Aircraft tail lock

Systems, devices, and methods are provided for a locking apparatus. A locking apparatus can be configured to operably attach a fixed-wing of an aircraft to a body of the aircraft. The locking apparatus can include a first connector configured to releasably receive a first tube, a second connector having a first side and second side, the first side configured to receive a second tube and the second side configured to releasably receive the first connector, and an end coupling cap configured to releasably lock the first connector and second connector together.

BACKGROUND

An unmanned vehicle is a vehicle capable of travel without a physically-present human operator. An unmanned vehicle may operate in a remote-control mode, in an autonomous mode, or in a partially autonomous mode. Unmanned aerial vehicles (“UAVs”), such as drones, are used in a wide variety of applications. For example, drones may be used to transport material or goods from one location to another.

Drone aircraft are typically one of two types. A first type is a fixed-wing design, where lift is provided by one or more fixed wings and forward thrust is provided by a spinning propeller, ducted fan, or jet engine. A second type is a helicopter-type design where lift and forward thrust are provided by one or more vertically oriented rotors or rotary wings. Included in this second type is the so-called ‘quad-copter’ design which incorporates four vertical rotors. Manipulation of the relative thrust provided by each of the four rotors provides for variable vertical thrust and forward and lateral movement. Fixed-wing aircraft of the first type are generally efficient in long distance transportation. The various multicopter designs of the second type are generally less efficient but have the unique ability to take off vertically. These aircraft designs are said to be capable of vertical take-off and landing, or VTOL.

Drone aircrafts that are capable of both long distance travel and VTOL can greatly benefit modern drone capabilities. Improvements in designing, assembling, and operating such drones can also benefit the effectiveness and efficiency of modern drone systems.

BRIEF SUMMARY

The present disclosure relates generally to systems and methods for a locking apparatus for components of an aircraft. In one aspect, a locking apparatus can include a first connector configured to releasably receive a first tube, a second connector having a first side and second side, the first side configured to receive a second tube and the second side configured to releasably receive the first connector, and an end coupling cap configured to releasably lock the first connector and second connector together. In one aspect, the first connector can include a shaft, having an inner diameter and outer diameter, and an annular flange. In one aspect, the annular flange of the first connector can have an outer diameter larger than that of the outer diameter of the shaft, the annular flange configured to secure the end coupling cap to the first connector from sliding beyond a desired position. In one aspect, the first side of the second connector can include a first shaft and the second side of the second connector includes a second shaft, the inner diameter of the first shaft can be smaller than that of the inner diameter of the second shaft, the outer diameter of the first shaft can be smaller than that of the outer diameter of the second shaft. In one aspect, the outer diameter of the first shaft can be equal to or smaller than that of the inner diameter of the second shaft. In one example, the second connector can include an annular flange separating the first side and second side of the second connector, the annular flange having an outer diameter larger than that of outer diameters of the first side and second side of the second connector. In one example, the annular flange can be configured to secure the end coupling cap to the second connector from sliding beyond a desired position when in a locked position. In one aspect, the end coupling cap can include a hollow body with an inner diameter, the inner diameter equal in length to an outer diameter of the second side of the second connector, such that when the locking apparatus can be in a locked position, the second connector can receive the first connector and the end coupling cap can secure the first connector and the second connector with the end coupling cap. In one aspect, the end coupling cap can include an annular inner lip at one end of the hollow body, the annular inner lip configured to secure the end coupling cap in a desired position when locking the first connector and second connector. In one aspect, the end coupling cap can prevent from sliding along a longitudinal axis beyond a locking position when locking the first connector and second connector when the lip is in secure contact with an annular flange of the first connector and an opposite end to the lip of the hollow body is in secure contact with an annular flange of the second connector. In one aspect, the end coupling cap can include a rotating lock connection. In one aspect, the rotating lock connection can include a cutout in the end coupling cap such that a lock pin protruding from an outer surface of the second connector can slide through a first portion of the cutout, can rotate about the end coupling cap along a second portion of the cutout, and can releasably secure the lock pin with in a groove configured to receive the lock pin. In one aspect, the end coupling cap can be configured to allow a rotation of 30 to 90 degrees relative to the first and second connector. In one aspect, the end coupling cap can include a magnetized holding pin configured to receive and releasably secure the lock pin.

In one aspect, the locking apparatus can include an electrical connection including a first PCB tray configured to releasably secure a first PCB and a first electrical connector, a second PCB tray configured to releasably secure a second PCB and second electrical connector, the first electrical connector operably can be connected to the second electrical connector when the locking apparatus is configured in a locking position. In one aspect, the first PCB tray can be releasably secured to the first connector and the second PCB tray can be releasably secured to the second connector. In one aspect, one or more fasteners can secure the first PCB tray, the first connector, and the first tube together.

In one aspect, the locking apparatus can lock a wing to a body of an aircraft. In one aspect, the first tube can be operably connected to a body of an aircraft and the second tube can be operably connected to a tail flap of the aircraft and the locking apparatus can lock the body of the aircraft to the tail flap. In one aspect, the first tube and second tube can include carbon fiber. In one aspect, the first tube can be configured to rotate such that the tail flap can also rotate about a longitudinal axis of the first tube and second tube. In one aspect, each of the first connector, second connector, and end coupling cap can include anodized aluminum. In one aspect, the lock pin can be comprised of hardened steel.

Other embodiments are directed to systems and computer readable media associated with methods described herein.

DETAILED DESCRIPTION

In this specification, reference is made in detail to specific examples of the disclosure. Some of the examples or their aspects are illustrated in the drawings.

For clarity in explanation, the disclosure has been described with reference to specific examples, however it should be understood that the disclosure is not limited to the described examples. On the contrary, the disclosure covers alternatives, modifications, and equivalents as may be included within its scope as defined by any patent claims. The following examples of the disclosure are set forth without any loss of generality to, and without imposing limitations on, the claimed disclosure. In the following description, specific details are set forth in order to provide a thorough understanding of the present disclosure. The present disclosure may be practiced without some or all of these specific details. In addition, well known features may not have been described in detail to avoid unnecessarily obscuring the disclosure.

In addition, it should be understood that steps of the exemplary methods set forth in this exemplary patent can be performed in different orders than the order presented in this specification. Furthermore, some steps of the exemplary methods may be performed in parallel rather than being performed sequentially.

A locking mechanism for attaching a wing or fixed-wing of an aircraft is described below. For example, an aircraft locking apparatus for attaching a tail wing or fixed-wing of a VTOL aircraft to an aircraft boom assembly is discussed below. The locking apparatus can be configured to securely attach a tail wing to a boom of a drone aircraft, capable of long distance travel under operation, and configured to be removed from the boom with a quick release mechanism of the aircraft locking apparatus.

In one example, an aircraft, such as a drone or unmanned aerial vehicle (UAV) is described having a fuselage, one or more wings, one or more booms or boom assemblies. The one or more wings can span across a fuselage of the drone and a pair of booms can be attached to the each side of two sides of the one or more wings such that one boom is on one side of the fuselage and another boom is on another side of the fuselage, connected to the fuselage through the wing. In this example, the vertical takeoff propellers can be mounted onto the pair of booms.

In one example application, the aircraft described above can be light weight and having modular components. For example, an assembled drone can include various modular components such as a fuselage or body, a wing including a main wing, one or more tail wings including a vertical tail wing, diagonal tail wing, horizontal tail wing, or a combination thereof, one or more booms, propellers, rotors, engines, battery, computer hardware, cables and wiring, sensors, etc. In one example, an assembled drone can receive multiple configurations of components that are all designed to fit the drone assembly. For example, an aircraft manufacturing organization can manufacture different designs of a wing or mass manufacture the same design wing, or both, and each wing manufacture can be fitted onto the aircraft. The ability for modular components used for assembling a drone and the ability to swap out one component, with another can greatly increase the productivity, quality, efficiency, time, labor, of operating and storing an aircraft or fleet of aircraft for commercial purposes.

In such a case, the difference between being able to assemble a modular drone from hours to minutes or from multiple human operators to a single human operator for the whole assembly or portions of the assembly can drastically affect the effectiveness of aircraft fleet operation. For example, a two person job of assembling an aircraft being cut down to one person in a similar range of time required with the same resulting aircraft assembly. Or a portion of assembling a drone that typically takes in the magnitude of tens of minutes or hours to seconds or minutes. Having these improvements, when applied to a fleet of hundreds or thousands of aircrafts, each having swappable and modular components, can greatly improve a fleet's operations.

In one example, the aircraft can also include a tail wing, tail flap, tail fin, or a plurality of modular tail wings such as a vertical tail wing, diagonal tail wing, horizontal tail wing, or a combination thereof. In this example, one tail wing can be configured to connect to a rear side of the boom. An aircraft with a pair of booms can be configured with a pair of tail wings, such that one tail wing connects to the rear side of one boom and the other tail wing connects to the rear side of the other boom. In one example, the tail wing can be operably connected to a tube extending outward from a leading edge of the tail wing along one end side of the wing. The boom can include or can be operably connected to a second tube extending outwardly from the rear side of the boom, extending along an axis of the length of the boom. In this example, the tube of the tail wing and the tube of the boom can be linked, effectively connecting the tail wing to the boom. The tube of the tail wing and the tube of the boom can be linked and securely locked with each other with a locking apparatus. The locking apparatus can be a quick release mechanism such that an aircraft assembly operator can easily assemble any and all of the tail wings of the drone to any and all of the booms of the drone and the tail wing will be secured to the boom of the drone during operation including long range flight.

A. Tail Locking Apparatus

FIGS.1A-1Eillustrate an aircraft tail locking assembly for connecting a first portion of an aircraft and a second portion of an aircraft.FIG.1Aillustrates an exploded view of an example locking apparatus for a portion of an aircraft, such as a drone, or UAV. As illustrated inFIG.1A, a locking apparatus100includes a first connector110, a second connector120, and a end coupling cap130. The first connector110can be configured to connect a first tube112. In one example, the first connector110can be configured to releasably receive the first tube112. The second connector120can be configured to connect the second tube122. In one example, the second connector120includes a first side and a second side. The first side can be configured to receive the second tube122. The second side of the second connector120can also be configured to releasably receive the first connector110. The end coupling cap130can be configured to releasably lock and unlock the first connector110and the second connector120together.

In one example, the first tube112can be received by the first connector110and secured with a pair of fasteners180. The fasteners can be threaded fasteners. In another example, the fasteners can be magnetic fasteners, screwed on fasteners, rivets, or bolts. In another example, the fasteners can be made of carbon fiber, carbon composite compound, plastic, metal, or ceramic. In this example, the first connector110includes a hollow interior with an inner diameter and outer diameter, an outer diameter of the first tube112being the same length as that of the inner diameter of first connector110. When locked by the fasteners180, the first tube112and first connector110are secured to each other such that the first tube112cannot continue to move through, or slide through, the first connector110, the first tube112does not rotate relative to the first connector110. One end of first tube112, when inserted and received by the first connector110and secured by the pair of fasteners180, is flush against one end of the first connector110. In one example, another end of the first tube112can include or support a tail wing of an aircraft.

In one example, the second tube122can be received by the second connector120and secured with a pair of fasteners180. In this example, the second connector122has a hollow cylindrical shape. The second connector122has a first side and second side. The first side and second side of the second connector120can each have an inner diameter and an outer diameter. In this example, the inner diameter of the first side of the second connector120can be configured to releasably receive the second tube122. An outer diameter of the second tube122can be the same length as that of the inner diameter of the first side of the second connector120. The second tube122and second connector120can be connected to each other and secured by a pair of fasteners180. In this is example, when locked by the fasteners180, the second tube122and the second connector120are secured to each other such that the second tube122cannot continue to move through, or slide through or retract away from, the second connector120, and the second tube122cannot rotate relative to the second connector120. On one end of the second tube122, when inserted and received by the first side of the second connector120and secured by the pair of fasteners180, is flush against a cross section of the second connector120where the first side of the second connector120meets the second side of the second connector120. In one example, another end of the second tube122can include, support, or be supported by a boom or boom assembly of an aircraft. The locking apparatus100locks a wing, such as the tail wing, or tail flap, to a body of the aircraft through a boom of the aircraft, and the locking apparatus100.

In one example, the inner diameter of the second side of the second connector120is equal to the outer diameter of the first connector110. When the second connector receives120receives the first connector110, a portion of a body of the first connector110is inserted into the second side of the second connector120. The first and second connector can be secured with a pair of locking pins170. The pins can be inserted through a pair of small holes on opposite ends of the second side of the second connector120and through a pair of small holes on opposite ends of the first connector110. When the locking pins170placed in the pair of small holes, the first connector110and second connector are mechanically locked to each other, such that one connector cannot slide through, or away, from the other connector and that one connector cannot rotate relative to the other connector. In this example, under operation of the aircraft, the tail wing will be operably connected to the boom of the aircraft and locked in a fixed position under flight. In this example, the longitudinal axis, or axis of the length, of the second tube122and first tube112are effectively lined up. The first tube112can be operably connected to the second tube122, and both tubes can be operably connected to a body of the aircraft. The second tube122can also be operably connected to the tail wing, or tail flap of the aircraft. Thus, under operation, the body of the aircraft and tail flap of the aircraft are effectively locked to each other by the locking apparatus100. If the second tube122turns or rotates about the axis of the second tube122's length, the tail wing will also turn or rotate about the axis of the first tube122and would be the same amount as that of the second tube122.

In one example, when secured, a portion of the pair of locking pins170will be inserted through the second connector and into the first connector and another portion of the pair of locking pins170will be protruding radially from the second connector120, to be engaged by the end coupling cap130.

The end coupling cap130is a cylindrical shape and can include a hollow body with an inner diameter and outer diameter. The inner diameter can be equal in length to the outer diameter of the second side of the second connector120, such that when the locking apparatus100is in a locked position, the second connector120receives the first connector110, and the end coupling cap130secures the first connector110and the second connector120with the end coupling cap130. In this example, the end coupling cap can include a cutout such that one or more magnetic pins172can be located at an end section of the cutout. When the end coupling cap engages the first connector110and second connector120, the locking pin170will engage the cutout as the end coupling cap130slides through the first connector110and second connector120. Once the end coupling cap130slides through the first connector110and second connector120, the end coupling cap130will eventually reach a stop as a portion of the first connector110and a portion of the second connector120will block the end coupling cap from sliding further. In this configuration, the end coupling cap will have secured the first connector110and second connector120from sliding away from each other and the end coupling cap130. The end coupling cap130can then be rotate about its longitudinal axis, or axis of its length, such that the locking pins170will each engage the magnetic pins172to secure and lock each of the first connector110, second connector120, and end coupling cap130to each other. The locking apparatus can be easily disassembled, effectively separating a tail wing and a boom of the aircraft from each other, by rotating the end coupling cap130in the opposite direction that allowed the locking pins170to engage and magnetically lock to the magnetic pins172.

In one example, electrical connections, such as cables, wiring, and electrical components can be installed and connected between the boom and the tail wing or between the boom and any other component of the aircraft. For example, one or more motors, one or more lights, or a combination thereof, can be part of the tail wing. The electrical connection that powers and controls the motors and lights of the tail wing will be electrically connected through the boom. Assembling the electrical connections are usually done before fully mounting and sealing one component with another so that electrical components or wires are not exposed on the outside during flight and that electrical components and wires are protected by the body of each component. In this example, each electrical component, such as PCB's, and the wiring that connects the electrical components a sealed by the locking apparatus and further wiring can be housed within the first and second tube.

For example, one or more motors, one or more lights, or a combination thereof, can be part of the tail wing. The electrical connection that powers and controls the motors and lights of the tail wing will be electrically connected through the boom. Each electrical component, such as PCB's, and the wiring that connects the electrical components a sealed by the locking apparatus and further wiring can be housed within the first and second tube.

In one example, as illustrated inFIG.1A, a first printed circuit board (PCB)152, configured as a connection interface of electrical components of a wing of an aircraft can be connected to a second PCB162, configured as a connection interface of electrical components and power of the body of the aircraft. In this example power, control, and other signals can be sent and received electrical components of the body of the aircraft to electrical components embedded or located near the tail wing by electrically coupling the first PCB152to the second PCB162. In this example, the first PCB152can be secured on a first PCB tray150and the second PCB162can be secured on a second PCB tray160. The first PCB tray150can also be received and secured to the first connector110and fastened to the first connector and first tube112by the pair of fasteners180that secures the first tube112to the first connector110. In this configuration, each of the first PCB152, first PCB tray150, first connector110, and first tube112will be secured to each other such that the components cannot rotate relative to each other. This configuration ensures that as the aircraft is under operation, the wiring that connects the first PCB152to electrical components of the tail wing do not rotate, loosen, mix up or clutter. The second PCB tray160can also be received and secured to the second connector120and fastened to the second connector120and second tube122by the pair of fasteners180that secures the second tube122to the second connector120. In this configuration, each of the second PCB162, second PCB tray160, second connector120, and second tube122will be secured to each other such that the components cannot rotate relative to each other. This configuration ensures that as the aircraft is under operation, the wiring that connects the second PCB162to electrical components of the boom and rest of the body of the aircraft do not rotate, loosen, mix up or clutter. In this example, the first tube can be configured to rotate as the second tube122rotates, thus also rotating the tail wing or tail flap about a longitudinal axis.

FIGS.1B-1Eillustrate the locking apparatus100under operation as components of the locking apparatus100are connected to each other. As illustrated inFIG.1B, the first connector110can include a shaft114, the shaft114having an inner diameter and outer diameter. The first connector110can also include an annular flange118. The annular flange118is configured to secure the first connector110with the second connector120. The first tube112can be received by the first connector110and secured with a pair of fasteners180. When locked by the fasteners180, the first tube112and first connector110are secured to each other such that the first tube112cannot continue to move through, or slide through, the first connector110, and that the first tube112does not rotate relative to the first connector110. One end of first tube112, when inserted and received by the first connector110and secured by the pair of fasteners180, is flush against one end of the first connector110. In one example, another end of the first tube112can include or support a tail wing of an aircraft. In one example, the annular flange118of the first connector110has an outer diameter larger than that of the outer diameter of the shaft114. As illustrated inFIG.1C, the annular flange118can be configured to secure the first connector to the second connector from sliding beyond a desired position.

In one example, the second tube122can be received by the second connector120and secured with a pair of fasteners180. In this example, the second connector122has a hollow cylindrical shape. The first side of the second connector120includes a first shaft124and the second side of the second connector120includes a second shaft126. In this example, each of the first shaft124and second shaft126has an inner diameter and outer diameter. The inner diameter of the first shaft124can be smaller than that of the inner diameter of the second shaft126, and the outer diameter of the first shaft124can be smaller than that of the outer diameter of the second shaft126. In one example, the outer diameter of the first shaft124can be equal to or smaller than that of the inner diameter of the second shaft. The second connector120can also include an annular flange128configured to engage the end coupling cap130when the locking apparatus100is configured in a locking position. In one example, the annular flange128separates the first side and second side of the second connector120. The annular flange128can have an outer diameter larger than that of the outer diameters of the first side and second side of the second connector120. As illustrated inFIG.1D, the annular flange128can be configured to secure the end coupling cap130to the second connector120from sliding beyond a desired position when the locking apparatus100is in a locked position.

In one example, the end coupling cap130is a cylindrical shape and can include a hollow body with an inner diameter and outer diameter. At one end of the hollow body of the end coupling cap130can include an annular lip134, the annular lip134configured to secure the end coupling cap130in a desired position when locking the first connector110and second connector120. In one example, the end coupling cap130can be prevented from sliding along a longitudinal axis beyond a locking position when locking the first connector110and second connector120when the annular lip134is in secure contact with the annular flange118of the first connector and an opposite end to the lip of the hollow body is in secure contact with an annular flange128of the second connector.

For example, as illustrated inFIG.1B. as a first step of locking the first tube112and the second tube122, the first tube112can first be inserted through the end coupling cap. The inner diameter of the annular lip134can be greater than the outer diameter of the first tube112and second tube122. Once the first tube112is passed through the end coupling cap130, the first tube112can engage the first connector110and locked to the first connector with a pair of fasteners180. Additionally, the second tube122can be inserted in the first shaft124of the second connector120and locked with a pair of fasteners.

As illustrated inFIG.1C, the next step can include coupling the first connector110with the second connector120. When coupled, the first connector will be flush against the inner diameter of the second shaft126. The annular flange118of the first connector will be engaged to one end of the second shaft126so that the first connector110will be secured in a desired position and cannot slide further into the first shaft124where the second tube122will be locked to the second connector120. Additionally, since the hollow body of the first shaft124is smaller than that of the hollow body of the first connector110, the first connector110will not be able to continue to slide into the second connector120beyond a desired position when in a locked position.

As illustrated inFIG.1D, a next step for configuring the locking apparatus100in a locking position can include sliding the end coupling cap130back towards the second connector120. In this configuration, the end coupling cap130can include a rotating lock connection including having a cutout134. The cutout can be a right angle cutout that starts from one edge, or end, of the end coupling cap130, the edge or end being on the opposite side of the annular lip. And the cutout134can include a first portion of the cutout that follows the hollow body from the end coupling cap until a certain point on the hollow body and include a second portion of the cutout134that follows a direction orthogonal to that of the first portion forming a right angle. At the end of the second portion of the cutout134, the end coupling cap130can include one or more magnetic pins172. In this example, as the end coupling cap130engages the second connector120, the locking pin170secured, and partially protruding out of the second connector120can slide through the first portion of the cutout. The second connector120can continue to receive the end coupling cap130until the annular flange128engages the end side of the end coupling cap, the end side being the side opposite of the annular lip134.

As illustrated inFIG.1E, at this point, a user can then rotate the end coupling cap130such that the locking pin170will rotate through the end coupling cap and slide through the second portion of the cutout134until the locking pin170engages a groove at the end of the cutout134and is releasably secure with the groove configured to receive the locking pin. In another example, the locking pin170can be rotated until it magnetically couples with the magnetic pin172. In one example, the locking pin170can be made of hardened steel to engage the magnetic pin172. In another example, the locking pin170can be made of any type of metal or metalloid that is capable of connecting with magnets. In one example a plurality of cutouts134, magnetic pins can be located on the hollow body of the end coupling cap130. For example, a pair of cutouts134can be located on opposite sides of the surface of the hollow body of the end coupling cap130.

In one example, the cutout134is configured to allow a rotation of the end coupling cap130when the locking pin engages the second portion of the cutout134, of 60 degrees. In another example the amount of rotation, based on the length of the second portion of the cutout134can range from 30 degrees to 90 degrees. In another example, the rotation can be 1 degree to 180 degrees.

In one example, the first connector110, second connector120, and end coupling cap130can each be made of anodized aluminum material. In one example, at least a portion of the end coupling cap130can include plastic, configured to deform as a locking pin engages groove formed by plastic. The first tube112and second tube122, can each be made of carbon fiber. The lock pin170can be made of hardened steel. In one example, the first tube112and second tube122can have the same diameter. In one example, the diameter of the first tube112and second tube122can be one inch in length. In another example, the diameter of the first tube112and second tube122can be 0.2 inches to 5.0 inches length.

In one example, one or more O-rings can be configured and placed on the first connector110, second connector120, or a combination thereof to seal the connection of electrical components disposed inside each of the first tube112and second tube122. In one example, one o-ring can be wrapped around the second shaft126of the second connector120and one o-ring can be wrapped around the shaft114of the first connector110.

FIGS.2A-2Eillustrates the locking apparatus100including electrical connection, components, cabling, wiring, and other components to support and connect the electrical components. As illustrated inFIG.2A, a first printed circuit board (PCB)152, configured as a connection interface of electrical components of a wing of an aircraft can be connected to a second PCB162, configured as a connection interface of electrical components and power of the body of the aircraft. In this example, a first PCB tray150is configured to releasably secure a first PCB152and a first electrical connector154. A second PCB tray160is configured to releasably secure a second PCB162and second electrical connector164, the first electrical connector154operably connected to the second electrical connector164when the locking apparatus100is configured in a locking position. The first PCB tray150can be releasably secured to the first connector154and the second PCB tray160can be releasably secured to the second connector164. The fasteners182secures the first PCB tray150, the first connector110, and first tube112together.

In this example power, control, and other signals can be sent and received electrical components of the body of the aircraft to electrical components embedded or located near the tail wing by electrically coupling the first PCB152to the second PCB162. In this example, the first PCB152can be secured on a first PCB tray150and the second PCB162can be secured on a second PCB tray160. The first PCB tray150can also be received and secured to the first connector110and fastened to the first connector and first tube112by the pair of fasteners180that secures the first tube112to the first connector110. In this configuration, each of the first PCB152, first PCB tray150, first connector110, and first tube112will be secured to each other such that the components cannot rotate relative to each other. This configuration ensures that as the aircraft is under operation, the wiring that connects the first PCB152to electrical components of the tail wing do not rotate, loosen, mix up or clutter. The second PCB tray160can also be received and secured to the second connector120and fastened to the second connector120and second tube122by the pair of fasteners180that secures the second tube122to the second connector120. In this configuration, each of the second PCB162, second PCB tray160, second connector120, and second tube122will be secured to each other such that the components cannot rotate relative to each other. This configuration ensures that as the aircraft is under operation, the wiring that connects the second PCB162to electrical components of the boom and rest of the body of the aircraft do not rotate, loosen, mix up or clutter. In this example, the first tube can be configured to rotate as the second tube122rotates, thus also rotating the tail wing or tail flap about a longitudinal axis.

As illustrated inFIG.2B, in one example, the first PCB152is connected to the electrical first PCB tray150by a plurality of fasteners182, such as a plurality of screws, and the second PCB162is connected to the second PCB tray160by a plurality of fasteners182. An electrical connector154connecting any electrical components supported or attached to the wing, for example a motor, light, sensor, camera, or a combination thereof, can be connected to the electrical connector154. The electrical connector154can act as an electrical interface to power, control, and receive signals from the electrical components of the wing connected to the first tube112, to the rest of the electrical components of the boom or rest of the body of the aircraft by coupling with electrical connector164. In one example, the electrical connectors154and164can be a pair of male and female pins configured to be supported by the first PCB152and second PCB162.

FIGS.2C-2Eillustrate the connection of the pair of electrical connectors154and164, first PCB152, second PCB162, with the first connector110, second connector120, and end coupling cap130. In this example, as illustrated inFIG.2C, the first PCB152is connected to the first PCB tray150by fastening a plurality of fasteners to secure the first PCB152to the first PCB tray150. The first PCB tray150can then be inserted into the first tube112. Next, the first connector110can receive the first tube112with the first PCB tray150disposed inside the hollow body of the first tube112. A pair of fasteners can then secure all of the first connector110, first tube112, and first PCB tray150to each other, which operably connects the first PCB152and electrical connector154to the first tube112such that electrical components can securely connect to the electrical connector154without being mixed, rotated relative to each other, cluttered, etc. during operation of the aircraft. Additionally, the second PCB162is connected to the second PCB tray160by fastening a plurality of fasteners to secure the second PCB162to the second PCB tray160. The second PCB tray160can then be inserted into the second tube122. Next, the second connector120can receive the second tube122with the second PCB tray160disposed inside the hollow body of the second tube122. A pair of fasteners can then secure all of the second connector120, second tube122, and second PCB tray160to each other, which operably connects the second PCB162and electrical connector164to the second tube122such that electrical components can securely connect to the electrical connector164without being mixed, rotated relative to each other, cluttered, etc. during operation of the aircraft.

As illustrated inFIG.2D, as the first connector110engages the second connector120, the first PCB152and electrical connector154will engage with second PCB162and electrical connector162. As illustrated inFIG.2E, as to lock the first connector110with the second connector120, the end coupling cap130can slide towards the second connector, and rotated, to lock each of the first connector110, second connector120, and end coupling cap130together.

In one example, different types of electrical connectors can be used, disposed and supported by the PCB's, such as electrical connectors154and164, and PCB's152and162, to connect electrical components supported by the first tube112to the electrical components supported by the second tube122. The use of multiple pin connectors for electrical connectors154and164are only an example and should not be construed as limiting the type of electrical connections that can be used with the PCB's, such as PCB's152and162.

In another example, the first and second PCB152and162can be of any size, customized to fit securely to any diameter tube. For example, a tube having a one inch diameter can have a PCB, such as first and second PCB152and162described above, that is also one inch or slightly smaller than one inch to fit inside a PCB tray, such as PCB trays150and160that is also configured to fit flush with the 1 inch diameter tube. And a tube having a five inch diameter can have a PCB that is also five inches or slightly smaller than five inches to fit inside a PCB tray that is also configured to fit flush with the 5 inch diameter tube.

In one example, the first connector110, second connector120, and end coupling cap130of the locking apparatus100are each comprised of aluminum to secure the first and second tube112and122such that under flight, vibrations, or forces exerted onto the wings of the aircraft will not move the first and second connector110and120, and that the end coupling cap130would not allow dust or other particles to enter one of the tubes such as first tube112and second tube122. In another example, the locking pins170will also be hardened steel so that under vibration during flight, the locking pins170will continue to stay in place and lock the end coupling cap130with the second connector120.

In one example, while the first tube112, second tube122, locking apparatus100, and electrical members such as the first and second PCB152and162, first and second PCB trays150and160, are each cylindrical shaped, the shape of the cross section of the tubs, connectors, locking apparatus, end coupling cap, and electrical members and components should not be construed as limiting the shape to cylindrical with a circular cross section. In one example, the shapes of the tubes, connectors, end coupling cap, PCB's, and PCB trays can vary, relative to each other, including but not limited to having a rectangular, oval, elliptical, triangular, tapered, jagged, or other annular shaped, symmetrically shaped, or asymmetrically shaped cross section. In this example, the connectors, end coupling cap, PCB's, and PCB trays can have the outer surface and inner surface shaped similar to that of the cross sectional shape of the desired first tube and second tube.

FIG.3illustrates an example locking apparatus locking together a boom of an aircraft to a wing of the aircraft. In this example, a wing350, such as a tail wing of an aircraft is connected, securely, to a boom360of an aircraft by a locking mechanism or apparatus such as tail lock310. The tail lock310can include a first connector to attach the boom360, a second connector to attach the wing350, and an end coupling cap to secure the first connector with the second connector.

FIG.4A-4Billustrates example embodiments of a drone. The drone depicted inFIGS.4A-4B, such as drone400, is configured with a pair of booms and a tail. In this example, the drone400can include a fuselage, a wing450that spans across the fuselage perpendicular to a length of the fuselage. Securely suspended beneath the wing450are a pair of booms460. A tail, tail wing, or an additional rear wing of the drone is connected to each of the booms460of the drone. In this embodiment, each boom includes a pair of VTOL propellers. One boom460is configured to physically connect to a first side of the wing450and the second boom460is configured to physically connect to a second side of the wing450. The booms460are also connected to each other through a tail wing at each of the rear portions of the booms460. In this embodiment, the fuselage, wing450, booms460, and tail wing can be modular such that each component can be swapped out for a different unit of the same component. In one example, the tail wing can be attached to the drone at the booms of the drone with a locking apparatus. The locking apparatus can be configured to securely attach the tail wing to the boom and configured to be removed from the boom with a quick release mechanism. When fully assembled, as illustrated inFIGS.4A-B, the drone400can include five propellers, four vertically mounted propellers for VTOL and one horizontally mounted propeller for long range flight.

While the disclosure has been particularly shown and described with reference to specific examples thereof, it should be understood that changes in the form and details of the disclosed examples may be made without departing from the scope of the invention. Although various advantages, aspects, and objects of the present disclosure have been discussed herein with reference to various examples, it will be understood that the scope of the disclosure should not be limited by reference to such advantages, aspects, and objects. Rather, the scope of the disclosure should be determined with reference to the claims.