Aircraft with deployable components

Abstract

To provide a telescoping expansible wing system.SOLUTION: A telescoping expansible wing system comprises: a first wing section comprising a hollow interior; a second wing section which is attached to a fuselage of an aircraft and configured to be stowed within an interior of the first wing section so that an external surface of the second wing section is adjacent to an internal surface of the first wing section; and a control surface hinged to an external surface of a trailing edge of the first wing section. The first wing section and the second wing section form a first wing width in a first arrangement comprising the second wing section stowed within an interior of the first wing section, and forms a second wing width in a second arrangement comprising the first wing section displaced at least partially along a length between first and second ends of the second wing section. In an attachment section of the control surface along the external surface of trailing edge of the first wing section, the second wing section as of when stowed in the first arrangement, overlaps at least partially a length of the attachment section.SELECTED DRAWING: Figure 1C

Description

[Technical field]

[0001] Applicant claims the benefit of U.S. Provisional Patent Application No. 62 / 254,098, filed November 11, 2015, the contents of which are incorporated herein by reference.

[0002] The priority claim of U.S. patent application Ser. No. 15 / 092,219, entitled "AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS" having attorney docket number 295EP.001US01 and filed in the name of Area-I, Inc. on April 6, 2016, is hereby incorporated by reference.

[0003] The priority claim of U.S. patent application Ser. No. 15 / 092,237, entitled "AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS" having attorney docket number 295EP.001US02 and filed in the name of Area-I, Inc. on April 6, 2016, is hereby incorporated by reference.

[0004] The priority claim of U.S. patent application Ser. No. 15 / 092,257, entitled "AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS" having attorney docket number 295EP.001US03 and filed in the name of Area-I, Inc. on April 6, 2016, is hereby incorporated by reference.

[0005] Although the concepts and embodiments disclosed herein are disclosed in the referenced applications having different limitations and configurations and described using different examples and terminology, each of the referenced applications is intended to apply to the concepts and embodiments.

[0006] The present disclosure relates generally to unmanned aerial vehicles. [Background technology]

[0007] Unmanned aerial vehicles may be used in multiple applications, including commercial applications including surveillance and photography, military applications, reconnaissance, and tactical missions. In certain circumstances, a compact configuration may be beneficial to enable certain types of missions. For example, a compact configuration reduces space and allows for various deployment options. However, current compact configurations are limited in flight range, endurance, and maximum payload.

[0008] Patent document 1 discloses an unmanned aerial vehicle according to the precharacterized portion of claim 1. [Prior art documents] [Patent documents]

[0009] [Patent Document 1] U.S. Patent No. 6,056,237 Summary of the Invention [Means for solving the problem]

[0010] According to the present invention, an unmanned aerial vehicle (UAVDC) having deployable components is provided as characterized by claim 1. The UAVDC may comprise a fuselage, at least one wing, and at least one stabilizer. In some embodiments, the UAVDC may further comprise a propulsion means and / or a modular payload. The UAVDC may be configured in a number of configurations. For example, in a compact configuration, the UAVDC may comprise at least one wing stored against the fuselage and at least one stabilizer stored against the fuselage. In a deployed configuration, the UAVDC may comprise at least one wing deployed from the fuselage and at least one stabilizer deployed from the fuselage. In an extended configuration, the UAVDC may comprise at least one wing telescopically extended to increase the wingspan of the deployed configuration.

[0011] In various embodiments, a UAVDC may be provided with a telescoping wing system. The telescoping wing system may include a first wing section with a substantially hollow interior and a second wing section configured to be stored within the first wing section. The second wing section may include an actuator configured to drive a belt coupled to an inner surface of the first wing section such that, upon actuation, displacement of an attached segment of the belt causes the first wing section to traverse at least a portion of the length of the second wing section.

[0012] In a first configuration, the first wing portion and the second wing portion may form a first wingspan in a first arrangement with the second wing portion stored within the first wing portion, and in a second configuration, the first wing portion and the second wing portion may form a second wingspan in a second arrangement with the first wing portion displaced along at least a portion of the length of the second wing portion.

[0013] Further, according to embodiments of the present disclosure, a UAVDC may include a fuselage and at least one stabilizer configured to pivot about a first axis and a second axis, and the at least one stabilizer may be configurable in at least a compact configuration in which the at least one stabilizer is stored against the fuselage and a deployed configuration in which the at least one stabilizer is deployed from the fuselage by pivoting about the first axis.

[0014] The UAVDC may further comprise a push rod configured to pivot the at least one stabilizer about a second axis. In some embodiments, the UAVDC may comprise a flexible fairing at a base of the stabilizer configured to allow the stabilizer to pivot about the second axis while maintaining aerodynamic efficiency.

[0015] In yet another embodiment, a UAVDC may include a fuselage with a modular payload section; at least one wing configurable in a first configuration and a second configuration, the first configuration including the at least one wing stowed against the fuselage and the second configuration including the wing deployed for flight at a first deployment angle; a fairing positioned relative to a base of the at least one wing, the fairing being constructed of a flexible material with at least one slit and at least one notch designed to enable the at least one wing to sweep from the first configuration to the second configuration, the fairing being configurable in a first configuration that conforms to the first configuration and a second configuration that conforms to the second configuration; and an actuator coupled to the sweep gearbox configured to initiate the sweep of the at least one wing from the first configuration to the second configuration.

[0016] It should be understood that a wing may be comprised of two left and right wing sections (a first portion and a second portion), as described in more detail below. The two wing sections may be referred to throughout this disclosure as two wings or two wing segments. Thus, in some embodiments, the two wings may be stacked against the fuselage in a first configuration, the stacking configuration comprising an upper wing and a lower wing, the upper wing being vertically offset from the lower wing in the first configuration. In yet another embodiment, when transitioning from the first configuration to the second configuration, the two wings may be configured to telescope to increase the wingspan in the second configuration.

[0017] Embodiments of the present disclosure may further include at least one control surface (e.g., stabilizer) configured to deploy from a first stabilizer configuration stowed close to the fuselage to a second stabilizer configuration deployed for flight at a second deployment angle.

[0018] In some embodiments, deployment of the at least one stabilizer plate can use at least one spring, the at least one spring configured to bias the at least one stabilizer plate from the first stabilizer plate configuration to the second stabilizer plate configuration.

[0019] The UAVDC may further comprise a propulsion mechanism. In some embodiments, the propulsion mechanism may comprise a propeller, the propeller comprising at least one blade configured to fold into a first propeller arrangement and extend in a second propeller arrangement. The fuselage may include at least one groove configured to receive at least one blade of the propeller in the first propeller arrangement, and the propeller may be configured to open into the second propeller arrangement by at least one of a propeller blade spring, an aerodynamic force, or a centripetal force due to rotation of the propeller.

[0020] Both the above summary and the following detailed description provide examples and are explanatory only. Thus, the above summary and the following detailed description should not be considered limiting. Furthermore, features or variations other than those described herein may be provided. For example, embodiments may be directed to combinations and subcombinations of the various features described in the detailed description.

[0021] The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate various embodiments of the present disclosure. The drawings contain various registered trademarks and copyrights owned by the applicant. In addition, the drawings may contain other trademarks owned by third parties and are used for illustrative purposes only. All rights to the various registered trademarks and copyrights shown herein, except as attributable to their respective owners, remain the property of the applicant. The applicant reserves and will retain all rights in the registered trademarks and copyrights contained herein and will only permit reproduction of the materials in connection with reproduction of granted patents and for no other purposes.

[0022] Additionally, the drawings may include text or captions that may describe particular embodiments of the present disclosure. This text is included for illustrative, non-limiting descriptions of the particular embodiments detailed in the present disclosure. [Brief description of the drawings]

[0023] [Figure 1A] FIG. 1 illustrates an unmanned aerial vehicle with deployable components in a first configuration. [Figure 1B] FIG. 2 shows an unmanned aerial vehicle with deployable components in a second configuration. [Figure 1C] FIG. 13 shows an unmanned aerial vehicle with deployable components in a third configuration. [Figure 2A] FIG. 1 is a cross-sectional view of a sweep gearbox coupled to an actuator. [Figure 2B] FIG. 1 shows a sweep gear box. [Figure 2C] FIG. 13 is another view of the sweep gearbox showing the wing sweep direction. [Figure 2D] FIG. 13 is a set of schematics for a sweep gearbox to ensure that the wings have dihedral and incidence angles when deployed and are flat when stowed. [Diagram 3] FIG. 2 is a diagram showing an example of a telescoping wing. [Figure 4A] FIG. 4 is a diagram showing an example of a stabilizer plate in the first embodiment. [Figure 4B] FIG. 11 is a diagram showing an example of a stabilizer plate in the second embodiment. [Figure 4C] FIG. 2 is another view of the stabilizer in the first embodiment. [Figure 4D] FIG. 11 is another view of the stabilizer in the second configuration. [Figure 4E] FIG. 2 illustrates an example of a stabilizer plate at a first pivot angle. [Figure 4F] FIG. 13 illustrates an example of a stabilizer plate at a second pivot angle. [Figure 4G] FIG. 13 illustrates an example of a stabilizer at a third pivot angle. [Diagram 5] FIG. 2 is a diagram showing an example of deployable propeller blades and their deployment directions. [Figure 6A] FIG. 2 illustrates an example of a modular payload. [Figure 6B] FIG. 2 illustrates an example of a modular payload with deployable components in a first configuration. [Figure 6C] FIG. 1 illustrates an example of a modular payload with deployable components in a second configuration. [Figure 6D] FIG. 13 illustrates an example of another modular payload in a compact configuration. [Figure 6E] FIG. 2 illustrates an example of a modular payload in a deployed configuration. [Figure 7] FIG. 2 shows possible positions of the antenna. [Figure 8] FIG. 2 illustrates a propeller and associated components. [Figure 9] FIG. 13 illustrates grooves in the fuselage configured to receive the propeller blades in the folded configuration. [Figure 10A] FIG. 2 shows a propeller blade trapped by a wing. [Figure 10B] FIG. 2 illustrates deployed propeller blades oriented in the mainstream. [Figure 11A] FIG. 2 is a diagram showing a fairing in a first configuration. [Figure 11B] FIG. 13 is a diagram showing the fairing in a second configuration. [Figure 11C] FIG. 1 shows a fairing with magnets. [Figure 12A] FIG. 2 illustrates components for controlling the ailerons. [Figure 12B] FIG. 1 illustrates several configurations of ailerons. [Figure 13] FIG. 1 is a diagram illustrating an example of the internal configuration of a UAVDC. [Figure 14] FIG. 1 illustrates a method of use for an unmanned aerial vehicle with deployable components. [Figure 15] FIG. 1 is a block diagram of a system including a computing device that enables operation of the device. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] As a preliminary matter, those skilled in the art will readily understand that the present disclosure has broad utility and applications. As will be understood, any embodiment can incorporate only one or more of the above-disclosed aspects of the present disclosure, and can further incorporate only one or more of the above-disclosed features. Furthermore, the embodiments described and identified as "preferred" are considered to be some of the best modes contemplated for carrying out the embodiments of the present disclosure. Other embodiments may also be discussed for further illustrative purposes in providing a complete and enabling disclosure. Furthermore, many embodiments, such as adjustments, variations, modifications, and equivalent arrangements, are implicitly disclosed by the embodiments described herein and are included within the scope of the present disclosure.

[0025] Thus, although the embodiments have been described in detail herein with respect to one or more embodiments, this disclosure should be understood to be illustrative and representative of the present disclosure, presented merely for the purpose of providing a complete and enabling disclosure. The detailed disclosure of one or more embodiments herein is not intended, and should not be construed, as limiting the scope of patent protection conferred by any claim of an issued patent, which scope is defined by the claims and their equivalents. The scope of patent protection is not intended to be defined by reading into any claim any limitations herein that are not expressly set forth in the claim itself.

[0026] Thus, for example, any sequence and / or time order of steps of the various processes or methods described herein is exemplary and not limiting. Thus, while various process or method steps are shown and described as being in a sequence or time order, it is understood that such process or method steps are not limited to being performed in a particular sequence or order, and are not otherwise indicated. Indeed, steps in such processes or methods may generally be performed in a variety of different sequences and orders, and still be within the scope of the invention. Thus, the scope of patent protection is intended to be defined by the issued claims, and not by the description set forth herein.

[0027] Additionally, it is important to note that each term used herein refers to what a person of ordinary skill in the art would understand that term to have based on its contextual use. To the extent that the meaning of a term used herein (as understood by a person of ordinary skill in the art based on the contextual use of that term) differs in any way from any particular dictionary definition of that term, the meaning of the term as understood by a person of ordinary skill in the art shall control.

[0028] Additionally, as used herein, it is important to note that "a" or "an" generally means "at least one," but does not exclude a plurality unless the contextual usage indicates otherwise. "Or," when used herein to add to a list of items, indicates the meaning of "at least one of the items," but does not exclude a plurality of items of the list. Finally, "and," when used herein to add to a list of items, indicates the meaning of "all of the items of the list."

[0029] The following detailed description refers to the accompanying drawings. Wherever possible, the same reference numbers are used in the drawings and the following description to refer to the same or similar elements. Although many embodiments of the present disclosure may be described, modifications, adjustments, and other implementations are possible. For example, substitutions, additions, or modifications may be made to the elements shown in the drawings, and the methods described herein may be modified by substituting, rearranging, or adding steps to the disclosed methods. Therefore, the following detailed description is not intended to limit the disclosure. Rather, the appropriate scope of the disclosure is defined by the appended claims. This disclosure includes headings. It is to be understood that these headings are used as a reference and are not to be construed as limiting the subject matter disclosed under the headings.

[0030] The present disclosure includes many aspects and features. Additionally, while many aspects and features are described in connection with unmanned aerial vehicles, embodiments of the present disclosure are not limited to use only in unmanned aerial vehicles. For example, embodiments of the present disclosure may be used in manned and unmanned aerial vehicles.

[0031] I. overview This Summary is provided to introduce a selection of concepts in a simplified form that are further described below. This Summary is not intended to identify key features or essential features of the claimed subject matter. This Summary is not intended to limit the scope of the claimed subject matter.

[0032] An improved unmanned aerial vehicle with deployable components (UAVDC) is provided in various embodiments disclosed herein. Various aspects of the UAVDC provide improvements over conventional unmanned aerial vehicles, including, but not limited to, improvements in portability, deployment, post-deployment flight control transition, aerodynamic efficiency, and endurance, maximum payload, and maximum mission capability over conventional unmanned aerial vehicles. As described in more detail below, the UAVDC of the present disclosure includes many features that lead to the above-mentioned improvements, including, for example, but not limited to, trailing edge hinged ailerons, deployable stabilizers, gearboxes, fairings, and swept and telescoping wing implementations.

[0033] The UAVDC may be configured in multiple configurations: a first configuration may be a compact configuration suitable for storage and launch embodiments, a second configuration may be a deployed configuration suitable for launch recovery and flight, and a third configuration may be an extended configuration suitable for long endurance, for example. As described in more detail below, the UAVDC may be fully functional and operable in intermediate configurations between these three configurations to provide some of the advantages of improved UAVDC at higher airspeeds.

[0034] 1A shows an example of a first configuration (e.g., compact configuration 102). The compact configuration 102 may allow for convenient storage and transportation of the UAVDC. Additionally, the compact configuration 102 may allow for specific launch methods, such as, for example, launch from a tube or release from, for example, an aircraft's weapons bay / bomb bay or wing mounting.

[0035] According to embodiments of the present disclosure, a UAVDC may be deployed after launch into a deployed configuration suitable for withstanding the high aerodynamic loads of launch recovery and high speed flight. During flight, the UAVDC may be further deployed into an extended configuration suitable for efficient long endurance flight. It should be understood that the terms "deploy" and "deployment" may refer to the transition of a deployable component from one UAVDC configuration to another UAVDC configuration.

[0036] 1B illustrates an example of the second configuration (e.g., deployed configuration 104). By using the deployed configuration 104, the embodiment can withstand the higher aerodynamic loads associated with flying at high airspeeds or high G pull-up maneuvers. Thus, at least one of the intermediate configurations (e.g., deployed configuration 104) may be used in launch recovery where the UAVDC has been launched and has not yet slowed down to a sustainable airspeed for the third configuration. Additionally, the deployed configuration can sustain high speed flight more efficiently than the extended configuration.

[0037] 1C illustrates an example of the third configuration (e.g., extended configuration 105). Using the extended configuration, the UAVDC can achieve an increased level of aerodynamic efficiency (i.e., flight time) and an increased maximum payload. In various embodiments, the second configuration (e.g., deployed configuration 104) and the third configuration (e.g., extended configuration 105) are considered common configurations, but have wingspans that correspond to the degree of telescopic displacement of the wings.

[0038] As described in more detail below, during transformation from the compact configuration 102 to the extended configuration 105, a UAVDC according to an embodiment of the present disclosure may implement at least one of, but is not limited to, wings 110 that may be configured to sweep and / or telescope, one or more trailing edge hinged control surfaces ("ailerons") 120 to enable rotational control, one or more foldable actuated stabilizers 125, one or more flexible aerodynamic fairings 130, one or more propulsion mechanisms (e.g., folding propellers 135), and a modular payload 140.

[0039] In further embodiments, the UAVDC may comprise intermediate configurations between the first and second configurations or between the second and third configurations. In the intermediate configurations, the wings 110 may be in various stages of sweep or telescoping. It should be appreciated that the use of the trailing edge ailerons 120 and the outboard telescoping outer wing panels 310 allows the UAVDC to continue to maintain controlled flight during the transition from the first to the third configuration.

[0040] In the first configuration, prior to deployment, the wings 110, stabilizers 125, and propellers 135 described above may be stored against the fuselage 106 of the UAVDC (i.e., folded out of the way upon launch of the vehicle). The fairing 130 may be configured to flex to accommodate the wings 110 in the stored configuration and then flex to accommodate the sweeping motion of the wings 110. Upon launch, the UAVDC may transform from the first configuration to the second configuration. In the second configuration, the wings 110 may be deployed by an outward sweeping motion (with the fairing 130 flexing to enable the sweeping motion). FIG. 2C illustrates the outward sweeping motion 250. As described in further detail below, the outward sweeping motion 250 may be enabled by, for example, but not limited to, a sweep gearbox coupled to an actuator. FIGS. 2A-2C illustrate an example of a sweep gearbox 205 coupled to an actuator 210. Additionally, the sweeping motion 250 of the wings 110 allows for configurable wing angles to optimize aerodynamic performance. The fairings 130 can be designed to accommodate the wings 110 in the stowed configuration, as well as the sweeping motion 250. Additionally, the fairings 130 can close around the wings 110 to maintain the aerodynamic integrity of the UAVDC, as shown in FIG. 11B.

[0041] By providing a gearbox 205 configured to sweep the wing 110 and orient the wing 110 at an optimal dihedral angle 265 and incidence angle 275, embodiments of the present disclosure can improve upon conventional systems. For example, in conventional systems, aircraft that achieve wing sweep and wing angle adjustment require the use of auxiliary mechanisms to orient the wing angle. Such auxiliary mechanisms add weight and cost, as well as introduce additional failure modes.

[0042] According to an embodiment of the present disclosure, the wing 110 may further be configured to telescopically extend (i.e., extend in length) in a third configuration. Such a telescopic wing may comprise a fixed inner portion and one or more substantially hollow outer portions that slide along adjacent portions to lengthen the wingspan when deployed. FIG. 3 shows an example of a telescopic wing 110 comprising a fixed inner portion 305 and an outer portion 310 attached to the fuselage 106. In further embodiments, multiple nested outer wing sections may be realized. In this manner, the wing 110 may be stored in the compact configuration 102 and then extend (i.e., telescopically extend) to provide additional lift during the extended configuration 105. As described in more detail below, a telescopic mechanism ("telescopic means") according to an embodiment of the present disclosure may use, for example, a belt system 315, a scissor mechanism, or a piston mechanism for extending and / or retracting the wing.

[0043] A telescoping means according to an embodiment of the present disclosure allows maximum wingspan while maintaining rotational control during transitions between configurations. For example, because the inner portion is fixed, the outer portion may include a substantially hollow interior such that the fixed inner portion can reside inside the outer portion. The outer portion can then slide (i.e., telescoping) outwardly from the fuselage 106, such that the fixed inner portion is exposed when the outer portion telescoping. Trailing edge-mounted control surfaces (e.g., ailerons 120) are exposed and operable during the deployment and telescoping process because they are attached to the outer portion. In this manner, the wingspan of the UAVDC can be extended (e.g., regardless of the position of the outer portion relative to the position of the inner portion) while continuing to maintain controlled flight during the transition.

[0044] In some embodiments, the inboard portion 305 may connect to the fuselage 106 and the outboard portion 310 may extend telescopically outside the fuselage 106. The trailing edge ailerons 120 may connect to the outboard portion 310 to provide rotation control. In this manner, the trailing edge ailerons 120 may provide rotation control even when the wing 110 is not extended. The trailing edge ailerons 120 may be hinged at the aft-most point of the wing to maximize the interior volume of the outboard portion 310, which maximizes the overall span of the wing 110 in the third configuration. In various embodiments, other configurations of wing control surfaces, such as spoilers, may be implemented within the spirit and scope of the present disclosure.

[0045] By implementing the hollow outer telescoping wing section 310 and the trailing edge hinged aileron 120, several improvements are introduced. A typical telescoping wing utilizes a telescoping outer panel housed within a fixed inner panel, which precludes the use of an aileron attached to the outer panel until the wing panel reaches a telescoping extended state. Furthermore, since conventional aileron implementations are constructed within the wing surface itself, the amount of interior volume available within the wing is reduced. The reduced interior volume reduces the depth available for placement of the inner wing section in a telescoping wing system, resulting in less displacement in the telescoping configuration. Thus, conventional rotating control surfaces may reduce the final length of the telescoping wing.

[0046] The attachment of the trailing edge hinged ailerons 120 to the outer portion 310 of the telescoping wing 110 allows the inner portion 305 of the telescoping wing 110 to be further retracted inside the outer portion 310 while providing the necessary rotational control to maintain flight in the deployed configuration before the wings are telescopically extended. Then, when the wings 110 are telescopically extended, the range of displacement of the outer portion 310 is greater than the range of displacement of other telescoping wing systems, resulting in an advantage of increased wingspan compared to conventional aircraft capable of compact configurations. Furthermore, extending the outer portion 310 of the telescoping wing 110 from the fuselage allows the trailing edge hinged ailerons 120 to increase the rotational control of the UAVDC.

[0047] According to embodiments of the present disclosure, the control surfaces (e.g., the trailing edge hinged ailerons 120) may be operable in all of the UAVDC configurations, i.e., the control surfaces may be operable in the compact configuration 102, the deployed configuration 104, and the extended configuration 105. Additionally, the control surfaces may be operable during transition phases between each of these configurations.

[0048] For example, the trailing edge hinged ailerons 120 may be operable between a first configuration (e.g., compact configuration 102) and the deployed configuration 104 (e.g., performed in an approximately 45 degree sweep motion) to stabilize the UAVDC after launch. Additionally, the trailing edge hinged ailerons 120 may be operable when the UAVDC is in the deployed configuration 104 to provide flight control as well as transition phases between the deployed configuration 104 and the extended configuration 105. Finally, the trailing edge hinged ailerons 120 may be operable in the extended configuration 105 to provide additional, more effective flight control.

[0049] One or more stabilizers 125 of the UAVDC may be deployed in an intermediate configuration, a second configuration, and / or a third configuration. The stabilizer 125 may be deployed from a first stabilizer configuration 450 to a second stabilizer configuration 455 by rotating about an axis 430, as shown in FIGS. 4A-4D. Once in the second stabilizer configuration 455, the stabilizer 125 may further function as a control surface and provide flight control by pivoting about an axis 425. As described in more detail below, the deployment about the axis 430 may be implemented, for example, via a preloaded spring 405. In a further embodiment, the stabilizer 125 may be deployed upon contact with an air resistance. For example, when the stabilizer 125 contacts an airflow, the resulting drag may move the stabilizer 125 to the deployed configuration. The servo mechanism 410 may actuate the stabilizer 125 about the axis 425 once the stabilizer 125 is deployed. 4E-4G show the stabilizer 125 in a deployed configuration at various pivot angles about axis 425. FIG.

[0050] The deployable control surfaces embodied in this disclosure as stabilizers 125 improve over conventional systems, for example, by allowing automatic deployment without the need to adjust control components (e.g., actuators and linkages). Additionally, aerodynamic efficiency may be improved by providing a flexible fairing. It should be understood that not all embodiments of a UAVDC may include each of the components described above, and that other embodiments of a UAVDC may include additional components, and yet other embodiments may include various combinations of the embodiments described in this disclosure.

[0051] The propellers 135 of the UAVDC may deploy upon contact with air resistance. In a further embodiment, centripetal force may be achieved by a spring and / or rotation of the propellers 135 when deploying the propellers 135. Figure 5 shows an example of a propeller 135 and illustrates the deployment direction 505 of the propeller blades 510.

[0052] A UAVDC according to embodiments of the present disclosure may be configured to receive a modular payload 140. In some embodiments, the modular payload 140 may remain fixed in both the first and second configurations. As a non-limiting example, the modular payload 140 may be configured within the UAVDC and serve as the nose of the fuselage 106. FIG. 6A illustrates an example of a plurality of modular payloads 140 configured to attach to the fuselage 106 at fixed locations 605. To facilitate modularity, the modular payload 140 may include a hook 610 configured to hook around a pin 615 in a twist-lock manner. In this manner, the modular payload 140 may be inserted into the fuselage 106. The ridge 620 may orient the modular payload and form a flush transition from the modular payload 140 to the fuselage 106. Additionally, the pin 615 may include threads for tightening around a nut, thereby locking the hook 610, and thus the modular payload 140, in place. In a further embodiment, modular payload 140 may include a protrusion configured to fit into a slot recessed within fuselage 106. Modular payload 140 may be inserted into fuselage 106 along the slot configured to receive the protrusion and rotated to lock modular payload 140 to fuselage 106.

[0053] The modular payload 140 may be locked in a fixed position 605, but may include deployable components therein, as shown in FIGS. 6B and 6C, which show the modular payload in a first configuration 630 and a second configuration 635, respectively.

[0054] In other embodiments, the modular payload 140 may have at least two configurations with respect to its position relative to the fuselage 106. FIG. 6D illustrates another example of the modular payload 140 in a first position 640, and FIG. 6E illustrates the modular payload 140 in a second position 645. For example, the modular payload 140 may be disposed in the first position 640 when the UAVDC is in the first configuration (the "compact configuration") and deployed to the second position 645 while in the second configuration. As a non-limiting example, the modular payload may be a detection device 650 configured on a boom 655 that telescopically extends out from the fuselage.

[0055] Embodiments of the present disclosure can provide improvements over conventional unmanned aerial vehicles, including, but not limited to, the following examples: Improved aerodynamic efficiency for increased flight time. -Increased maximum payload. Launch and transition to flight without the aid of external aerodynamic treatments such as parachutes or balloons. Maximizing mission capability (i.e., modular payloads and reconfigurable, highly efficient airframes enable UAVDCs to efficiently execute more diverse missions, such as, but not limited to, Intelligence, Surveillance, and Reconnaissance (ISR), Signals Intelligence (SIGINT), weather, geophysical, and environmental).

[0056] Both the above summary and the following detailed description provide examples and are explanatory only. Thus, the above summary and the following detailed description should not be considered limiting. Furthermore, features or variations other than those described herein may be provided. For example, embodiments may be directed to combinations and subcombinations of the various features described in the detailed description.

[0057] II. composition 1C illustrates a UAVDC according to an embodiment of the present disclosure. An embodiment of the present disclosure may include a fuselage 106, one or more antennas 705, a power source 1310, wings 110 that may be configured to sweep and / or telescope, stabilizers 125, and a payload 140. Further embodiments may include a propulsion mechanism, such as, for example, a propeller 135.

[0058] The fuselage 106 may be made of, for example, but not limited to, carbon fiber. Additionally, the fuselage 106 may be made of, for example, but not limited to, composite materials (e.g., fiberglass, Kevlar, Spectra). In various embodiments, plastics may be used, including, but not limited to, 3D printed plastics. The fuselage 106 may assume an aerodynamic shape that facilitates acceleration and reduced air resistance.

[0059] Referring now to FIG. 7, the antenna 705 may be positioned on various portions of the UAVDC. For example, the antenna 705 may be fixed and, in some embodiments, may be conformal (i.e., integrated into the skin of the fuselage 106). Alternatively, the antenna 705 may be deployable. For example, the antenna 705 may be configured to deploy on a hinge out of the fuselage (e.g., via a spring). As another example, as shown in FIG. 7, the antenna 705 may be integrated into at least one of the stabilizer fins 125. In this way, when the stabilizer fins 125 are deployed, the antenna 705 may also be deployed. In a further embodiment, the modular payload 140 may be embodied as the antenna 705, as shown in FIGS. 6D and 6E. In this way, the antenna 705 may be configured to be attached to the boom 655 and extend from the fuselage 106. In yet another embodiment, multiple antennas may be built into the UAVDC.

[0060] Antenna 705 may be in operative communication with an on-board controller, as described in further detail with reference to FIG. 15. In this manner, antenna 705 may transmit and receive data to and from a remote location (e.g., a UAVDC operator). For example, antenna 705 may be used to receive control signals from an operator located at a remote location. The control signals may be processed and interpreted by the on-board controller, which may operate the UAVDC accordingly. Additionally, antenna 705 may be used to communicate various data from the UAVDC, for example, to an operator located at a remote location.

[0061] The data may include, for example, but is not limited to, sensor data collected by various sensors on board the UAVDC (e.g., sensors in modular payload 140). In yet another embodiment, the data may include telemetry data for the UAVDC, including, for example, but not limited to, global positioning data, accelerometer data, gyro data, velocity data, etc. In some embodiments, the above-mentioned data may be collected, processed, and encrypted by the on-board controller prior to its communication.

[0062] It should be understood that the UAVDC may be configured with various propulsion mechanisms, with the propeller 135 shown in FIG. 8 being just one variation. Other propulsion mechanisms may include, but are not limited to, rockets, jet engines, and compressed gas jets. Additionally, in some embodiments, propulsion may not be required at all, as the UAVDC may have glider characteristics. In such embodiments, the UAVDC may be launched, for example, from a tube, or may be released, for example, from an airplane within gliding distance of the mission target. The various characteristics of the UAVDC, as described in various embodiments herein, may provide the UAVDC with sufficient flight time (e.g., upon deployment, as described in more detail below with reference to FIG. 14) to accomplish its mission without requiring additional propulsion.

[0063] The propeller 135 may include propeller blades 510 that fold against the fuselage 106. Although the propeller 135 is shown as having two propeller blades 510, it should be understood that more or less propeller blades may be used. For example, only a single propeller blade may be used. As shown in FIG. 9, the fuselage 106 may include grooves 905 configured to receive the propeller blades 510 in the folded configuration. During flight, the propeller 135 may be unfolded using, for example, air pressure against the propeller (e.g., due to drag) or centripetal force due to the rotation of the propeller 135. In other embodiments, the propeller 135 is unfolded by using a spring (e.g., torsion spring 805) that allows for rapid deployment, which may prevent the propeller blades 510 from hitting the stabilizer 125 before the propeller 135 is fully unfolded.

[0064] While many of the figures show the propellers 135 in a rear mounted position, it should be understood that in embodiments where a propulsion mechanism is provided, the propellers 135 may be configured in different locations on the UAVDC. For example, in some embodiments, the propellers 135 may be mounted on the front of the UAVDC instead of the rear. Figures 6D and 6E show one embodiment of a UAVDC with a towing propeller 675 mounted on the front of the UAVDC.

[0065] Additionally, the positioning of the propeller 135 may be affected by the deployment of the wings 110. Referring to FIG. 10A, the propeller blades 1005 are attached to the fuselage 106, which are tucked under the wings 110. Upon launch of the UAVDC in the first configuration, air drag or springs 805 may bias the propeller blades 1005 in the upper position (e.g., attached to the top of the fuselage 106) toward their deployed state. However, such deployment of the propeller blades 1005 may be impeded by the wings 110 retracted directly above, as shown in the first configuration.

[0066] The remaining propeller blades 1010 that are not obstructed by the wing 110 can deploy into the second configuration as designed since they cannot be impeded from deploying. To keep the remaining propeller blades 1010 from hitting the windmill while the propeller blades 1005 are still trapped, the blade's hinge travel 1015 can be extended to fold the blades 1010 into a position 1020 that aligns the blades 1010 with the main current, as shown in FIG. 10B.

[0067] Referring again to FIG. 1A, the UAVDC may have a wing arrangement consisting of a single wing with two wing sections. The wing arrangement is divided into a left wing section and a right wing section to allow for variable sweep in a generally symmetrical lateral direction between the left wing section and the right wing section. In some embodiments, the wing sections may be a left wing and a right wing (e.g., wing 110). However, according to embodiments of the present disclosure, the wing arrangement may be a single wing consisting of two wing sections.

[0068] The wing arrangement may be configured in a first arrangement (e.g., corresponding to a first configuration of the UAVDC), a second arrangement (e.g., corresponding to a second or third configuration of the UAVDC), and a third arrangement. In the first arrangement, the left and right wing sections may be retracted against the fuselage at a first sweep deployment angle. In the second arrangement, the wing arrangement may be fully deployed for flight at a second sweep deployment angle. The third arrangement may include the wing sections at any wing deployment angle between the first and second sweep deployment angles.

[0069] To enable the sweep deployment angle, the UAVDC may include a sweep gearbox configured to pivot the left and right wing sections to enable the wing arrangement to sweep from a first arrangement to a second arrangement at any sweep deployment angle. The UAVDC may include an actuator coupled to the sweep gearbox configured to initiate the sweep of the wing arrangement at any sweep deployment angle.

[0070] During a sweeping motion, the fairing 130 may be configured to change from an open configuration to a closed configuration. The fairing 130 may begin in an open configuration by flexing such that the first and second wing portions are stored under the fairing in a first configuration, and transition to a closed configuration to provide an aerodynamic and / or environmental advantage in a second configuration.

[0071] The wings 110 may be stored in a launch configuration as shown in the first configuration 102. In some embodiments, the launch configuration of the wings 110 may include a vertical offset. The wings 110 may be swept into a flight configuration by a sweep gearbox 205 (e.g., a sweeping means). For example, an actuator 210 attached to the sweep gearbox 205 may include a worm gear 220 coupled to each wing and a worm 225 coupled to the worm gear 220 and configured to spread the wings with a sweeping motion 250. The sweep gearbox 205 may be mounted on a wing mount 215. Various other means may be used to sweep the wings 110, including, but not limited to, springs. In some embodiments, the wings 110 do not need to be fully swept to enable flight. For example, the UAVDC may fly at an angle less than a full sweep.

[0072] The gearbox 205 may be configured such that the wings 110 may be stored at a first set of angles relative to each other (e.g., flat against each other) and relative to the fuselage (e.g., flat against the fuselage) in the launch configuration. The gearbox 205 may further be configured to deploy the wings 110 at optimal angles of incidence and dihedral in the sweep configuration. This may be achieved by orienting the axis of rotation of each wing as well as the attachment of each wing to the worm gear 220 (or "wing pivot"). Thus, the gearbox 205 may comprise two pivot axes about which the wings may sweep. FIG. 2D is a schematic diagram showing a geometry for enabling the gearbox 205. For example, the axis of rotation may be oriented such that the angle in the YZ plane 270 may coincide with the attachment angle 265 to the worm gear 220, as shown with respect to the axis 255. Additionally, the angle in the XZ plane 260 may coincide with the attachment angle 275 to the worm gear 220. In this configuration, the wings 110 can be stowed flat relative to each other and to the fuselage and deployed at an optimal dihedral angle and incidence angle. The optimal dihedral angle can be a combination of the angle in the XZ plane 260 and the installation angle 265, and the optimal incidence angle can be a combination of the angle in the XY plane and the installation angle 275. In this manner, a single mechanism can sweep the wings 110 and orient the wings 110 at a desired dihedral angle and incidence angle. A single mechanism for sweeping and orienting the wings can reduce weight and complexity, thereby increasing endurance and reducing costs.

[0073] The UAVDC may include a fairing 130 to reduce drag while allowing the outward sweeping motion 250 of the wing 110. FIGS. 11A and 11B show the fairing 130 in a first configuration 1105 and a second configuration 1110, respectively. The fairing 130 may be made of a flexible material (e.g., fiberglass) so that it can flex out of the way as the wing 110 sweeps. In various embodiments, other materials may be used, including, but not limited to, carbon fiber, Kevlar, and sheet metal. The fairing 130 may include a wing hole cutout 1115 that fits the contour of the wing 110 when the wing 110 is in the second configuration 1110.

[0074] As shown in FIG. 11A, the fairing 130 in the first configuration 1105 may be under tension by resting on the sweeping wing 110 in the compact configuration 102 and being held in a taut ("buckled") state. Slits 1120 may be provided in the fairing 130 to allow the fairing 130 to flex sufficiently to accommodate the sweeping wing 110 in the compact configuration 102. When the UAVDC enters the second configuration (e.g., the extended configuration 105), the fairing 130 may flex and close around the wing 110 as shown in FIG. 11B when the wing 110 reaches the wing hole notch 1115. In the second configuration 1110, the fairing 130 may be untensioned as it fits tightly against the wing 110 to minimize drag. If the fairing 130 comprises a fiber composite material, it may be desirable to use fiber orientation to promote buckling and flexibility of the laminate (e.g., using + / - 45 degree plies may increase flexibility and easily buckle in the 0 degree and 90 degree directions).

[0075] In a further embodiment, magnets 1125 may be used to further anchor the fairing 130 around the swept wing 110, as shown in Figure 11C. The magnets 1125 may be located on the fuselage 106. A magnet or magnetic metal 1130 of opposite polarity may be located on the fairing 130 to receive the magnetic force of the magnets 1125. In a further embodiment, the positions of the magnets 1125 and the corresponding magnetic metal 1130 may be reversed.

[0076] As the wing 110 is being swept, or in some embodiments after the wing 110 is fully swept, the wing 110 can extend in a telescopic fashion. For example, the inner portion 305 can be attached to the fuselage 106 of the UAVDC. The inner portion 305 can be at least partially stored within the outer portion 310 during the first compact configuration. The outer portion 310 can include a substantially hollow interior. An outer surface of the inner portion 305 can be stored against an inner surface of the outer portion 310. To be in the second configuration, the outer portion 310 can slide along the inner portion 305 and extend outwardly from the fuselage 106. As the outer portion 310 slides along the inner portion 305, an extending portion of the inner portion 305 can be exposed. The wingspan of the wing 110 can be approximately the length of the outer portion 310 and the exposed portion of the inner portion 305. Both the inner portion 305 and the outer portion 310 may adopt an aerodynamic profile to provide lift during flight. Some embodiments may utilize a belt system 315 for the telescoping wings 110.

[0077] The belt system 315 may include a belt pulley 325 that may be attached to the inner wing 305 ("second portion"). At least one pulley 325 may be driven by an actuator 320. In further embodiments, multiple pulleys 325 may be driven by multiple actuators 320. A belt 330 may be wrapped around the pulley 325. A notch in the belt 330 may allow the actuator 320 to move the belt 330. One of the straight lengths 331 of the belt 330 may be housed within the inner wing 305, and the other length 332 of the belt 330 may be housed in a groove in the bottom of the inner wing 305 ("second portion") that abuts the outer wing 310 ("first portion") before the wing 110 extends telescopically.

[0078] The belt 330 may be attached to at least a portion of the outer wing 310 along the length 332 so that it can telescope. In this manner, rotation of the actuator 320 not only moves the belt 330 but also displaces the outer wing 310 by attaching the outer wing 310 to the belt 330. Thus, actuation in the direction 335 causes the portion 310 to extend outwardly from the fuselage 106, thereby increasing the wingspan of the UAVDC. As the portion 310 moves outward, the inner portion 305 is simultaneously pulled outwardly from within the outer portion 310, thereby increasing the wingspan of the UAVDC. Thus, as the wings 110 are telescoped, the length 332 may be exposed, but the grooves may prevent the belt 330 from protruding from the bottom of the exposed inner wing 305.

[0079] Attachment of the outer portion 310 to the length 332 may be performed, for example, but not limited to, by clamps, screws, or adhesive. In some embodiments, the belt 330 may include a length of fiber reinforced rubber material. By stripping the rubber from each end of the belt to expose the fibers, another attachment mechanism for attaching the belt 330 to the outer portion 310 is available. For example, the exposed fibers may be knotted to the outer wings 310 (e.g., holes in the outer wings 310). The knotted fibers may be further secured, for example, with an adhesive. In this manner, both ends of the belt 330 may be attached to form a connecting loop without the use of a coupler to secure the ends, thereby eliminating bulky sections commonly used in the prior art.

[0080] According to embodiments of the present disclosure, the belt system 315 can provide a lighter and / or more compact mechanism than conventional telescoping systems. In some embodiments, the telescoping of the wings can be reversed by reversing the direction 335 of the actuator 320 for retracting the wings 110. In another embodiment according to the present disclosure, the components of the belt system 315 can be reversed such that the outer wing 310 is fixed to the fuselage 106 and the inner wing 305 can be telescoping outward. In yet another embodiment, a similar belt system can be provided to extend a boom from the fuselage 106. For example, instead of attaching the belt 330 to the outer wing 310, the belt 330 can be attached to the boom.

[0081] The wing 110 may include an aileron 120. In some embodiments, the aileron 120 may be attached to the trailing edge of the outer portion 310 via a hinge 1215. In this manner, the aileron 120 may minimize the obstruction of the interior volume of the outer portion 310 compared to a conventional aileron. By optimizing the interior volume of the outer portion 310, the inner portion 305 may have an optimized profile and increased wingspan that would be limited with more commonly used ailerons. For example, the inner portion 305 may overlap at least a portion of the length of the trailing edge aileron attachment to the outer portion 310 when stored within the first compact configuration. In this manner, the surface area ratio between the inner portion 305 and the outer portion 310 may be increased. By maximizing the wingspan, the efficiency, endurance, and maximum payload of the aircraft may be significantly improved. Types of hinges that may enable such trailing edge ailerons 120 include, but are not limited to, living hinges or other bending bearings.

[0082] Additionally, by attaching the ailerons 120 to the outer portion 310 that extends away from the fuselage 106, the ailerons 120 may allow for rotational control during the wing deployment phase. This means that the UAVDC can fly with positive rotational control regardless of the position of the outer portion 310 relative to the inner portion 305, which may be beneficial during launch and flight recovery phases where a transition to stable flight may be performed with less structural loads on the airframe when the wings are configured in a non-telescopically extended position. Additionally, this may be beneficial as the wingspan may be reduced or increased in flight to maximize aerodynamic efficiency without compromising rotational control. FIG. 12A illustrates the configuration of components for controlling the ailerons. Each aileron 120 may be positioned by a servo mechanism 1320 via a link mechanism 1210 as shown in FIG. 13. Each servo mechanism 1320 may be positioned within the outer wing section 310 in some embodiments. In further embodiments, the ailerons 120 may be operated by other means including, but not limited to, gears or shafts. Each servo mechanism 1320 may be controlled by a controller 1500 .

[0083] FIG. 12B illustrates possible configurations of the ailerons 120, including, but not limited to, a tucked position 1230 where the storage volume is minimized, a partially folded position 1235, and a fully deployed position 1240. The servos 1320 may be operated via control lines positioned in the outer wing 310 and the inner wing 305. The control lines may extend from the fuselage 106 through the inner wing 305. The ends of the wing 305 may include openings through which the control lines may extend into the interior of the outer wing 310 where they connect to the servos 1320. In various embodiments, the lines may have a length sufficient to accommodate the telescoping of the wings. The control lines may be coiled or neatly folded inside either wing while the wings are not telescoping.

[0084] 4A-4D show one embodiment of a deployable pivoting control surface embodied as a stabilizer 125. While this disclosure uses the term "stabilizer" in reference to a deployable pivoting and / or pitching control surface, it should be understood that such control surfaces may not be limited to stabilizers. For example, deployable pivoting control surfaces implementing the same components may be used in other forms including, but not limited to, wings.

[0085] In some embodiments, the stabilizer 125 may be transitioned to the flight configuration by other means, including but not limited to air drag. In further embodiments, the stabilizer 125 may be spring loaded to transition to the flight configuration upon launch. For example, a torsion spring 405 may transition the stabilizer 125 to the flight configuration. The stabilizer 125 may be used to provide flight control with a servo mechanism 410 that operates a push rod 415 and a horn 416 that pivots the stabilizer 125 about an axis 425. For example, the servo mechanism 410 may rotate the stabilizer 125 about an axis 425 by pivoting in a hinge 420. Additionally, the stabilizer 125 may include a fairing 485. The fairing 485 may be embodied as a flexible material (e.g., rubber or elastomer) configured to rotate around a shaft 445 to enable pitching motion while maintaining aerodynamic efficiency, as shown in FIGS. 4E-G. As mentioned above, the stabilizer 125 may include one or more antennas 705 such that deployment of the stabilizer 125 may further deploy the one or more antennas 705 .

[0086] The stabilizer 125 can be transitioned into the flight configuration by pivoting about an axis 430. In this manner, the axis 430 can be constant relative to the fuselage 106 in the transition 440 from the first configuration 450 to the second configuration 455. Furthermore, by aligning the centerline of the horn 416 with the axis 430 during deployment, as further shown in Figures 4A and 4B, the servo mechanism 410 does not need to move during the transition 440 from the first configuration 450 to the second configuration 455.

[0087] The servo mechanism 410 may be configured to move a push rod 415 coupled to a horn 416 on the at least one stabilizer to deflect / rotate the at least one stabilizer about its spanwise axis. The horn 416 may then be configured to remain in a relatively fixed position as the at least one stabilizer deploys into the flight configuration (second configuration).

[0088] 4E-4G show a stabilizer fairing 485. The stabilizer fairing 485 may be used to cover various components that allow at least one stabilizer to deflect / rotate about its spanwise axis to provide positive flight control during the second stabilizer configuration 455. The stabilizer fairing 485 may comprise a flexible material such as, for example, rubber. In this manner, the stabilizer fairing 485 flexes to reduce drag on various components, including but not limited to the shaft 445, while at the same time allowing a full range of motion for the stabilizer 125.

[0089] A number of internal components may be mounted within the interior 1305 of the fuselage 106. FIG. 13 illustrates an example of an internal configuration of the UAVDC in which a power source 1310 may be positioned within the fuselage 106. The power source 1310 may comprise, for example, a fuel tank or one or more batteries. Various components of the UAVDC may be connected to the power source 1310, including, but not limited to, the modular payload 140, the controller 1500, the sweep gearbox actuator 210, the control mechanisms (e.g., servo mechanisms 1320) for the ailerons, the servo mechanisms 410 for the stabilizer 125, the motors 1315 driving the propellers 135, and the antennas 705. UAVDC embodiments that include a propulsion device (e.g., the propellers 135) may be powered by an alternative power source, such as, for example, an internal combustion engine. In such an embodiment, a fuel source (e.g., a gas tank) for the internal combustion engine may be positioned within the interior 1305 of the fuselage 106.

[0090] The internal components may further include, but are not limited to, the following components (e.g., described in more detail with respect to Section III below): sweep gearbox 205 and actuator 210 used to sweep wings 110, control mechanisms for ailerons 120 (e.g., servo mechanisms 1320) for manipulating ailerons 120 and servo mechanisms 410 for manipulating stabilizers 125), motors 1315 for driving propellers 135, drive shafts 1330 for coupling motors 1315 to propellers 135, and on-board controller 1500 for controlling the deployment, flight, and operation of the UAVDC. The illustrated configuration of internal components is one possible configuration and other embodiments are possible. The internal components may be distributed to balance weight in an optimal manner for flight.

[0091] III. operation FIG. 14 is a flow chart illustrating general steps included in a method 1400 according to an embodiment of the present disclosure for operating a UAVDC. The method 1400 may be implemented at least in part using a controller 1500 (e.g., an on-board computing device), as described in more detail below with respect to FIG. 15. The controller 1500 may comprise a controller for operating the deployable components as well as performing other mission details including, but not limited to, flight control, payload manipulation, and communications. Thus, the controller 1500 may be in an operable configuration and in communication with, for example, but not limited to, the modular payload 140, the sweep gearbox actuator 210, the control mechanisms (e.g., servo mechanisms 1320) for the ailerons 120, the servo mechanisms 410 for the stabilizers 125, the motors 1315 for driving the propellers 135, the power source 1310, the inertial measurement unit, the global positioning system, various telemetry sensors, and the antenna 705, as well as all other units. 15, the controller 1500 may include a remote communication module that enables remote operation as described above with respect to the antenna 705. In other embodiments, the controller 1500 may be completely self-operating when configured. In this manner, the UAVDC may be self-operating.

[0092] Additionally, although steps are disclosed with respect to controller 1500, it should be understood that a number of other components may enable operation of method 1400, including, but not limited to, other computing components, mechanical parts, environmental characteristics (e.g., air resistance), remote operators, etc.

[0093] Additionally, although the steps depicted by the flow charts are disclosed in a particular order, it should be understood that the order is disclosed for illustrative purposes only. Steps may be combined, separated, or rearranged, and various intermediate steps may be present. Thus, it should be understood that the various steps depicted in the flow charts may be performed in different arrangements than those depicted, in various embodiments. Additionally, various steps may be added to or removed from the flow charts without altering or interfering with the basic scope of the methods and systems disclosed herein.

[0094] The method 1400 may begin at start block 1405 and proceed to stage 1410 where the UAVDC may be launched. For example, the UAVDC may be released from a tube launched from an airplane or dropped from a carrier aircraft. The compact placement 102 of the first form of the UAVDC (e.g., as specified with respect to FIG. 1A) may allow the UAVDC to be tube launched, such as a missile. In some embodiments, the UAVDC may be aerodynamically designed (as shown) and have a weight distribution that allows it to self-orient from a somersault dive when dropped from a carrier aircraft.

[0095] The method 1400 may proceed from step 1410, where the UAVDC is launched, to step 1420, where the flight components may be deployed. Although disclosed in a particular order for illustrative purposes, the deployment of the flight components may occur in other arrangements.

[0096] Upon launch, the stabilizer 125 and the propeller 135 may deploy. In applicable embodiments, springs 405 and 805 may deploy the stabilizer 125 and the propeller blades 510, respectively. In other embodiments, air resistance upon launch and the stowed configuration of the stabilizer 125 and the propeller blades 510 (e.g., first stabilizer configuration 450) creates an expansion vector force that causes the stabilizer 125 and the propeller blades 510 to deploy in the deployed configuration (e.g., second stabilizer configuration 455).

[0097] The controller 1500 (e.g., an on-board computing device) can automatically engage the actuators and wing deployment mechanisms immediately after launch, or after a set time has elapsed. In other embodiments, engagement may occur upon specific readings from on-board sensors (e.g., including but not limited to sensors deployed on the modular payload 140). For example, wing deployment and extension may depend on certain on-board factors, such as, for example, the speed, acceleration, and leveling of the UAVDC. The controller 1500 may be configured to trigger the deployment of various components when certain pre-set conditions are met. Such conditions may be defined prior to deployment.

[0098] The actuator 210 can drive the sweep gearbox 205 to sweep the wing 110. In some embodiments, the UAVDC can control sustained flight once the wing 110 has swept 45 degrees. Once the wing 110 reaches full sweep, the wing 110 moves into the wing hole notch 1115 of the fairing 130 that was opened by the stress of the sweeping motion 250 and is locked again with the help of magnets positioned within the fuselage. Thus, the fairing 130 can automatically slam shut around the contour of the wing 110 to improve aerodynamic performance. The magnets 1125 can further lock the fairing 130 around the wing 110.

[0099] As the wing 110 begins to sweep or after the wing 110 is fully swept, the wing 110 can begin to telescope. For example, the belt system 315 can pull the outer portion 310 along the inner portion 305 to telescope the wing 110. The wing sweep angle and telescope position can further be dynamically adjusted during flight.

[0100] Additionally, in deployable embodiments, the modular payload 140 may be deployed from its first configuration to a second configuration. For example, the modular payload 140 may include multiple sensing devices better positioned for performance in a deployed position (e.g., extended boom). Such deployment may occur during a stabilized segment of the flight of the UAVDC after launch.

[0101] Method 1400 may proceed from stage 1420, where flight components are deployed and UAVDC flight is stabilized, to stage 1430, where the UAVDC may be used to perform a mission. During all stages of flight, the UAVDC may be in operative communication with an operator via antenna 705. The operator may receive various readings from various components of the UAVDC.

[0102] In some embodiments, an operator can control the operation of the UAVDC during a mission. For example, the operator can control flight components including, but not limited to, the wing deployment mechanism (e.g., sweep gearbox 205, actuator 210, and belt system 315), propeller 135, stabilizer 125, aileron 120, and further deployable components (e.g., telescoping boom 710 for antenna 705, and boom 655 for antenna 650). In other embodiments, on-board controller 1500 can be pre-configured with mission control data.

[0103] UAVDC embodiments may be used for multiple missions, including, but not limited to, data acquisition, payload deployment, and providing electrical communication relay. UAVDC embodiments may be controlled in data acquisition and transmission, in addition to communications for flight control. In further embodiments, UAVDC may enable an operator to release modular payloads 140.

[0104] Method 1400 may proceed from stage 1430, where the UAVDC is used to perform a mission, to stage 1440, where the mission is terminated. For example, the mission may be terminated by flying the UAVDC to a recoverable recapture location. Additionally, the UAVDC may terminate the mission by a crash landing. For example, the UAVDC may crash into a rock or hard surface to destroy functional components. In further embodiments, the UAVDC may be equipped with a demolition device to self-destruct upon mission completion. After stage 1440, method 1400 may end at stage 1450.

[0105] IV. Onboard system architecture The UAVDC may include, but is not limited to, an on-board computing module. The computing module may be in operational configuration, for example, but not limited to, in communication with the modular payload 140, the sweep gearbox actuator 210, the control mechanism (e.g., servo mechanism 1320) for the aileron 120, the servo mechanism 410 for the stabilizer 125, the motor 1315 for driving the propeller 135, the power source 1310, the global positioning system, various telemetry sensors, and the antenna 705. Additionally, the computing device may be in operational communication with another computing device according to the description herein, and may include, but is not limited to, a desktop computer, a laptop, a tablet, or a mobile communication device. Such remote devices may be used to control and / or configure the on-board computing module (e.g., deployment conditions, mission control, etc.).

[0106] Additionally, the UAVDC may be in operative communication with a centralized server, such as, for example, a cloud computing service. Although operations are described as being performed in part by the controller 1500, it should be understood that in some embodiments, different operations may be performed by different network elements in operative communication with the controller 1500.

[0107] An embodiment of the present disclosure may include a system having a memory storage device and a processing unit. The processing unit may be coupled to the memory storage device, the processing unit configured to perform the steps of the method 1400.

[0108] FIG. 15 is a block diagram of a system including a controller 1500. According to an embodiment of the disclosure, the memory storage and processing unit described above may be implemented in a computing device such as the controller 1500 of FIG. 15. Any suitable combination of hardware, software, or firmware may be used to implement the memory storage and processing unit. For example, the memory storage and processing unit may be implemented with the controller 1500 or in combination with any of the other UAVDC devices and components 1518. The other UAVDC devices and components 1518 may include, for example, but are not limited to, the modular payload 140, the sweep gearbox actuator 210, the control mechanisms for the ailerons 120 (e.g., servo mechanisms 1320), the servo mechanisms 410 for the stabilizers 125, the motors 1315 that drive the propellers 135, the power source 1310, the global positioning system, various telemetry sensors, and the antennas 705. The above-mentioned systems, devices, and processors are examples, and other systems, devices, and processors may include the above-mentioned memory storage devices and processing units according to embodiments of the present disclosure.

[0109] With reference to FIG. 15, a system according to an embodiment of the present disclosure may include a computing device such as a controller 1500. In a basic configuration, the controller 1500 may include at least one processing unit 1502 and a system memory 1504. The system memory 1504 may comprise, but is not limited to, volatile (e.g., random access memory (RAM)), non-volatile (e.g., read only memory (ROM)), flash memory, or any combination, depending on the configuration and type of computing device. The system memory 1504 may include an operating system 1505, one or more programming modules 1506, and may include program data 1507. For example, the operating system 1505 may be adapted to control the operation of the controller 1500. In one embodiment, the programming module 1506 may include a flight control application 1520. Additionally, embodiments of the present disclosure may be implemented with graphics libraries, other operating systems, or any other application programs, and are not limited to any particular application or system. This basic configuration is illustrated in FIG. 15 with those components within dashed line 1508.

[0110] The controller 1500 may have additional features or functionality. For example, the controller 1500 may further include additional data storage devices (removable and / or non-removable), such as, for example, magnetic disks, optical disks, or tape. Such additional storage is illustrated in FIG. 15 by removable storage 1509 and non-removable storage 1510. Computer storage media may include volatile and non-volatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules, or other data. The system memory 1504, the removable storage 1509, and the non-removable storage 1510 are all examples of computer storage media (i.e., memory storage devices). The computer storage medium may include, but is not limited to, RAM, ROM, Electrically Erasable Read Only Memory (EEPROM), flash memory or other memory technology, CD-ROM, digital versatile disk (DVD) or other optical storage, magnetic cassette, magnetic tape, magnetic disk storage or other magnetic storage device, or any other medium usable to store information and accessible by the controller 1500. Such computer storage medium may be part of the device 1500. The controller 1500 may further cooperate with input device(s) 1512, such as a keyboard, mouse, pen, voice input device, touch input device, etc. The input device(s) 1512 may be used, for example, to manually access and program the controller 1500. Output device(s) 1514, such as a display, speaker, printer, etc. may also be included. The above devices are merely examples and other devices may be used.

[0111] The controller 1500 may further include communication connections 1516 that enable the device 1500 to communicate with other UAVDC devices and components 1518 (e.g., antenna 705), for example, over an encrypted network in a distributed computing environment. The communication connections 1516 are an example of a communication medium. Communication media may typically be embodied by computer-readable instructions, data structures, program modules, or other data in a modulated data signal, such as a carrier wave or other transport mechanism, and includes any information delivery media. The term "modulated data signal" may refer to a signal that has one or more characteristics set or changed in such a manner as to encode information in the signal. By way of example, and not limitation, communication media may include wired media, such as a wired network or direct-wired connection, and wireless media, such as acoustic, radio frequency (RF), infrared, and other wireless media. As used herein, the term computer-readable media may include both storage media and communication media.

[0112] As mentioned above, a number of program modules and data files may be stored in the system memory 1504, including the operating system 1505. While executing on the processing unit 1502, the programming module 1506 (e.g., controller application 1520) may perform processes including, for example, one or more stages or portions of stages of the method 1400, as described above. The controller application 1520 may be configured to operate the UAVDC devices and components 1518, for example, to receive instructions from the communication connection module 1516. The process described above is an example, and the processing unit 1502 may perform other processes.

[0113] Generally, in accordance with embodiments of the present disclosure, program modules may include routines, programs, components, data structures, and other types of structures that may perform particular tasks or implement particular abstract data types. Additionally, embodiments of the present disclosure may be practiced with other computer system configurations, including handheld devices, multiprocessor systems, microprocessor-based or programmable consumer electronics, minicomputers, mainframe computers, and the like. Additionally, embodiments of the present disclosure may also be practiced in distributed computing environments where tasks are performed by remote processing devices that are linked through a communications network. In a distributed computing environment, program modules may be located in both local and remote memory storage devices.

[0114] Furthermore, embodiments of the present disclosure may be implemented on electronic circuits with discrete electronic elements, packaged or integrated electronic chips containing logic gates, circuits utilizing microprocessors, or single chips containing electronic elements or microprocessors.Embodiments of the present disclosure may also be implemented using other technologies capable of performing logical operations such as, for example, AND, OR, and NOT, including, but not limited to, mechanical, optical, fluidic, and quantum technologies.Furthermore, embodiments of the present disclosure may be implemented within a general purpose computer or in any other circuit or system.

[0115] The embodiments of the present disclosure may be implemented, for example, as a computer process (method), a computing system, or as an article of manufacture, such as a computer program product or a computer readable medium. The computer program product may be a computer storage medium readable by a computer system and encoding a computer program of instructions for executing a computer process. The computer program product may further be a propagated signal on a carrier wave readable by a computing system and encoding a computer program of instructions for executing a computer process. Thus, the present disclosure may be embodied in hardware and / or software (including firmware, resident software, microcode, etc.). In other words, the embodiments of the present disclosure may take the form of a computer program product on a computer usable or computer readable storage medium having embodied therein computer usable or computer readable program code for use by or in conjunction with an instruction execution system. The computer usable or computer readable medium may be any medium capable of containing, storing, communicating, propagating, or carrying a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0116] The computer usable or computer readable medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, device, or propagation medium. In more specific computer readable medium examples (non-limiting list), the computer readable medium may include an electrical connection having one or more wires, a portable computer diskette, a random access memory (RAM), a read only memory (ROM), an erasable programmable read only memory (EPROM or flash memory), an optical fiber, and a portable compact disk read only memory (CD-ROM). It should be noted that the computer usable or computer readable medium may be a paper or other suitable medium on which the program is printed, since the program may be captured electronically, for example, via optical scanning of the paper or other medium, and then compiled, interpreted, or processed in an appropriate manner as required, and then stored in the computer memory.

[0117] The embodiments of the present disclosure are described above with reference to, for example, block diagrams and / or operational diagrams of methods, systems, and computer program products according to the embodiments of the present disclosure. The functions / acts described in the blocks may occur out of the order shown in the flowcharts. For example, two blocks shown in succession may in fact be executed substantially simultaneously or the blocks may be executed in the reverse order depending on the functions / acts involved.

[0118] Although specific embodiments of the present disclosure have been described, other embodiments may exist. Additionally, although the embodiments of the present disclosure have been described as relating to data stored in memory and other storage media, the data may be stored in or read from other types of computer-readable media, such as secondary storage such as hard disks, solid-state storage (e.g., USB drives), or CD-ROMs, carrier waves from the Internet, or other forms of RAM or ROM. Additionally, the steps of the disclosed methods may be modified in any manner, for example, by changing the order of steps and / or inserting or deleting steps, without departing from the present disclosure.

Claims

1. 1. An unmanned aerial vehicle (UAV), the UAV comprising a fuselage including at least one wing and at least one stabilizer; The at least one wing and the at least one stabilizer include at least: a compact arrangement including the at least one wing stowed against the fuselage and the at least one stabilizer stowed against the fuselage; a deployment configuration including the at least one wing deployed from the fuselage and the at least one stabilizer deployed from the fuselage; and the at least one wing is telescopically extended to increase the wingspan of the deployed configuration. can be configured to the at least one wing comprises an outer portion including a substantially hollow interior and an inner portion configured to be attached to the fuselage and stored within the interior in the compact configuration, the outer portion being telescopically extended along a length of the inner portion in the extended configuration; the UAV comprising at least one control surface hinged to an outer surface of a trailing edge of the outer portion, the at least one control surface operable when the UAV is transitioning from the compact configuration to the deployed configuration to stabilize the UAV for a subsequent transition to the extended configuration; The at least one control surface attachment along the outer surface of the trailing edge of the outer portion enables the inner portion to overlap at least a portion of a length of the attachment when the inner portion is stored within the interior of the outer portion in the compact configuration.

2. The UAV of claim 1 , further comprising a sweep means for deploying the at least one wing from the compact configuration to the deployed configuration.

3. The UAV of claim 1 , further comprising a telescoping means for extending the wingspan of the at least one wing from the deployed configuration to the extended configuration.

4. 2. The UAV of claim 1, wherein the at least one stabilizer is configured to deploy from the compact configuration to the deployed configuration by a spring configured to bias the at least one stabilizer to the deployed configuration.

5. The UAV of claim 1 further comprising a propulsion means.

6. The UAV of claim 5 , wherein the propulsion means comprises at least one blade.

7. The at least one blade comprises: stored against the fuselage in the compact configuration; The UAV of claim 6 , deployed from the fuselage in the deployed configuration and the extended configuration.

8. The UAV of claim 1 , further comprising a modular payload fuselage section.

9. The UAV of claim 1 , further comprising a deployable payload including a first configuration of the compact configuration and a second configuration of at least one of the deployed configuration and the extended configuration.

10. The UAV of claim 1 , wherein the compact configuration allows the UAV to be stored in at least one of a tube, a weapons storage bay, and a wing mounting.

11. The UAV of claim 1 , wherein the deployment configuration is configured to stabilize the UAV in controlled flight.

12. 12. The UAV of claim 11, wherein the deployed configuration configured to stabilize the UAV into the controlled flight includes the at least one wing and the at least one stabilizer configured to deploy into the deployed configuration after being released from at least one of a tube, a weapons bay, and a wing attachment.

13. The UAV of claim 1 , wherein the extended configuration is configured to increase efficiency of controlled flight.

14. 14. The UAV of claim 13, wherein the extended configuration configured to increase the efficiency of the controlled flight includes the at least one wing configured to extend and retract when stabilized in the controlled flight.

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