UAV NAVIGATION AND SENSOR SYSTEM CONFIGURATION

• US 20180024555A1
• Filed: 01/29/2016
• Published: 01/25/2018
• Est. Priority Date: 01/29/2015
• Status: Abandoned Application

• Current Assignee: Rocky Mountain Equipment Canada, Ltd. (Rocky Mountain Equipment Alberta Ltd.)
• Original Assignee: Rocky Mountain Equipment Canada, Ltd. (Rocky Mountain Equipment Alberta Ltd.)
• Inventors: PARKS, Curtis, POLOWICK, Chris
• Application Number:
  US15/547,208
• Publication Number:
  US 20180024555A1
• Time in Patent Office: Days
• CPC Class Codes: B32B 15/02 Layer formed of wires, e.g. mesh
• CPC Class Codes: B32B 15/14 next to a fibrous or filamentary layer
• CPC Class Codes: B32B 15/20 comprising aluminium or copper B32B15/016 and B32B15/017 take precedence
• CPC Class Codes: B32B 2250/40 Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
• CPC Class Codes: B32B 2260/021 Fibrous or filamentary layer layers of natural mineral fibres or particles being impregnated in a plastic substance B32B19/02
• CPC Class Codes: B32B 2260/046 Synthetic resin
• CPC Class Codes: B32B 2262/0269 Aromatic polyamide fibres
• CPC Class Codes: B32B 2262/106 Carbon fibres, e.g. graphite fibres
• CPC Class Codes: B32B 2307/202 Conductive
• CPC Class Codes: B32B 2307/546 Flexural strength; Flexion stiffness
• CPC Class Codes: B32B 2607/00 Walls, panels
• CPC Class Codes: B32B 27/04 as impregnant, bonding, or embedding substance not used
• CPC Class Codes: B32B 3/02 characterised by features of form at particular places, e.g. in edge regions non-uniform thickness B32B3/263
• CPC Class Codes: B32B 3/04 characterised by at least one layer folded at the edge, e.g. over another layer ; characterised by at least one layer enveloping or enclosing a material
• CPC Class Codes: B32B 3/12 characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
• CPC Class Codes: B32B 5/26 another layer next to it also being fibrous or filamentary relative arrangement of fibres or filaments of different layers B32B5/12
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 2101/30 : for imaging, photography or videography
• CPC Class Codes: B64U 2101/32 : for cartography or topography
• CPC Class Codes: B64U 2201/10 : autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: E04B 2/7422 : with separate framed panels without intermediary support posts
• CPC Class Codes: F16S 1/10 : Composite members, e.g. with ribs or flanges attached F16S1/02 takes precedence
• CPC Class Codes: G01C 11/02 : Picture taking arrangements specially adapted for photogrammetry or photographic surveying, e.g. controlling overlapping of pictures
• CPC Class Codes: G01C 21/1652 : with ranging devices, e.g. LIDAR or RADAR
• CPC Class Codes: G01C 21/1656 : with passive imaging devices, e.g. cameras
• CPC Class Codes: G01S 19/15 : Aircraft landing systems
• CPC Class Codes: G01S 19/43 : using carrier phase measurements, e.g. kinematic positioning; using long or short baseline interferometry
• CPC Class Codes: G01S 19/53 : Determining attitude
• CPC Class Codes: G05D 1/0088 : characterized by the autonomous decision making process, e.g. artificial intelligence, predefined behaviours using knowledge based models G06N5/00
• CPC Class Codes: G05D 1/101 : specially adapted for aircraft
• CPC Class Codes: G06T 11/60 : Editing figures and text; Combining figures or text
• CPC Class Codes: H04N 23/90 : Arrangement of cameras or camera modules, e.g. multiple cameras in TV studios or sports stadiums

Abstract

Systems, methods and devices for use with unmanned aerial vehicles (UAV). A central controller is coupled to the autopilot system for a UAV. Navigation is implemented by using two GPS antennas and obtaining a difference between the locations from these two antenna to arrive at a high precision bearing or direction of travel. This single GPS derived bearing is used to trigger all the various subsystems on the UAV for imaging or mapping. Areas and locations to be mapped and imaged are determined by geolocation and mapping and imaging equipment are triggered based on the single GPS signal derived from the two GPS antennas. To reduce vibration effects on navigational and imaging or mapping equipment, these are positioned as close as possible to the vehicle'"'"'s center of gravity and are deployed in a shielded box on vibration isolation mounts.

Claims

1. A system for use in an unmanned aerial vehicle (UAV), the system comprising:

a primary GPS antenna;

a secondary GPS antenna;

a controller for receiving GPS readings from said primary and secondary GPS antennas and for producing a single GPS signal based on readings from the GPS readings;

wherein

said primary GPS antenna is spaced apart from said secondary GPS antenna;

said system determines a heading of said UAV by determining a difference between GPS readings from said primary GPS antenna and GPS readings from said secondary GPS antenna;

said single GPS signal is used to control at least one other subsystem on said UAV.

2. A system according to claim 1, wherein said system further comprises a plurality of image capturing devices, said image capturing devices being controlled by said controller using said single GPS signal such that said controller activates said image capturing devices only when a location of said UAV is near a predetermined target area.

3. A system according to claim 1, wherein electronics on said UAV are enclosed in an electronics box located adjacent a center of gravity of said UAV.

4. A system according to claim 3, wherein said electronics box is mounted on vibration isolation mounts.

5. A system according to claim 1, wherein said system further comprises an autopilot subsystem, said autopilot subsystem using said single GPS signal such that said heading of said UAV is derived from said primary and said secondary GPS antennas to control a flight of said UAV.

6. A system according to claim 2, wherein every image captured by said plurality of image capturing devices is marked with a location indicating a location of an area portrayed in said image.

7. A system according to claim 1, wherein said single GPS signal synchronizes all other subsystems on said UAV.

8. A system according to claim 1, further including a data network for allowing said other subsystems to communicate with one another.

9. A system according to claim 8, wherein said data network comprises a data network switch to which said other subsystems are coupled to thereby allow said other subsystems to communicate with one another.

10. A system according to claim 8, wherein said data network is coupled to at least one communications module to thereby allow data from said communications module to control at least one of said other subsystems.

11. A system according to claim 1, wherein said UAV is equipped with at least one structural panel having a sandwich structure in which a core material is sandwiched between a first layer of carbon fiber skin and a second layer of carbon fiber skin, said core material and said first and second layers of carbon fiber skin being infused with a resin.

12. A system according to claim 11, wherein said at least one structural panel further comprises at least one rigid insert sandwiched between said first and said second layer of carbon fiber skin, said insert being for providing structural support for at least on load bearing mounting.

13. A system according to claim 12, wherein said insert is metal.

14. A structural panel comprising:

a first layer of carbon fiber skin;

a second layer of carbon fiber skin;

a core material sandwiched between said first layer and said second layer;

a rigid insert sandwiched between said first layer and said second layer and surrounded by said core material;

wherein

said first layer, said second layer, and said core material are infused with a resin.

15. A panel according to claim 14, wherein said panel is used on a UAV.

16. A panel according to claim 14, wherein said core material has a honeycomb structure.

17. A panel according to claim 14, wherein said core material is a meta-aramid material.

18. A panel according to claim 14, wherein said rigid insert is constructed of aluminum.

19. A panel according to claim 14, further comprising an aluminum mesh placed between said core material and at least one of said first layer or said second layer.