturing device 150 to capture at least one image at a waypoint between and including the first and second locations. Such a navigation device may also be used, for example, to guide the device 100 to any number of waypoints, or to capture any number of waypoints in response to an on-board or remote trigger.
In another instance, the device 100 may also include a controlled descent and recovery system 1050 operably engaged therewith for facilitating recovery of the device 100 following completion of a flight or mission. Such a controlled descent and recovery system 1050 may comprise, for example, a parachute device 1100, as shown in
When necessary, the parachute device 1100 of the controlled descent and recovery device 1050 may be selectively released from the pod 1150 or body portion 300 in different manners, such that the descent of the device 100 is controlled or otherwise slowed from a free-fall, thereby facilitating recovery of the device 100. In some instances, the parachute device 1100 may be deployed at a particular minimum altitude, for example, either automatically or as a step in a landing sequence. Should the propulsion device 600 be deactuated or otherwise be rendered inoperable, for instance, and the device 100 begins to descend, the securing mechanism/release mechanism may be configured so as to be responsive to an altitude condition to deploy the parachute device 1100 at a minimum altitude above the ground. In other instances, the controller device, previously discussed, may be programmable to execute a particular sequence of operations (including, for example, flight path, image capture, and landing), independently of any remote actuation, wherein the deployment of the parachute device 1100 of the controlled descent and recovery system 1050 may be included in the programming as part of the landing sequence. As before, a manual override of that functionality of the controller device, via the remote station, for example, may also be provided. In addition, the deployment of the parachute device 1100 of the controlled descent and recovery system 1050 may also be performed through “manual” actuation by an operator via the remote station and the controller device. Accordingly, one skilled in the art will appreciate that the controlled descent and recovery system 1050 may advantageously provide, for example, a “zero runway” landing capability for the device 100 and/or greater landing accuracy at a designated site. Further, the controlled descent aspect may result in less stress on the device 100 and the components thereof, which may result in less maintenance and an extended service life of the device 100. Further, the controlled descent and recovery system 1050 may also provide an emergency landing provision in the event that the device 100 experiences damage or an operational malfunction that would prevent continued flight.
In an alternate embodiment as shown in
The wing portions 800, 850 may be configured to be operably engaged to form a discrete wing assembly with respect to the remainder of the device 100, wherein the wing assembly can be removably engaged with the body portion 300 and/or the extension member 500 to form the device 100. For example, the wing portions 800, 850 may be configured such that the respective leading spars 800A, 850A and trailing spars 800B, 850B are first secured together to form the wing assembly. One or more support members 900, 950 extending from respective ones of the common connections 800C, 850C are then connected together so as to spread the leading spars 800A, 850A and trailing spars 800B, 850B apart about the lateral center of the wing assembly. In some instances, one or more wing spreader members 810 may be operably engaged between the leading and trailing spars of the respective wing portions 800, 850 so as to maintain the approximately elliptical deployed shape of the wing assembly when the leading spars 800A, 850A and trailing spars 800B, 850B are spread apart, wherein such wing spreader members 810 may be configured, for example, with pivotable hinge mechanisms 820 to facilitate folding of the wing portions 800, 850. The pivotable hinge mechanisms 820 may, in some instances, be engaged with the respective support members 900, 950 such that, when the support members 900, 950 are tensioned so as to be connected together, the pivotable hinge mechanisms 820 are deployed to support the spacing between the leading and trailing edges of the wing portions 800, 850.
The wing assembly, once prepared, can then be operably engaged with the body portion 300 and/or the extension member 500, for example, through a hook member 960 (
The wing assembly, once deployed and operably engaged with the body portion 300 and/or the extension member 500, may have the common connections 800C, 850C (or wingtip brackets 1100) thereof connected by a tensioning member 975 extending therebetween (
As shown in
As such, embodiments of the present invention provide an unmanned aerial surveillance device 100 capable of deployment in a variety of situations, for example, in law enforcement and military applications. The device 100 can be configured to be lightweight (in one example, such a device may be configured to weigh on the order of 5 pounds or less and be in a “backpack” transportable class of devices), and capable of capturing aerial surveillance images up to the optical limitations of the image-capturing device 150 (for example, on the order of between about 200 and about 400 feet above the ground for one particular camera device), while being capable of operating on on-board power (battery-dependent) in a relatively silent manner for the required mission duration (in one example, on the order of several hours). In one instance, the device 100 may be disassembled and stored in an appropriate case, for example, a tubular storage container 1000 (
Embodiments of the present invention thus provide an unmanned aerial surveillance device that is lighter, less bulky, durable, responsive, and stable, as well as a device capable of accommodating various components and sub-assemblies, as well as any payload, in an efficient and readily adaptable manner.
Many modifications and other embodiments of the inventions set forth herein will come to mind to one skilled in the art to which these inventions pertain having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Therefore, it is to be understood that the inventions are not to be limited to the specific embodiments disclosed and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.
This application claims the benefit of U.S. Provisional Application No. 60/708,889, filed Aug. 17, 2005, and U.S. Provisional Application No. 60/752,478, filed Dec. 21, 2005, which are incorporated by reference herein in their entirety.
| Number | Date | Country | |
|---|---|---|---|
| 60708889 | Aug 2005 | US | |
| 60752478 | Dec 2005 | US |
