Unmanned aerial vehicles

Abstract

An example of an apparatus is provided. The apparatus includes a base module having a first end and a second end. The first end is opposite the second end. The apparatus also includes a first base connector disposed on the first end of the base module. In addition, the apparatus includes a first arm module to mate with the first base connector. The first arm module includes a first propulsion system to be controlled by the base module. Furthermore, the apparatus includes a second base connector disposed on the second end of the base module. In addition, the apparatus includes a second arm module to mate with the second base connector. The second arm module includes a second propulsion system to be controlled by the base module.

Description

UNMANNED AERIAL VEHICLESBACKGROUND

[0001] Drones or unmanned aerial vehicles are well known and have many applications. For example, drones may be used to collect data, such as images or atmospheric data as well as other data to be captured with an aircraft. Drones may also be used to deliver payloads or to access locations that are not easily accessible with a traditional aircraft operated by a pilot, such as locations that may be impractical or too dangerous for a person to be physically there. Due to the wide variety of applications for drones, various setups may be used depending on the mission of the drone. In particular, different mechanical and electrical characteristics may be more suitable for some missions than others. For example, larger payloads may call for more thrust and thus larger rotors, motors that drive the rotors, and battery storage. However, a larger device may not be suitable for some missions that call for better maneuverability or to improve power efficiency.SUMMARY

[0002] In accordance with an aspect of the invention, there is provided an apparatus. The apparatus includes a base module having a first end and a second end. The first end is opposite the second end. The apparatus also includes a first base connector disposed on the first end of the base module. In addition, the apparatus includes a first arm module to mate with the first base connector. The first arm module includes a first pair of rotors to be controlled by the base module. Furthermore, the apparatus includes a second base connector disposed on the second end of the base module. Also, the apparatus includes a second arm module to mate with the second base connector. Thesecond arm module includes a second pair of rotors to be controlled by the base module.

[0003] The first arm module may be substantially similar to the second arm module.

[0004] The apparatus may include a first alignment mechanism to align the first arm module to the base module and a second alignment mechanism to align the second arm module to the base module.

[0005] The first base connector may include a securing mechanism to lock the first arm module to the base module. The securing mechanism may be manually operated.

[0006] The apparatus may further include an external battery pack mounted to the base module.

[0007] The base module may include an autopilot system. The base module may include a camera. The base module may include a global positioning system.BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Reference will now be made, by way of example only, to the accompanying drawings in which:

[0009] Figure 1 A is a first perspective view of an example of an apparatus to provide a configurable unmanned aerial vehicle;

[0010] Figure 1 B is a second perspective view of an example of the apparatus shown in figure 1A;

[0011] Figure 2A is a first perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle;

[0012] Figure 2B is a second perspective view of an example of the apparatus shown in figure 2A;

[0013] Figure 3A is a first perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle;

[0014] Figure 3B is a second perspective view of an example of the apparatus shown in figure 3A;

[0015] Figure 4A is a first perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle;

[0016] Figure 4B is a second perspective view of an example of the apparatusshown in figure 4A;

[0017] Figure 5A is a first perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle;

[0018] Figure 5B is a second perspective view of an example of the apparatus shown in figure 5A;

[0019] Figure 6A is a detailed view of an arm module being inserted into a base connector example of the apparatus shown in figures 5A and 5B;

[0020] Figure 6B is a detailed view of an arm module being inserted into the other base connector of the apparatus shown in figures 5A and 5B;

[0021] Figure 7 is a detailed view of the arm module shown in figure 6B fully inserted into the base connector of the apparatus;

[0022] Figure 8 is a detailed view of the arm module shown in figure 6B fully inserted into the base connector of the apparatus with the screw tightened;

[0023] Figure 9A is a first perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle using the base module of the apparatus shown in figures 5A and 5B;

[0024] Figure 9B is a second perspective view of an example of the apparatus shown in figure 9A;

[0025] Figure 10 is a perspective view of an example of an apparatus to provide a configurable unmanned aerial vehicle with fixed wings using the base module of the apparatus shown in figures 5A and 5B;

[0026] Figure 11 is a detailed view of the fixed wings of the apparatus shown in figure 10 being connected to the base connector;

[0027] Figure 12A is a perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle in a storage configuration with fixed wings using the base module of the apparatus shown in figures 5A and 5B;

[0028] Figure 12B is a perspective view of the apparatus shown in figure 12A in an operational configuration;

[0029] Figure 13 is a perspective view of another example of an apparatus toprovide a configurable unmanned aerial vehicle in a storage configuration with fixed wings using the base module of the apparatus shown in figures 5A and 5B;

[0030] Figure 14A is a perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle in an operational configuration with fixed wings using the base module of the apparatus shown in figures 5A and 5B;

[0031] Figure 14B is a perspective view of the apparatus shown in figure 14A in an operational configuration;

[0032] Figure 15A is a perspective view of another example of an apparatus to provide a configurable unmanned aerial vehicle in an operational configuration with fixed wings using the base module of the apparatus shown in figures 5A and 5B;

[0033] Figure 15B is a perspective view of the apparatus shown in figure 15A in an operational configuration;

[0034] Figure 16 is a perspective view of an example of an apparatus to provide a configurable unmanned ground vehicle using the base module of the apparatus shown in figures 5A and 5B; and

[0035] Figure 17 is a flowchart of an example method of reconfiguring an apparatus in the field.DETAILED DESCRIPTION

[0036] As used herein, any usage of terms that suggest an absolute orientation (e.g., “top”, “bottom”, “up”, “down”, “left”, “right”, “low”, “high”, etc.) may be for illustrative convenience and refer to the orientation shown in a particular figure. However, such terms are not to be construed in a limiting sense as it is contemplated that various components will, in practice, be utilized in orientations that are the same as, or different than those described or shown.

[0037] Drones or aircraft (also referred to as unmanned aerial vehicles) have many applications and are generally designed with specifications and limits that are suitable for an intended application. Accordingly, an unmanned aerial vehicle may be designedfor a relatively limited range of applications to improve the efficiency of the device when used for the intended application. Although some unmanned aerial vehicles may be modified with replacement parts to vary specifications such as a payload limit, substituting parts on an unmanned aerial vehicle, such as a rotor, may not be compatible due to power demands or mechanical tolerances. In addition, due to the interconnection of electronics and mechanical components that control the unmanned aerial vehicle as well as the precision of the mechanical components, other components may not be compatible with the existing base unit of the unmanned aerial vehicle.

[0038] An apparatus is provided to operate as an unmanned aerial vehicle with a wide range of configurations suitable for different applications. In particular, the apparatus provides an unmanned aerial vehicle that may be assembled into multiple configurations with different compatible components in the field without the use of any tools or with limited use of tools. By providing the apparatus with the ability to vary its configuration in the field, the apparatus may obtain different performance characteristics, such as speed, flight time, and payload capacity.

[0039] Referring to figure 1 A and figure 1 B, an apparatus 50 to provide a configurable unmanned aerial vehicle is generally shown. It is to be appreciated by a person of skill with the benefit of this description that the apparatus 50 may include variations and additional features. In addition, the apparatus 50 may take other forms or dimensions. For example, although the apparatus 50 is a quadcopter design aircraft, other designs with different propulsion systems are contemplated. The apparatus 50 may include designs with more than four rotors, or may include a single lift rotor with a tail rotor design. In further examples, the apparatus 50 may also be modified to be a fixed-wing aircraft design. In the present example the apparatus 50 includes a base module 55, base connectors 60-1 , 60-2 (generically, these base connectors are referred to herein as “base connector 60” and collectively they are referred to as “base connectors 60”), and arm modules 65-1 , 65-2 (generically, these arm modules are referred to herein as “arm module 65” and collectively they are referred to as “arm modules 65”).

[0040] The base module 55 is the core of the apparatus 50 and may include various components to operate the apparatus 50. For example, the base module 55 mayinclude a central processor to operate the propulsion system based on commands received via a communication signal. In other examples, the central processor may be used to generate control signals to operate the apparatus 50 in either an autonomous mode or a semi-autonomous mode. For example, the base module 55 may include an autopilot computer, motor speed controller, radio transmitter / receiver, arm selector, and a global positioning system. In addition, the base module 55 may include other sensors such as a barometer, which may be used to determine altitude and inertial measurement units, which may be used to determine attitude and acceleration.

[0041] The base connectors 60 are to receive the arm modules 65. In the present example, the base connector 60-1 and the base connector 60-2 are disposed on opposite ends of the base module 55. The base connectors 60 are not particularly limited and may include various components to facilitate a mechanical connection to rigidly hold the arm modules 65. For example, the base connectors 60 may each include a securing mechanism to lock each respective arm module 65 rigidly to the base module 55. The securing mechanism is not particularly limited and may work in combination with a complimentary mechanism on each of the arm modules 65. The securing mechanism provides for rapid connection and disconnection of the arm modules 65, such as in less than about 15 seconds, manually (i.e. , without tools) or with basic tools, such as a screwdriver.

[0042] In addition to providing a mechanical connection, the base connectors 60 include mechanisms to electrically connect the arm modules. For example, electrical connections may be provided to provide power to the propulsion system or control signals to various control systems. In the present example, the propulsion system includes a plurality of rotors 66 that can be controlled by adjusting the speed and angle for each rotor 66 to control the overall movement of the apparatus 50. In particular, the electrical connections may include a sole electrical connection between an electronic speed controller in the base module and the three phases inside each motor on the arm modules 65. Pulsed power may be sent from the electronic speed controller to the motor, and the electronic speed controller may collect feedback via the same connections to determine motor state and adjust its output.

[0043] In the present example, each arm module 65 includes a propulsion system,which in this case is a pair of rotors 66 to provide lift to the apparatus 50 during operation. It is to be appreciated by a person of skill that the arm modules are not particularly limited and may be varied with other designs. In the present example, the control arm module 65-1 includes two 4” rotors 66 that can be operated in combination with rotors on another arm module 65-2 of the apparatus 50. During operation, the rotors 66 may vary in rotational speed to control the lift provided to the apparatus 50. In addition, the rotors 66 may be pivoted to control the direction of flight. It is to be appreciated by a person of skill with the benefit of this description that the operation of the arm module 65 may be controlled via commands received from the base module 55.

[0044] In the present example, each of the arm modules 65 is substantially similar to each other. The substantially similar arm modules 65 provide a balanced apparatus 50. In some examples, the arm modules 65 may be different based on the design to distinguish the different rotors 66 and control signals for each of the rotors 66.

[0045] The arm modules 65 are designed to be easily removable and installed. Accordingly, a user may carry multiple arm modules 65 into the field and reconfigure the apparatus 50 to have different lengths for the arm modules 65 to support different rotor sizes and designs. The different rotor sizes will allow the same apparatus 50 to be used for different missions with different technical specifications.

[0046] In some examples, the base module 55 may include alignment mechanisms to guide and align the arm modules 65 relative to the base module. Accordingly, the arm module 65 may be inserted into an alignment mechanism at one end of the base module 55 and another arm module 65 may be inserted into another alignment mechanism at the opposite end of the base module. The alignment mechanisms are not particularly limited. For example, the alignment mechanism may include various guides, such as angled mating surfaces and features to center the arm module 65 as it is being inserted such that the resistance increases as the arm module 65 is inserted until electrical connectors of the base module 55 mate with complimentary connectors on the arm module 65. The arm module 65 may then be secured to the base module with a clip or fastener, such as a screw, to avoid disengagement during flight.

[0047] Furthermore, the base module 55 may include an arm selector to modify the configuration of the base module 55 for different arm modules 65. For example, largerarm modules 65 used to carry larger payloads may use more power to operate larger motors. Accordingly, a power distribution system of the base module 55 may change configurations to provide higher power to the arm modules 65. The base module 55 may also load different configurations to modify an autopilot system to improve flight control and characteristics based on the size of the arm module 65. The manner by which the arm selector changes the configuration of the base module 55 is not particularly limited. In some examples, the arm selector may be a physical switch that can be manipulated by a user installing the arm module 65. In some examples, the physical switch may mate with a portion of the arm module 65 such that when the arm module 65 is inserted into the base connector 60 a feature of the arm module 65 physically manipulates the switch to select the correct configuration. In other examples, additional electronics in the arm modules 65 may self-identify when connected to the base module 55, and the selection of a configuration may be carried out electronically.

[0048] Referring to figure 2A and figure 2B, another example of an apparatus 50a to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50a bear like reference to their counterparts in the apparatus 50, except followed by the suffix “a”. In the present example, the apparatus 50a includes a base module 55a, base connectors 60a-1 , 60a-2 (generically, these base connectors are referred to herein as “base connector 60a” and collectively they are referred to as “base connectors 60a”), arm modules 65a-1 , 65a-2 (generically, these arm modules are referred to herein as “arm module 65a” and collectively they are referred to as “arm modules 65a”) with rotors 66a, a camera 70a, and an external battery pack 75a.

[0049] In the present example, the camera 70a is part of the base module 55a and is used to capture images. The applications of the camera 70a is not particularly limited. In the present example, the camera 70a may be used to provide a first-person view from the apparatus 50a in real time for the pilot of the apparatus 50a. In other examples, the camera 70a may be used to collect data for subsequent download. In further examples, the camera 70a may be used by a processor in the base module 55a to provide image processing that can also be used for semi-autonomous or autonomous flight. Additionally, the camera 70a may be used to detect obstacles or other hazards to avoid a crash.

[0050] The external battery pack 75a may be mounted to the base module 55a and in electrical communication with the base module components. The external battery pack 75a is not particularly limited and may include a lithium ion cell with a capacity of about 150 Wh to about 500 Wh. The external battery pack 75a is to provide additional energy for longer operation before recharging. It is also to be appreciated by a person of skill with the benefit of this description that the external battery pack 75a may be smaller, such as 30 Wh for smaller arm modules 65a.

[0051] Referring to figure 3A and figure 3B, another example of an apparatus 50b to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50b bear like reference to their counterparts in the apparatus 50a, except followed by the suffix “b”. In the present example, the apparatus 50b includes a base module 55b, base connectors 60b-1 , 60b-2 (generically, these base connectors are referred to herein as “base connector 60b” and collectively they are referred to as “base connectors 60b”), arm modules 65b-1 , 65b-2 (generically, these arm modules are referred to herein as “arm module 65b” and collectively they are referred to as “arm modules 65b”), a camera 70b, and an external battery pack 75b.

[0052] In the present example, the apparatus 50b includes different arm modules 65b connected to the base module 55b. The base module 55b may be substantially identical to the base module 55a. Accordingly, the apparatus 50b may be a different configuration of the apparatus 50a where the arm modules 65a are substituted with the arm modules 65b. In the present example, the arm module 65b-1 includes two 7” rotors 66b that can be operated in combination with rotors on another arm module 65b-2 of the apparatus 50b.

[0053] Referring to figure 4A and figure 4B, another example of an apparatus 50c to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50c bear like reference to their counterparts in the apparatus 50a, except followed by the suffix “c”. In the present example, the apparatus 50c includes a base module 55c, base connectors 60c-1 , 60c-2 (generically, these base connectors are referred to herein as “base connector 60c” and collectively they are referred to as “base connectors 60c”), arm modules 65c-1 , 65c-2 (generically, these arm modules are referred to herein as “arm module 65c” and collectively they are referred to as “armmodules 65c”), a camera 70c and external battery packs 75c-1 , 75c-2 (generically, these external battery packs are referred to herein as “external battery pack 75c” and collectively they are referred to as “external battery packs 75c”).

[0054] In the present example, the apparatus 50c includes different arm modules 65c connected to the base module 55c. The base module 55c may be substantially identical to the base module 55a. Accordingly, the apparatus 50c may be a different configuration of the apparatus 50b where the arm modules 65b are substituted with the arm modules 65c. In the present example, the arm module 65c-1 includes two 10” rotors 66c that can be operated in combination with rotors on another arm module 65c-2 of the apparatus 50c. Since the rotors 66c are larger in the present example compared with previous examples, such as the rotor 66, additional energy is used to maintain flight. Accordingly, the present example includes another external battery pack 75c in communication with the base module 55c to provide extended flight time.

[0055] It is to be appreciated by a person of skill that variations are possible and that the apparatus 50 may include various design changes. Although the examples shown support a different propeller diameter, which affects performance measures of the unmanned aerial vehicle, such as speed, flight time, payload capacity, etc., other variations of the design are also contemplated. For example, the arm modules 65 may be modified to provide a vertical-takeoff-and-landing plane. After installing both arm modules, each containing the motors to support its intended functionality, the user may power up their ground control system and set their arm module either automatically or with a selector, such as a multi-position switch.

[0056] Referring to figure 5A and figure 5B, another example of an apparatus 50d to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50d bear like reference to their counterparts in the apparatus 50a, except followed by the suffix “d”. In the present example, the apparatus 50d includes a base module 55d, base connectors 60d-1 , 60d-2 (generically, these base connectors are referred to herein as “base connector 60d” and collectively they are referred to as “base connectors 60d”), arm modules 65d-1 , 65d-2 (generically, these arm modules are referred to herein as “arm module 65d” and collectively they are referred to as “arm modules 65d”), rotors 66d and a camera 70d.

[0057] In the present example, the apparatus 50d includes a locking mechanism to secure each of the arm modules 65d to the base module 55d. The locking mechanism is not particularly limited and may include variations to secure the arm modules 65d rigidly to the base module 55d to improve flight stability. For example, the locking mechanism may include screws 67d-1 , 67d-2 (generically, these screws are referred to herein as “screw 67d” and collectively they are referred to as “screws 67d”. The screws engage the arm modules and can be tightened to reduce relative movement between each arm module 65d and the base module 55d. Referring to figures 6A and 6B, the arm modules 65d can be inserted into their respective base connectors 60d. Each of the base connectors 60d includes electrical connectors to provide power to the rotor motors and control signals to various control systems that adjust speed and angle for each rotor 66d. Upon inserting the arm module 65d in the base connector, the screw 67d is inserted through arm module 65d and tightened to lock the arm module 65d in place relative to the base module 55d.

[0058] In other examples, alternative locking mechanisms may be substituted if the mechanism is sufficiently strong and mechanically rigid to secure the arm module 65d to the base module 55d. It is to be appreciated by a person of skill with the benefit of this description that if arm module 65d is free to shift or vibrate relative to the base module 55d, flight control may be affected and deteriorate as random motions of the rotors 66d will lead to unpredictable motions to be compensated for.

[0059] To improve flight stability, a vibration dampening system may be added to the apparatus 50d. For example, a resilient material may be used to line the contact points between the arm module 65d and the base module 55d. As the arm module 65d is tightened against the base module, the resilient material may reduce movement between the arm modules 65d and the base module 55d. In the present example, the apparatus 50d includes a flexible plate 68d disposed on the base module 55d. The flexible plate 68d is not particularly limited and may be made from any material that can be flexed under tension to apply a force to clamp each of the arm modules 65d against the base module. For example, the flexible plate 68d may be made of metal, such as aluminum or steel. In other examples, the flexible plate 68d may be made from a plastic or composite material. In use, once the arm module 65d is inserted into the baseconnector (shown in figure 7), the screw 67d can be inserted and tightened as shown in figure 8. Upon tightening the screw 67d-1 , the edge 168-1 of the flexible plate 68d is bent toward the arm module 65d-1 under tension from the screw 67d-1 . The edge 168- 1 clamps down to engage the arm 65d-1 and urges it against the other surface of the base module 55d to limit relative motion between the arm module 65d and the base module to reduce relative vibrations and increase the strength of the mechanical connection between the arm module 65d and the base module 55d.

[0060] It is to be appreciated by a person of skill with the benefit of this description that other locking mechanisms may be substituted as long as they can provide similar mechanical stability. For example, the arrangement of the screw 67d and other mechanical guidance features is not limited and may be disposed in different configurations. In other examples, locking mechanisms may involve a friction fit or magnetic coupling as well. The locking mechanism provides a simple way to exchange arm modules in the field for different applications. In the example described above, a simple two-step process involving loosening and tightening a screw without additional tools or special training is provided that can be used to change configurations.

[0061] Referring to figure 9A and figure 9B, another example of an apparatus 50e to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50e bear like reference to their counterparts in the apparatus 50d, except followed by the suffix “e”. In the present example, the apparatus 50e includes a base module 55d, arm modules 65e-1 , 65e-2 (generically, these arm modules are referred to herein as “arm module 65e” and collectively they are referred to as “arm modules 65e”), and a camera 70e.

[0062] In the present example, the apparatus 50e includes different arm modules 65e connected to the base module 55d from the example shown in figures 5A and 5B. In particular, the base module 55d includes a locking mechanism with screws 67d. The screws may be loosened to exchange the arm modules 65d with the arm modules 65e to reconfigure the apparatus 50d into the apparatus 50e.

[0063] Accordingly, the apparatus 50e may be a different configuration of the apparatus 50d where the arm modules 65d are substituted with the arm modules 65e while using the same base module 55d. Accordingly, the arm modules 65e areconfigured to connect to the same base connectors 60d with the same locking mechanism using the screws 67d. In the present example, the arm module 65e-1 includes two 10” rotors 66e that can be operated in combination with rotors on another arm module 65e-2 of the apparatus 50e. Since the rotors 66e are larger, the apparatus 55e is capable of achieving greater lift to support heavier equipment such as the camera 70e, which is an upgraded version of the camera 70d. It is to be appreciated by a person of skill with the benefit of this description that the camera 70e may be another component of the base module 55d that can be readily substituted in the field to adapt the apparatus 50e to different applications. For example, an upgraded camera may include additional features, such as increased zoom capabilities or detecting different spectrums such as infrared. In further examples, the camera 70e may be substituted with other equipment, such as packages for delivery, crop dusting chemicals, weapons, etc.

[0064] Referring to figure 10, another example of an apparatus 50f to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50f bear like reference to their counterparts in the apparatus 50d, except followed by the suffix “f” . In the present example, the apparatus 50f includes a base module 55d, and fixed wings 80f-1 , 80f-2 (generically, these fixed wings are referred to herein as “fixed wing 80f” and collectively they are referred to as “fixed wings 80f”).

[0065] In the present example, the apparatus 50f replaces arm modules 65d from the example apparatus 50d shown in figures 5A and 5B with fixed wings 80f. In particular, the same base module 55d is used and the fixed wings 80f are configured to mechanically engage around the base module 55d. In particular, each of the fixed wings 80f is configured to connect with the base connectors 60d to receive power for the rotors 66f as well as control signals to operate the rotors 66f as well as other control components, such as flaps (not shown) on the fixed wings 80f. The fixed wings 80f are configured to engage the locking mechanism with screws 67d such that the base module 55d may be modified in the field to convert from a quadcopter design to a fixed wing design to increase flight times, payload capacity, speed, and / or range. To aid with mounting of the fixed wings 80f, each fixed wing 80f may include mechanical features 85f, 87f (as shown in figure 11) to mate with complimentary features on the other fixedwing 80f or the base module 55d.

[0066] Referring to figure 12A and figure 12B, another example of an apparatus 50g to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50g bear like reference to their counterparts in the apparatus 50f, except followed by the suffix “g”. In the present example, the apparatus 50g includes a base module 55d, and fixed wings 80g-1 , 80g-2 (generically, these fixed wings are referred to herein as “fixed wing 80g” and collectively they are referred to as “fixed wings 80g”).

[0067] In the present example, the apparatus 50g includes fixed wings 80g, which are configured to convert between a storage configuration (shown in figure 12A) and an operational configuration (shown in figure 12B). It is to be appreciated by a person of skill with the benefit of this description that the fixed wing 80g allows for a more compact form for transportation and that it can be deployed readily at a specific location.

[0068] In the present example, the apparatus 50g uses the same base module 55d and the fixed wings 80g are configured to mechanically engage around the base module 55d. In particular, each of the fixed wings 80g is configured to connect with the base connectors 60d to receive power for the rotors 66g as well as control signals to operate the rotors 66g as well as other control components. The fixed wings 80g are configured to engage the locking mechanism with screws 67d such that the base module 55d may be modified in the field to convert from a quadcopter design to a fixed wing design or to different fixed wings to achieve certain parameters, such as vertical flight capabilities, maneuverability, flight times, payload capacity, speed, and / or range.

[0069] Referring to figure 13, another example of an apparatus 50h to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50h bear like reference to their counterparts in the apparatus 50g, except followed by the suffix “h”. In the present example, the apparatus 50h includes a base module 55d, and fixed wings 80h-1 , 80h-2 (generically, these fixed wings are referred to herein as “fixed wing 80h” and collectively they are referred to as “fixed wings 80h”).

[0070] In the present example, the apparatus 50h includes fixed wings 80h that are much larger than the fixed wings 80g. In addition, the fixed wings 80g include additional rotors 66g. It is to be appreciated by a person of skill with the benefit of this descriptionthat the fixed wing 80g provides more lift allowing for increased payload for applications.

[0071] The apparatus 50g uses the same base module 55d and the fixed wings 80g are configured to mechanically engage around the base module 55d. In particular, each of the fixed wings 80g is configured to connect with the base connectors 60d to receive power for the rotors 66g as well as control signals to operate the rotors 66g as well as other control components. The fixed wings 80g are configured to engage the locking mechanism with screws 67d such that the base module 55d may be modified in the field to convert from a quadcopter design to a fixed wing design or to different fixed wings to achieve certain parameters, such as vertical flight capabilities, maneuverability, flight times, payload capacity, speed, and / or range.

[0072] Referring to figure 14A and figure 14B, another example of an apparatus 50i to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50i bear like reference to their counterparts in the apparatus 50g, except followed by the suffix “i”. In the present example, the apparatus 50i includes the base module 55d, and fixed wings 80i-1 , 80i-2 (generically, these fixed wings are referred to herein as “fixed wing 80i” and collectively they are referred to as “fixed wings 80i”).

[0073] In the present example, the apparatus 50i includes fixed wings 80i where the rotors 66i are mounted in front of the fixed wing 80i to pull the wing. It is to be appreciated by a person of skill with the benefit of this description that the fixed wing 80i provides more common aerodynamic design for fixed wing aircraft, s

[0074] In the present example, the apparatus 50i includes fixed wings 80i, which are configured to convert between an operational configuration (shown in figure 12A) and a storage configuration (shown in figure 12B). It is to be appreciated by a person of skill with the benefit of this description that the fixed wing 80i allows for a more compact form for transportation and that it can be deployed readily at a specific location.

[0075] Referring to figure 15A and figure 15B, another example of an apparatus 50k to provide a configurable unmanned aerial vehicle is generally shown. Like components of the apparatus 50k bear like reference to their counterparts in the apparatus 50i, except followed by the suffix “k”. In the present example, the apparatus 50k includes the base module 55d, and fixed wings 80k-1 , 80k-2 (generically, these fixed wings arereferred to herein as “fixed wing 80k” and collectively they are referred to as “fixed wings 80k”).

[0076] In the present example, the apparatus 50k includes fixed wings 80k, which are configured to convert between an operational configuration (shown in figure 15A) and another storage configuration (shown in figure 15B). It is to be appreciated by a person of skill with the benefit of this description that the fixed wing 80k allows for a more compact form for transportation and that it can be deployed readily at a specific location.

[0077] Referring to figure 16, another example of an apparatus 50m to provide another type of vehicle is generally shown. In the present example, the apparatus 50m includes the base module 55d, and a ground propulsion system including pairs of wheels 90m-1 , 90m-2 (generically, these wheels are referred to herein as “wheel 90m” and collectively they are referred to as “wheels 90m”).

[0078] In the present example, the apparatus 50m includes wheels 90m, where each wheel 90m may be powered by a motor (not shown) controlled by the base module 55d. In some examples, one or more of the wheels 90m may not be powered such that the apparatus 50m has one, two, or three drive wheels 90m. It is to be appreciated by a person of skill with the benefit of this description that the wheels 90m may be varied depending on the intended terrain and substituted with a chain track, sleds, or other ground propulsion systems. Furthermore, the base module 55d may also be used on other types of vehicles, such as boats, submarines, or trains.

[0079] Referring to figure 17, a flowchart of an example method of reconfiguring a apparatus in the field is generally shown at 200. In order to assist in the explanation of method 200, it will be assumed that method 200 may be performed on the apparatus 50. Indeed, the method 200 may be one way in which the apparatus 50 may be configured in the field. Furthermore, the following discussion of method 200 may lead to a further understanding of the apparatus 50 and its components.

[0080] Beginning at block 210, mission parameters may be received in the field. The manner by which the parameters are received is not particularly limited. In the present example, the parameters may be received at the apparatus 50 and displayed on a screen. In other examples, the parameters may be predetermined prior to travel to thefield or may be received by a user on a separate portable electronic device, such as a phone, tablet, or laptop device. The parameters themselves are also not particularly limited and may include specifications, such as the components to use for the mission, or it may be more general, such as the type of payload and / or flight time, leaving the selection of the components to be decided at the field.

[0081] Block 220 comprises selecting first and second arm modules 65 to be used for a mission. The selection of the arm modules 65 is to be based on the mission parameters received at block 210. In addition to the parameters, other factors may be considered in the selection of the arm modules 65. For example, environmental factors, such as temperature, pressure, and weather conditions may be considered.

[0082] Next, block 230 comprises connecting the arm modules 65 to opposite ends of the base module 55. The manner by which the arm modules 65 are connected is not particularly limited. In the present example, the arm modules 65 may be connected to base connectors 60 disposed on opposite ends of the base module 55. The base connectors 60 may include various components to facilitate a mechanical connection to rigidly hold the arm modules 65 relative to the base module 55. In some examples, the base connectors 60 may each include a securing mechanism to lock each respective arm module 65 rigidly to the base module 55 to provide for rapid connection and disconnection of the arm modules 65, manually (i.e., without tools) or with basic tools, such as a screwdriver.

[0083] Since different missions may benefit from different performance characteristics, such as speed, flight time, and payload capacity, offering multiple arm modules supporting various propeller sizes and configurations allows a user to customize the apparatus to meet specific mission specifications. Therefore, the present apparatus provides a quick-change arm mechanism and the ability to adapt the size and form of the assembled airframe to suit different propeller sizes via the exchange of arm modules to reduce the amount of equipment used in the field to accommodate varying mission specifications.

[0084] It should be recognized that features and aspects of the various examples provided above may be combined into further examples that also fall within the scope of the present disclosure.

Claims

What is claimed is:1 . An apparatus comprising: a base module having a first end and a second end, wherein the first end is opposite the second end; a first base connector disposed on the first end of the base module; a first arm module to mate with the first base connector, wherein the first arm module includes a first propulsion system to be controlled by the base module; a second base connector disposed on the second end of the base module; and a second arm module to mate with the second base connector, wherein the second arm module includes a second propulsion system to be controlled by the base module.

2. The apparatus of claim 1 , wherein the first propulsion system is a first pair of rotors and the second propulsion system is a first pair of rotors.

3. The apparatus of claim 1 or 2, further comprising a first alignment mechanism to align the first arm module to the base module and a second alignment mechanism to align the second arm module to the base module.

4. The apparatus of any one of claims 1 to 3, wherein the first base connector includes a securing mechanism to lock the first arm module to the base module.

5. The apparatus of claim 4, wherein the securing mechanism is manually operated.

6. The apparatus of any one of claims 1 to 5, further comprising an external battery pack mounted to the base module.

7. The apparatus of any one of claims 1 to 6, wherein the base module includes an autopilot system.

8. The apparatus of any one of claims 1 to 7, wherein the base module includes a camera.

9. The apparatus of any one of claims 1 to 8, wherein the base module includes a global positioning system.

10. The apparatus of any one of claims 1 to 9, further comprising a first screw to engage the first arm module to the base module and a second screw to engage the second arm module to the base module.11 . The apparatus of claim 10, further comprising a vibration dampening system to reduce vibration between the first arm module, the second arm module and the base module.

12. The apparatus of claim 11 , wherein the vibration dampening system is a flexible plate disposed on the base module to clamp the first arm module and the second arm module.

13. The apparatus of claim 12, wherein the first screw bends a first end of the flexible plate to engage the first arm module and the second screw bends a second end of the flexible plate to engage the second arm module.

14. A method comprising: receiving mission parameters;selecting a first arm module and a second arm module based on the mission parameters; connecting the first arm module to a first base connector, wherein the first base connector is disposed on a first end of a base module, and disposed on the first end of the base module; and connecting the second arm module to a second base connector, wherein the second base connector is disposed on a second end of the base module, and disposed on the second end of the base module.

15. The method of claim 14, wherein mating the first arm module to a first base connector comprises aligning the first arm module to the base module, and wherein mating the first arm module to a first base connector comprises aligning the first arm module to the base module.

16. The method of claim 14 or 15, further comprising locking the first arm module and the second arm module to the base module.

17. The method of claim 16, wherein locking the first arm module and the second arm module comprising using a first screw to engage the first arm module and a second screw to engage the second arm module.

18. The method of claim 17, further comprising reducing vibration between the first arm module, the second arm module and the base module with a vibration dampening system.

19. The method of claim 18, wherein reducing vibration between the first arm module, the second arm module and the base module comprises clamping the first armmodule and the second arm module with a flexible plate disposed on the base module.

20. The method of claim 19, further comprising bending a first end of the flexible plate with the first screw to clamp the first arm module, and bending a second end of the flexible plate with the second screw to clamp the second arm module.

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