DESC:TECHNICAL FIELD OF THE INVENTION
The present disclosure relates to unmanned aerial vehicles and more particularly to a mounting arrangement for sensors and antenna of an unmanned aerial vehicle.
BACKGROUND OF THE INVENTION
Unmanned aerial vehicles (UAVs) are typically deployed with one or more sensors or sensor modules. The sensor modules may be designed to collect data concerning an environment into which the UAV is released as well as concerning the unmanned vehicle itself. The UAVs are often fitted with a magnetometer for measuring the strength and direction of magnetic fields. Extremely accurate positioning details may be calculated by using a magnetometer and combining it with the data from a Global navigation satellite system (GNSS) module, a PPK (Post Processed Kinematic) module and a helix antenna. The antenna provides precision, high bandwidth, and an advanced signal design for Global Positioning System (GPS), GLONASS, BeiDou, Galileo, IRNSS and SBAS navigation.
In most of the UAVs, the magnetometer sensors are mounted inside the main housing of the UAV whereas the antenna and GNSS module are mounted separately. This makes it difficult to assemble and disassemble the magnetometer sensor and the antenna during debugging, servicing, and maintenance of the UAV. In addition, it is difficult to undertake wire routing of these UAVs as the magnetometer is mounted inside the main housing and helix antenna is mounted outside the main housing.
Accordingly, there is a need for a mounting assembly for sensor and antenna of the UAVs that eliminates all the above-mentioned drawbacks.

SUMMARY OF THE INVENTION
An object of the present invention is to provide sensor and antenna mount assembly which provides ease to assemble and disassemble the magnetometer sensor and the antenna for debugging, services, and maintenance of the UAV.
In an embodiment, the present invention provides a mounting assembly for an unmanned aerial vehicle (UAV) comprising a first subassembly mountable on a first side of a main housing of the UAV and a second subassembly mountable on a second side of the main housing of the UAV. The first subassembly having at least a sensor disposed within an interior thereof. The first subassembly having a cylindrical body with a projection, the projection enclosed by attaching a cover to the cylindrical body, the first subassembly having an antenna mounted on an exterior portion at a distal end thereof. The second subassembly having a cylindrical body with a projection, the projection enclosed by attaching a cover to the cylindrical body, the second subassembly having a first sensor accommodated within a hollow space of the cylindrical body, the second subassembly having at least a second sensor mounted at a distal end of the cylindrical body.
According to an embodiment of the present invention, the first and second subassemblies are perpendicular to an upper face and a lower face of the main housing. Each of the first and second subassemblies has a cylindrical body lower end connected to the main housing.
According to an embodiment of the present invention, the first sensor is a magnetometer sensor. The second sensor is slidably mounted at the distal end of the cylindrical body. The second sensor is selected from a Post-Processed Kinematic (PPK) module, a real time kinematics (RTK) module, a Global navigation satellite system (GNSS) sensor, inertial measurement unit (IMU) sensor and a combination thereof.
According to an embodiment of the present invention, the subassemblies include a plurality of electrical wiring disposed within to provide an electrical connection and communication between the UAV, the sensors, and the antenna.
According to an embodiment of the present invention, the assemblies are supported by a support rib, the support rib has a first end and a second end such that the first end is fastened on an upper face of the main housing and the second end is fastened on a proximal side of the subassembly.
According to an embodiment of the present invention, the antenna is a helix antenna. The antenna is positioned with a cap.
According to an embodiment of the present invention, the cover is provided with a plurality of protrusions configured to lock the sensor in the subassembly.
In this respect, before explaining the current embodiments of the present invention in detail, it is to be understood that the present invention is not limited in its applications to the details of construction and arrangements of the components set forth in the following description or illustration. Those skilled in the art will appreciate that the concept of this disclosure may be readily utilized as a basis for the design of other structures, methods, and systems for carrying out the several purposes of the present invention.
BRIEF DESCRIPTION OF THE DRAWING
The detailed description is described with reference to the accompanying figures. The same numbers are used throughout the drawings to reference like features and modules.
Figure 1 is a perspective view of an unmanned aerial vehicle (UAV) including an embodiment of a sensor and antenna subassembly of the present disclosure;
Figure 2 is an exploded view of an embodiment of a first subassembly;
Figure 3 is an exploded view of an embodiment of a second subassembly; and
Figure 4 is an exploded view of an embodiment of the assembly illustrating a plurality of protrusions configured to restrict movement of the sensors within the subassembly.
DETAILED DESCRIPTION OF THE INVENTION
In the following description, for the purpose of explanation, specific details are set forth in order to provide an understanding of the present disclosure. It will be apparent, however, to one skilled in the art that the present disclosure may be practiced without these details.
One skilled in the art will recognize that various implementations of the present disclosure, some of which are described below, may be incorporated into a number of systems.
Further, structures and devices shown in the figures are illustrative of exemplary implementations of the present disclosure and are meant to avoid obscuring the present disclosure.
References in the present disclosure to “one embodiment” or “an embodiment” mean that a particular feature, structure, characteristic, or function described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase “in an embodiment” in various places in the specification are not necessarily all referring to the same embodiment.
Referring to Figure 1, a mounting assembly for an unmanned aerial vehicle (100) (UAV) in accordance with the present invention is shown. The mounting assembly comprises at least two subassemblies, namely a first subassembly (200) mountable on a first side of a main housing (103) of the UAV (100) and a second subassembly (300) mountable on a second side of the main housing (103) of the UAV (100). In an embodiment, the first and second subassemblies (200, 300) are mounted on the main housing (103) through a plurality of fasteners (102). In an embodiment, the fasteners (102) include but not limited to rivets, bolts and nuts, snap fitting attachments, keyways, screws, studs and the like.
In an embodiment, the first and second subassemblies (200, 300) are supported by a support rib (101). The support rib (101) has a first end that is fastened on the upper face (103a) of the main housing (103). The support rib (101) has a second end that is fastened on the proximal side of the subassembly (200, 300). In an embodiment, the support rib (101) is fastened to the main housing (103) and the subassemblies (200,300) with fasteners (102). In an embodiment, the fasteners (102) include but not limited to rivets, bolts and nuts, snap fitting attachments, keyways, screws, studs, and the like. In an embodiment, one end of the support rib (101) is permanently fastened to the subassembly (200, 300).
In an embodiment, the first and second subassemblies (200, 300) are mounted on the opposite sides of the main housing (103). In an embodiment, the subassemblies (200, 300) are mounted on the main housing (103) such that the subassemblies (200, 300) are perpendicular to an upper face (103a) and a lower face (103b) of the main housing (103).
Referring to Figure 2, the first subassembly (200) comprises at least a sensor (204) disposed inside the first subassembly (200) and an antenna (205) mounted on the first subassembly (200). In an embodiment, the sensors (204) include but not limited to magnetometer sensor, Post-Processed Kinematic (PPK) module, real time kinematics (RTK) module, Global navigation satellite system (GNSS) sensor, inertial measurement unit (IMU) sensor and the like. In an embodiment, the first subassembly (200) includes a cylindrical body (201) with a projection (202) defined thereon. The cylindrical body (201) is a L-shaped hollow cylinder in accordance with one preferred embodiment of the present invention. The cylindrical body (201) may have circular, elliptical, triangular, square, rectangular, or any polygonal shapes in other alternative embodiments of the present invention. The sensor (204) is accommodated inside a hollow space (201a) of the vertical hollow cylindrical body (201). In an embodiment, the sensor (204) is a magnetometer. The magnetometer is mounted at predetermined height such that the magnetic field of the magnetometer does not interfere with magnetic field of the other accessories or other elements of the UAV (100). In an embodiment, the antenna (205) is mounted outside at the distal end of the cylindrical body (201). According to an embodiment of the present invention, the antenna (205) is a helix antenna. In an embodiment, the antenna (205) is positioned with a cap (206). Thus, the cap (206) prevents the loosening and unscrewing of the antenna (205) due to vibration during the operation of the UAV (100). A cover (203) is attached to the cylindrical body (201) to enclose the projection (202). The lower end of the cylindrical body (201b) is connected to the main housing (103).
Referring to Figure 3, the second subassembly (300) comprises at least two sensors (304, 305) disposed inside the second subassembly (300). In an embodiment, the sensors (304, 305) can be selected from magnetometer sensor, PPK module, RTK module, GNSS sensor, IMU sensor and the like. In an embodiment, the second subassembly (300) is having a L-shaped hollow cylindrical body (301) defined with a projection (302). The cylindrical body (301) may have circular, elliptical, triangular, square, rectangular or any polygonal shape in alternative embodiments of the present invention. In an embodiment, the second subassembly (200) includes a first sensor (304) accommodated within a hollow space (301a) of the cylindrical body (301), the second subassembly (200) having at least a second sensor (305) mounted at a distal end of the cylindrical body (301). In an embodiment, the second sensor (305) is slidably mounted at the upper end of the cylindrical body (301). In an embodiment, the first sensor (304) is a magnetometer. The magnetometer (304) is mounted at predetermined height such that the magnetic field of the magnetometer (304) does not interfere with magnetic field of the other accessories or other elements of the UAV (100). A cover (303) is attached to the cylindrical body (301) to enclose the projection (302) of the cylindrical body (301). The cylindrical body (301) has a lower end (301b) that is connected to the main housing (103).
The subassemblies (200, 300) have a plurality of electrical wiring disposed therein and said electrical wiring is configured to provide an electrical connection and communication between the UAV (100), the sensors (204, 304, 305), and the antenna (205). Thus, the electrical wiring disposed inside the subassemblies (200, 300) is secure and fool proof.
In an embodiment, the second subassembly (300) comprises a magnetometer sensor as the first sensor (304) and a GNSS sensor as the second sensor (305). In an embodiment, the GNSS sensor is mounted inside at the distal end of the cylindrical body (301). The GNSS sensor is slidably mounted at the upper end of the cylindrical body (301). Combining the data of the GNSS sensor and the magnetometer provides accurate positioning details of the UAV.
In an embodiment, a plurality of protrusion is provided to restrict the movement of the sensors within the subassemblies (200, 300). Referring to Figure 4, the cover (203, 303) is provided with the plurality of protrusions (210, 310) configured to lock the sensor(s) in the subassembly (200, 300). In one preferred embodiment, the protrusion (310) of the second subassembly (300) locks the second sensor (305) i.e., GNSS sensor within the second subassembly (300) thereby restricting the movement thereof.
Thus, the mounting subassemblies (200, 300) of the present invention provides an ease to assemble and disassemble the magnetometer sensor(s), the GNSS sensor and the antenna for debugging, replacing, services, and maintenance of the UAV (100), without disturbing a main assembly of the UAV (100).
The embodiments herein and the various features and advantageous details thereof are explained with reference to the non-limiting embodiments in the following description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein.
Any discussion of devices, articles or the like that has been included in this specification is solely for the purpose of providing a context for the disclosure. It is not to be taken as an admission that any or all of these matters form a part of the prior art base or were common general knowledge in the field relevant to the disclosure as it existed anywhere before the priority date of this application.20
,CLAIMS:
1. A mounting assembly for an unmanned aerial vehicle (100) (UAV) comprising:
a first subassembly (200) mountable on a first side of a main housing (103) of the UAV (100), the first subassembly (200) having at least a sensor (204) disposed within an interior thereof, the first subassembly (200) having a cylindrical body (201) with a projection (202), the projection (202) enclosed by attaching a cover (203) to the cylindrical body (201), the first subassembly (200) having an antenna (205) mounted on an exterior portion at a distal end thereof;
a second subassembly (300) mountable on a second side of the main housing (103) of the UAV (100), the second subassembly (300) having a cylindrical body (202) with a projection (302), the projection (302) enclosed by attaching a cover (303) to the cylindrical body (301), the second subassembly (200) having a first sensor (304) accommodated within a hollow space (301a) of the cylindrical body (301), the second subassembly (200) having at least a second sensor (305) mounted at a distal end of the cylindrical body (301).
2. The mounting assembly as claimed in claim 1, wherein the first and second subassemblies (200, 300) are perpendicular to an upper face (103a) and a lower face (103b) of the main housing (103).
3. The mounting assembly as claimed in claim 1, wherein the cylindrical body (201, 301) of the first and second subassemblies (200, 300) has a lower end (201b, 301b) connected to the main housing (103).
4. The mounting assembly as claimed in claim 3, wherein the cylindrical body (201, 301) is a L-shaped cylinder.
5. The mounting assembly as claimed in claim 1, wherein the first sensor (204, 304) is a magnetometer sensor.
6. The mounting assembly as claimed in claim 1, wherein the second sensor (305) is selected from a Post-Processed Kinematic (PPK) module, a real time kinematics (RTK) module, a Global navigation satellite system (GNSS) sensor, an inertial measurement unit (IMU) sensor and a combination thereof.
7. The mounting assembly as claimed in claim 1, wherein the subassemblies (200, 300) include a plurality of electrical wiring disposed within to provide an electrical connection and communication between the UAV (100), the sensors (204, 304, 305), and the antenna (205).
8. The mounting assembly as claimed in claim 1, wherein the second sensor (305) is slidably mounted at the distal end of the cylindrical body (301).
9. The mounting assembly as claimed in claim 1, wherein the assemblies (200, 300) are supported by a support rib (101), the support rib (101) has a first end and a second end such that the first end is fastened on an upper face (103a) of the main housing (103) and the second end is fastened on a proximal side of the subassembly (200, 300).
10. The mounting assembly as claimed in claim 1, wherein the antenna (205) is positioned with a cap (206).
11. The mounting assembly as claimed in claim 1, wherein the cover (203, 303) is provided with a plurality of protrusions (210, 310) configured to lock the sensor in the subassembly (200, 300).

12. The mounting assembly as claimed in claim 1, wherein the antenna (205) is a helix antenna.