Patent Publication Number: US-2023142917-A1

Title: Aerial vehicle with deployable components

Description:
RELATED APPLICATIONS 
     The present application is a continuation of U.S. application Ser. No. 16/700,436 filed on Dec. 2, 2019, which issues on Jan. 3, 2023 as U.S. Pat. No. 11,541,986, which is a continuation of U.S. application Ser. No. 15/388,433 filed on Dec. 22, 2016, which issued on Dec. 3, 2019 as U.S. Pat. No. 10,494,081, which is a continuation of U.S. application Ser. No. 15/092,237 filed on Apr. 6, 2016, which issued on Jan. 31, 2017 as U.S. Pat. No. 9,555,873, which claims benefit of U.S. Provisional Application No. 62/254,098 filed on Nov. 11, 2015, each of which are hereby incorporated by reference herein in their entirety. 
    
    
     Related U.S. patent application Ser. No. 15/092,219 filed on Apr. 6, 2016, which issued on Feb. 28, 2017 as U.S. Pat. No. 9,580,165, is hereby incorporated by reference herein in its entirety. 
     Related U.S. patent application Ser. No. 15/092,257 filed on Apr. 6, 2016, which issued on Jan. 17, 2017 as U.S. Pat. No. 9,545,991, is hereby incorporated by reference herein in its entirety. 
     It is intended that each of the referenced applications may be applicable to the concepts and embodiments disclosed herein, even if such concepts and embodiments are disclosed in the referenced applications with different limitations and configurations and described using different examples and terminology. 
     FIELD OF DISCLOSURE 
     The present disclosure generally relates to unmanned aerial vehicles. 
     Unmanned aerial vehicles may be used for a plurality of applications. Such applications comprise commercial applications including surveillance and filming, and for military applications, reconnaissance and tactical missions. In certain circumstances, compact configurations can be beneficial to enabling particular types of missions. For example, compact configurations reduce space and enable various deployment options. 
     However, current compact configurations are limited in flight range, endurance, and payload capacity. 
     BRIEF OVERVIEW 
     Embodiments of the present disclosure provide an improved aerial vehicle with deployable components. This brief overview is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This brief overview is not intended to identify key features or essential features of the claimed subject matter. Nor is this brief overview intended to be used to limit the claimed subject matter&#39;s scope. 
     An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. 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 plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one stabilizer stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one stabilizer deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. 
     In various embodiments, a UAVDC with a telescoping wing system may be provided. The telescoping wing system may comprise a first wing section comprising a substantially hollow interior, a second wing section configured to be stowed within the interior of the first wing section. The second wing section may comprise an actuator configured to drive a belt coupled to the internal surface of the first wing section such that, upon actuation, a displacement of the attached segment of the belt causes the first wing section to traverse at least a portion of a length of the second wing section. 
     In the first configuration, the first wing section and the second wing section may form a first wingspan in a first arrangement, the first arrangement comprising the second wing section stowed within the interior of the first wing section. In a second configuration, the first wing section and the second wing section may form a second wingspan in a second arrangement, the second arrangement comprising the first wing section displaced along at least a portion of the length of the second wing section. 
     Still consistent with embodiments of the present disclosure, the UAVDC may comprise a fuselage, and at least one stabilizer configured to pivot about a first axis and a second axis. The at least one stabilizer may be configurable in at least the following arrangements: a compact arrangement comprising, wherein the at least one stabilizer is stowed against the fuselage, and a deployed arrangement, wherein the least one stabilizer is deployed from the fuselage by pivoting about the first axis. 
     The UAVDC may further comprise a pushrod configured to pivot the at least one stabilizer about the second axis. In some embodiments, the UAVDC may comprise a flexible fairing at the base of the stabilizer configured to enable the stabilizer to pivot about second axis while maintaining an aerodynamic efficiency. 
     In yet further embodiments, the UAVDC may comprise a fuselage comprising a modular payload section; at least one wing configurable in a first arrangement and a second arrangement, wherein the first arrangement comprises the at least one wing stowed against the fuselage, and wherein the second arrangement comprises the wings deployed for flight at a first deployment angle; a fairing positioned relatively at a base of the at least one wing, the fairing being constructed of a flexible material comprising at least one slit and at least one cutout designed to enabling a sweeping of the at least one wing from the first arrangement to the second arrangement, the fairing being configurable in: a first configuration to accommodate the first arrangement, and a second configuration to accommodate the second arrangement; an actuator coupled to a sweeping gearbox configured to actuate the sweeping of the at least one wing from the first arrangement to the second arrangement. 
     As will be detailed below, it should be understood that a single wing may be comprised of two left and right wing sections (a first section and a second section). The two wing sections may, throughout the present disclosure, be referred to as two wings or two wing segments. Accordingly, in some embodiments, the two wings may stacked against the fuselage in the first arrangement, the stacked configuration comprising a top wing and a bottom wing with the top wing vertically offset from the bottom wing in the first arrangement. In yet further embodiments, at a transition from the first arrangement to the second arrangement, the two wings may be configured to telescope to expand a wing span in the second arrangement. 
     Embodiments of the present disclosure may further comprise at least one control surface (e.g., a stabilizer) configured to deploy from a first stabilizer configuration stowed against the fuselage to a second stabilizer configuration deployed for flight at a second deployment angle. 
     In some embodiments, deployment of the at least one stabilizer may employ at least one spring, wherein the at least one spring is configured to force the at least one stabilizer from the first stabilizer configuration to the second stabilizer configuration. 
     The UAVDC may further comprise a propulsion mechanism. In some embodiments, the propulsion mechanism may comprise a propeller, wherein the propeller comprises at least one blade configured to fold into a first propeller arrangement and expand in a second propeller arrangement. The fuselage may comprise 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 unfold to the second propeller arrangement by means of at least one of the following: propeller blade springs, aerodynamic force, or a centripetal force from a rotation of the propeller. 
     Still consistent with embodiments of the present disclosure, methods and systems for deploying the wings of the UAVDC into a second arrangement are disclosed. For example, after a launch of the UAVDC, the UAVDC may monitor for at least one pre-set condition. The at least one pre-condition may be associated with deploying wings of the UAVDC into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAVDC may be deployed into a second arrangement. Deploying the wings may comprise activating, in response to detecting the at least one pre-set condition associated with the UAVDC, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment. 
     In some embodiments, the at least one pre-set condition comprises at least one of the following: velocity, acceleration, and leveling associated with the UAV upon determining that UAV has launched. 5. In some embodiments, deploying the at least one additional flight component further comprises deploying at least one stabilizer. Still, in further embodiments, deploying the wings of the UAV comprises deploying the wings of the UAV when it is determined that the UAV has traveled a certain distance after launching. Consistent with embodiments of the present disclosure, the UAVDC may be configured to maintain roll control of the UAV in the expanded arrangement by actuating the at least one control surface on the wings of the UAV and/or by actuating the at least one stabilizer. 
     Both the foregoing brief overview and the following detailed description provide examples and are explanatory only. Accordingly, the foregoing brief overview and the following detailed description should not be considered to be restrictive. Further, features or variations may be provided in addition to those set forth herein. For example, embodiments may be directed to various feature combinations and sub-combinations described in the detailed description. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The accompanying drawings, which are incorporated in and constitute a part of this disclosure, illustrate various embodiments of the present disclosure. The drawings contain representations of various trademarks and copyrights owned by the Applicants. In addition, the drawings may contain other marks owned by third parties and are being used for illustrative purposes only. All rights to various trademarks and copyrights represented herein, except those belonging to their respective owners, are vested in and the property of the Applicants. The Applicants retain and reserve all rights in their trademarks and copyrights included herein, and grant permission to reproduce the material only in connection with reproduction of the granted patent and for no other purpose. 
       Furthermore, the drawings may contain text or captions that may explain certain embodiments of the present disclosure. This text is included for illustrative, non-limiting, explanatory purposes of certain embodiments detailed in the present disclosure. In the drawings: 
         FIG.  1 A  illustrates an unmanned aerial vehicle with deployable components in a first configuration; 
         FIG.  1 B  illustrates the unmanned aerial vehicle with deployable components in a second configuration; 
         FIG.  1 C  illustrates the unmanned aerial vehicle with deployable components in a third configuration; 
         FIG.  2 A  illustrates a cut-away view of a sweeping gearbox coupled to an actuator; 
         FIG.  2 B  illustrates a view of the sweeping gearbox; 
         FIG.  2 C  illustrates another view of the sweeping gearbox and a direction of wing sweeping; 
         FIG.  2 D  illustrates a set of schematic drawings for enabling the sweeping gearbox to allow wings to have dihedral and incidence when deployed and to lay flat while stowed; 
         FIG.  3    illustrates an example of telescoping wings; 
         FIG.  4 A  illustrates an example of stabilizers in a first configuration; 
         FIG.  4 B  illustrates an example of the stabilizers in a second configuration; 
         FIG.  4 C  illustrates another view of the stabilizers in the first configuration; 
         FIG.  4 D  illustrates another view of the stabilizers in the second configuration; 
         FIG.  4 E  illustrates an example of stabilizers in a first pivot angle; 
         FIG.  4 F  illustrates an example of stabilizers in a second pivot angle; 
         FIG.  4 G  illustrates an example of stabilizers in a third pivot angle; 
         FIG.  5    illustrates an example of deployable propeller blades and a direction of deployment; 
         FIG.  6 A  illustrates an example of a modular payload; 
         FIG.  6 B  illustrates an example of a modular payload with deployable components in a first configuration; 
         FIG.  6 C  illustrates an example of the modular payload with deployable components in a second configuration; 
         FIG.  6 D  illustrates an example of another modular payload in a compact configuration; 
         FIG.  6 E  illustrates an example of the modular payload in a deployed configuration; 
         FIG.  7    illustrates potential positions for an antenna; 
         FIG.  8    illustrates a propeller and associated components; 
         FIG.  9    illustrates grooves in the fuselage configured to receive propeller blades in a folded configuration; 
         FIG.  10 A  illustrates a propeller blade confined by wings; 
         FIG.  10 B  illustrates a deployed propeller blade oriented with a free stream; 
         FIG.  11 A  illustrates a fairing in a first configuration; 
         FIG.  11 B  illustrates the fairing in a second configuration; 
         FIG.  11 C  illustrates the fairing comprising magnets; 
         FIG.  12 A  illustrates components for controlling ailerons; 
         FIG.  12 B  illustrates a plurality of configurations for the ailerons; 
         FIG.  13    illustrates one example of internal configuration of the UAVDC; 
         FIG.  14    illustrates a method for using the unmanned aerial vehicle with deployable components; and 
         FIG.  15    is a block diagram of a system including a computing device for enabling operation of the apparatus. 
     
    
    
     DETAILED DESCRIPTION 
     As a preliminary matter, it will readily be understood by one having ordinary skill in the relevant art that the present disclosure has broad utility and application. As should be understood, any embodiment may incorporate only one or a plurality of the above-disclosed aspects of the disclosure and may further incorporate only one or a plurality of the above-disclosed features. Furthermore, any embodiment discussed and identified as being “preferred” is considered to be part of a best mode contemplated for carrying out the embodiments of the present disclosure. Other embodiments also may be discussed for additional illustrative purposes in providing a full and enabling disclosure. Moreover, many embodiments, such as adaptations, variations, modifications, and equivalent arrangements, will be implicitly disclosed by the embodiments described herein and fall within the scope of the present disclosure. 
     Accordingly, while embodiments are described herein in detail in relation to one or more embodiments, it is to be understood that this disclosure is illustrative and exemplary of the present disclosure, and are made merely for the purposes of providing a full and enabling disclosure. The detailed disclosure herein of one or more embodiments is not intended, nor is to be construed, to limit the scope of patent protection afforded in any claim of a patent issuing here from, which scope is to be defined by the claims and the equivalents thereof. It is not intended that the scope of patent protection be defined by reading into any claim a limitation found herein that does not explicitly appear in the claim itself. 
     Thus, for example, any sequence(s) and/or temporal order of steps of various processes or methods that are described herein are illustrative and not restrictive. Accordingly, it should be understood that, although steps of various processes or methods may be shown and described as being in a sequence or temporal order, the steps of any such processes or methods are not limited to being carried out in any particular sequence or order, absent an indication otherwise. Indeed, the steps in such processes or methods generally may be carried out in various different sequences and orders while still falling within the scope of the present invention. Accordingly, it is intended that the scope of patent protection is to be defined by the issued claim(s) rather than the description set forth herein. 
     Additionally, it is important to note that each term used herein refers to that which an ordinary artisan would understand such term to mean based on the contextual use of such term herein. To the extent that the meaning of a term used herein—as understood by the ordinary artisan based on the contextual use of such term—differs in any way from any particular dictionary definition of such term, it is intended that the meaning of the term as understood by the ordinary artisan should prevail. 
     Regarding applicability of 35 U.S.C. §112, ¶6, no claim element is intended to be read in accordance with this statutory provision unless the explicit phrase “means for” or “step for” is actually used in such claim element, whereupon this statutory provision is intended to apply in the interpretation of such claim element. 
     Furthermore, it is important to note that, as used herein, “a” and “an” each generally denotes “at least one,” but does not exclude a plurality unless the contextual use dictates otherwise. When used herein to join a list of items, “or” denotes “at least one of the items,” but does not exclude a plurality of items of the list. Finally, when used herein to join a list of items, “and” denotes “all of the items of the list.” 
     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. While many embodiments of the disclosure may be described, modifications, adaptations, and other implementations are possible. For example, substitutions, additions, or modifications may be made to the elements illustrated in the drawings, and the methods described herein may be modified by substituting, reordering, or adding stages to the disclosed methods. Accordingly, the following detailed description does not limit the disclosure. Instead, the proper scope of the disclosure is defined by the appended claims. The present disclosure contains headers. It should be understood that these headers are used as references and are not to be construed as limiting upon the subjected matter disclosed under the header. 
     The present disclosure includes many aspects and features. Moreover, while many aspects and features relate to, and are described in, the context of unmanned aerial vehicles, embodiments of the present disclosure are not limited to use only in this context. For example, embodiments of the present disclosure may be employed on manned and unmanned aerial vehicles. 
     I. OVERVIEW 
     This overview is provided to introduce a selection of concepts in a simplified form that are further described below. This overview is not intended to identify key features or essential features of the claimed subject matter. Nor is this overview intended to be used to limit the claimed subject matter&#39;s scope. 
     An improved unmanned aerial vehicle with deployable components (UAVDC) is provided in the various embodiments disclosed herein. Various aspects of the UAVDC lead to improvements over conventional unmanned aerial vehicles, including, but not limited to, for example, improved portability, deployment, post-deployment transition to flight control, aerodynamic efficiency and flight endurance, payload capacity, and maximized mission capability over conventional unmanned aerial vehicles. As will be detailed below, the UAVDC of the present disclosure includes a number of features that lead to the aforementioned improvements, including, but not limited to, for example, trailing-edge hinged ailerons, deployable stabilizers, gearbox, fairing, and sweeping and telescoping wing implementations. 
     The UAVDC may be configured in a plurality of arrangements. A first configuration may be a compact arrangement suitable in, for example, storage and launching embodiments, while a second configuration may be a deployed arrangement suitable in, for example, launch recovery and flight, and a third configuration may be an expanded configuration suitable in, for example, high-endurance flight. As will be detailed below, the UAVDC may be fully functional and operable in intermediary configurations between these three configurations to provide some of the advantages of the improved UAVDC at higher airspeeds. 
       FIG.  1 A  illustrates an example of a first configuration (e.g., compact arrangement  102 ). Compact arrangement  102  may enable convenient storage and transportation of the UAVDC. In addition, compact arrangement  102  may enable certain launch methods, such as a launch from, for example, a tube or a release from, for example, an aircraft&#39;s weapons/bomb bay or wing attachment. 
     Consistent with embodiments of the present disclosure, the UAVDC may be deployed after launch into the deployed arrangement that is suitable to survive the high aerodynamic loads of launch recovery and high-speed flight. During the flight, the UAVDC may be further deployed into the expanded arrangement that is suitable for efficient, long-endurance flight. It should be understood that the term “deploy” and “deployment” may refer to the deployable components moving from one UAVDC configuration to another. 
       FIG.  1 B  illustrates an example of a second configuration (e.g., deployed arrangement  104 ). By using a deployed arrangement  104 , embodiments may be able sustain the higher aerodynamics loads associated with flight at a high airspeed or high-g pull-up maneuvers. In this way, at least one of the intermediary configurations (e.g., the deployed arrangement  104 ) may be used in a launch recovery, wherein the UAVDC has been launched and has not slowed to an airspeed that the third configuration can sustain. Furthermore, the deployed arrangement may be able to sustain high-speed flight more efficiently than the expanded arrangement. 
       FIG.  1 C  illustrates an example of a third configuration (e.g., an expanded arrangement  105 ). By using the expanded arrangement the UAVDC may be able to achieve an increased level of aerodynamic efficiency (i.e., flight endurance) as well as an increased payload weight capacity. In various embodiments, the second configuration (e.g., deployed arrangement  104 ) and the third configuration (e.g., expanded arrangement  105 ) may be referred to as a common arrangement, but having wingspans that depend on the extent of the telescoped displacement of the wings. 
     As will be detailed below, during transformation from compact arrangement  102  to expanded arrangement  105 , a UAVDC consistent with embodiments of the present disclosure may implement, but not be limited to, at least one of the following: wings  110  that may be configured to sweep and/or telescope, one or more trailing-edge hinged control surfaces that enable roll control (“ailerons”)  120 , one or more fold-away actuating stabilizers  125 , one or more flexible aerodynamic fairings  130 , one or more propulsion mechanisms (e.g., fold-away propeller  135 ), and a modular payload  140 . 
     In further embodiments, the UAVDC may comprise intermediary configurations between the first configuration and second configuration or the second configuration and the third configuration. In the intermediary configurations, wings  110  may be at various stages of sweep or telescoping. It should be understood that the use of trailing-edge ailerons  120  and externally telescoped outer wing panels  310  may enable the UAVDC to continuously maintain controlled flight during transitions from the first configuration to the third configuration. 
     In the first configuration, prior to deployment, the aforementioned wings  110 , stabilizers  125 , and propeller  135  may be stowed against a fuselage  106  of the UAVDC (i.e., folded and out of the way during vehicle launch). Fairing  130  may flex to accommodate wings  110  in their stowed configuration and then be configured to flex in a way so as to accommodate a sweeping motion of wings  110 . Once launched, the UAVDC may transform from the first configuration into the second configuration. In the second configuration, wings  110  may be deployed by way of an outward sweeping motion (with fairing  130  flexing in a way to enable the sweeping motion).  FIG.  2 C  illustrates an outward sweeping motion  250 . As will be further detailed below, outward sweeping motion  250  may be enabled by, but not limited to, for example, a sweeping gearbox coupled to an actuator.  FIGS.  2 A- 2 C  illustrate an example of a sweeping gearbox  205  coupled to an actuator  210 . Further, sweeping motion  250  of wings  110  may enable configurable wing angles to optimize aerodynamics. Fairing  130  may be designed to accommodate wings  110  in the stored configuration as well as sweeping motion  250 . Further, fairing  130  may close around wings  110  in order to maintain the aerodynamic integrity of the UAVDC, as shown in  FIG.  11 B . 
     By implementing a gearbox  205  configured to sweep wings  110  as well as orient wings  110  with optimal dihedral angles  265  and angles of incidence  275 , embodiments of the present disclosure may provide improvements over conventional systems. For example, in conventional systems, aircrafts that implement sweeping wings and wing angle adjustments require use of secondary mechanics to orient the wing angles. Such secondary mechanics add to weight and cost, as well as provide additional modes of failure. 
     Still consistent with embodiments of the present disclosure, wings  110  may further be configured to telescope (i.e., expand in length) in the third configuration. Such telescoping wings may comprise a fixed inner section and one or more substantially hollow outer sections that slide along adjacent sections to provide a longer wingspan once deployed.  FIG.  3    illustrates an example of telescoping wings  110  comprising a fixed inner section  305  that attaches to fuselage  106  and an outer section  310 . In further embodiments, a plurality of nested outer wing sections may be implemented. In this way, wings  110  may be stored in a compact arrangement  102  and later extend (i.e., telescope) to provide additional lift during the expanded arrangement  105 . As will be detailed below, a telescoping mechanism (“telescoping means”) consistent with embodiments of the present disclosure may employ, for example, a belt system  315 , a scissors mechanism, or a piston mechanism to extend and/or retract the wings. 
     The telescoping means consistent with embodiments of the present disclosure enable a maximized wing span while maintaining roll control throughout the transition between configurations. For example, as the inner section is fixed, the outer sections may comprise a substantially hollow interior so as to enable the fixed inner section to reside within the interior of the outer section. The outer section may then slide outwards (i.e., telescopes), away from fuselage  106 , thereby exposing the fixed inner section as it telescopes. The trailing-edge mounted control surfaces (e.g., ailerons  120 ) are mounted to the outer section and are therefore exposed and operable throughout the deployment and telescoping process; in this way, the wingspan of the UAVDC can expand while continually maintaining controlled flight during the transition (e.g., regardless of the outer section position relative to the inner section position). 
     In some embodiments, inner section  305  connects to the fuselage  106 , while outer section  310  may be telescoped outward from fuselage  106 . Trailing-edge ailerons  120  may connect to outer section  310  to enable roll control. In this way, trailing-edge ailerons  120  may provide roll control even when wings  110  are not extended. Trailing-edge ailerons  120  may be connected by a hinge at a rear-most point of the wing in order to maximize an internal volume of the outer section  310 , which, in turn, maximizes the overall span of the wing  110  in its 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. 
     By implementing hollow outer telescoping wing section  310  and trailing-edge hinged aileron  120 , a plurality of improvements are introduced. A typical telescoping wing utilizes telescoping outer panels that are stored within the fixed inner panel, this precludes the use of ailerons mounted to the outer panels until the wing panels reach a telescoped state. Furthermore, conventional aileron implementations are configured within the wing surface itself, thereby reduce the amount of internal volume available in the wing. The reduced internal volume decreases the available depth of an interior wing section placement in a telescoping wing system, thereby leading to a smaller displacement in a telescoped configuration. In this way, conventional roll control surfaces may reduce the final length of a telescoped wing. 
     Attaching trailing-edge hinged ailerons  120  to the outer section  310  of the telescoping wing  110  enables the inner section  305  of telescoping wing  110  to be stowed further within the interior of outer section  310  while still providing the necessary roll control to maintain flight in the deployed arrangement, before the wings are telescoped. In turn, when wings  110  are telescoped, the displacement of the outer section  310  is increased by a range greater than that of other telescoping wing systems, thereby leading to the benefits of increased wingspan over a conventional aerial vehicle capable of compact configurations. Further still, extending outer section  310  of the telescoping wing  110  from the fuselage further enables the trailing-edge hinged ailerons  120  to provide increased roll control of the UAVDC. 
     Consistent with embodiments of the present disclosure, the control surfaces (e.g., trailing-edge hinged ailerons  120 ) may be operable in all of the UAVDC&#39;s configurations. That is, the control surfaces may be operable in the compact arrangement  102 , the deployed arrangement  104 , and in the expanded arrangement  105 . Furthermore, the control surfaces may be operable during the transitionary phases between each of those arrangement. 
     For example, trailing-edge hinged ailerons  120  may be operable in between the first configuration (e.g., compact arrangement  102 ) and the deployed arrangement  104  (e.g., engaged in operation at approximately a 45-degree sweep) in order to provide post-launch stabilization for the UAVDC. Moreover, trailing-edge hinged ailerons  120  may be operable when the UAVDC is in the deployed arrangement  104  to provide flight control, as well as the transitionary stage between the deployed arrangement  104  and the expanded arrangement  105 . Finally, trailing-edge hinged ailerons  120  may be operable in the expanded arrangement  105  to provide additional, more effective flight control. 
     One or more stabilizers  125  of the UAVDC may be deployed in the intermediary configurations, second configuration, and/or the third configuration. Stabilizers  125  may deploy from a first stabilizer configuration  450  to a second stabilizer configuration  455  by rotating about axis  430 , as shown in  FIGS.  4 A- 4 D . Once in the second stabilizer configuration  455 , stabilizer  125  can further serve as a control surface, providing flight control by pivoting about axis  425 . As will be detailed below, deployment about axis  430  may be implemented via, for example, pre-loaded springs  405 . In further embodiments, stabilizers  125  may be deployed upon interfacing with air resistance. For example, when stabilizers  125  interface with an airstream, a resulting drag force may cause stabilizers  125  to move into a deployed configuration. Servos  410  may actuate the stabilizers  125  about axis  425  once stabilizers  125  are deployed.  FIGS.  4 E- 4 G  illustrate the stabilizer  125  in the deployed configuration, at various pivot angle about axis  425 . 
     Deployable control surfaces, embodied in the present disclosure as stabilizers  125 , are improved over conventional systems, for example, by enabling automatic deployment without requiring controlling components (e.g., actuators and linkages) to adjust. Further, by implementing a flexible fairing, the aerodynamic efficiencies may be improved. It should be understood that not all embodiments of the UAVDC may comprise each of the aforementioned components, while other embodiments of the UAVDC may comprise additional components, and yet other embodiments still may comprise various combinations of the embodiments described in the present disclosure. 
     Propeller  135  of the UAVDC may deploy upon interfacing with the air resistance. In further embodiments, springs and/or centripetal force from a rotation of propeller  135  may be implemented in deploying propeller  135 .  FIG.  5    illustrates an example of propeller  135  and a direction of deployment  505  for propeller blades  510 . 
     A UAVDC consistent with embodiments of the present disclosure may be configured to receive a modular payload  140 . In some embodiments, modular payload  140  may remain fixed in both the first and second configuration. By way of non-limiting example, modular payload  140  may be configured into the UAVDC, serving as a nose of fuselage  106 .  FIG.  6 A  illustrates an example of a plurality of modular payloads  140  configured to be attached to fuselage  106  in a fixed position  605 . To facilitate modularity, modular payload  140  may comprise hooks  610  configured to hook around pins  615  in a twist-to-lock fashion. In this way, modular payload  140  may be inserted into fuselage  106 . A ridge  620  may orient modular payload and provide a flush transition from modular payload  140  to fuselage  106 . Further, pins  615  may comprise screw threads to tighten around a nut, thus securing hooks  610 , and accordingly, modular payload  140 , in place. In further embodiments, modular payload  140  may comprise protrusions that are configured to fit into slots embedded within fuselage  106 . Modular payload  140  may be inserted into fuselage  106  along slots configured to receive the protrusions and turned to lock modular payload  140  to fuselage  106 . 
     While modular payload  140  may be locked in a fixed position  605 , it may comprise deployable components within, as shown in  FIGS.  6 B and  6 C , illustrating modular payload in a first configuration  630  and a second configuration  635 , respectively. 
     In other embodiments, modular payload  140  may have at least two configurations for location with respect to fuselage  106 .  FIG.  6 D  illustrates another example of a modular payload  140  in a first position  640 ;  FIG.  6 E  illustrates modular payload  140  in a second position  645 . For example, modular payload  140  may be arranged in first position  640  when the UAVDC is in the first configuration (“compact configuration”), and deployed into a second position  645  while in the second configuration. By way of non-limiting example, the modular payload may be a sensing device  650  configured to a boom  655  telescoping out of the fuselage. 
     Embodiments of the present disclosure may provide improvements over conventional unmanned aerial vehicles including, but not limited to the following examples: 
     Improved aerodynamic efficiency which increases flight endurance; 
     Increased payload capacity; 
     Launch and transition to flight without the assistance of external aerodynamic treatments such as a parachute or balloon; and 
     Maximized mission capability (i.e., its modular payload and reconfigurable and highly efficient airframe enable the UAVDC to efficiently perform a wider array of missions such as, for example, but not limited to, Intelligence Surveillance Reconnaissance (ISR), Signals Intelligence (SIGINT), weather, geophysical, environmental, and the like. 
     Both the foregoing overview and the following detailed description provide examples and are explanatory only. Accordingly, the foregoing overview and the following detailed description should not be considered to be restrictive. Further, features or variations may be provided in addition to those set forth herein. For example, embodiments may be directed to various feature combinations and sub-combinations described in the detailed description. 
     II. CONFIGURATION 
       FIG.  1 C  illustrates an UAVDC consistent with embodiments of the present disclosure. Embodiments of the present disclosure may comprise a fuselage  106 , one or more antennas  705 , power source  1310 , wings  110  that may be configured to sweep and/or telescope, stabilizers  125 , and payload  140 . Further embodiments may comprise a propulsion mechanism, such as, for example, propeller  135 . 
     Fuselage  106  may be comprised of, but not limited to, for example, carbon fiber. Further, fuselage  106  may be comprised of, but not limited to, for example, a composite material (e.g., fiberglass, Kevlar, Spectra). In various embodiments, plastics may be used, including, but not limited to 3D printed plastics. Fuselage  106  may take an aerodynamic configuration to facilitate speed and reduced air resistance. 
     Referring now to  FIG.  7   , antenna  705  may be positioned in various portions of the UAVDC. For example, antenna  705  may be fixed, and, in some embodiments, may be conformal (i.e., built into the skin of fuselage  106 ). Alternatively, antenna  705  may be deployable. For example, antenna  705  may be configured to deploy out from the fuselage (e.g., via a spring) on a hinge. As another example, as illustrated in  FIG.  7   , antenna  705  may be built into at least one of stabilizers  125 . In this way, when stabilizers  125  are deployed, antenna  705  may also be deployed. In further embodiments, and as illustrated in  FIGS.  6 D and  6 E , modular payload  140  may be embodied as antenna  705 . In this way, antenna  705  may be attached to boom  655  and configured to extend from fuselage  106 . In yet further embodiments, a plurality of antennas may be integrated within the UAVDC. 
     Antenna  705  may be in operable communication with an on-board controller, as further detailed with reference to  FIG.  15   . In this way, antenna  705  may both send 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 a remotely-located operator. The control signals may be processed and decrypted by the on-board controller, which, in turn, may operate the UAVDC accordingly. Furthermore, the antenna  705  may be used to communicate various data from the UAVDC to, for example, the remotely located operator. 
     Data may include, but not be limited to, for example, sensor data collected by various sensors on-board the UAVDC (e.g., sensors within modular payload  140 ). In yet further embodiments, the data may include telemetric data for the UAVDC, including, but not limited to, for example, global positioning data, accelerometer data, gyroscopic data, velocity data, and the like. In some embodiments, the aforementioned data may be collected, processed, and encrypted by the on-board controller prior to its communication. 
     It should be understood that the UAVDC may be configured with various propulsion mechanisms, and that propeller  135  illustrated in  FIG.  8    is just one illustrated variation. Other propulsion mechanisms may include, but are not limited to, rockets, jet engines and compressed gas jets. Moreover, in some embodiments, no propulsion may be required at all, as the UAVDC may have characteristics of a glider. In such embodiments, the UAVDC may be launched from, for example, a tube or released from, for example, an airplane within gliding range of its mission target. The various properties of the UAVDC, as described in various embodiments herein, may provide the UAVDC with sufficient flight time (upon, for example, deployment as detailed below with reference to  FIG.  14   ) to accomplish its mission without requiring additional propulsion. 
     Propeller  135  may comprise propeller blades  510  that fold against fuselage  106 . While propeller  135  is shown as having two propeller blades  510 , it should be understood that more or fewer propeller blades may be utilized. For example, only a single propeller blade may be used. As illustrated in  FIG.  9   , fuselage  106  may comprise grooves  905  configured to receive propeller blades  510  in a folded configuration. During flight, propeller  135  may be unfolded by means of, for example, air pressure (e.g., due to drag) against the propeller or centripetal force from rotation of propeller  135 . In other embodiments, propeller  135  may be unfolded by using springs (e.g., torsion springs  805 ) to enable rapid deployment, thus preventing propeller blades  510  from hitting the stabilizers  125  before propeller  135  is completely unfolded. 
     Although many of the figures illustrate propeller  135  in a rear-mounted position, it should be understood that, in embodiments where a propulsion mechanism is provided, propeller  135  may be configured at different positions of the UAVDC. For example, in some embodiments, propeller  135  may mount to the front of the UAVDC instead of the rear.  FIG.  6 D and  6 E  illustrate an embodiment of a UAVDC comprising a tractor propeller  675  mounting to the front of the UAVDC. 
     Moreover, the positioning of propeller  135  may be impacted by the deployment of wings  110 . Referring to  FIG.  10 A , propeller blade  1005  is mounted to fuselage  106 , trapped beneath wings  110 . During a launch of the UAVDC in the first configuration, air drag or springs  805  may force propeller blade  1005  in the top position (e.g., mounted to the top of fuselage  106 ) towards its deployed state. Such deployment of propeller blade  1005 , however, may be obstructed by wings  110  stowed immediately above, as illustrated in the first configuration. 
     The remaining propeller blade  1010  not obstructed by wings  110  may not be impeded from deployment, and therefore may deploy into the second configuration as designed. In order to prevent damage from the tendency of the remaining propeller blade  1010  to windmill while the propeller blade  1005  is still trapped, the hinge travel  1015  of the blades may be extended to allow blade  1010  to fold back to a position  1020  that aligns blade  1010  with the free stream as shown in  FIG.  10 B . 
     Referring back to  FIG.  1 A , the UAVDC may have a wing arrangement comprised of a single wing with two wing sections. The wing arrangement may be segmented in a left wing section and a right wing section to enable variable sweep at approximately a lateral plane of symmetry 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., wings  110 ). Still consistent with embodiments of the present disclosure, however, the wing arrangement may be a single wing comprised of the two wing sections. 
     The wing arrangement being configurable in a first arrangement (e.g., corresponding to the first configuration of the UAVDC), a second arrangement (e.g., corresponding to the second or third configuration of the UAVDC), and a third arrangement. In the first arrangement, the left wing section and the right wing section may be stowed 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. A third arrangement may comprise the wing sections at any wing deployment angle in between the first sweep deployment angle and the second sweep deployment angle. 
     To enable the sweep deployment angle, the UAVDC may comprise a sweeping gearbox configured to pivot the left wing section and the right wing section to enable the wing arrangement to sweep from the first arrangement to the second arrangement at any sweep deployment angle. The UAVDC may comprise an actuator coupled to the sweeping gearbox configured to actuate the sweeping of the wing arrangement at any sweep deployment angle. 
     Throughout the sweeping motion, fairing  130  may be configured to change from an open configuration to a closed configuration. Fairing  130  may begin in an open configuration by flexing to allow the first wing section and the second wing section to be stowed under the fairing in the first arrangement, and move to a closed configuration to provide aerodynamic and/or environmental advantages in the second arrangement. 
     The wings  110  may be stowed in a launch configuration as shown in first configuration  102 . In some embodiments, the launch configuration of wings  110  may comprise a vertical offset. Wings  110  may be swept to a flight configuration by sweeping gearbox  205  (e.g., a sweeping means). For example, actuator  210  attached to sweeping gearbox  205  may comprise a worm gear  220  coupled to each wing and a worm  225  coupled to worm gears  220  and configured to spread the wings in sweeping motion  250 . Sweeping gearbox  205  may sit on wing mount  215 . Various other means may be used in sweeping wings  110 , including, but not limited to, springs. In some embodiments, wings  110  may not need to be fully swept in order to enable flight. For example, the UAVDC may be capable of flight at an angle less than full sweep. 
     Gearbox  205  may be configured such that wings  110  may be stored in the launch configuration with a first set of angles with respect to each other (e.g., flat with respect to each other) and with respect to the fuselage (e.g., flat with respect to the fuselage). Gearbox  205  may further be configured to cause wings  110  to be deployed with optimal incidence angles and dihedral angles in the swept configuration. This may be achieved by orienting each wing&#39;s axis of rotation as well as each wing&#39;s attachment to worm gear  220  (or “wing pivot”). As such, gearbox  205  may comprise two pivot axes around which the wings may sweep.  FIG.  2 D  illustrates a schematic for illustrating geometry to enable a gearbox  205 . For example, the axis of rotation may be oriented such that its angle in the Y-Z plane  270 , as shown in reference to axes  255 , may match an angle of attachment  265  to worm gear  220 . Further the angle in the X-Z plane  260  may match an angle of attachment  275  to worm gear  220 . With this configuration, wings  110  may be stowed flat with respect to each other and with respect to the fuselage, while deployed with optimal dihedral and incidence angles. The optimal dihedral angle may be the combination of the angle in the X-Z plane  260  and the angle of attachment  265 ; the optimal angle of incidence may be the combination of the angle in the X-Y plane and the angle of attachment  275 . In this way, a single mechanism may both sweep wings  110  and orient wings  110  to desired dihedral angles and angles of incidence. The single mechanism for sweeping and orienting wings may reduce weight and complexity, thus increasing endurance and decreasing cost. 
     The UAVDC may comprise fairing  130  to reduce drag while enabling the outward sweeping motion  250  of wings  110 .  FIGS.  11 A and  11 B  illustrate fairing  130  in a first configuration  1105  and a second configuration  1110 , respectively. Fairing  130  may be made of a flexible material (e.g., fiberglass) such that it may bend out of the way as wings  110  sweep. In various embodiments, other materials may be used, including, but not limited to carbon fiber, Kevlar, and sheet metal. Fairing  130  may comprise wing hole cutouts  1115  to fit around wings  110 &#39;s profile as wings  110  reach second configuration  1110 . 
     As illustrated in  FIG.  11 A , fairing  130  in first configuration  1105  may be resting upon the sweeping wings  110  in compact arrangement  102  and undergoing tension from being held in a strained (“buckled”) state. Slits  1120  may be implemented in fairing  130  to enable fairing  130  to flex adequately to accommodate sweeping wings  110  in compact arrangement  102 . Upon the UAVDC entering second configuration (e.g., expanded arrangement  105 ), fairing  130  may flex as illustrated in  FIG.  11 B  to close around the wing as wings  110  reach wing hole cutouts  1115 . In second configuration  1110 , fairing  130  may be in an unstrained state as it securely fits around wing  110  to minimize drag. If fairing  130  comprises a fibrous composite material, it may be desirable to use a fiber orientation to facilitate buckling and flexibility in the laminate (e.g., using +/−45 degree plies may exhibit greater flexibility and buckle easily in 0 and 90 degree directions). 
     In further embodiments, magnets  1125  may be employed to further lock fairing  130  around the swept wings  110 , as shown in  FIG.  11 C . Magnets  1125  may be located on fuselage  106 . Magnets of opposite polarity or a magnetic metal  1130  may be on fairing  130  to receive magnets  1125 &#39;s magnetic attraction. In further embodiments, the location of the magnets  1125  and corresponding magnetic metal  1130  may be reversed. 
     As wings  110  are being swept, or, in some embodiments, after wings  110  have completely been swept, wings  110  may telescope. For example, inner section  305  may attach to fuselage  106  of the UAVDC. Inner section  305  may be stowed at least partially within outer section  310  during the compact first configuration. Outer section  310  may comprise a substantially hollow interior. An exterior surface of interior section  305  may be stowed against and interior surface of the exterior section  310 . To reach the second configuration, outer section  310  may slide along inner section  305  to extend outwards from the fuselage  106 . As outer section  310  slides along inner section  305 , an increasing portion of inner section  305  may be exposed. The wingspan of wings  110  may be approximately the length of exterior section  310  and the exposed portion of interior section  305 . Both inner section  305  and outer section  310  may employ an aerodynamic profile to provide lift during flight. Some embodiments may utilize belt system  315  for telescoping wings  110 . 
     Belt system  315  may comprise belt pulleys  325 , which may attach to the inner wing section  305  (“second section”). At least one pulley  325  may be driven by an actuator  320 . In further embodiments, a plurality of pulleys  325  may be driven by a plurality of actuators  320 . Belt  330  may loop around pulleys  325 . Notches in belt  330  may enable actuator  320  to move belt  330 . One of the straight lengths  331  of belt  330  may be contained within the inner wing section  305 , while the other length  332  of belt  330  may be contained in a groove on the bottom of the inner wing section  305  (“second section”) that is exposed to the outer wing section  310  (“first section”) prior to the telescoping of wings  110 . 
     To enable telescoping, belt  330  may be attached to at least a portion of outer wing section  310  along length  332 . In this way, actuator  320 &#39;s rotation not only causes a movement of belt  330  but also a displacement of outer wing section  310  due to its attachment to belt  330 . Accordingly, actuation in direction  335  would cause section  310  to be extended outward from the fuselage  106 , thereby increasing the wingspan of the UAVDC. As outer section  310  travels outward, inner section  305  is simultaneously withdrawn from the interior of outer section  310 , increasing the wingspan of the UAVDC. Accordingly, as wings  110  are telescoped, length  332  may become exposed but the groove may prevent the belt  330  from protruding from the bottom of the exposed inner wing section  305 . 
     Attaching outer section  310  to length  332  may be implemented by, for example, but not limited to, a clamp, screw or adhesive. In some embodiments, belt  330  may comprise a length of fiber-reinforced rubber material. By stripping rubber from each end of the belt to expose fibers, further attachment mechanisms for attaching belt  330  to outer section  310  may be available. For example, the exposed fibers may be tied to the outer wing section  310  (e.g., to holes in outer wing section  310 ). The tied fibers may further be secured, for example, with an adhesive. In this way, ends of belt  330  may be attached to create a connected loop without the use of a coupler clamping the ends, thereby eliminating bulky parts commonly used in the art. 
     Consistent with embodiments of the present disclosure, belt system  315  may provide a lighter and/or a more compact mechanism for telescoping over conventional telescoping systems. In some embodiments, the telescoping of the wings may be reversed by reversing direction  335  of actuator  320  to retract wings  110 . In further embodiments consistent with the present disclosure, components of belt system  315  may be reversed, such that outer wing section  310  may be affixed to fuselage  106  and inner wing section  305  may be telescoped outward. In yet further embodiments, a similar belt system may be implemented for extending a boom from fuselage  106 . For example, instead of attaching belt  330  to outer wing section  310 , belt  330  may attach to the boom. 
     Wings  110  may comprise ailerons  120 . In some embodiments, ailerons  120  may be attached via a hinge  1215  to the trailing edge of outer section  310 . In this way, ailerons  120  may minimize interference with outer section  310 &#39;s internal volume as compared to conventional ailerons. By optimizing outer section  310 &#39;s internal volume, inner section  305  may have an optimized profile and an increased span that would otherwise be limited by the more commonly-used ailerons. For example, inner section  305  may, when stowed within the first compact configuration, overlap at least a portion of the length of the trailing edge aileron attachment to outer section  310 . In this way, a ratio of the surface area between the inner section  305  and outer section  310  may be increased. Maximizing wing span can significantly increase airframe efficiency, flight endurance, and payload capacity. Hinge types that may enable such trailing edge ailerons  120  include, but are not limited to, a living hinge, or other flexure bearing. 
     Further, by mounting ailerons  120  to the outer section  310  extending away from fuselage  106 , ailerons  120  may enable roll control throughout the wing deployment phase. This means the UAVDC may be flown with positive roll control regardless of outer section  310 &#39;s position relative to inner section  305 , which can be beneficial during launch and flight recovery phases where transition to stable flight can be carried out with lower structural loads on the air frame when the wings are configured in their non-telescoped position. This may also be beneficial as the span may be reduced or increased in flight, to maximize aerodynamic efficiency without losing roll control.  FIG.  12 A  shows a configuration of components for controlling the ailerons. Each aileron  120  may be positioned by a servo  1320 , as illustrated in  FIG.  13   , through a linkage  1210 . Each servo  1320  may, in some embodiments, be positioned within outer wing section  310 . In further embodiments, ailerons  120  may be operated by other means, including, but not limited to, gears or shafts. Each servo  1320  may be controlled by controller  1500 . 
       FIG.  12 B  illustrates possible configurations for ailerons  120 , including, but not limited to, a tucked position  1230 , which minimizes stowed volume, a partially folded position  1235 , and a fully deployed position  1240 . Servo  1320  may be operated through a control wire positioned within outer wing section  310  and inner wing section  305 . The control wire may extend from fuselage  106  via inner wing section  305 . An end of wing section  305  may comprise an opening through which the control wire may extend into the interior of outer wing section  310 , connecting to servo  1320 . In various embodiments, the wire may comprise sufficient length to accommodate the telescoping of the wings. While the wings are not telescoped, the control wire may be spooled or neatly folded within either of the wing sections. 
       FIGS.  4 A- 4 D  illustrate an embodiment of a deployable pivoting control surface embodied as a stabilizer  125 . While this disclosure uses the term “stabilizers” in reference to deployable pivoting and/or pitching control surfaces, it should be understood that such controls surfaces may not be limited to stabilizers. For example, deployable pivoting control surfaces implementing the same components may be used in other ways, including, but not limited to, wings. 
     In some embodiments, stabilizers  125  may be moved into the flight configuration by other means, including, but not limited to, air drag. In further embodiments, stabilizers  125  may be spring-loaded such that they move into the flight configuration upon launch. For example, torsion springs  405  may move stabilizers  125  into the flight configuration. Stabilizers  125  may be used to provide flight control by servos  410  operating push rods  415  and control horns  416  which pivot the stabilizer about axis  425 . For example, servos  410  may cause stabilizers  125  to rotate around axis  425  by pivoting within hinge  420 . Further, stabilizers  125  may comprise fairings  485 . Fairings  485  may be embodied as a flexible material (e.g., a rubber or elastomer) configured to go around shaft  445  for enabling a pitching motion while maintaining aerodynamic efficiency as shown in  FIGS.  4 E through  4 G . As stated above, stabilizers  125  may comprise one or more antennas  705  such that deployment of stabilizers  125  may further deploy one or more antennas  705 . 
     Stabilizers  125  may move into the flight configuration by pivoting around axis  430 . In this way, axis  430  may be constant relative to fuselage  106  in transition from first configuration  450  to second configuration  455 . Further, by aligning control horn  416 &#39;s centerline with axis  430  during deployment, servos  410  need not move during transition  440  from first configuration  450  to second configuration  455 , as further shown in  FIGS.  4 A and  4 B . 
     Servos  410  may be configured to move push rods  415  coupled to control horns  416  on the at least one stabilizer for deflecting/rotating the at least one stabilizer about its spanwise axis. Control horns  416 , in turn, may be configured to remain in a relatively fixed position as the at least one stabilizer deploys into flight configuration (the second configuration). 
       FIGS.  4 E- 4 G  illustrate a stabilizer fairing  485 . Stabilizer fairing  485  may be used to cover the various components that enable the least one stabilizer to be deflected/rotated about its spanwise axis to provide positive flight control while in the second stabilizer configuration  455 . Stabilizer fairing  485  may comprise a flexible material, such as, for example, rubber. As such, stabilizer fairing  485  may reduce drag on various components, including, but not limited to shaft  445 , while flexing to enable the full range of motion of stabilizer  125 . 
     A number of internal components may be mounted within an interior  1305  of fuselage  106 .  FIG.  13    illustrates one example of internal configuration of the UAVDC in which a power source  1310  may be positioned within the interior of fuselage  106 . Power source  1310  may comprise, for example, a fuel tank or one or more batteries. Various components of the UAVDC may be connected to power source  1310 , including, but not limited to, modular payload  140 , controller  1500 , sweeping gearbox actuator  210 , control mechanisms for ailerons (e.g., servos  1320 ), servos  410  for stabilizers  125 , a motor  1315  to drive the propeller  135 , and antenna  705 . Embodiments of the UAVDC comprising a propulsion device (e.g., propeller  135 ) may be powered by alternative power sources, such as, for example, an internal combustion engine. In such embodiments, a fuel source for the internal combustion engine (e.g., gas tank) may be positioned within interior  1305  of fuselage  106 . 
     Internal components may further include, for example, but not be limited to, the following components, which will be further detailed with reference to section III below, sweeping gearbox  205  and actuator  210  employed to sweep wings  110 ; control mechanisms for ailerons  120  (e.g., servos  1320 ) for operating ailerons  120  and servos  410  for operating stabilizers  125 ); a motor  1315  for driving propeller  135 ; driveshaft  1330  for coupling motor  1315  to propeller  135  and an on-board controller  1500  for controlling the deployment, flight, and operation of the UAVDC. The illustrated configuration of internal components is just one possible configuration, and other embodiments are possible. The interior components may be distributed to balance the weight in an optimal way for flight. 
     III. Operation 
       FIG.  14    is a flow chart setting forth the general stages involved in a method  1400  consistent with an embodiment of the disclosure for operating the UAVDC. Method  1400  may be implemented using, at least in part, a controller  1500  (e.g., on board computing device) as described in more detail below with respect to  FIG.  15   . Controller  1500  may comprise a controller for operating the deployable components as well as well as performing other mission details, including, but not limited to, flight control, payload operation, and communication. As such, controller  1500  may be in operative configuration and communication with, for example, but not be limited to, modular payload  140 , sweeping gearbox actuator  210 , control mechanisms for ailerons  120  (e.g., servos  1320 ), servos  410  for stabilizers  125 , a motor  1315  to drive the propeller  135 , power source  1310 , inertial measurement unit, global positioning system, various telemetry sensors, and antenna  705 , as well as all other units. As will be detailed with reference to  FIG.  15   , controller  1500  may comprise a remote communication module to enable remotely operation as described above with reference to antenna  705 . In other embodiments, controller  1500  may be completely self-operating upon configuration. In this way, the UAVDC may be self-piloting. 
     Furthermore, although stages are disclosed with reference to controller  1500 , it should be understood that a plurality of other components may enable the operation of method  1400 , including, but not limited to, other computing components, mechanical components, environment properties (e.g., air resistance), remote operators, and the like. 
     Further still, although the stages illustrated by the flow charts are disclosed in a particular order, it should be understood that the order is disclosed for illustrative purposes only. Stages may be combined, separated, reordered, and various intermediary stages may exist. Accordingly, it should be understood that the various stages illustrated within the flow chart may be, in various embodiments, performed in arrangements that differ from the ones illustrated. Moreover, various stages may be added or removed from the flow charts without altering or deterring from the fundamental scope of the depicted methods and systems disclosed herein. 
     Method  1400  may begin at starting block  1405  and proceed to stage  1410 , where the UAVDC may be launched. For example, the UAVDC may be fired from a tube launched from a craft or dropped from a carrier aerial vehicle. The compact arrangement  102  of the UAVDC&#39;s first configuration (as specified, for example, with reference to  FIG.  1 A ) may enable the UAVDC to be tube-launched as, for example, a missile. In some embodiments, once dropped from a carrier aerial vehicle, the UAVDC may be aerodynamically designed (as illustrated) and with such a weight distribution that it may self-orient from a tumbling drop into a dive. 
     From stage  1410 , where the UAVDC is launched, method  1400  may proceed to stage  1420  where the flight components may be deployed. The deployment of flight components, though disclosed in a particular order for illustrative purposes, may occur in other arrangements. 
     Upon launch, the stabilizers  125  and propeller  135  may deploy. In applicable embodiments, springs  405  and springs  805 , may deploy stabilizers  125  and propeller blades  510 , respectively. In other embodiments, the air resistance at launch and the stowed arrangement of stabilizers  125  (e.g., first stabilizer configuration  450 ) and propeller blades  510  create a force in a vector of expansion, thereby causing stabilizers  125  and propeller blades  510  to deploy in a deployed arrangement (e.g., second stabilizer configuration  455 ). 
     Controller  1500  (e.g., on-board computing-device) may automatically engage actuators and the wing deployment mechanisms instantly or after a set amount of time has passed since the launch. In other embodiments, engagement may occur upon certain reading from on-board sensors (e.g., including, but not limited to, sensors deployed in modular payload  140 ). For example, wing deployment and extension may be dependent on certain in-flight factors such as, for example, velocity, acceleration, and leveling of the UAVDC. Controller  1500  may be configured to trigger deployment of various components upon the satisfaction of certain pre-set conditions. Such conditions may be defined prior to deployment. 
     Actuator  210  may drive sweeping gearbox  205  to sweep wings  110 . In some embodiments, the UAVDC may be capable of controlling sustained flight once wings  110  sweep out 45 degrees. As wings  110  reach full sweep, wings  110  may move within wing hole cutouts  1115  of fairing  130 , which has opened due to the strain of the sweeping motion  250 , and relocked with the aid of magnets positioned within the fuselage. Accordingly, fairing  130  may automatically snap shut around the profile of wings  110  to improve aerodynamics. Magnets  1125  may further lock fairing  130  around wings  110 . 
     As wings  110  begin sweeping, or after wings  110  are fully swept, wings  110  may begin telescoping. For example, belt system  315  may pull outer section  310  along inner section  305  to telescope wings  110 . The wing sweep angles and telescoped positions may further be dynamically adjusted in flight. 
     Further, in embodiments where deployable, modular payload  140  may deploy from its first arrangement to its second arrangement. For example, modular payload  140  may comprise a plurality of sensing devices better situated for performance at a deployed position (e.g., an extended boom). Such deployment may occur upon the post-launch stabilization segment of the UAVDC&#39;s flight. 
     From stage  1420 , where the flight components are deployed and UAVDC flight is stabilized, method  1400  may proceed to stage  1430 , where the UAVDC may be used to perform a mission. During all stages of flight, the UAVDC may be in operable communication with an operator via antenna  705 . The operator may receive various readings from the various components of the UAVDC. 
     In some embodiments, the operator may control the operation of the UAVDC during the mission. For example, the operator may be able to control the flight components, including, but not limited to, the wing deployment mechanisms (e.g., sweeping gearbox  205 , actuator  210 , and belt system  315 ), propeller  135 , stabilizers  125 , ailerons  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  may be pre-configured with mission control data. 
     Embodiments of the UAVDC may be used fora plurality of missions including, but not limited to, data capture, payload deployment, and providing a telecommunications relay. In addition to communicating for flight control, embodiments of the UAVDC may be controlled in data capture and transmission. In further embodiments, the UAVDC may enable the operator to release modular payload  140 . 
     From stage  1430 , where the UAVDC is used to perform a mission, method  1400  may proceed to stage  1440 , where the mission is terminated. For example, the mission may be terminated by flying the UAVDC to a recapture location where it may be recovered. Further, the UAVDC may terminate a mission by crash landing. For example, the UAVDC may be flown into rocks or a hard surface in order to destroy functional components. In further embodiments, the UAVDC may be equipped with an explosive device such that it may be self-destructed upon mission completion. After stage  1440 , method  1400  may end at stage  1450 . 
     IV. On-Board System Architecture 
     The UAVDC may comprise, but not be limited to, an on-board computing module. The computing module may be in operative configuration and communication with, for example, but not be limited to, modular payload  140 , sweeping gearbox actuator  210 , control mechanisms for ailerons  120  (e.g., servos  1320 ), servos  410  for stabilizers  125 , a motor  1315  to drive the propeller  135 , power source  1310 , global positioning system, various telemetry sensors, and antenna  705 . Further, the computing device may be in operative communication with another computing device consistent with the description herein, and may comprise, but not be limited to, a desktop computer, laptop, a tablet, or mobile telecommunications device. Such remote devices may be used to control and/or configure on-board computing module (e.g., deployment conditions, mission controls, and the like). 
     Moreover, the UAVDC may be in operative communication with a centralized server, such as, for example, a cloud computing service. Although operation has been described to be performed, in part, by a controller  1500 , it should be understood that, in some embodiments, different operations may be performed by different networked elements in operative communication with controller  1500 . 
     Embodiments of the present disclosure may comprise a system having a memory storage and a processing unit. The processing unit may be coupled to the memory storage, wherein the processing unit is configured to perform the stages of method  1400 . 
       FIG.  15    is a block diagram of a system including controller  1500 . Consistent with an embodiment of the disclosure, the aforementioned memory storage and processing unit may be implemented in a computing device, such as 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 controller  1500  or any of other UAVDC devices and components  1518 , in combination with controller  1500 . Other UAVDC devices and components  1518  may comprise, for example, but not be limited to, modular payload  140 , sweeping gearbox actuator  210 , control mechanisms for ailerons  120  (e.g., servos  1320 ), servos  410  for stabilizers  125 , a motor  1315  to drive the propeller  135 , power source  1310 , global positioning system, various telemetry sensors, and antenna  705 . The aforementioned system, device, and processors are examples and other systems, devices, and processors may comprise the aforementioned memory storage and processing unit, consistent with embodiments of the disclosure. 
     With reference to  FIG.  15   , a system consistent with an embodiment of the disclosure may include a computing device, such as controller  1500 . In a basic configuration, controller  1500  may include at least one processing unit  1502  and a system memory  1504 . Depending on the configuration and type of computing device, 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. System memory  1504  may include operating system  1505 , one or more programming modules  1506 , and may include a program data  1507 . Operating system  1505 , for example, may be suitable for controlling controller  1500 &#39;s operation. In one embodiment, programming modules  1506  may include flight control application  1520 . Furthermore, embodiments of the disclosure may be practiced in conjunction with a graphics library, other operating systems, or any other application program and is not limited to any particular application or system. This basic configuration is illustrated in  FIG.  15    by those components within a dashed line  1508 . 
     Controller  1500  may have additional features or functionality. For example, controller  1500  may also 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 a removable storage  1509  and a non-removable storage  1510 . Computer storage media may include volatile and nonvolatile, 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. System memory  1504 , removable storage  1509 , and non-removable storage  1510  are all computer storage media examples (i.e., memory storage.) Computer storage media 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 disks (DVD) or other optical storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to store information and which can be accessed by controller  1500 . Any such computer storage media may be part of device  1500 . Controller  1500  may also be operative with input device(s)  1512  such as a keyboard, a mouse, a pen, a sound input device, a touch input device, etc. Input device(s)  1512  may be used to, for example, manually access and program controller  1500 . Output device(s)  1514  such as a display, speakers, a printer, etc. may also be included. The aforementioned devices are examples and others may be used. 
     Controller  1500  may also contain a communication connection  1516  that may allow device  1500  to communicate with other UAVDC devices and components  1518  (e.g., antenna  705 ), such as over an encrypted network in a distributed computing environment. Communication connection  1516  is one example of communication media. 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 describe 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. The term computer readable media as used herein may include both storage media and communication media. 
     As stated above, a number of program modules and data files may be stored in system memory  1504 , including operating system  1505 . While executing on processing unit  1502 , programming modules  1506  (e.g., controller application  1520 ) may perform processes including, for example, one or more of stages or portions of stages of method  1400  as described above. Controller application  1520  may be configured to operate UAVDC devices and components  1518  and receive instructions from, for example, communications connections module  1516 . The aforementioned process is an example, and processing unit  1502  may perform other processes. 
     Generally, consistent with embodiments of the disclosure, program modules may include routines, programs, components, data structures, and other types of structures that may perform particular tasks or that may implement particular abstract data types. Moreover, embodiments of the disclosure may be practiced with other computer system configurations, including hand-held devices, multiprocessor systems, microprocessor-based or programmable consumer electronics, minicomputers, mainframe computers, and the like. Embodiments of the 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. 
     Furthermore, embodiments of the disclosure may be practiced in an electrical circuit comprising discrete electronic elements, packaged or integrated electronic chips containing logic gates, a circuit utilizing a microprocessor, or on a single chip containing electronic elements or microprocessors. Embodiments of the disclosure may also be practiced 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. In addition, embodiments of the disclosure may be practiced within a general purpose computer or in any other circuits or systems. 
     Embodiments of the disclosure, for example, may be implemented as a computer process (method), a computing system, or as an article of manufacture, such as a computer program product or computer readable media. The computer program product may be a computer storage media readable by a computer system and encoding a computer program of instructions for executing a computer process. The computer program product may also be a propagated signal on a carrier readable by a computing system and encoding a computer program of instructions for executing a computer process. Accordingly, the present disclosure may be embodied in hardware and/or in software (including firmware, resident software, micro-code, etc.). In other words, embodiments of the present disclosure may take the form of a computer program product on a computer-usable or computer-readable storage medium having computer-usable or computer-readable program code embodied in the medium for use by or in connection with an instruction execution system. A computer-usable or computer-readable medium may be any medium that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device. 
     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. More specific computer-readable medium examples (a non-exhaustive list), the computer-readable medium may include the following: 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 disc read-only memory (CD-ROM). Note that the computer-usable or computer-readable medium could even be paper or another suitable medium upon which the program is printed, as the program can be electronically captured, via, for instance, optical scanning of the paper or other medium, then compiled, interpreted, or otherwise processed in a suitable manner, if necessary, and then stored in a computer memory. 
     Embodiments of the present disclosure, for example, are described above with reference to block diagrams and/or operational illustrations of methods, systems, and computer program products according to embodiments of the disclosure. The functions/acts noted in the blocks may occur out of the order as shown in any flowchart. For example, two blocks shown in succession may in fact be executed substantially concurrently or the blocks may sometimes be executed in the reverse order, depending upon the functionality/acts involved. 
     While certain embodiments of the disclosure have been described, other embodiments may exist. Furthermore, although embodiments of the present disclosure have been described as being associated with data stored in memory and other storage mediums, data can also be stored on or read from other types of computer-readable media, such as secondary storage devices, like hard disks, solid state storage (e.g., USB drive), or a CD-ROM, a carrier wave from the Internet, or other forms of RAM or ROM. Further, the disclosed methods&#39; stages may be modified in any manner, including by reordering stages and/or inserting or deleting stages, without departing from the disclosure. 
     V. Aspects 
     The following disclose various Aspects of the present disclosure. The various Aspects are not to be construed as patent claims unless the language of the Aspect appears as a patent claim. The Aspects describe various non-limiting embodiments of the present disclosure.
         Aspect 1. A telescoping wing system for an aerial vehicle comprising:   an inner section configured to be stowed within an interior of an outer section in a first configuration; and   a telescoping mechanism configured to, after satisfaction of a pre-set condition, extend the outer section along a length of the inner section to increase a wingspan in a second configuration.   Aspect 2. The telescoping wing system of Aspect 1, wherein the pre-set condition comprises a set amount of time having passed after a detected launch.   Aspect 3. The telescoping wing system of Aspect 1, further comprising a control surface attached to a trailing-edge of the outer section, wherein the control surface attaches to the outer section via a hinge mounted on an external surface of the trailing-edge.   Aspect 4. The telescoping wing system of Aspect 1, wherein the inner section is attached to a fuselage of the aerial vehicle.   Aspect 5. The telescoping wing system of Aspect 4, wherein at least a portion of an increased wingspan of the aerial vehicle is comprised of approximately a length of the outer section and a length of an exposed portion of the inner section.   Aspect 6. The telescoping wing system of Aspect 5, wherein the length of the exposed portion of the inner section increases as the outer section is displaced by at least a portion of the length between a first end of the inner section and a second end of the inner section.   Aspect 7. The telescoping wing system of Aspect 6, wherein displacement of the outer section along the length of the exposed portion of the inner section extends the wingspan of the aerial vehicle by approximately the length of the exposed portion of the inner section to form the increased wingspan.   Aspect 8. The telescoping wing system of Aspect 1, wherein the inner section and the outer section are configured, in the first configuration, to be stowed against a fuselage of the aerial vehicle.   Aspect 9. The telescoping wing system of Aspect 8, wherein the inner section and the outer section are configured, in the first configuration, to be deployed at an angle relative to the fuselage of the aerial vehicle.   Aspect 10. The telescoping wing system of Aspect 9, wherein the inner section and the outer section are configured to transition from the first configuration to the second configuration at the angle into the second configuration.   Aspect 11. The telescoping wing system of Aspect 1, wherein the pre-set condition comprises a set distance after a detected launch.   Aspect 12. The telescoping wing system of Aspect 1, wherein the telescoping wing system is configured to dynamically adjust wing sweep angle after satisfaction of the pre-set condition.   Aspect 13. The telescoping wing system of Aspect 1, wherein the outer section is dynamically adjustable after the wingspan is in the second configuration.   Aspect 14. The telescoping wing system of Aspect 1, wherein the telescoping mechanism is configured for a telescoping boom.   Aspect 15. The telescoping wing system of Aspect 14, wherein the telescoping boom comprises an antenna.   Aspect 16. The telescoping wing system of Aspect 1, wherein the telescoping mechanism comprises a belt system.   Aspect 17. The telescoping wing system of Aspect 16, wherein the belt system is attached to the outer section to increase the wingspan to the second configuration.   Aspect 18. The telescoping wing system of Aspect 1, wherein the outer section comprises at least one flight control mechanism.   Aspect 19. The telescoping wing system of Aspect 18, wherein the at least one flight control mechanism provides increased roll control after extending the outer section.   Aspect 20. The telescoping wing system of Aspect 19, wherein the at least one flight control mechanism comprises trailing-edge hinged ailerons.   Aspect 21. The telescoping wing system of Aspect 19, wherein the at least one flight control mechanism maintains roll control as the outer section extends along the inner section.   Aspect 22. The telescoping wing system of Aspect 1, wherein the outer section extends to an intermediate position between the first configuration and the second configuration to decrease drag generated by the telescoping wing system.       

     VI. Claims 
     While the specification includes examples, the disclosure&#39;s scope is indicated by the following claims. Furthermore, while the specification has been described in language specific to structural features and/or methodological acts, the claims are not limited to the features or acts described above. Rather, the specific features and acts described above are disclosed as example for embodiments of the disclosure. 
     Insofar as the description above and the accompanying drawing disclose any additional subject matter that is not within the scope of the claims below, the disclosures are not dedicated to the public and the right to file one or more applications to claims such additional disclosures is reserved.