Unmanned aerial vehicle (UAV) launch systems and methods

An unmanned aerial vehicle (UAV) launch system includes a launch container including a housing defining an internal chamber. A UAV includes a main body defining an inflatable envelope. The UAV is configured to be contained within the internal chamber. The main body is in a deflated state when the UAV is contained within the internal chamber. A reactant is configured to react with water to produce a lifting gas. The inflatable envelope is configured to be inflated by the lifting gas in response to the reactant reacting with the water to deploy the UAV from the launch container.

FIELD OF THE DISCLOSURE

Embodiments of the present disclosure generally relate to systems and methods for launching unmanned aerial vehicles (UAVs).

BACKGROUND OF THE DISCLOSURE

Unmanned aerial vehicles (UAVs), such as drones, are used in a wide variety of applications. For example, in military applications, drones may be deployed to monitor various locations, deliver ordnance on a target, and/or the like. Drones may be deployed from various platforms, such as on land or sea. For example, a drone may be deployed from a base on land, or from a deck of a ship on a body of water.

Typically, a drone includes one or more propulsion systems, such as one or more motors having propeller blades attached thereto. Each propulsion system extends outwardly from a main housing of the drone. As such, a drone may define an outer axial cross-section that includes the main housing and one or more propulsion systems extending from the main body.

Due to their size, however, drones may occupy relatively large amounts of space within a confined area. For example, fuselage sections of drones occupy space. The size, shape, and somewhat delicate nature (such as propellers) of drones often make assembly processes and transport (for example, shipping) between locations awkward and time-consuming.

SUMMARY OF THE DISCLOSURE

Needs exist for efficient systems and methods of storing and deploying UAVs, such as drones.

With those needs in mind, certain embodiments of the present disclosure provide an unmanned aerial vehicle (UAV) launch system that includes a launch container including a housing defining an internal chamber. A UAV includes a main body defining an inflatable envelope. The UAV is configured to be contained within the internal chamber. The main body is in a deflated state when the UAV is contained within the internal chamber. A reactant is configured to react with water to produce a lifting gas. The inflatable envelope is configured to be inflated by the lifting gas in response to the reactant reacting with the water to deploy the UAV from the launch container.

In at least one embodiment, the lifting gas includes hydrogen. The reactant may include sodium borohydride and boric oxide. The reactant may be contained within a reactant container. The reactant container may be within the internal chamber of the launch container. The UAV launch system may also include a water inlet port that is configured to channel the water to the reactant.

The weight of the reactant may be between 50 percent and 100 percent of the weight of the UAV. A volume ratio between the UAV and the reactant within the internal chamber of the launch container may be 9:1.

In at least one embodiment, the launch container further includes a cover moveably coupled to the housing. The cover is moveable between an open position and a closed position. Inflation of the inflatable envelope causes the cover to move from the closed position to the open position. A portion of the UAV may form the cover.

The UAV may include an inflation inlet port in fluid communication with the inflatable envelope. In at least one embodiment, the reactant is contained within a reactant container that is in fluid communication with the inflation inlet port through a detachable coupling. The main body detaches from the detachable coupling in response to the UAV inflating into an inflated state.

The UAV may include a propulsion system, and/or a payload. The payload may include a control unit, one or more batteries, a communication device, an imaging system, a navigation system, ordnance, and/or the like.

The UAV launch system may also include one or more pontoons coupled to the launch container. A container of helium may be in fluid communication with the pontoon(s). The pontoons may be configured to be inflated by the helium.

Certain embodiments of the present disclosure provide an unmanned aerial vehicle (UAV) launch method that includes providing a launch container including a housing defining an internal chamber, securing a UAV including a main body defining an inflatable envelope within the internal chamber (wherein the securing includes providing the main body in a deflated state), exposing a reactant to water to cause a reaction that produces a lifting gas, inflating the inflatable envelope with the lifting gas due to the exposing, and deploying the UAV from the launch container due to the inflating. The UAV launch method may also include channeling the water to the reactant via a water inlet port.

DETAILED DESCRIPTION OF THE DISCLOSURE

Certain embodiments of the present disclosure provide UAV launch systems and methods that include a launch container including compact reactant chemicals that react with water, such as salt water, to produce a lifting gas (such as hydrogen) to inflate a main body of a UAV. When the main body is inflated, the UAV is a lighter-than-air vehicle that ascends into the air, such an airship or dirigible.

In at least one embodiment, the UAV is configured to ascend from the launch container and provide persistent, airborne over-the-horizon communication capability. The UAV launch system, including the launch container and the UAV, is configured to be moved into a body of water, such as from watercraft (such as a submarine or boat), aircraft (such as an airplane or helicopter), a land-based vehicle or structure (such as an ejection gun secured to a vehicle or fixed on land), or even dropped or thrown into the body of water by an individual.

The UAV is in a stowed, uninflated state within the launch container until released into a body of water. The UAV launch system includes a reactant container that contains reactant chemicals. When the reactant chemicals are combined with water (such as salt water), the ensuring reaction produces a lifting gas, such as hydrogen, that inflates the main body of the UAV, which inflates and deploys from the launch container.

The UAV may include a payload having a wide range of components, depending on a particular mission. For example, the payload may include communication devices (such as antennas, transceiver, radios, or the like) for over-the-horizon communications, hydrocarbon sensors, a magnetic anomaly detector (MAD), underwater acoustic sensors and modems, a satellite modem, electro-optical sensors, an imaging system, a navigation sub-system, ordnance, and/or the like.

Certain embodiments of the present disclosure provide a UAV launch system that includes a reactant (such as a chemical compound), a UAV including a main body in a stowed, uninflated state, and a launch container that stores the reactant and the UAV in the stowed, uninflated state. In response to the launch container contacting water (such as salt water), the reactant interacts with the water to produce a lifting gas (such as hydrogen) that inflates the UAV. As the UAV inflates, the UAV deploys from the launch container.

Certain embodiments of the present disclosure provide UAV launch systems and methods that provide an extremely long endurance sensor platform and communication relay for anti-submarine warfare (ASW) missions at comparatively low cost, and which may be rapidly deployed. In the deployed, inflated state, the UAV is configured to hover using passive aerostatic lift.

Certain embodiments of the present disclosure provide a UAV launch system that includes a launch container (such as canister), which may include inflatable pontoons for providing buoyancy to the launch container. The inflatable pontoons may be configured to inflate using a small quantity of compressed helium upon contact with a body of water. Optionally, the inflatable pontoons may be inflated by inflation gas that inflates the main body of the UAV. In at least one other embodiment, the launch container itself may be buoyant and not need inflatable pontoons to ascend to and float at a water surface.

A UAV includes a main body having an inflatable envelope that is stowed within the launch container in a stowed, uninflated (or deflated) state. A reaction apparatus including a detachable conduit is coupled to the inflatable envelope. The reaction apparatus contains dry reactant that is configured to produce a lighter-than-air gas that is vented into the inflatable envelope in response to water (such as salt water) contacting the reactant within the reaction apparatus. The detachable conduit is configured to detach from the UAV when the inflatable envelope is fully inflated.

The UAV may be inflated when the launch container is released into a body of seawater. As the UAV inflates to a fully inflated state, the UAV launches from the launch container into an airborne deployed state.

In at least one embodiment, the weight of the reactant contained within the reaction apparatus is between 50 percent and 100 percent of the weight of the UAV.

Additionally, an accelerator may be disposed in the reaction apparatus with the reactant. In at least one embodiment, the accelerator includes boric oxide.

FIG. 1illustrates a simplified schematic diagram of a UAV launch system100, according to an embodiment of the present disclosure. The UAV launch system100includes a launch container102(such as a canister) including an outer housing104that defines an internal chamber106and a cover108that closes the internal chamber106in a closed position, and exposes the internal chamber106in an open position. The launch container102may be tubular, for example. Alternatively, the launch container102may be formed in various other shapes or sizes, such as a rectangular box, sleeve, or the like. As described herein, inflation of a main body112of a UAV110may cause the cover108to move from the closed position to the open position. As a non-limiting example, the launch container102may be a cylindrical container having a diameter between 5-10 inches, and a length of 2-10 feet.

A pivot member, such as a hinge, may be configured to allow the cover108to be pivoted between closed and open positions. In at least one other embodiment, the launch container102may not include a pivot member. Instead, the cover108may be removably secured to the housing104such as through a press fit, an interference fit, and/or the like. The cover108may be configured to separate from the housing104upon exertion of a defined force, such as that exerted by an inflating or inflated UAV110. In at least one embodiment, a portion of the UAV110may form the cover108. For example, a nose of the UAV110may form the cover. In at least one other embodiment, the launch container102may not include the cover108. Instead, the launch container102may include an open end. In at least one other embodiment, instead of a cover, the launch container102may include a thin membrane (such as formed of plastic, cardboard, an elastomeric material, and/or the like) that may be punctured by an inflating or inflated UAV110.

The launch container102contains an unmanned aerial vehicle (UAV) (or drone)110in a stowed, uninflated (or deflated) state within the internal chamber106. The UAV110includes a main body112defining an inflatable envelope114in fluid communication with an inflation inlet port116. The inflatable envelope114is configured to be inflated with lighter-than-air gas (such as hydrogen) such that the UAV110rises within air. As such, the UAV110may be a dirigible or airship.

The UAV110may also include a propulsion system118. In at least one embodiment, the propulsion system118includes one or more rotors, propellers, or the like coupled to one or more motors, engines, or the like. Optionally, the UAV110may not include a propulsion system118.

In at least one embodiment, the UAV110includes a payload120. The payload120includes one or more components configured for a mission of the UAV110.

FIG. 2illustrates a simplified schematic diagram of the payload120, according to an embodiment of the present disclosure. Referring toFIGS. 1 and 2, the payload120may include a control unit122that is configured to control operation of the UAV110. The control unit122is operatively coupled to a communication device124, such through one or more wired or wireless connections. The control unit122may be configured to control operation of the communication device124. The communication device124may be one or more antennas, one or more radios, one or more transceivers, and/or the like. Optionally, the payload120may not include the control unit122and/or the communication device124.

One or more batteries123(such as lithium ion batteries) may provide a power source for the UAV110. The batter(ies)123may be rechargeable. For example, the batter(ies)123may be solar cells that are recharged through solar energy. Optionally, the batter(ies)123may be recharged through thermal energy or wind energy.

The payload120may include an imaging system126, which may be in communication with the control unit122through one or more wired or wireless connections. The control unit122may be configured to control operation of the imaging system126. The imaging system126may include one or more cameras, thermal imaging devices, infrared imaging devices, ultrasonic imaging devices, and/or the like. Optionally, the payload120may not include the imaging system126.

The payload120may include a navigation system128, which may be in communication with the control unit122through one or more wired or wireless connections. The control unit122may be configured to control operation of the navigation system128. The navigation system128may be a global positioning system (GPS), for example. Optionally, the payload120may not include the navigation system126.

The payload120may include ordnance130. A deployment mechanism132may be operatively coupled to the ordnance130. The control unit122may be in communication with the deployment mechanism132, which is configured to deploy the ordnance130from the UAV110, such as through one or more wired or wireless connections. Optionally, the payload120may not include the ordnance130and the deployment mechanism132.

The payload120may include more or less components than shown, depending on a particular mission of the UAV110. For example, the payload120may include hydrocarbon sensors, a magnetic anomaly detector (MAD), underwater acoustic sensors and modems, a satellite modem, electro-optical sensors, and/or the like.

As described herein, the control unit122may be used to control operation of one or more components of the UAV110. As used herein, the term “control unit,” “unit,” “central processing unit,” “CPU,” “computer,” or the like may include any processor-based or microprocessor-based system including systems using microcontrollers, reduced instruction set computers (RISC), application specific integrated circuits (ASICs), logic circuits, and any other circuit or processor including hardware, software, or a combination thereof capable of executing the functions described herein. Such are exemplary only, and are thus not intended to limit in any way the definition and/or meaning of such terms. For example, the control unit122may be or include one or more processors that are configured to control operation of the component(s) of the UAV110.

The control unit122is configured to execute a set of instructions that are stored in one or more storage elements (such as one or more memories), in order to process data. For example, the control unit122may include or be coupled to one or more memories. The storage elements may also store data or other information as desired or needed. The storage elements may be in the form of an information source or a physical memory element within a processing machine.

The diagrams of embodiments herein may illustrate one or more control or processing units, such as the control unit122. It is to be understood that the processing or control units may represent circuits, circuitry, or portions thereof that may be implemented as hardware with associated instructions (e.g., software stored on a tangible and non-transitory computer readable storage medium, such as a computer hard drive, ROM, RAM, or the like) that perform the operations described herein. The hardware may include state machine circuitry hardwired to perform the functions described herein. Optionally, the hardware may include electronic circuits that include and/or are connected to one or more logic-based devices, such as microprocessors, processors, controllers, or the like. Optionally, the control unit122may represent processing circuitry such as one or more of a field programmable gate array (FPGA), application specific integrated circuit (ASIC), microprocessor(s), a quantum computing device, and/or the like. The circuits in various embodiments may be configured to execute one or more algorithms to perform functions described herein. The one or more algorithms may include aspects of embodiments disclosed herein, whether or not expressly identified in a flowchart or a method.

Referring again toFIG. 1, the launch container102also includes a reactant container140in fluid communication with a water inlet port142. The reactant container140contains dry reactant144, such as a compound of chemicals that are configured to produce a lighter-than-air gas (such as hydrogen) when in contact with water (such as salt water). The reactant144may be or include one or more chemicals that react with water (such as seawater) to produce an inflation gas, such as hydrogen. For example, the reactant144may be or include sodium borohydride and an accelerator, such as boric oxide.

The reactant container140is in communication with the inflation inlet port116of the UAV110through a detachable coupling146. The water inlet port142may be an opening formed in the housing104of the launch container102that is in fluid communication with the reactant container140. Optionally, the water inlet port142may be a conduit extending out of the launch container102.

As shown, the reactant container140and the water inlet port142may be at least partially within the internal chamber106. Optionally, the reactant container140and the water inlet port142may be disposed on an outside of the housing104. In at least one other embodiment, the reactant container140may be part of the internal chamber106. For example, the reactant144may be disposed within the internal chamber106, instead of within a separate and distinct container within the internal chamber106or otherwise secured to the housing104.

It is to be understood that the launch container102, the UAV110, the reactant container140, the water inlet port142and other components shown inFIGS. 1 and 2are not drawn to scale.

In operation, in order to deploy the UAV110from the launch container102, the launch container102is positioned within a body of water, such as seawater. For example, the launch container102may be launched into the body of water from watercraft (such as a submarine or ship), dropped or launched from an aircraft (such as an airplane or helicopter), dropped or launched from a land-based structure, or even dropped or thrown in the body of the water by an individual.

The launch container102may be naturally buoyant and float to a surface of the water. Optionally, the launch container102may include one or more buoyant structures (such as inflatable pontoons) which ensure that the launch container102floats at a surface of the body water. In at least one embodiment, the inflatable pontoons may be operatively coupled to compressed helium that releases the helium into the pontoons (thereby inflating the pontoons) upon impact with the body of water.

When the launch container102is in the body of water, water passes into the reactant container140via the water inlet port142. As the water contacts the reactant144within the reactant container140, the reaction therebetween produces a lighter-than-air inflation gas (such as hydrogen). The inflation gas passes into the inflation inlet port116of the UAV110via the detachable coupling146. The inflation gas passes into the inflatable envelope114of the main body112through the inflation inlet port116. As the inflation gas passes into the inflatable envelope114, the inflation gas inflates the inflatable envelope114of the main body112. As the main body112inflates, the main body112exerts pressure on the cover108, thereby opening the cover and exposing the inflating UAV110within the internal chamber106. With continued inflation, the main body112extends out of the exposed internal chamber106. When completely inflated (that is, in an inflated state), the UAV110detaches from the detachable coupling146and ascends out of the launch container102into the air. The inflated main body112causes the UAV110to be airborne. As such, the UAV110deploys from the launch container102and proceeds on a particular mission.

FIG. 3illustrates a simplified view of the UAV launch system100containing the UAV110in a stowed, deflated state, according to an embodiment of the present disclosure. As shown, the main body112of the UAV110is deflated and contained within the internal chamber106of the launch container102with the cover108closing the internal chamber106. The main body112is connected to the reactant container140by the detachable coupling146. The water inlet port142is in fluid communication with an internal chamber of the reactant container140, and includes an opening143that allows water to pass therein.

FIG. 4illustrates a simplified view of the UAV110inflating and deploying from the launch container102of the UAV launch system100, according to an embodiment of the present disclosure. As shown, the launch container102floats in a body of water200(such as sea water). A portion201of the water200enters the reactant container140via the water inlet port142. The water200reacts with the reactant144within the reactant container140to generate the inflation gas, which passes into the main body112through the coupling146connected to the inflation inlet port116, thereby inflating the main body112into an inflated state. As the main body112inflates, a top portion115is urged into an underside109of the cover108. With increased inflation, the force exerted by the main body112into the cover108causes the cover108to open, thereby allowing the main body112to continue to inflate and expand outside of the internal chamber106. In at least one embodiment, the UAV launch system100may be configured to float length-wise on the water200.

FIG. 5illustrates a simplified view of the UAV110deployed out of the launch container102of the UAV launch system100, according to an embodiment of the present disclosure. Upon fully inflating into the inflated state, the main body112detaches from the detachable coupling146, thereby allowing the UAV110to ascend into the air away from the launch container102. The inflation inlet port116may include a valve (not shown) that closes as the main body112detaches from the detachable coupling146, thereby ensuring that the inflation gas remains within the main body112so that the UAV110remains airborne.

FIG. 6illustrates a simplified view of the UAV launch system100containing the UAV110in a stowed, deflated state, according to an embodiment of the present disclosure. In this embodiment, a nose117of the main body112of the UAV110provides a cover for the launch container102.

FIG. 7illustrates a simplified view of the launch container102, according to an embodiment of the present disclosure. In this embodiment, one or more pontoons220are secured to the launch container102. The pontoons220provide buoyancy to the launch container102. The pontoons220may be inflatable. In at least one embodiment, a container222of compressed inflation gas (such as helium) is in fluid communication with the pontoons220. Upon impact, a valve of the container222may break, and release the compressed inflation gas into the pontoons220.

FIG. 8illustrates a simplified view of the launch container102, according to an embodiment of the present disclosure. In this embodiment, the reactant container140and the water inlet port142may be outside of the housing104.

FIG. 9illustrates a simplified view of the UAV launch system100, according to an embodiment of the present disclosure. In this embodiment, the reactant144is contained within the internal chamber106of the launch container102. The reactant144may or may not be within a separate and distinct container within the internal chamber106.

FIG. 10illustrates a flow chart of a UAV launch method, according to an embodiment of the present disclosure. Referring toFIGS. 1-10, the method begins at300, at which the UAV110in a stowed, deflated state is secured within the internal chamber106of the launch container102.

At302, reactant144of the launch container102(for example, contained within or secured to an outer portion of the launch container102) is exposed to water (such as salt water) to cause a reaction. At304, an inflation gas is produced from the reaction of the water contacting the reactant.

At306, the main body112of the UAV110is inflated with the inflation gas. At308, the UAV110is deployed in an inflated, deployed state from the launch container102.

As described herein, embodiments of the present disclosure provide an autonomous, high-endurance, launch container-encapsulated UAV110that may be configured to provide an airborne, over-the-horizon communication capability and persistent sensor platform. The UAV launch system100allows a relatively large airship to be encapsulated in the compact launch container102, due to the UAV110receiving lifting gas from the reactant144and seawater.

Unlike fixed wing UAVs, the UAV110may fly very slowly and also hover, relying on static rather than aerodynamic lift, which requires little power consumption. The batteries123may be recharged from solar, thermal and wind energy. The UAV110may remain on station for weeks, unlike canister launched fixed-wing UAVs, whose endurance is but a few hours. The endurance of the UAV110may be extended dramatically by alighting on the water surface to replenish its supply of lifting gas either through electrolysis or by retaining a small supply of hydrogen-producing reactant on board.

The UAV launch system100allows a relatively large UAV110(such as an inflatable airship) to be encapsulated in the comparatively compact launch container102, due to the UAV110receiving the inflation gas from the reaction of the reactant144with the water200. As such, inflation gas need not be stored in the UAV launch system100, thereby decreasing weight, and increasing internal space within the launch container102(due to there not being a separate container of inflation gas). The reactant144may reside within a small portion of the internal chamber106of the launch container102. In general, producing the lifting gas from the reaction of the reactant144with the water200(such as seawater) eliminates the need to store the gas in compressed form, allowing a relatively large UAV110to fit within the launch container102.

In at least one embodiment, the main body112of the UAV110may inflate in response to the launch container102floating on a surface of water. For example, the water inlet port142may be coupled to an inlet valve that opens when the launch container102is at or proximate to a surface of the water. The inlet valve may be coupled to a timer, accelerometer, altimeter, or the like that sends an opening signal to the inlet valve in response to a predetermined condition (such as a predetermined time, altitude in relation to sea level, and/or the like).

In at least one other embodiment, the main body112may begin to inflate as the UAV launch system100is deployed underneath the water, such as from a submarine. For example, the water inlet port142may provide water ingress into the reactant container140underneath an upper surface of the water. As such, the main body112may begin to inflate prior to the launch container102floating at the top surface of the water. The inflation of the main body112below the top surface of the water may increase the buoyancy of the launch container102, and thereby decrease a time for the UAV launch system100to reach the top surface of the water.

In at least one embodiment, the launch container102may include a deployable parachute. For example, when launched from an aircraft, the launch container102may deploy the parachute to slow the rate of descent into a body of water.

In at least one embodiment, the lifting gas generated by the reaction of the reactant144with the water is hydrogen. In at least one other embodiment, the lifting gas may be helium.

Utilizing chemical reactions to generate the lifting gas allows the UAV110to not only refrain from carrying its own supply of lifting gas in a compressed compartment (which typically requires extremely high pressures to store sufficient quantities of lifting gas), but to also replenish its supply of lifting gas during its mission. In general, the reactant144may be in dry granular form and is safe to handle. Products of the reaction other than hydrogen may be discarded (or used as ballast). The reaction container140detaches from the UAV110to save weight, though a small reserve of reactant144may be maintained to replenish the hydrogen lifting gas in lieu of using electrolysis.

Seawater includes at least one reactant, thereby greatly reducing the weight of reactant144that is present in the UAV launch system100. An exemplary reaction between the reactant144and seawater is that of Sodium Borohydride and water:

Na⁢⁢BH4+2⁢H2⁢0⁢(l)⁢→Accelerator⁢⁢(B2⁢O3)⁢NaBO2+4⁢H2⁡(g)
To expedite generation of the lifting gas, the reaction may proceed in the presence of an accelerator, such as boric oxide, B2O3.

As one non-limiting example, to lift a UAV110variant weighing 14 pounds (lbs.) requires 234.644 moles of hydrogen lifting gas. As such, 58.661 moles of sodium borohydride (NaBH4) and 29.3305 moles of boric oxide are used. Liquid water H2O is ingested into the reactant container144from the ocean surface.

A total of approximately 4.26 kilograms (kg), or 9.3917 lbs., of sodium borohydride and boric oxide are carried as the reactant144. This requires only about 10 percent of the volume of the internal chamber106of the launch container102. As such, 90 percent of the volume of the internal chamber106may be used to carry other components, such as the UAV110. In this manner, use of the reactant144and the water200to generate the lifting gas allows for an inflatable UAV110of increased size. That is, the volume ratio between the UAV110and components within the launch container102for producing the lifting gas (for example, the reactant container140and/or the reactant144) may be 9:1. In at least one embodiment, the weight of the reactant144may be between 50 percent and 100 percent of the weight of the UAV110.

The propulsion system118may include one or more propellers that also serve as wind turbines to provide power. For example, should there be insufficient battery or solar power, the UAV110may switch to power-conservation mode and use the propellers to charge the batteries123. The propellers may be used when the UAV110has touched down on the water200. When solar power is unavailable, such as at night, and wind conditions allow, the propellers may be used as turbines to supply power.

The propellers may be driven by electric motors directly, so as to eliminate gearing (and the associated weight). The propellers and electric motors may be situated above pontoons to avoid contact with salt water. The propellers may be articulated, so that thrust may be directed as needed including upward and downward directions.

The UAV110may include control surfaces modified to deploy from the launch container102. The control surfaces may include fold-out rudders, stabilizers and an aerodynamic envelope. The shape of the envelope may be maintained by ballonets, as is conventional for non-rigid airships.

Additional control mechanisms may include vents within the envelope for venting lifting gas when, for example, the pressure height—the altitude at which the envelope is fully inflated and ballonets are empty—would be exceeded. Additionally, a ballast mechanism which allows the UAV110to eject ballast so as to gain height quickly may be used. Ballast may take the form of seawater and be replenished when the vehicle rests on the surface of the water. Expendables may also provide ballast and be dropped, as necessary.

As described herein, embodiments of the present disclosure provide efficient systems and methods of storing and deploying UAVs.