MODULAR PAYLOAD DEVICE FOR AN UNMANNED AIRCRAFT

OBJECT OF THE INVENTION

The present invention relates to a modular payload device which is preferably intended for the connection thereof with unmanned aircrafts and is modular in nature with several possible final configurations to allow the coupling of more than one component and to thereby facilitate the exchange, synchronization, and display of data incorporated in an unmanned aerial system.

BACKGROUND OF THE INVENTION

Unmanned aircrafts which facilitate countless day-to-day operations are extremely well known and widely used. In fact, devices of this type are highly versatile, which allows the inclusion of various accessories that allow expanding their functionalities.

Nevertheless, the applicant of the present utility model observes that devices known in this sector do not allow freedom in terms of the integration of sensors for remote sensing with unmanned aircrafts.

In fact, most known unmanned aircrafts only allow the connection of one external payload device or a payload device with the capacity for a single sensor, which significantly limits the functions thereof.

All of the above has led the applicant of the present utility model to detect the need to develop a payload device which incorporates improvements to allow the inclusion of more than one sensor and accessories depending on the required needs.

DESCRIPTION OF THE INVENTION

The modular payload device of the present invention is made up of an electromechanical assembly of components which allows an easy data exchange, synchronization, and display for sensors for remote sensing incorporated in an unmanned aerial system which is known internationally as UAS (Unmanned Aircraft System) or also as RPAS (Remotely Piloted Aircraft System) and referred to hereinafter as an unmanned aircraft.

In this sense, the modular payload device for an unmanned aircraft proposed by the present invention is provided with a body and a printed circuit board PCB. The body is thereby formed by the following elements:

- At least two longitudinal members, wherein each longitudinal member is provided with at least one coupling element.

- At least four guides, wherein each guide has attachment means through which it is coupled to the longitudinal members.

Four rods, such that one end of the rod rests on a base which is provided with anchoring means.

- At least two frames provided with a plurality of perforations and guiding recesses, wherein the guiding recesses allow coupling the frame to the guide.

- A plurality of complementary coupling elements attached to the frames.

The PCB, which is linked to one of the longitudinal members, has a plurality of standardized connectors and a plurality of power regulators for connecting flight instruments and payload instruments of the unmanned aircraft.

Moreover, the frames are fixed to the body by means of introducing the rods through the perforations of the frames. Likewise, the coupling means of the vertical longitudinal members and the anchoring means of the base are linked with the complementary anchoring means by tongue and groove clipping.

The main advantage provided by the device of the invention lies in that fact that its mechanical components ensure a quick and simple connection of instruments, while the electric circuit of the PCB allows the integration and synchronization of sensors for remote sensing or other elements such as an on-board computer, a positioning and localization system (GPS/GNSS), or a touch screen. Likewise, the developed device is modular in nature, offering complete development and connection freedom with respect to the on-board computer present in an unmanned aircraft.

According to the nature of the sensors incorporated in the modular device of the invention, it will therefore be possible to collect data for mapping, inspection, or improving the air navigation of the unmanned aircraft.

The modular device incorporates a printed circuit board (PCB) which will be connected to the sensors, an on-board computer, and a flight controller present in the unmanned aircraft.

In a practical assembly of the modular payload device on the aircraft, a battery powers the PCB which acts as a power source integrating system and enables connection between the sensors arranged in the modular payload device and the printed circuit of the unmanned aircraft. The printed circuit of the unmanned aircraft is formed by a flight controller, an on-board computer, and a screen. The flight controller is controlled by the on-board computer. The sensors connected to the PCB can therefore be used for changing flight functions of the unmanned aircraft.

Lastly, it should be pointed out that the developed modular payload device allows the time required for adapting its structural configuration to each project to be reduced, whereby the task can be performed in a matter of hours instead of days or months.

BRIEF DESCRIPTION OF THE DRAWINGS

To complete the description that will be made below and for the purpose of helping to better understand the features of the invention, a set of drawings is attached as an integral part of said description in which the following is depicted in an illustrative and non-limiting manner:

Figure 1 shows a perspective view of the modular payload device for an unmanned aircraft according to a preferred embodiment of the invention.

Figure 2 shows a perspective view of the preferred embodiment of the invention seen from an angle opposite that of the preceding figure.

Figure 3 shows a detailed view of the body and the linkage thereof to the frames and tray making up the preferred embodiment of the modular payload device for an unmanned aircraft.

Figure 4 shows a detail of a section view of the body and the linkage thereof to the frames and to a tray according to the depiction of Figure 3. Figure 5 shows a view of a rod, a base, and the attachment means making up the preferred embodiment of the modular payload device for an unmanned aircraft object of the invention.

Figure 6 shows a view of a coupling element and a complementary coupling element that collaborate with one another in the preferred embodiment of the modular payload device for an unmanned aircraft object of the invention.

Figure 7 shows a section view depicting the way in which a coupling element and a complementary coupling element, depicted in Figure 6, are attached to one another.

Figure 8 shows a depiction of a first auxiliary element which can be screwed to the frame of the modular payload device for an unmanned aircraft object of the invention.

Figure 9 shows a depiction of a second auxiliary element which can be screwed to the frame of the modular payload device for an unmanned aircraft object of the invention.

Figure 10 shows a depiction of a third auxiliary element which can be screwed to the frame of the modular payload device for an unmanned aircraft object of the invention.

Figure 11 shows a depiction of an auxiliary suspension element which can be coupled to the modular payload device for an unmanned aircraft object of the invention.

Figure 12 shows a perspective view of the modular payload device for an unmanned aircraft according to a preferred embodiment of the invention including a touch screen, a battery, GPS, IMU, LiDAR, and a PCB.

Figure 13 shows a depiction of an unmanned aircraft including a modular payload device according to the object of the present invention.

PREFERRED EMBODIMENT OF THE INVENTION

In view of the mentioned figures, specifically Figures 1 , 2, and 3, it can be observed that in a preferred embodiment of the invention the modular payload device is made up of a body (1 ) preferably formed by: - Three longitudinal members (2), wherein two of the longitudinal members (2) are provided with four coupling elements (20), two of which can be seen in Figure 4.

- Four guides (5), wherein each guide (5) has attachment means (6) through which it is coupled to the longitudinal members (2).

- Four rods (7) such that one end of the rod (7) rests on a base (8) which is provided with anchoring means (3), as can be seen in Figure 5.

- Three frames (1 1 ) provided with a plurality of perforations (12) and guiding recesses (13). Advantageously, the guiding recesses (13) allow coupling the frame (1 1 ) to the guide (5), as can be seen in Figure 3, so the frames (1 1 ) are fixed to the body (1 ) by means of introducing the rods (7) through the perforations (12) of the frames (1 1 ).

- A plurality of complementary coupling elements (14) attached to the frames (1 1 ), preferably by screwing.

As can be seen in Figures 4, 6, and 7, the anchoring means (3’) of the coupling elements (20) of the longitudinal members (2) and the anchoring means (3) of the base (8) are linked with the complementary anchoring means (14) by tongue and groove clipping. Preferably, the longitudinal members (2) are manufactured from polymer matrix composite due to its high mechanical strength relative to weight.

Likewise, the modular payload device is provided with a printed circuit board (PCB) (15) linked to one of the longitudinal members (2), wherein the PCB has a plurality of standardized connectors and a plurality of power regulators for connecting flight instruments and payload instruments of the unmanned aircraft. Preferably, the standardized connectors are at least a USB connector, an Ethernet connector, a UART connector, and an I2C connector.

As can be seen in Figure 5, the anchoring means (3) of the base (8) are preferably configured by a rigid fastener element. On the other hand, each coupling element (20) of the longitudinal members (2) is provided with a rigid fastener element (3’), as can be seen in Figures 6 and 7. Each complementary coupling element (14) is thereby preferably made up of a flexible fastener element. Therefore, as depicted in Figure 4, the rigid fastener element (3’) of the coupling element (20) facilitates attachment with the flexible fastener element of the complementary coupling element (14) by clipping, generating a linkage between the central and upper frames (11 ) and the longitudinal members (2). Similarly, the anchoring means (3) of the base (8) are attached to the complementary coupling element (14) by clipping, generating a linkage between the lower frame (11 ) and the longitudinal members (2).

The modularity of the developed device is achieved through the multiple options for arranging the frames (11 ) in height offered by the body (1 ). To that end, the base (8) has a notch (9) for coupling the guide (5); in a complementary manner, the guide (5) includes attachment means (6) which are coupled to the longitudinal member (2) and one end of the rod (7) rests on the base (8). A structure which has a plurality of frames (11 ) at different heights and attached to the longitudinal members (2) is thereby configured, such that it is possible to introduce the frames (1 1 ) on the rods (7) through the perforations (12) thereof and to fix said frames by means of the coupling elements (20).

Figure 12 shows that the modular payload device can include trays (10) associated with the longitudinal members (2) of the body (1 ), defining a space in which there are incorporated elements such as: a touch screen (17) for displaying the data collected by the sensors of the unmanned aircraft and for checking the operation of the systems on board the unmanned aircraft during flight campaigns, one or two batteries (18) for powering the modular device, an alarm for indicating the level of the battery (18), and/or an on-board computer. Specifically, it should be indicated that the inclusion of the on-board computer will be very useful if the unmanned aircraft linked to the modular payload device of the invention does not have an onboard computer.

Likewise, Figure 2 shows that the longitudinal members (2) and the trays (10) are provided with openings (4) which help to reduce the weight of the longitudinal member. Additionally, the opening (4) of the longitudinal members (2) allows for an area for anchoring elements, such as for example, the PCB (15), as can be seen in Figure 12.

Moreover, it should be pointed out that auxiliary elements (16), (16’), (16”), such as those depicted in Figures 8, 9, and 10, respectively, can be screwed onto the perforations (12) of the frames (11 ), said elements having different configurations for offering different surface constructions on the frames (11 ) depending on the elements to be incorporated thereon.

The auxiliary elements (16), (16’), (16”) added to the body (1 ) are used for coupling payload instruments at the different levels or heights as described in detail above. The auxiliary elements (16), (16’), (16”) provide the capacity to distribute the payload and add structural reinforcements if the load so requires. For example, said auxiliary elements allow incorporating additional components such as: a GPS (19), an IMU (19’), and a LiDAR (19”), as can be seen in Figure 12. IMU (19’) is an electronic device referred to as inertial measurement unit which measures and provides information about the speed, orientation, and gravitational forces of the unmanned aircraft. The inclusion of LiDAR (19”) (Light Detection and Ranging or Laser Imaging Detection and Ranging) will allow the distance from that element, as a laser emitter, to an object or surface to be determined using a pulsed laser beam.

Likewise, Figure 11 depicts an auxiliary suspension element (21 ) which can also be linked to the perforations of the frames (1 1 ) to enable the suspension of, for example, a LiDAR (19”), as can be seen in Figure 12.

Based on the foregoing, the developed modular payload device is characterized by being a useful tool. As can be seen in Figure 13, the modular payload device (23) is designed to be mounted in an unmanned aircraft (22), preferably in hybrid aircrafts referred to as VTOL (vertical take-off and landing), as depicted in Figure 13, although it can also be mounted in fixed-wing aircrafts.

The modular payload device is preferably located in the center of the fuselage of the unmanned aircraft (23) around the center of gravity, so as not to affect air navigation during pitching with load variation.