FIELD OF INVENTION
This invention is related to the Unmanned Aerial Vehicle Systems, more specifically a tilting rotor system and coaxial Propulsion system, capable of flying and navigating either by any control devices or fully autonomous system.
BACKGROUND OF THE PRESENT INVENTION
Unmanned aerial vehicle can be mainly classified in two types, Fixed wing aircraft and Rotary wing aircrafts. The rotary wing aircrafts is further classified into (helicopter & Mul tiro tor). The multirotor is generally used in a large scale for commercial and military purpose. The Fixed wing aircraft has more efficiency and endurance when compared to rotary wing aircraft but the rotary wing has its own advantages like vertical take-off and landing, capable of hovering at a particular point and able to stay in a fixed position. Hence it is necessary to build an Unmanned Aerial Vehicle which encompasses the advantages of both fixed wing and rotary wing aircraft.
US Patent No: US9120560 Bl dated Sep.l,2015-claimed a Vertical Take-off and landing aerial vehicle: an unmanned aircraft which has the capability to perform vertical take-off and landing operations, in this they use four different thrust rotors to perform vertical take-off and landing, further it uses an internal combustion engine for producing forward thrust.
US Patent No: US 20160375997 Al dated Dec.29,2016-claimed an unmanned aerial vehicle with tri-wing configuration: an unmanned aircraft which generate lift through the tri-wing configuration and thus the forward movement can be achieved through single forward thrust rotor placed at the front and rear, further it comprises of four thrust rotors to produce required thrust for vertical take-off and landing operations.

OBJECTIVES OF INVENTION
*> To fabricate the new Unmanned Aerial Vehicle structure which combines the advantage of both fixed wing and rotary wing aircrafts.
♦ To overcome the limitations of existing Fixed wing such as large space for take-off and landing.
♦ To overcome the limitations of rotary wings such as high power consumption, low endurance and low speed cruising.
♦ To combine the configurations of fixed wing and Rotary wing in the proposed work, the objectives framed are,

> High lift-to-drag ratio
> Vertical take-off & Landing
> Better efficiency with High-speed cruising
> Hovering & Maneuvering.
STATEMENT OF INVENTION
The proposed UAV is a concept of hybrid assembly which comprises the architecture of a fixed wing and rotary wing aircrafts to enhance the experience of UAV operations. The tilting rotor mechanism provides convenient transition between both these configurations which increase maneuvarability and aerial feasibility for better surveiliance. In case of high payload, coaxial propulsion system can be installed.

SUMMARY OF THE INVENTION
This summary is provided to introduce a selection of concepts in a simplified form that are further described below in detailed description. This summary is not intended to identify essential feature of the claimed subject, nor is it intended to be used as an aid in determining the scope of the claimed subject.
Provided, is an unmanned vertical take-off and landing (VTOL) device. The VTOL device may include a frame and an outer body shell comprising one or more pieces, and a propulsion system selected from co-axial propulsion and a single-axis propulsion system respectively. The propulsion system may comprise of multiple motor and propellers. The propellers may be selected either from clockwise propellers, counter clockwise propellers, and variable pitch propellers.
The VTOL device may further include a propeller protection system, a landing system that conforms to a landing Surface, one or more control surfaces selected from a group comprising of rudder, aileron, flap, elevator, antenna feed-through, a single or multi-axis tilting
system, electronic control system and battery. Furthermore, it may include_a Global Positioning
System module, a lost model alert, quick connect payloads.

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWING:
The Figures illustrate the vertical takeoff and landing of the device with their components, according to the example embodiments.
Fig-01 illustrates the top view of presented vertical takeoff and landing (VTOL) aircraft, comprising of multi rotor system along with tilting mechanism on the front and single motor propulsion unit on the rear for lower payloads.
Fis-02 illustrates the top view of presented vertical takeoff and landing (VTOL) aircraft, comprising of multirotor system along with tilting mechanism on the front and arrangement of co-axil propulsion system on the rear for lifting higher payloads.
Fig-03 illustrates the isometric view of the above mentioned vertical takeoff and landing aircraft suggested for lower payloads in Fig-01.
Fig-04 illustrates the isometric view of the above mentioned vertical takeoff and landing aircraf suggested for higher payloads in Fig-02.
Fig-05 shows the tilting mechanism provided for the single motor propulsion pairs between the nose and leading edge of the wing for the both higher and lower payload configuration.
Fig-06 shows the detailed view of single motor propulsion system mounted in between the trailing edge of the wing and empennage group of the VTOL aircraft ,that has been proposed for lower payloads.
Fig-07 shows the detailed picture of how the motors and propellers are mounted in coaxial configuration and place in between the trailing edge of the wing and the empennage group for VTOL aircraft with higher payloads.
Fig-08 highlights the isometric view of the tilting mechanism in proposed VTOL aircraft.
Fig-09 shows the isometric exploded view of tilting mechanism in the above mentioned VTOL aircraft.

Fig-10 illustrates the detailed isometric view of how the wings and empennage group of VTOL aircraft can be detached and use as normal multi rotor aircraft.
Fig-11 shows the detailed picture of the aircraft after the wings and empennage group has been detached.
Fig-12 shows the glassy view of individual tilting provided for each propulsion system in accordance with the embodiment.
DETAILED DESCRIPTION OF THE DRAWING:
The Figure discloses the detailed configuration of the Unmanned Aerial Vehicle (UA V) which is a Fusion of fixed wing and Multi rotor. Two motors with tilting mechanism are assigned between the nose and leading edge of the wing. This Aerial Vehicle is designed to maneuver at Variable Payloads. For lower payloads it runs with two pairs of single motor propulsion system and for higher payloads it runs on co-axial motor propulsion system pairs between the Wing and Empennage groups. The aerial vehicle may position the rotors perpendicular to a launching surface/Ground and take off vertically like a rotary wing aircraft.
The aerial vehicle may further transform into a full forward flight through fixed wing mode by orienting the rotors into a fixed horizontal position. In another aerial setting, the aerial vehicle may tilt the rotor in dynamic increments when the aerial vehicle receives the input from the operator to move either forward or backward. To Maintain the stability of the aerial vehicle while transforming from hover mode to flightmode , the rear pair of single motor propulsion unit or co-axial motor propulsion unit propels until the minimum stall speed is attained. The propulsion units at the rear cuts-off as soon as the minimum stall speed is attained to maintain the efficiency of the aerial vehicle. During horizontal movements, both fixed and hovering modes are alternatively used for maneuvering. To increase the speed, the rotors are tilted at an angle between 60°to 90°. For lesser payloads the lower rotors of the rear coaxial motors aren't required to function. Whereas, for higher payloads all the rotors are operated. While moving in the Y-axis direction, the speed of rotors are varied to maintain a stable position.The same tilt rotor locomotion techniques may be applied to the X-axis for efficient lateral motion.

The aerial vehicle may hover by tilting the rotors into a vertical position. The Unmanned aerial vehicle navigates the airspace through control surfaces (Aileron, Elevator, Elevon, Rudder) while operating on fixed wing mode.
Fie-OJ & Fis-02 Indicates the top view of the primary VTOL configurations proposed according to the implementation. As illustrated, the UAV includes the perimeter frame / fuselage (001) which can be designed as per user convenience. The wing set up (Port and Starboard) (003) which is applicable for the entire wing Positions & wing Geometry (Elliptical wing, Delta wing, Trapezoidal wing etc.). (005) represent the aileron; it is a control surface which helps in Rolling. Tail Boom (002) is a part of fuselage which connects the main body to stabilizers. Horizontal Stabilizer (004(a)) helps in maintaining longitudinal stability which is positioned at the rear end. Pitching movement of the plane is controlled by the elevator (006).
Fis-03 & Fig-04 Describes an isometric view of the two proposed configuration of aerial vehicle one for minimum payload and another for maximum pay loads, which gives a detailed view of the vehicle. Deflecting the rudder (007) leads to yawing, (007) is a part of vertical stabilizer (004 (b))5 positioned perpendicular to horizontal stabilizer (004 (a)). The brushless motor (017) in the rear is mounted as single rotor configuration using a mount (008 (a)) for lower payloads & the brushless motors 017 are mounted in co-axial configuration using a mount (008 (b)) in the rear for higher payloads as described in Fig-03 & Fig-04 respectively. The single or co-axial brushless motor mount (008 (a) & 008 (b)) has been attached to the fuselage (001) with the help of an Arm (009) extruded form the fuselage (001) as shown in Fig-03. The VTOL aerial vehicle makes the propellers 010 to Operate at a higher rpm to produce the required thrust. Each brushless motor (017) used in this configuration are provided with individual propellers (010), which should either be fixed pitch propellers or variable pitch propellers. A tilting mechanism is provided on both sides of the fuselage (001) in between the nose and the leading edge of the wing (003) which comprises of a brushless motor (017) and Propeller (010) on both sides. These tilting mechanisms are attached to both sides of the fuselage (001) with the extruded Arm (011). These arms can be of different geometry (cylindrical-tube, rectangular tube or an arm having a aerofoil shape in its cross section).

Fis-05 gives a closer view of tilting Mechanism with a motor and propeller which Proposed in this VTOL aerial vehicle is subjected to positioned between Nose and the Leading Edge of the Wing.
Fis-06 & Fig-07 shows a detailed view of the single rotor configuration & co-axial configuration that is embedded on the rear of the VTOL aircrafts for variable loads. The single motor propeller configuration comprising of motor (017) mounted on motor mount (008(a)) is preferred for lower payloads and the co-axial configuration comprising of a motor mount (008(b)) and a brushless motor (017) on the top and bottom of the motor mount (008(b)) are preferred for larger payloads. All the motors (017) are provided with an individual propeller (010) which should either be a fixed pitch propeller or a variable pitch propeller. The rotation of these propellers will be either clockwise or counter clockwise direction.
In co-axial configuration, the space between the two propellers will not exceed the half the diameter of the upper propeller for effective use of the energy. The arrangement of co-axial configuration is like both the upper and lower propeller has same diameter with same pitch or same diameter with different pitch or same pitch with different diameter or different diameter with different pitch propellers. The entire setup is attached to an arm (009) which connects the motor mount and the body.
Fie-08 gives the view of tilting mechanism assigned between the nose and the leading edge of the wing (003) for tilting the brushless motors (017) and propeller pair (010).
Fig-09 illustrates an exploded view of one of the tilting mechanism provided, which comprises of servo motor (013) for tilting. The tilting mechanism has blocks (012) and (014) for holding the servo (013) and both are fused together. Further it has been linked with a slider (015) for providing an angular motion to the motor and propeller pair in the front portion of the aerial vehicle. The block (012) is provided with a holder (016) to attach the tilting mechanism to the fuselage (001) through the arm (011). The block (012) is provided with an extra compartment (018) to hold the electronic speed controller.

Fie-10 & fis-11 Shows a detailed picture of conversion into a multirotor by detaching the wings and empennage from the body and make it as portable multirotor. The UAV is also provided with a landing gear (019) which can either be fixed or foldable using a servo motor while flying.
Fifi-12 illustrates the isotropic view of the secondary VTOL configuration which can be used for a standard payload (camera, thermal imaging, etc.). This configuration is similar to primary VTOL, except that the co-axial arrangement of motors (017) at the rear has been replaced by motors (017) with individual tilting mechanism. Thus, it allows us to control the VTOL aerial vehicle more effectively in hover mode.
In hover mode multi rotors change its movement by varying the thrust produced by the motors, to move forward it drops an amount of thrust at the front and increase the same amount at the rear, thus allows the multi rotor to bank forward at a certain degree.
in secondary VTOL arrangement, no need of varying the thrust for different motors instead the thrust angle produced by the motors (017) can be varied for forward movement, this can be achieved by the tilting mechanism for all the individual motors. To move the Secondary VTOL forward, the front motor pairs with tilting mechanism should maintain certain angle between 45 to 90 degree of thrust direction and the rear motors (017) must maintain an angle greater than that of front for achieving high speed. The side movements can also be achieved by implementing a tilting mechanism perpendicular to the plane axis. Fig-12 is provided for the better understanding of the concept.

CLAIMS:
What claimed is,
1. The present embodiment comprises of
a. A Vertical take-off and landing unmanned aerial vehicle holding a fuselage (001)
designed with high strength to weight ratio material which is attached with left and
right wings (003) to generate a lifting action and the direction of the vehicle is
controlled by aileron (005).
b. A fuselage (001) further coupled to an empennage comprising of horizontal (004a)
and vertical stabilizers (004b) through tail boom (002).
c. The unmanned aerial vehicle has a plurality of thrust motors arranged in such a way
that they produce variable vertical thrust depending upon the payload.
d. A single propulsion system along with tilting mechanism mounted on both sides of
the fuselage (001) between the nose of the aircraft and leading edge of the wing
using a mounting arm (011).
e. A single or co-axial propulsion system is provided on either side of the rear fuselage
(001) between trailing edge and empennage of the vehicle using a mounting arm
(009), which can either be operated as single propulsion system or co-axial
propulsion system depending on the payload applied to the vehicle.
f. A fuselage (001) provided with a landing gear (019) operated by a servo motor
which is fixed during take-off and landing operations and foldable during the flying
mode.
2. As claimed in claim], a servo mechanism provided for tilting the single propulsion
system is attached with a fuselage (001) through an arm (011) using a holder (016)
provided with necessary servo motor (013), bottom (012) and a top cover (014). A slider
(015) is used for providing an angular motion to the single propulsion unit in the front
portion of the aerial vehicle.

3. As claimed in claim 2, A separate casing (018) is provided in the tilting mechanism to accommodate the electronic speed controller which prevents the global positioning sensor from the magnetic fluxes.
4. As claimed in claim 1, The position of the single motor propulsion unit along with tilting mechanism provided at the front and single or co-axial motor propulsion unit provided at the rear can also be interchanged based on the convenience.
a. The co-axial or single propulsion systems at the rear portion of body can be replaced
by single propulsion system along with tilting mechanism according to our
convenience.
b. The set of propellers provided in both single propulsion and co-axial system is either
operated in clockwise or anti-clockwise direction to balance the gyroscopic effect.
5. As claimed in claim 1, A fuselage (001) provided with proper payload engaging and disengaging mechanisms for adopting into various applications such as packages, camera, thermal imaging equipment, medicines and mapping instruments.
6. As claimed in claim 1, the proposed unmanned aerial vehicle further comprises of electronic controlling devices such as flight controller, global positioning sensor, video transmitter and receiver, data transmitter and receiver, air speed sensor, obstacle avoidance sensors and one or more antenna.
7. As claimed in claim 1, The removable empennage is mounted in either one of the following configurations (Cruciform tail, T-tail, Fuselage mounted, V-tail, Inverted V-tail or X-tail). Further, the control surfaces are chosen from the following group (rudders, elevators & elevons) based on the empennage configuration.
8. As claimed in claim 1, the wings 003, empennage assembly (004a,004b) and its tail boom (006) can be easily attached and detached from body to use it as a conventional multi rotor aircraft.