Remotely controlled modular VTOL aircraft and re-configurable system using same

A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability.

BACKGROUND

Field of the Invention

This invention relates to powered flight, and more specifically to a vertical take-off and landing aircraft, method, and system.

Description of Related Art

VTOL capability may be sought after in manned vehicle applications, such as otherwise traditional aircraft. An unmanned aerial vehicle (UAV) is a powered, heavier than air, aerial vehicle that does not carry a human operator, or pilot, and which uses aerodynamic forces to provide vehicle lift, can fly autonomously, or can be piloted remotely. Because UAVs are unmanned, and cost substantially less than conventional manned aircraft, they are able to be utilized in a significant number of operating environments.

UAVs provide tremendous utility in numerous applications. For example, UAVs are commonly used by the military to provide mobile aerial observation platforms that allow for observation of ground sites at reduced risk to ground personnel. The typical UAV that is used today has a fuselage with wings extending outward, control surfaces mounted on the wings, a rudder, and an engine that propels the UAV in forward flight. Such UAVs can fly autonomously and/or can be controlled by an operator from a remote location. UAVs may also be used by hobbyists, for example remote control airplane enthusiasts.

A typical UAV takes off and lands like an ordinary airplane. Runways may not always be available, or their use may be impractical. It is often desirable to use a UAV in a confined area for takeoff and landing, which leads to a desire for a craft that can achieve VTOL.

SUMMARY

A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability.

DETAILED DESCRIPTION

In some embodiments of the present invention, as seen inFIGS. 1A-B, a remotely piloted, autonomously controlled and/or automatically stabilized unmanned aerial vehicle101is seen in a vertical takeoff and landing configuration141with the leading edges of its two wings or four half-wings oriented skyward and the two wings or four half wing assemblies102,109arranged in a biplane configuration. The four half wing assemblies102,109consist of two right half wings103with thrust producing elements104and two left half wings108with thrust producing elements104. In this embodiment, the vehicle101has upper right side wing assemblies and lower right side wing assemblies which are identical in length and wing profile. Also, the vehicle101has upper left side wing assemblies and lower left side wing assemblies which are identical in length and wing profile. Each of the four half wings carries two thrust producing elements104. In an exemplary embodiment, each of the half wings has a half span of 1.0 meters and a half area, with a mean aerodynamic chord of 0.17 meters. Each of the half wings may have two control surfaces adapted to move around a pivot axis to support aerial vehicle control.

A single aerodynamic central body pylon105is used to connect the four half wing assemblies102,109in a biplane configuration. The vehicle101also features a extended nose section106at the intersection of the aerodynamic central body pylon105and one or both of the wings in a biplane configuration, which may be the bottom half wing set. The aerodynamic central body pylon may be a vertical symmetric airfoil is some aspects. The transition of the vertical airfoil of the central body may include blended sections to aerodynamically blend the vertical airfoil of the central body pylon to the horizontal airfoil sections of the wings. This bulbous nose is designed to carry a payload internally or protruding from it107. The protruding equipment portion107may be an imaging aperture in some embodiments. Each half wing103,108in the biplane configuration and its two associated thrust producing elements104form a modular unit, a half wing assembly102,109which can be detached from the aerodynamic central body pylon105to allow packing for transportation and/or to be replaced by another wing half with thrust producing elements of the same design for maintenance and repair purposes and/or with another wing half with thrust producing elements of a different design to suit the aerodynamic and thrust requirements for a variety of missions. In an exemplary embodiment, the aerodynamic central body pylon105is substantially a vertically oriented symmetric airfoil, which is is 0.625 meters high, 0.12 meters thick, and with a chord of 0.35 meters.

FIGS. 2A-Cshows the remotely piloted, autonomously controlled and/or automatically stabilized unmanned aerial vehicle101in a forward flight configuration142with the leading edges of its two wings or four half-wings oriented in the direction of flight and the two wings or four half wings arranged in a biplane configuration. Each of the four half wing assemblies102,109further carries two thrust producing elements104. Either one or both of these thrust producing elements104may be active during the forward flight phase of the flight. In some embodiments, the thrust producing elements are 900 Watt continuous power brushless motors with propellers with a diameter in the range of 14-17 inches. In some embodiments, one or more of the propellers on each wing assembly may be a folding propeller adapted to fold back when not being used to support vertical take-off and landing (VTOL). In some embodiments, the outboard propellers on each wing assembly may be folding propellers. The single aerodynamic central body pylon105that is used to connect the four half wings in a biplane configuration is oriented as a vertical fin in the forward flight configuration. The extended nose section106of the vehicle101at the intersection of the aerodynamic pylon105and one of the wings in a biplane configuration is carrying a payload protruding from it107. In the forward flight configuration, this equipment107has an unobstructed view in a downward pointing hemisphere. In an exemplary embodiment, the full vehicle may have an upper and lower wing which use identical right side and left wing assemblies, with an overall span of 2.4 meters, a mean aerodynamic chord (MAC) of 0.26 meters, a lifting surface area of 1.0 square meters, with a maximum take-off weight of 14.6 kg.

In some embodiments of the present invention, as seen inFIGS. 3A-C, the modular aspect of the aerial vehicle system is seen. The half wing assemblies102,109, with their associated thrust producing elements104and half wings103,108, are detached from the aerodynamic central body pylon105and its associated bulbous nose106and payload107. The half wing assemblies102,109, with their associated thrust producing elements104and half wings103,108, are detached from the aerodynamic central body pylon105adapted to be removably attached to the central body pylon105. The vehicle's extended nose section106is also adapted to be removable from the aerodynamic central body pylon105, in order to allow access to the payload107through an opening110in the extended nose section105. The extended nose106can, in some embodiments, be removed and replaced with a nose of a different design to accommodate different payloads. In addition, the modular aspect of the aerial vehicle system allows for re-configuration of the vehicle system with differing wing set types. The removable half wing assemblies may be coupled to the central body pylon105such that both structural attachment is achieved, as well as electrical coupling of the thrust assemblies104and other aspects, such as control surface controlling mechanisms. In such a system, the central body pylon105may house aspects of the system which may be common to all configurations, such as the control electronics, battery packs (or other power source), and attitude sensors. Another modular aspect is the interchangeability of the extended nose with other profiles, allowing for the use of differing imaging payload packages, for example.

In some embodiments, the central body pylon may allow for the through insertion of cross spars adapted to be inserted a partial distance into the adjoining portions of the half wings to allow for structural coupling of the central body pylon to the half wings, and by extension of the right half wings to the left half wings, and of the upper half wings to the lower half wings. Electrical connectivity may be implemented with wiring harnesses and connectors, and through other means.

FIGS. 4A-Billustrate the modularity aspect of the extended nose section. Depending upon the flight profile of the flight of the vehicle, and/or the type of payload to be carried during such a flight, varying types of extended nose sections106,116,117,118may be used. In some aspects, an extended nose section may include access for an imaging device, or sensor, to protrude through the nose section to facilitate imaging. In some aspects, the extended nose section allows for imaging downward with an unobstructed field of view.FIGS. 5A-Billustrate a configuration of the vehicle system using a long version extended nose section116attached to the aerodynamic central body pylon105. Different extended nose sections may better facilitate differing payloads. Exemplary payloads may include a stabilized gimbal visual imaging system, a stabilized combined visual/infrared imaging system, LIDAR systems, and hyperspectral imaging systems.

FIGS. 6A-Cillustrate a second embodiment301of an unmanned aerial vehicle system. This second embodiment with different half wing types on the upper and lower wings illustrates an advantage of the modular aspect of the present system. Using the same aerodynamic central body pylon105as seen in other embodiments, the upper right wing assembly302and the upper left wing assembly309utilize regular half wings303,308of the same length and other characteristics. However, the lower right wing assembly305and the lower left wing assembly310utilize short half wings304,311which are considerably shorter than those of the upper wings. Such a configuration may be utilized when the mission profile demands increased stability.

FIGS. 7A-Billustrate a third embodiment401of an unmanned aerial vehicle system. This third embodiment with different half wing types on the upper and lower wings illustrates an advantage of the modular aspect of the present system. Using the same aerodynamic central body pylon105as seen in other embodiments, the upper right wing assembly402and the upper left wing assembly409utilize short half wings403,408of the same length and other characteristics. However, the lower right wing assembly405and the lower left wing assembly410utilize regular half wings404,411which are considerably longer than those of the upper wings. Such a configuration may be utilized when the mission profile demands increased agility.

Of note is the adaptability of the system with a central body and two wing set types, both longer and shorter. For example, the use of two longer wing sets, both upper and lower, allows for greater range and endurance, or for higher payload capability with the same range and endurance. As discussed above, the use of a longer wing set on the top of the vehicle and a shorter wing set for the lower wing set increases stability. Also as discussed above, the use of a shorter wing set for the top wing and a longer wing set for the lower wing increases agility. Further, the use of shorter wing sets both on the top wing and on the bottom wing allows for higher speed, as certain flight missions may call for.

FIGS. 8A-Billustrate a fourth embodiment501of an unmanned aerial vehicle system. This fourth embodiment with different half wing types on the upper and lower wings again illustrates an advantage of the modular aspect of the present system. Using the same aerodynamic central body pylon105as seen in other embodiments, the upper right wing assembly502and the upper left wing assembly509utilize extra long half wings503,508of the same length and other characteristics. However, the lower right wing assembly505and the lower left wing assembly510utilize regular half wings504,511which are shorter than those of the extra long upper wings. Such a configuration may be utilized when the mission profile demands increased agility, but may also provide substantially extra payload capacity relative to the second configuration.

FIGS. 9A-Billustrate a fourth embodiment601of an unmanned aerial vehicle system. This fifth embodiment with the same half wing types on the upper and lower wings again illustrates an advantage of the modular aspect of the present system. Using the same aerodynamic central body pylon105as seen in other embodiments, the upper right wing assembly502and the upper left wing assembly509utilize extra long half wings503,508of the same length and other characteristics. The lower right wing assembly505and the lower left wing assembly510also utilize extra long half wings504,511which are the same length as those of the upper wings. Such a configuration may be utilized when the mission profile demands increased range and endurance, or significantly enhanced payload capability.

FIGS. 10A-Billustrate a sixth embodiment701of an unmanned aerial vehicle system. This sixth embodiment with the same half wing types on the upper and lower wings again illustrates an advantage of the modular aspect of the present system. Using the same aerodynamic central body pylon105as seen in other embodiments, the upper right wing assembly602and the upper left wing assembly609utilize short half wings603,608of the same length and other characteristics. The lower right wing assembly605and the lower left wing assembly610also utilize short half wings604,611which are the same length as those of the upper wings. Such a configuration may be utilized when the mission profile demands increased speed.

FIGS. 11A-Band12A-B illustrate the compact way in which half wing assemblies may be stored for transport. As seen above, a system with two full sets (upper and lower) of half wings of two different sized (regular and short) allows for four separate configurations. Thus, a single vehicle system with two wing sets allows for four configurations, which allows for customization of the vehicle for a variety of flight profile needs.

FIGS. 13A-Billustrate the interior of the aerodynamic central body pylon, including the batteries mounted just lower than the midpoint of the interior space of the central body pylon. The payload itself, which may be an imaging package, may reside partially in the central body pylon and partly within the extended nose section, or in the extended nose section.

In some aspects, a method for configuring a re-configurable aerial vehicle system may include evaluating the flight mission and flight profile parameters in order to best configure the aerial vehicle. A set of typical mission profiles may be seen in Table 1.

Based upon factors such as the payload weight, the desire for more stability, the desire for more agility, the desire for speed, the desire for more time aloft, the type of payload, and other factors, the user may configure the aerial vehicle by selection wing sets and nose sections which best suit the mission profile. The steps may include assessing the mission profile, selecting wing set types (upper and lower) based upon assessment of mission needs, selecting a nose section based upon payload requirements, assembling the aerial vehicle in concert with the identified priorities and needs, and flying the mission.

As evident from the above description, a wide variety of embodiments may be configured from the description given herein and additional advantages and modifications will readily occur to those skilled in the art. The invention in its broader aspects is, therefore, not limited to the specific details and illustrative examples shown and described. Accordingly, departures from such details may be made without departing from the spirit or scope of the applicant's general invention.