Patent Description:
Some aircraft, such as unmanned aerial vehicles (UAVs), are deployed with a launcher. The launcher accelerates the UAV to a relatively high speed within a short distance. This eliminates the need for a runway to deploy the UAV.

The document <CIT> states, in accordance with its abstract, launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods. A representative method for lofting a payload includes directing a lifting device upward, releasing a parachute from the lifting device, with the parachute carrying a pulley and having a flexible line passing around the pulley. The flexible line is connected between a tension device (e.g., a winch) and the payload. The method further includes activating the tension device to reel in the flexible line and accelerate the payload upwardly.

The document <CIT> states, in accordance with its abstract, that load deployment device for deploying an aerial load comprises a carriage constrained to move along a track and load engagement arms carried by the carriage and movable at a deployment location on the track in a direction transverse to the direction of movement of the carriage from engaged positions in which they engage and support the load to retracted positions in which they are clear of the load.

The document <CIT> states, in accordance with its abstract, that a launching device of an airplane is provided to conveniently launch the airplane without runway by installing a balloon and a locking/separating device. A base plate is fixed in a ground vehicle. A crank device connects with a connecting plate in front of the base plate through a fourfold lever crank on all side. A locking device fixes/releases a hook pin of an airplane by installing under a settling saddle. Thereby, the airplane is safely launched by the crank device and the locking device through the movement of the ground vehicle.

The document <CIT> states, in accordance with its abstract, methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch axis. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff.

The document <CIT> states, in accordance with its abstract, that a fixture is provided for securing an annular drone module to a test stand. The fixture includes a rear outside annulus, a front inside annulus, a plurality of tabs, and a plurality of flanges. The rear outside annulus extend radially to an outer rim and longitudinally from an aft surface and a lip surface. The front inside annulus extends radially to a mezzanine rim and longitudinally from the lip surface to a fore surface. The tabs extending radially from the mezzanine rim on the front inside annulus. The plurality of flanges extending from the outer rim on the rear outside annulus. The drone module is disposed facing the lip surface between the tabs and the mezzanine rim by first mechanical fasteners, and the flanges mount to the test stand by second mechanical fasteners, such as screws. The fixture can be a unitary construction and be composed of thermoset plastic.

The document <CIT> states, in accordance with its abstract, that methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

According to the present disclosure, a system and a method as defined in the independent claims <NUM> and <NUM> are provided. Further embodiments of the claimed invention are defined in the dependent claims. Although the claimed invention is only defined by the claims, the below embodiments, examples, and aspects are present for aiding in understanding the background and advantages of the claimed invention.

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.

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.

A fixed wing aircraft, such as a fixed wing unmanned aerial vehicle (UAV) (e.g., a drone), is typically deployed from a runway or airstrip, similar to a commercial aircraft. However, this method of deploying a fixed wing UAV requires a relatively large amount of space to accommodate a runway. In other words, a relatively flat and open space is needed to launch the UAV. In many instances, such as in reconnaissance missions, runways are not readily available. Further, launching a UAV from an airstrip may result in the UAV and/or a remote operation station being exposed.

Some examples systems (e.g., an unmanned aerial system (UAS)) include a launcher to deploy a UAV. The launcher includes a carriage that is moveable along a track, which is relatively short compared to a runway. The UAV is set on or attached to the carriage, and the carriage accelerates rapidly along the track to propel the UAV into the air. Known launcher manufacturers provide specific UAVs with integrated structures or points for interfacing with their carriages. Therefore, only the manufacturer's UAVs can be launched from the launcher. However, other UAV manufacturers or UAV operators desire to utilize various launchers with their UAVs.

Disclosed herein are example adapter assemblies (which may also be referred to as adapters, brackets, or interfaces) that be used on various aircraft, such as a UAVs, to enable the UAVs to be deployed with a launcher. The example adapter assemblies can be removeably coupled to a UAV and interface with the specific structures on the carriage of the launcher. This enables UAVs that are not specifically designed or built for a specific launcher to be launched or deployed on the launcher. Further, various adapter assemblies can be constructed so that the same UAV can be launched with various types or styles of launchers. Further, the example adapter assemblies are removeably coupled to the UAV, such that the adapter assembly can be removed after use. This reduces the footprint and allows flexibility for on-site selection of a launcher and adapter.

<FIG> show an example system <NUM> (e.g., a UAS) that may be used to deploy an aircraft <NUM>. In this example, the aircraft <NUM> is an unmanned aerial vehicle (UAV), referred to herein as the UAV <NUM>. However, in other examples, the aircraft <NUM> may be implemented as a manned aircraft. In the illustrated example, the UAV <NUM> is a fixed-wing aircraft. In other examples, the UAV <NUM> can be implemented as another type of aircraft.

The system <NUM> includes a launcher <NUM> to launch or deploy the UAV <NUM>. In the illustrated example, the launcher <NUM> includes a track <NUM> and a carriage <NUM> that is moveable along the track <NUM>. In some examples, the launcher <NUM> is pneumatically powered by a control module <NUM>. When activated, the control module <NUM> supplies high pressure fluid (e.g., to a piston inside of the track <NUM>) to rapidly accelerate the carriage <NUM> along the track <NUM>. In the illustrated example, the carriage includes a first set of arms 112a, 112b and a second set of arms 114a, 114b (labeled in <FIG>). In the illustrated example, the UAV <NUM> includes an example adapter assembly <NUM> that may be used to mount or interface the UAV <NUM> with the carriage <NUM>. In the illustrated example, the adapter assembly <NUM> is coupled to a fuselage <NUM> of the UAV <NUM>. However, in other examples, the adapter assembly <NUM> can be coupled to another part of the UAV <NUM>.

As an example use application, the UAV <NUM> is set on the carriage <NUM>. For example, as shown in <FIG>, the UAV <NUM> may be set downward on the arms 112a, 112b, 114a, 114b of the carriage <NUM> to the position shown in <FIG>. Then, as shown in <FIG>, the control module <NUM> can be activated to drive the carriage <NUM> along the track <NUM> to launch the UAV <NUM>. When the carriage <NUM> reaches the end of the track <NUM>, the carriage <NUM> stops, but the UAV <NUM> continues to move forward and releases from the carriage <NUM>. In some examples, when the carriage <NUM> reaches the end of the track <NUM>, the arms 112a, 112b, 114a, 114b rotate forward to help propel or launch the UAV <NUM> into the air. The launcher <NUM> provides sufficient acceleration to launch the UAV <NUM> into the air. Then, one or more thrust generators (e.g., propellers, turbo-jet engines, etc.) on the UAV <NUM> can be activated to continue to fly the UAV <NUM>. Launchers are advantageous because they eliminate the need for a long runway.

<FIG> is a side view of the first set of arms 112a, 112b. In the illustrated example, the first arm 112a has a first interface point <NUM> and the second arm 112b has a second interface point <NUM>. The first and second interface points <NUM>, <NUM> define where the UAV <NUM> engages or otherwise interfaces with the carriage <NUM> (<FIG>). The first and second interface points <NUM>, <NUM> are notches formed in the ends of the first set of arms 112a, 112b. In other examples not covered by the scope of the claims, the first and/or second interface points <NUM>, <NUM> can have different shapes and/or structures. The example adapter assembly <NUM> (<FIG>) has corresponding features that interface with the first and second interface points <NUM>, <NUM>. The second set of arms 114a, 114b (<FIG>) are substantially the same as the first set of arms 112a, 112b. Thus, any of the example structural or functional features dislcosed in connection with the first set of arms 112a, 112b can likewise apply to the second set of arms 114a, 114b.

<FIG> is an exploded view of an example adapter assembly <NUM>. The adapter assembly <NUM> includes a first adapter <NUM> that is to be removeably coupled to a first side (e.g., a left side) of the fuselage <NUM> (<FIG>) of the UAV <NUM> (<FIG>). The first adapter <NUM> provides an interface between the UAV <NUM> and the carriage <NUM>, which is the first set of arms 112a, 112b of the carriage <NUM> shown in <FIG>). In the illustrated example, the first adapter <NUM> includes a first plate <NUM> and first and second posts 304a, 304b extending from the first plate <NUM>. The first and second posts 304a, 304b may also be referred to as first posts or a first set of posts. The first and second posts 304a, 304b are to interface with the carriage <NUM> of the launcher <NUM>. For example, the first and second posts 304a, 304b are spaced apart according to (e.g., to equal) the spacing between the first set of arms 112a, 112b. Further, the first and second posts 304a, 304b are shaped to match the first and second interface points <NUM>, <NUM> (<FIG>) with notches respectively, on the first set of arms 112a, 112b (<FIG>). For example, the first post 304a has a shape corresponding to (e.g., complementary to) the first notch of the first arm 112a and the second post 304b has a shape corresponding to (e.g., complementary to) the second notch of the second arm 112b. In other examples, the first and second posts 304a, 304b may have a smaller shape and/or size than the first and second interface points <NUM>, <NUM>. When the UAV <NUM> (<FIG>) is set on the carriage <NUM> (<FIG>), the first and second posts 304a, 304b sit or rest in the first and second interface points <NUM>, <NUM> with notches respectively, of the first set of arms 112a, 112b to support the UAV <NUM>.

In some examples, the first and second posts 304a, 304b have the same cross-sectional shape and size. However, in other examples, such as shown in <FIG>, the first and second posts 304a, 304b may be shaped and/or sized differently. For example, the first and second posts 304a, 304b can have different cross-sectional shapes and sizes. The first and second posts 304a, 304b can be constructed longer or shorter depending on the size (e.g., width) of the UAV <NUM> (<FIG>) and the location of the corresponding interface points on the carriage <NUM> (<FIG>). For example, if the fuselage <NUM> (<FIG>) of the UAV <NUM> is relatively small, the first and second posts 304a, 304b can be longer to ensure the first and second posts 304a, 304b extend outward enough to reach the interface points on the carriage <NUM>. While in this example the first adapter <NUM> includes two posts, in other examples, the first adapter <NUM> may include more posts (e.g., three posts) depending on the number of interface points on the corresponding carriage. In some examples, as shown in <FIG>, the first plate <NUM> can include one or more locator holes <NUM>. The locator holes <NUM> can be used to position the first adapter <NUM> in a specific a location on the side of the fuselage <NUM> of the UAV <NUM>.

In the illustrated example, the adapter assembly <NUM> includes a second adapter <NUM> that is substantially the same as the first adapter <NUM> (except the arrangement of the posts is mirrored). Thus, any of the example structural and/or functional features dislcosed in connection with the first adapter <NUM> can likewise apply to the second adapter <NUM>. The second adapter <NUM> includes a second plate <NUM> and third and fourth posts 310a, 310b (the third post 310a is shown in <FIG>) extending from the second plate <NUM>. The third and fourth posts 310a, 310b may be referred to as second posts or a second set of posts. The third and fourth posts 310a, 310b similarly interface with the carriage <NUM> (<FIG>) of the launcher <NUM> (<FIG>). In particular, when the UAV <NUM> is set on the carriage <NUM>, the third and fourth posts 310a, 310b sit or rest in the interface points with notches respectively, of the second set of arms 114a, 114b to support the UAV <NUM>.

In some examples, instead of the posts 304a, 304b, 310a, 310b interfacing (e.g., contacting) the interface points of the carriage <NUM>, the adapter assembly <NUM> includes one or bolts (e.g., shoulder bolts) that can interface with the interface points on the carriage <NUM>. For example, as shown in <FIG>, a bolt <NUM> can be threaded into the end of the first post 304a. When the UAV <NUM> is set on the carriage <NUM>, the bolt <NUM> sits in the first interface point <NUM> (<FIG>) of the first arm 112a. Other bolts can be similarly coupled to the ends of the other posts 304b, 310a, 310b.

In some examples, the first and second adapters <NUM>, <NUM> are constructed of aluminum. In other examples the first and/or second adapters <NUM>, <NUM> are constructed of one or more materials, such as titanium or a composite (e.g., carbon fiber).

In some examples, to removeably couple the first and second adapters <NUM>, <NUM> to the fuselage <NUM> (<FIG>) of the UAV <NUM> (<FIG>), the adapter assembly <NUM> includes a clamp <NUM>. The clamp <NUM> extends around the fuselage <NUM> of the UAV <NUM> to secure (e.g., clamp) the first and second adapters <NUM>, <NUM> to the sides of the fuselage <NUM>. In this example, the clamp <NUM> is a band clamp. In other examples, other types of clamps can be used. Further, in other examples, the first and/or second adapters <NUM>, <NUM> can be removeably coupled to the UAV <NUM> using other techniques (e.g., an elastomeric ring, a zip tie, a threaded fastener (bolts, screws, etc.), an adhesive, a latch, etc.).

In some examples, the adapter assembly <NUM> includes a first spacer <NUM> and a second spacer <NUM> to be disposed around the top and bottom sides of the fuselage <NUM> (<FIG>) to fill any gaps between the clamp <NUM> and the fuselage <NUM> of the UAV <NUM> when tightening the clamp <NUM>. In some examples, the first and second spacers <NUM>, <NUM> are constructed of acrylonitrile butadiene styrene (ABS) plastic. In other examples, the first and/or second spacers <NUM>, <NUM> can be constructed of other materials. In the illustrated example, the first and second spacers <NUM>, <NUM> are scored to improve flexibility.

<FIG> is a front view of the UAV <NUM> showing the adapter assembly <NUM> coupled to the UAV <NUM>. As shown in <FIG>, the first and second posts 304a, 304b of the first adapter <NUM> (<FIG>) extend outward from a first side of the fuselage <NUM>, and the third and fourth posts 310a, 310b of the second adapter <NUM> (<FIG>) extend outward from a second side of the fuselage <NUM>. When the UAV <NUM> is set downward onto the carriage <NUM> (<FIG>), the first and second posts 304a, 304b sit in the interface points with notches in the first set of arms 112a, 112b, respectively, and the third and fourth posts 310a, 310b sit in the interface points with notches in the second set of arms 114a, 114b, respectively. As such, the first and second adapters <NUM>, <NUM> enable the UAV <NUM> to be launched with the launcher <NUM>.

<FIG> is a side view of the UAV <NUM> showing the adapter assembly <NUM> coupled to the UAV <NUM>. As shown in <FIG>, the first adapter <NUM> is coupled to a side of the fuselage <NUM>. The second adapter <NUM> (<FIG>) is similarly coupled to the opposite side of the fuselage <NUM>. In some examples, the first and second adapters <NUM>, <NUM> are in direct contact with the sides of the fuselage <NUM>. In other examples, one or more spacers can be disposed between the first and/or second adapters <NUM>, <NUM> and the sides of the fuselage <NUM>. Spacers can be used to position the first and second adapters <NUM>, <NUM> more outward from the sides of the fuselage <NUM>.

In the illustrated example, the first spacer <NUM> is disposed on a top side of the fuselage <NUM> between the fuselage <NUM> and the clamp <NUM>. Further, the second spacer <NUM> is disposed on a bottom side of the fuselage <NUM> between the fuselage <NUM> and the clamp <NUM>. As disclosed above, the first and second spacers <NUM>, <NUM> fill any gap or space between the clamp <NUM> and the fuselage <NUM>. The clamp <NUM> encircles the fuselage <NUM> and is tightened to clamp the first and second adapters <NUM>, <NUM> to the sides of the fuselage <NUM>, thereby removeably coupling the first and second adapters <NUM>, <NUM> to the fuselage <NUM> for the UAV <NUM>. In some examples, the clamp <NUM> is positioned between the posts of the first and second adapters <NUM>, <NUM>. In other examples, the clamp <NUM> can be positioned outside of the posts (e.g., closer to one end of the first and second adapters <NUM>, <NUM>). In some examples, multiple clamps can be used (e.g., two or three clamps can be used). In some examples, in addition to or as an alternative to the clamp <NUM>, one or more threaded fasteners (e.g., bolts) can be threaded through the first and second adapters <NUM>, <NUM> and into the sides of the fuselage <NUM> to removeably coupled the first and second adapters <NUM>, <NUM> to the UAV <NUM>.

<FIG> is a perspective view of the UAV <NUM> showing the adapter assembly <NUM> coupled to the UAV <NUM>. In this example, bolts <NUM>, <NUM> are shown on the ends of the first and second posts 304a, 304b. As disclosed above, in some examples, the bolts <NUM>, <NUM> can be used to engage the interface points with notches on the carriage <NUM>. However, in other examples, the posts 304a, 304b, 310a, 310b engage or otherwise interface with the interface points on the carriage <NUM>.

In some examples, various adapter assemblies can be designed for different launchers that have different interface points. Depending on the type of launcher being used, the corresponding adapter assembly can be coupled to the UAV <NUM>. For example, a first type of adapter assembly can be removeably coupled to the UAV <NUM> and used when launching the UAV <NUM> with a first type of launcher. Then, the first type of adapter assembly can be removed and a second type of adapter assembly can be removebaly coupled to the UAV <NUM> and used when launching the UAV <NUM> with a second type of launcher. As a result, the UAV <NUM> can be used with any type or style of launcher. Further, an adapter assembly can be removed from the UAV <NUM> and coupled to another UAV <NUM>. Thus, the adapter assemblies disclosed herein are easily transferable.

Also, because the adapter assembly <NUM> is not permanently coupled to the UAV <NUM>, the adapter assembly <NUM> can be removed when not being used with the launcher <NUM>. For example, if the UAV <NUM> is being deployed via a regular runway, the adapter assembly <NUM> can be removed, which reduces weight and drag of the UAV <NUM>.

<FIG> is an example method <NUM> of using an example adapter assembly when launching an aircraft from a launcher. The example method is disclosed in connection with the example UAV <NUM>, the example launcher <NUM>, and the example adapter assembly <NUM> of the example system <NUM>. However, it is understood the example method <NUM> could be implemented in connection with other types of aircraft, launchers, and/or adapter assemblies.

An adapter assembly, such as the adapter assembly <NUM>, can be selected on site or off site for compatibility with a particular launcher. At block <NUM>, the first adapter <NUM> is removeably coupled to a first side of the fuselage <NUM> of the UAV <NUM>. At block <NUM>, the second adapter <NUM> is removeably coupled to a second side of the fuselage <NUM> of the UAV <NUM>. In some examples, the first and second adapters <NUM>, <NUM> are removeably coupled to the fuselage <NUM> of the UAV <NUM> using the clamp <NUM>. For example, the first adapter <NUM> can be held (e.g., via a user or a temporary fixing mechanism) on the first side of the fuselage <NUM>, and the second adapter <NUM> can be held on the second side of the fuselage <NUM>. Then, the clamp <NUM> is placed around the fuselage <NUM> and the first and second adapters <NUM>, <NUM>. The clamp <NUM> is tightened, thereby coupling the first and second adapters <NUM>, <NUM> to the UAV <NUM>. In some examples, prior to tightening the clamp <NUM>, the first and second spacers <NUM>, <NUM> are placed around the top and bottom sides of the fuselage <NUM>.

At block <NUM>, the UAV <NUM> is set on the carriage <NUM> of the launcher <NUM>. For example, the first and second posts 304a, 304b of the first adapter <NUM> are set in the interface points with notches of the first set of arms 112a, 112b, and the third and fourth posts 310a, 310b of the second adapter <NUM> are set in the interface points with notches of the second set of arms 114a, 114b. Thus, the first and second adapters <NUM>, <NUM> enable the UAV <NUM> to interface with the carriage <NUM> and support the UAV <NUM> on the carriage.

At block <NUM>, the launcher <NUM> is activated (e.g., via the control module <NUM>) to launch the UAV <NUM>. After the UAV <NUM> lands and the flight is over, at block <NUM>, the first and second adapters <NUM>, <NUM> can be removed from the UAV <NUM>. For example, the clamp <NUM> can be loosened, and the first and second adapters <NUM>, <NUM> can be taken off of the sides of the fuselage <NUM>. The adapter assembly <NUM> can be used again with the UAV <NUM> or with another UAV. Further, another adapter assembly can be removeably coupled to the UAV <NUM> and used to launch the UAV <NUM> from another type of launcher.

Modifications or changes may be made without departing from the invention, which is defined by the appended claims.

Although certain example apparatus and methods have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all apparatus and methods falling within the scope of the claims of this patent.

Claim 1:
A system for an unmanned aerial vehicle, UAV, (<NUM>) comprising:
a launcher (<NUM>) to deploy the UAV (<NUM>), the launcher (<NUM>) including a moveable carriage (<NUM>); (<NUM>),
an adapter assembly (<NUM>) comprising:
a first adapter (<NUM>) configured to be removeably coupled to a first side of a fuselage (<NUM>) of the UAV (<NUM>), the first adapter (<NUM>) including first and second posts (304a, 304b) to interface with the carriage (<NUM>) of the launcher (<NUM>); and
a second adapter (<NUM>) configured to be removeably coupled to a second side of the fuselage (<NUM>) of the UAV (<NUM>), the second adapter (<NUM>) including third and fourth posts (310a, 310b) to interface with the carriage (<NUM>) of the launcher (<NUM>);
wherein the carriage (<NUM>) has a first set of arms (112a, 112b) with notches (<NUM>, <NUM>) and a second set of arms (114a, 114b) with notches (<NUM>, <NUM>), and wherein the first and second posts (304a, 304b) are configured to be set in the notches of the first set of arms (112a, 112b) and the third and fourth posts (310a, 310b) are configured to be set in the notches of the second set of arms (114a, 114b).