Aerial vehicles with deployable components

Abstract

(Figure 1C) An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and / or a modular 5 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 control surface 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 control surface deployed from the fuselage. In an expanded arrangement, 10 the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. 20 24 27 81 10 04 D ec 2 02 4 2 0 2 4 2 7 8 1 1 0 0 4 D e c 2 0 2 4

Description

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’s first configuration (as specified, for example, with reference to FIG. 1A) 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 32 2024278110   04 Dec 2024 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. 5         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, 10 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 15 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 20 stabilization segment of the UAVDC’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 25 various components of the UAVDC. 2024278110   04 Dec 2024 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 for a 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 selfdestructed 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 34 2024278110   04 Dec 2024 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 maybe 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 35 2024278110   04 Dec 2024 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’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 nonremovable) 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 nonremovable 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 36 2024278110   04 Dec 2024 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, 37 2024278110   04 Dec 2024 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 maybe configured to operate UAVDC devices and components 1518 and receive instructions from, for example, communications 5 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. 10 Moreover, embodiments of the disclosure may be practiced with other computer system configurations, including hand-held devices, multiprocessor systems, microprocessorbased 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 15 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 maybe 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 20 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. 2024278110   04 Dec 2024 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 39 2024278110   04 Dec 2024 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’ stages may be modified in any manner, including by reordering stages and / or inserting or deleting stages, without departing from the disclosure. V. CLAIMS While the specification includes examples, the disclosure’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 40 2024278110   04 Dec 2024 are not dedicated to the public and the right to file one or more applications to claims such additional disclosures is reserved.

Claims

2024278110   04 Dec 2024THE FOLLOWING IS CLAIMED1. An unmanned air-vehicle with deployable components (UAVDC) comprising: a fuselage;a segmented wing having a left wing section and a right wing section;a sweeping gearbox configured to enable the leftwing section and the rightwing section to move in a sweeping motion to transition the segmented wing between:a first arrangement in which the left wing section and the right wing section are stowed against the fuselage at a first sweep deployment angle,anda second arrangement in which the left wing section and the right wing section are fully deployed for flight at a second sweep deployment angle; and a propeller having at least one blade configured to move between a folded propeller arrangement and a deployed propeller arrangement.

2. The UAVDC of claim 1, wherein the left wing section and the right wing section are stacked against the fuselage in the first arrangement, with the left wing section vertically offset from the right wing section.

3. The UAVDC of claim 2, wherein the at least one blade of the propeller is disposed between the fuselage and the left wing section, when the propeller is in the folded arrangement and the segmented wing is in the first arrangement.

4. The UAVDC of claim 3, wherein the segmented wing retains the propeller in the folded arrangement while the segmented wing is in the first arrangement.

5. The UAVDC of claim 1, wherein the sweeping gearbox comprises a worm gear coupled to each of the left wing section and right wing section.

6. The UAVDC of claim 5, wherein the sweeping gearbox further comprises a worm configured to spread the left wing section and the right wing section in a sweeping motion.2024278110   04 Dec 20247. The UAVDC of claim 5, wherein the left wing section and the right wing section sweep about a pivot axis.

8. The UAVDC of claim 5, wherein the segmented wing is further configured to telescope during the sweeping motion to increase a wingspan of the second arrangement.

9. The UAVDC of claim 5, wherein the segmented wing is further configured to telescope subsequent to the sweeping motion to increase a wingspan of the second arrangement10. The UAVDC of claim 1, wherein the sweeping gearbox is configured to enable configurable wing angles to adjust aerodynamics of the UAVDC.

11. The UAVDC of claim 10, wherein adjusting the aerodynamics comprises adjusting at least one of:angles of incidence of the left wing section and the right wing section, or dihedral angles of the left wing section and the right wing section.

12. The UAVDC of claim 1, wherein the sweeping gearbox comprises a locking mechanism to secure the left wing section and the right wing section at the second sweep deployment angle.

13. The UAVDC of claim 1, further comprising a controller configured to control the sweeping gearbox to sweep the left wing section and the right wing section to predetermined angles based on flight conditions.

14. The UAVDC of claim 13, wherein the controller is configured to cause the sweeping gearbox to begin the sweeping motion after a set amount of time has passed since launch.2024278110   04 Dec 202415. The UAVDC of claim 13, wherein the controller is configured to cause the sweeping gearbox to begin the sweeping motion upon achievement of one or more in-flight factors16. The UAVDC of claim 15, wherein the one or more in-flight factors includes at least one of the following:exceeding a threshold velocity;exceeding a threshold acceleration, or leveling of the UAVDC.

17. The UAVDC of claim 1, further comprising: at least one stabilizer configured to deploy from a first stabilizer configuration stowed against the fuselage at a first deployment angle to a second stabilizer configuration deployed for flight at a second deployment angle, wherein the at least one stabilizer can be deflected / rotated about its spanwise axis to provide positive flight control while in the second stabilizer configuration.

18. The UAVDC of claiml7, further comprising 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.

19. The UAVDC of claim 17, further comprising:a servo configured to move a control horn coupled to the at least one stabilizer for rotating the at least one stabilizer about its spanwise axis, andwherein the control horn is configured to remain in a relatively fixed position as the at least one stabilizer deploys from the first stabilizer configuration to the second stabilizer configuration.

20. The UAVDC of claim 1, wherein the fuselage comprises at least one groove configured to receive at least one blade of the propeller in the first propeller arrangement.

Images