1. TECHNICAL FIELD OF THE INVENTION

The present invention generally relates to a system and method of a docking system for fixed wing unmanned aerial vehicle, or non-fixed wing unmanned aerial vehicle such as rotorcraft, or combination thereof, comprising at least a docking and/or launching pad capable of arranged in an array or staggered manner; said pad has a surface for said vehicle docking and launching, said docking and launching surface comprising a latching mechanism which includes electromagnets that can be energized to capture a docking vehicle; and another energy harvesting surface has photovoltaic panel to harness solar energy to generate electricity or hydrogen fuel for a variety of onboard applications such as to charge the said vehicle, to power the docking system, or the unmanned marine vehicle if the present invention is being deployed on water.

2. BACKGROUND OF THE INVENTION

Fixed-wing UAVs triumph over non-fixed/ rotary- wing UAVs in terms of flight endurance, which is a highly valuable attribute for many applications such as surveillance. However, a key disadvantage of fixed- W

2 wing aircraft is that they generally require a runway for taking off and landing with an airspeed of approximately 30 kmlr ¹ and above depending on the wing loading. The kinetic energy (KE) associated with the forward velocity of the aircraft has to be dissipated in a gradual manner prior to the 5 touch-down phase to prevent structural damage to the airframe.

Efforts have been made to develop airplanes that can perform vertical take-off and landing (VTOL) and thus eliminating the need for runway and the dissipation of KE upon touched down. However, the solutions often involve significant increase in mechanical complexity of the aircraft which 10 in turn deteriorate the reliability and safe operation of the aircraft This invention recognizes that an airframe that keeps complex mechanical component count to the minimum is critical to mission success.

3. SUMMARY OF THE INVENTION

15 Accordingly, it is the primary aim of the present invention to provide a fully automated docking system for fixed and non-fixed wing unmanned vehicle with the ability to dock, stow in a safe manner, replenish onboard energy storage, and re-launch without human intervention.

It is an object of the present invention to handle fixed wing UAV 20 capable of 'harrier" maneuver and VTOL (vertical take-off and landing) maneuver. It is an object of the present invention to stow both fixed and non- fixed wing UAV in an opened top compartment away from weather elements such as gusty winds, rain-water, and damaging ultraviolet exposure. It is an object of the present invention to provide energy harvesting surface to gather solar energy to charge the vehicle energy storage system.

It is an object of the present invention to provide electromagnet- based mechanism on the docking and launching surface to allow the vehicle to securely attach on the surface during take-off and docking procedures. It is an object of the present invention to have a plurality of transceivers on the docking and launching surface to receive signals emitted from at least one vehicle transceiver during a docking procedure, to allow the surface to adjust inclination angle.

Additional objects of the invention will become apparent with an understanding of the following detailed description of the invention or upon employment of the invention in actual practice.

According to the preferred embodiment of the present invention the following is provided:

A docking system (1) for fixed or non- fixed wing unmanned aerial vehicle (2), comprising: at least one docking and launching surface (6) to enable said vehicle (2) to dock and launch; characterized in that at least one energy harvesting surface (4) is disposed opposite of said docking and launching surface (6) to harvest solar energy to charge up said vehicle (2) energy storage system; further characterized in that said docking system (1) comprising a plurality of transceivers, to receive signals emitted from at least one vehicle transceiver (19), during a docking procedure to enable said vehicle (2) to make self-alignment and dock on said surface (6).

In an aspect of the present invention, there is provided,

A method of docking system (1) for fixed or non-fixed wing unmanned aerial vehicle (2) for a take-off procedure (50), comprising steps of: energizing said vehicle propulsion system to suitable pre-determined take-off power (503); and releasing latching mechanism on said docking surface to enable said vehicle to be released (504). In another aspect of the present invention, there is provided,

A method of docking system (1) for fixed or non-fixed wing unmanned aerial vehicle (2) for a docking procedure (51), comprising steps of: activating transceivers to transmit and emit signals on said vehicle for detecting and ranging the docking system (506); turning off said vehicle propulsion (512); and rotating said docking surface about the pivot for safe stowage of said vehicle (513). 4. BRIEF DESCRIPTION OF THE DRAWINGS

Other aspect of the present invention and their advantages will be discerned after studying the Detailed Description in conjunction with the accompanying drawings in which:

FIG. 1 shows an exemplary side view of the present invention with an unmanned aerial vehicle in an initial position of safe stowage and solar energy harvesting.

FIG. 2- A shows a bottom view of an UAV. FIG. 2-B shows an example image as seen by an image processor of the docking system. Such information is used to establish the correct final approach.

FIG. 3-A shows a perspective view of three dynamic contact pads which consist of the electromagnets and the latching mechanisms.

FIG. 3-B shows a closed up view of the contact pad with electromagnet and the latching mechanisms.

FIG. 3-C shows a closed up view of a landing gear of the vehicle on the contact pad. FIG. 3-D shows a closed up view of the landing gear of the vehicle being latched on by the latching mechanisms.

FIG. 3-E shows a closed up view of the latching mechanisms with the individual latches which can be independently retracted.

FIG. 4-A shows a side view of a plurality of the present inventions in safe stowage position.

FIG. 4-B shows a side view of a plurality of the present inventions rotated by pivot to allow a plurality of vehicles for take-off/launching procedure. W

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FIG. 4-C shows a side view of a plurality of vehicles taking off from the present invention.

FIG. 4-D shows a side view of a plurality of the present inventions return to the initial position of safe stowage.

5 FIG. 4-E shows a side view of an unmanned aerial vehicle flight approaching the docking surface of the present invention which includes the UAV making the "harrier" maneuver in the process in order to achieve an ultimate forward airspeed of less than 15 krnh- ¹ .

FIG. 5-A shows a top view of a plurality of present inventions being 10 arranged in an array formation.

FIG. 5-B shows a top view of a plurality of present inventions being arranged in a V-formation.

FIG. 6-A shows a diagram of take-off procedure of fixed wing UAV of the present invention.

15 FIG. 6-B shows a diagram of landing or docking procedure of fixed wing UAV of the present invention.

5. DETAILED DESCRIPTION OF THE DRAWINGS In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, it will be understood by the person having ordinary skill in the art that the invention may be practised without these specific details. In other instances, well known methods, procedures and/or components have not been described in detail so as not to obscure the invention.

The invention will be more clearly understood from the following description of the embodiments thereof, given by way of example only with reference to the accompanying drawings, which are not drawn to scale.

Referring to FIG. 1 illustrates side view of the present invention of docking system (1) for fixed or non-fixed wing unmanned aerial vehicle (2), comprising at least one docking and launching surface (6) to enable vehicle (2) to dock and launch, and at least one energy harvesting surface (4) is disposed opposite of the surface (6), preferably photovoltaic solar cell, to harvest solar energy (10) to charge up the vehicle (2) energy storage system (not shown) via landing gear (7) or via electric cables (14) to power the vehicle propulsion system. The solar energy (10) can also be used to supply electricity to the mother vehicle (not shown) or to drive an electrolysis reactor (not shown) to generate hydrogen as energy carrier for the vehicle (2). Preferably, the vehicle propulsion system is propeller driven (single or co-axial) with electric motor(s). At least one pivotal mean (8) is provided on the docking system to allow the system to rotate according to which procedures to be executed, such as initial stage of safe stowage of vehicles, launching of the vehicles, or docking of the vehicles. The docking system (1) is preferable to allow the docking and launching surface (6) and the energy harvesting surface (4) mounted in an opened top compartment (3) to protect any vehicles (2) from harmful weather elements such as gusty winds, rain, and ultraviolet rays.

The docking system (1) comprising a plurality of transceivers capable of transmitting and/ or receiving signals, or a combination thereof, to receive signals emitted from at least one vehicle transceiver (19), preferably with emitters located on the landing gear (7) and underneath vehicle wing or fuselage as shown in FIG. 2- A. The emitted signals are primarily used for self-alignment purpose for the vehicle (2) during a docking procedure to dock on said surface (6). Similarly, the surface (6) is also capable of self- alignment to allow said vehicle (2) to dock. Conversely, for non-fixed wing vehicle docking, the surface (2) will be in an approximate parallel plane of the ground surface.

Signals are defined as visible light or invisible lights such as infrared or the like, audible sound waves, inaudible sound waves such as ultrasound or the like, or radio waves as radio frequency (RF) or the like, or a combination thereof. Depending on the environmental condition, the system (1) and the vehicle (2) can select a signal type best suit for the condition, for example, in foggy weather, transmission and receiving of visible light signal will be affected, thus, L-band waves (1 to 2 GHz) can be used as they are largely unaffected by fog, rain, and cloud.

The vehicle (2) transmits its vehicle information to the docking system (1) at the onset of the final approach, and the docking surface (6) will be set to the correct angle for that particular class of aircraft Referring to FIG. 2-B, there is shown an example image as seen by an image processor of the docking system (1). Such information is used to establish the correct final approach of said vehicle (2). An onboard computer on the system (1) instructs the latching mechanisms to self-align with the aircraft prior to docking.

Referring now to FIG. 3-A, there is shown a docking and launching surface (6) comprising at least one contact pad (31) traversing in guided tracks (30). When a vehicle (2) is performing a docking procedure, the movable pad (31) is docile and it has real-time capability to intercept and realign itself with the approaching UAV in case the vehicle (2) veers off course due to air turbulence.

Referring now to FIG. 3-B, there is shown a single unit of contact pad (31) in disengaged mode comprising electromagnet (37), at least a latching mechanism consisting of latches (33) running along guiding grooves (35). The electromagnet (37) is de-energized with the latching mechanism disengaged. This configuration occurs in scenarios such as retrieving an approaching unmanned helicopter. Referring now to FIG. 3-C, there is shown a part of the vehicle (not shown) landing gear (7) is firmly attached on the electromagnet (37). The electromagnet (37) is energized to draw the landing gear (7) onto the electromagnet (37) and providing a temporary hold on the gear (7) while the latching system is in disengaged mode.

Referring now to FIG. 3-D, there is shown the latches (33) moving along the grooves (35) and secures the gear (7). The electromagnet (37) is de- energized once the latches (33) has secured the landing gear.

Referring now to FIG. 3-E, the latches (33) can be independently retracted into the contact pad (31) when necessary and this feature is particularly useful during the launching phase of fixed-wing UAVs.

Referring now to FIG. 4-A, there is shown a side view of the present invention with a plurality of vehicles (2) in upside down position, or initial safe stowage position. The vehicles (2) are held onto the docking and launching surface (6) by latching mechanism. In a take-off/launching procedure, referring to FIG. 4-B, the docking and launching surface (6) is rotated to expose the vehicles (2) from the compartment (3). In a take-off procedure, referring to FIG. -C, the vehicles (2) propulsion system is engaged and the latching mechanism on the docking and launching surface (6) is set to "release" position to allow the vehicle for take-off. Referring to FIG. -D, after the vehicles (2) have departed from the surface (6), the surface (6) can be rotated to the initial safe stowage position. This position also facilitates solar energy harvesting. Referring to FIG. 4-E, during a docking procedure, the vehicle (2) approaches the surface (6), it performs the "harrier" maneuver at a pre-determined distance (18) to achieve slow and controlled forward flight. The docking surface (6) performs auto alignment, activate the electromagnets and followed by the latching mechanism to secure said vehicle (2) upon docking.

Referring now to FIGS. 5-A and 5-B, there are shown a plurality of present inventions being arranged in an array formation. However, person skilled in the art would appreciate the other arrangements such as single file, multiple file, or staggered array are possible.

Referring to FIGS. 6-A and 6-B, there are shown diagrams of the present invention operates during a safe-stowage, launching, and docking procedures of fixed wing unmanned aerial vehicles. Performing a take-off procedure (50), data exchange is carried out between the system and the vehicle in step (500), refuelling, recharging lines, and datalink disengage from said vehicle in step (501), the docking surface is tilted to expose the vehicle to an angle to allow high alpha take-off or vertical take-off in step (502); energizing said vehicle propulsion system to suitable pre-determined take-off power in step (503); releasing latching mechanism or de-energize electromagnet on said docking surface to enable said vehicle to be released in step (504). W

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Performing a docking procedure (51), wireless communication is established between the docking system and the vehicle to automatically set the docking surface to a correct inclination angle in step (505); activating transceivers on said vehicle for detection and ranging in step (506);

5 initiating final approach toward said docking surface whereby said vehicle is remotely piloted or fully autonomous in step (507); the vehicle performing a "harrier" maneuver or high-angle flight on final approach toward the docking and launching surface in step (508), detecting signals emitted by said vehicle on said docking system transceivers and continuously fine

10 tuning the lateral position of ktching mechanisms until said vehicle completes the docking procedure in step (509); energizing docking surface electromagnet to draw said vehicle landing gear toward said docking surface to prevent said vehicle from rebound landing in step (510); engaging docking surface latching mechanism to latch on said vehicle landing gear,

15 and said docking surface electro-magnetic mechanism is de-energized in step (511); turning off said vehicle propulsion in step (512); rotating said docking surface about the pivot for safe stowage of said vehicle in step (513); and refuelling/ recharging and establishes data exchange between the system and the vehicle in step (514).

20 While the present invention has been shown and described herein in what are considered to be the preferred embodiments tliereof, illustrating the results and advantages over the prior art obtained through tlie present invention, the invention is not limited to those specific embodiments. Thus, the forms of the invention shown and described herein are to be taken as illustrative only and other embodiments may be selected without departing from the scope of the present invention, as set forth in the claims appended hereto.