Patent Description:
In recent years, unmanned aerial vehicles (UAVs) or drones have been used to fly significant distances to transport payloads (e.g., packages, supplies, equipment, etc.) or gather information. A weight and an aerodynamic design of a UAV can affect a payload that can be carried by the UAV, as well as a flight range of the UAV. Typically, UAVs are designed for specific performance and/or mission needs.

<CIT>, in accordance with its abstract, states an aircraft includes a fuselage module and at least two vertical lift rotor modules supporting at least four rotor assemblies. Each rotor assembly is supported by a rotor boom having at least one boom free end and a boom mounting portion. Each rotor assembly has at least one vertical lift rotor mounted on the boom free end. Each boom mounting potion is removably couplable to the fuselage module. The vertical lift rotor modules are configured such that when coupled to the fuselage module, a pair of the rotor assemblies are located on each of laterally opposite sides of the fuselage module, and the rotor assemblies of each pair are respectively located forward of and aft of a wing center portion. A pair of wings are configured to be removably couplable to the wing center portion. The aircraft includes a forward thrust module removably couplable to the fuselage body.

<CIT>, in accordance with its abstract, states that an unmanned aerial vehicle includes a fuselage, tail, wings and an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle is configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle is configured with direct connection to moveable flight control surfaces.

<CIT>, in accordance with its abstract, states a modular Unmanned Aerial System (UAS) includes an Unmanned Aerial Vehicle (UAV) parent module and UAV child modules. A main wing extends from a respective fuselage of the modules. The UAS includes docking mechanisms coupled to wingtips of the main wings. The child modules dock with the wingtips of the parent or an adjacent child module. Docking forms a linked-flight configuration, with undocking and separation from the parent or adjacent child modules achieving an independent-flight configuration. The modules have booms arranged transverse to the main wings and parallel to the longitudinal axis, as well as front and rear rotors/propellers. The front and rear propellers have axes of rotation that are normal to a plane of the longitudinal axis in a vertical takeoff and landing (VTOL) configuration, with the axis of rotation of the rear propellers parallel to the longitudinal axis in a forward-flight configuration.

<CIT>, in accordance with its abstract, states an aircraft has a fuselage, a wing assembly coupleable to the fuselage, and an empennage including a pair of tail booms configured to be removably coupled to the wing assembly. The wing assembly includes a pair of boom interfaces located on laterally opposite sides of the fuselage. Each tail boom has a boom forward end configuration to be mechanically attached to one of the boom interfaces using an externally-accessible mechanical fastener.

<CIT>, in accordance with its abstract, states an aircraft, preferably an unmanned aircraft (UAV), drone, or Unmanned Aerial System (UAS), comprising a rigid wing which enables aerodynamic horizontal flight, and at least four rotors which are driven by means of controllable electric motors and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism, wherein all electric motors and rotors are arranged on the wing.

<CIT>, in accordance with its abstract, states an aircraft including an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (T/V) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

<CIT>, in accordance with its abstract, states that an aircraft includes an airframe having a fixed-wing section and a plurality of articulated electric rotors, at least some of which are variable-position rotors having different operating configurations based on rotor position. A first operating configuration is a vertical-flight configuration in which the rotors generate primarily vertical thrust for vertical flight, and a second operating configuration is a horizontal-flight configuration in which the rotors generate primarily horizontal thrust for horizontal fixed-wing flight. Control circuitry independently controls rotor thrust and rotor orientation of the variable-position rotors to provide thrust-vectoring maneuvering. The fixed-wing section may employ removable wing panels so the aircraft can be deployed both in fixed-wing and rotorcraft configurations for different missions.

<CIT>, in accordance with its abstract, states that there is provided an aircraft system in the tilt-rotor category with four propulsion units where the tilt angle and thrust of each unit is controlled independently of the other units. The tilt angle for each unit can be adjusted anywhere from below horizontal, to fully forward, and to greater than <NUM> degrees (i.e. tilted backwards).

According to the presently claimed invention, as defined in claim <NUM>, there is described herein an unmanned aerial vehicle (UAV) comprising: a fuselage that extends along a longitudinal axis; a releasably couplable wing; a motor; a motor boom configured to support the motor, wherein the motor boom is configured to be swivelled and/or rotated relative to the fuselage and/or the releasably couplable wing; a wing support frame extending from the fuselage and along a wingspan of the unmanned aerial vehicle, the wing support frame having distal ends to support: the releasably couplable wing, the releasably couplable wing to extend along the wingspan when coupled to the wing support frame, and the motor boom such that the motor boom extends parallel to the longitudinal axis and supports the motor that is oriented to generate lift for the unmanned aerial vehicle; and a releasably couplable tail boom, wherein the tail boom supports a combined rudder-elevator, and wherein the combined rudder-elevator swivels relative to the tail boom.

According to the presently claimed invention, as defined in claim <NUM>, there is also described herein, a method comprising: coupling a fuselage that extends along a longitudinal axis to a wing support frame, the wing support frame extending from the fuselage and along a wingspan of an unmanned aerial vehicle (UAV); releasably coupling a wing to a distal end of the wing support frame, the wing to be releasably coupled to the wing support frame at the distal end, the distal end to support a motor boom that is parallel to the longitudinal axis; coupling the motor boom to the wing support frame, wherein the motor boom supports a motor, and wherein the motor boom is configured to be swivelled and/or rotated relative to the fuselage and/or the wing; coupling a tail boom to the fuselage; and coupling a combined rudder/elevator to the fuselage, wherein the combined rudder-elevator swivels relative to the tail boom.

The figures are not to scale. Instead, the thickness of the layers or regions may be enlarged in the drawings. In general, the same reference numbers will be used throughout the drawing(s) and accompanying written description to refer to the same or like parts. As used herein, unless otherwise stated, the term "above" describes the relationship of two parts relative to Earth. A first part is above a second part, if the second part has at least one part between Earth and the first part. Likewise, as used herein, a first part is "below" a second part when the first part is closer to the Earth than the second part. As noted above, a first part can be above or below a second part with one or more of: other parts therebetween, without other parts therebetween, with the first and second parts touching, or without the first and second parts being in direct contact with one another. As used in this patent, stating that any part is in any way on (e.g., positioned on, located on, disposed on, or formed on, etc.) another part, indicates that the referenced part is either in contact with the other part, or that the referenced part is above the other part with one or more intermediate part(s) located therebetween. As used herein, connection references (e.g., attached, coupled, connected, and joined) may include intermediate members between the elements referenced by the connection reference and/or relative movement between those elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and/or in fixed relation to each other. As used herein, stating that any part is in "contact" with another part is defined to mean that there is no intermediate part between the two parts.

Unless specifically stated otherwise, descriptors such as "first," "second," "third," etc. are used herein without imputing or otherwise indicating any meaning of priority, physical order, arrangement in a list, and/or ordering in any way, but are merely used as labels and/or arbitrary names to distinguish elements for ease of understanding the disclosed examples. " In such instances, it should be understood that such descriptors are used merely for identifying those elements distinctly that might, for example, otherwise share a same name. As used herein, "approximately" and "about" refer to dimensions that may not be exact due to manufacturing tolerances and/or other real world imperfections.

Modular unmanned aerial vehicles (UAVs) are disclosed. Some known UAVs have a limited flight range based on weight (e.g., structural weight, fuel carried, payload, etc.), as well as aerodynamic design. Further, to save on weight, known UAVs are not generally customizable or adaptable due to additional structures or weight corresponding to such customizability. In other words, most known UAVs are designed for specific application needs (e.g., mission needs, payload requirements, etc.) and many different UAVs are usually purchased, utilized and maintained to meet varying application needs.

Examples disclosed herein enable UAVs that are lightweight, highly maneuverable, highly adaptable and relatively low cost. Examples disclosed herein are modular to enable different components to be replaced and/or swapped for different applications, thereby enabling the UAVs to be versatile for different applications.

Examples disclosed herein include a UAV having a fuselage that extends along a longitudinal axis. A wing support frame, which may also be referred to herein as a strongback, extends from the fuselage and along a wingspan of the UAV. The wing support frame has distal ends to support a releasably couplable wing and a motor boom that extends parallel to the longitudinal axis (e.g., within <NUM> degrees of the longitudinal axis).

In some examples, the wingspan is <NUM> to <NUM> meters (m) or approximately <NUM> to approximately <NUM>. According to the presently claimed invention, the UAV includes a releasably couplable tail boom. The tail boom supports a combined rudder-elevator that swivels relative to the tail boom. The combined rudder-elevator is releasably couplable to the tail boom. In some examples, the motor boom is at least partially composed of carbon fiber. Additionally or alternatively, the motor boom is releasably couplable to the wing support frame. In some examples, the motor boom mounts a first motor and a second motor on an opposite side of the wing support frame and/or the wing.

As used herein, the term "releasably couplable" refers to an object that is intended to be coupled and released through numerous cycles with relatively little or no plastic deformation. Accordingly, the term "releasably couplable" can refer to a snap fit, a slip fit, a magnetic connection, a lock interface (e.g., a spring-loaded pin, a lever lock, etc.).

<FIG> is an example UAV <NUM> in accordance with teachings of this disclosure. The UAV <NUM> is modular and adaptable to enable adjustments that can allow customization associated with different performance requirements. In particular, different components of the UAV <NUM> can be easily swapped to vary functionality of the UAV <NUM>. Thus, the UAV <NUM> can be adapted for a wide range of application and/or flight needs.

The UAV <NUM> of the illustrated example includes a fuselage <NUM>, which carries fuel and at least one payload. The fuselage <NUM> defines a longitudinal axis <NUM> and includes a controller <NUM>. Further, the example fuselage <NUM> is operatively coupled to a tail boom <NUM> that supports rudder-elevators (e.g., a combined rudder and elevator, a combined rudder-elevator, etc.) <NUM>, which are also known as ruddervators, and a tail motor <NUM>. In some examples, including the illustrated example, the fuselage <NUM> is coupled to a wing support frame <NUM> having respective distal ends <NUM>. In some examples, including this example, the distal ends <NUM> support releasably couplable wings <NUM>, as well as booms (e.g., motor booms, wing booms, etc.) <NUM> that, in turn, support motors <NUM> (hereinafter the motors 120a, 120b, 120c, 120d, etc.). In some examples, including this example, the booms <NUM> extend parallel or generally parallel (e.g., within five degrees) to the aforementioned longitudinal axis <NUM> and do not support batteries and/or a power source for the motors 120a, 120b, 120c, 120d. In other examples, the booms <NUM> are angled from the longitudinal axis <NUM> (e.g., <NUM> to <NUM> degrees from the longitudinal axis <NUM>). Further, each of the booms <NUM> supports ones of the motors <NUM> at opposite sides of the wing support frame <NUM> and/or the corresponding wing(s) <NUM>.

To move the UAV <NUM>, the tail motor <NUM> of the illustrated example is controlled to propel the UAV <NUM> forward. Further, the motors 120a, 120b, 120c, 120d are operated to vary a lift of the UAV <NUM> during flight. For example, at least one of the motors 120a, 120b, 120c, 120d is operated to maneuver the UAV <NUM>. In some examples, the motors 120a, 120b, 120c, 120d are utilized for hovering. Additionally or alternatively, the motors 120a, 120b, 120c, 120d are utilized for vertical takeoff, such as vertical take-off and landing (VTOL) or short take-off and landing (STOL) functionality.

To increase a maneuverability of UAVs such as the example UAV <NUM>, the rudder-elevators <NUM> can be rotated, as generally indicated by double arrows <NUM>, for example. Additionally or alternatively, an orientation of at least one of the motors 120a, 120b, 120c, 120d can be adjusted, as generally indicated by double arrows <NUM>. In particular, in some such examples, the motors 120a, 120b, 120c, 120d are swiveled during flight of the UAV <NUM>.

To increase a range and fuel efficiency of the UAV <NUM>, a wingspan of the UAV <NUM> can range from <NUM> to <NUM> (e.g., <NUM> in length). In some examples, including this example, the wingspan is defined as a distance between distal outer ends of the wings <NUM> and, thus, can include a width of the wing support frame <NUM>. Further, a length of the fuselage can range from <NUM> to <NUM> (e.g., <NUM>). These example dimensions can be advantageous in operating the UAV <NUM> in terms of fuel efficiency and range.

To enable the UAV <NUM> to be adaptable and/or modular, the wings <NUM> are releasably couplable to the wing support frame <NUM>. In particular, the wings <NUM> can be exchanged, replaced and/or swapped for wings that are better suited for another application and/or mission requirement. For example, the wings <NUM> can be swapped with a shorter wing (i.e., a decreased wingspan) for faster flight or a longer wing (i.e., an increased wingspan) for gliding, thereby enabling a great degree of versatility of the UAV <NUM>. In other words, different wings can be selected for different functions and/or performance requirements. As a result of this flexibility, an operator may purchase and maintain a reduced number of operational UAVs, thereby saving expenses and costs associated with a large fleet of UAVs. Moreover, the replaceability of the wings <NUM> enables a damaged wing to be replaced and, thus, increases a service life of the UAV <NUM>.

In some examples, the wing support frame <NUM> is releasably couplable to the fuselage <NUM>. Further, the rudder-elevators <NUM> are releasably couplable to the fuselage <NUM> and/or the tail boom <NUM>. In some examples, the booms <NUM> are at least partially composed of carbon fiber. Additionally or alternatively, the wings <NUM>, the fuselage <NUM>, the wing support frame <NUM>, the tail boom <NUM> and/or the rudder-elevators <NUM> are at least partially composed of carbon fiber.

In some examples, the booms <NUM> are rotatable (e.g., rotatable along an axis parallel to the longitudinal axis <NUM>). In some example UAVs, including this example UAV <NUM>, the UAV can weigh less than <NUM> kilograms (kg). Further, the UAV <NUM> can have a hover duration of <NUM> seconds (or approximately <NUM> seconds) and a sortie duration of <NUM> hours (or approximately <NUM> hours). The example UAV <NUM> also includes an airframe mass of <NUM> (or approximately <NUM>) and can carry a payload weight of <NUM> (or approximately <NUM>). Further, the example UAV <NUM> has a maximum speed of <NUM>/h (<NUM> knots) or approximately <NUM>/h (<NUM> knots), and can withstand wind speeds of <NUM>/h (<NUM> knots) or approximately <NUM>/h (<NUM> knots).

<FIG> depicts an example rotor configuration that can be implemented in examples disclosed herein. As can be seen in the illustrated example of <FIG>, the UAV <NUM> is shown with the motors 120a, 120b, 120c, 120d being simultaneously operated (e.g., operated at independent speeds and/or rotational orientations). In some examples, including this example, an arrow <NUM> depicts a direction of flight while an arrow <NUM> depicts a direction of air flow.

In operation, the motors 120a and 120d move the UAV <NUM> forward while the motors 120b and 120c move the UAV <NUM> backward. In some examples, including this example, the motors 120a and 120d are angled upward from the ground while the motors 120b and 120c are angled downward toward the ground.

In some examples, the motors 120a, 120b, 120c, 120d can be swiveled and/or re-oriented during flight or hover of the UAV <NUM> (e.g., the motors 120a, 120b, 120c, 120d are rotated via an actuator, motor and/or solenoid). This movement of the motors 120a, 120b, 120c, 120d can enable increase lateral movement and/or turning of the UAV <NUM>. The booms <NUM> are configured to be swiveled and/or rotated relative to the fuselage <NUM> and/or the wings <NUM>. Further, the motors 120a, 120b, 120c, 120d can be operated speeds different from one another to enhance maneuverability of the UAV <NUM>.

While four of the motors <NUM> are shown in connection with the UAV <NUM>, any appropriate number of the motors <NUM> can be implemented instead (e.g., six, ten, twenty, one hundred, etc.). In some examples, the example UAV <NUM> has a wingspan of approximately <NUM>, and may be <NUM>. In some examples, the height the UAV <NUM> is approximately <NUM> and may be <NUM>. In some examples, a length of the UAV <NUM> is approximately <NUM>, and may be <NUM>. In some examples, including this example, the UAV <NUM> is being assembled and/or prepared for flight. In particular, the UAV <NUM> has been previously disassembled to facilitate shipping. Now that the UAV <NUM> has been shipped, the UAV <NUM> will be configured to perform a mission.

At block <NUM>, the wing support frame <NUM> is coupled to the fuselage <NUM>. In some examples, the wing support frame <NUM> is releasably coupled to the fuselage <NUM>. In other examples, the wing support frame <NUM> is bonded, adhered and/or welded to the fuselage <NUM>.

At block <NUM>, in some examples, the wing boom <NUM> is coupled to the wing support frame <NUM>. In some examples, including this example, the boom <NUM> is releasably coupled to the wing support frame <NUM>. In other examples, the boom <NUM> is integral (e.g., pre-assembled) to the wing support frame <NUM>.

At block <NUM>, the wing <NUM> is coupled to the distal end <NUM> of the wing support frame <NUM>. In some examples, including this example, the wing support frame <NUM> defines at least a portion of a wingspan of the UAV <NUM>. In some examples, the wing <NUM> is replaced with another wing based on a performance and/or mission requirement(s).

At block <NUM>, the tail boom <NUM> is coupled to the fuselage <NUM>. In some examples, the tail boom is releasably coupled to the fuselage <NUM>. In other examples, the tail boom <NUM> is foldable relative to the fuselage <NUM>.

At block <NUM>, the rudder-elevator <NUM> is coupled to the tail boom <NUM> and/or the fuselage <NUM> and the method <NUM> ends. In some examples, including this example, the rudder-elevator <NUM> is releasably couplable to the tail boom <NUM> and/or a frame associated with the tail boom <NUM> via a slip fit. In some examples, a lock pin (e.g., a spring-loaded lock pin) is implemented to retain or hold the rudder-elevator <NUM> to the tail boom <NUM>.

In a first example, not explicitly claimed by the appended claims, there is provided an unmanned aerial vehicle (UAV) including a fuselage that extends along a longitudinal axis, a wing support frame extending from the fuselage and along a wingspan of the UAV. The wing support frame includes distal ends to support a releasably couplable wing, the releasably couplable wing to extend along the wingspan when coupled to the wing support frame, and a motor boom that extends parallel to the longitudinal axis, the motor boom to support a motor that is oriented to generate lift for the UAV.

The UAV may further include a releasably couplable tail boom. Further , the tail boom may support a combined rudder-elevator. Further, the combined rudder-elevator may swivel relative to the tail boom. The combined rudder-elevator may be releasably couplable to the tail boom.

The UAV may have a wingspan of <NUM> to <NUM> meters or approximately <NUM> to <NUM> meters.

The motor boom may releasably couplable to the wing support frame.

The motor boom may be integral with the wing support frame.

The motor may be a first a motor, and the motor boom may supports a second motor on an opposite side of the wing support frame from the first motor.

Further, the first motor may be oriented in a direction opposing an orientation of the second motor.

The first motor may be directed downward toward the ground and the second motor is directed upward away from the ground.

In another example, not explicitly claimed by the appended claims, there is provided a method including coupling a fuselage that extends along a longitudinal axis to a wing support frame, the wing support frame extending from the fuselage and along a wingspan of an unmanned aerial vehicle (UAV), and coupling a wing to a distal end of the wing support frame, the wing to be releasably coupled to the wing support frame at the distal end, the distal end to support a motor boom that is parallel to the longitudinal axis.

The method may further include coupling the motor boom to the wing support frame.

The method may further include coupling a tail boom to the fuselage.

The method may further include coupling a combined rudder/elevator to the fuselage.

Further, coupling the combined rudder/elevator to the fuselage may include a slip fit.

Additionally, or alternatively, coupling the combined rudder/elevator to the fuselage may include use of a spring-loaded pin.

The method may further include orienting a first motor of a motor boom coupled to the distal end of the distal frame support toward the ground, and orienting a second motor of the motor boom away from the ground.

The wing may include a first wing that corresponds to a first performance requirement, and the method may further include exchanging the first wing with a second wing that corresponds to a second performance requirement different from the first performance requirement.

The fuselage may be releasably coupled to the wing support frame.

From the foregoing, it will be appreciated that example methods, apparatus and articles of manufacture have been disclosed that enable a highly adaptable UAV that is light weight, cost-effective and fuel efficient. Examples disclosed herein enable UAVs to be adapted for different performance and/or mission requirements, thereby reducing a need to purchase, maintain and store many different types of UAVs.

Claim 1:
An unmanned aerial vehicle (UAV) (<NUM>) comprising:
a fuselage (<NUM>) that extends along a longitudinal axis;
a releasably couplable wing (<NUM>);
a motor (<NUM>);
a motor boom (<NUM>) configured to support the motor (<NUM>), wherein the motor boom (<NUM>) is configured to be swivelled and/or rotated relative to the fuselage (<NUM>) and/or relative to the releasably couplable wing (<NUM>);
a wing support frame (<NUM>) extending from the fuselage (<NUM>) and along a wingspan of the unmanned aerial vehicle (<NUM>), the wing support frame (<NUM>) having distal ends (<NUM>) to support:
the releasably couplable wing (<NUM>), the releasably couplable wing (<NUM>) to extend along the wingspan when coupled to the wing support frame (<NUM>), and
the motor boom (<NUM>) such that the motor boom (<NUM>) extends parallel to the longitudinal axis and supports the motor (<NUM>) such that the motor (<NUM>) is oriented to generate lift for the unmanned air vehicle (<NUM>); and
a releasably couplable tail boom (<NUM>), wherein the tail boom (<NUM>) supports a combined rudder-elevator (<NUM>), and wherein the combined rudder-elevator (<NUM>) swivels relative to the tail boom (<NUM>).