TECHNICAL FIELD

The present invention relates to an unmanned air vehicle which can be operated in different flying modes and which can generate electricity during flight.

PRIOR ART

Unmanned air vehicle (IHA) is a kind of airplane which has no pilot and passenger therein and which has ready-made equipment like camera, GNSS, laser scanning device, etc. and which is remotely controlled and/or which can fulfill its function automatically. The professional usage of IHAs with military, civil and scientific purposes increases rapidly in our country and in the whole world. Among the basic reasons of this dense usage which increases every passing day, the following can be mentioned: particularly the IHAs with civil purposes have a very wide usage area, and they have high accuracy in various vocational usages, and they provide time and cost saving.

In the present art, IHAs can be separated into three groups, namely fixed flap, rotary flap and hybrid. IHAs, which have motionless and fixed flaps which hold the vehicle in air, are essentially called fixed flap. Airplanes are in this group. The fixed flap IHAs stay in air thanks to the continuous movements of their bodies. The thrust force which provides movement is provided by means of propellers connected to electrical motor or by means of inner combustion engine with liquid fuel. The thrust force is exerted in an orthogonal manner to the gravity force direction. A big part of the design and production of fixed flaps is formed by mechanical works. Even though wide areas are needed for their flights and for take off- landing, their flying ranges are substantially high. IHAs, which have propeller flaps which keep the vehicle in air in the opposite direction to the gravity direction and which continuously rotate, are called rotary flap. These vehicles are named depending on number of propellers they have, these vehicles which have one, three, four, six and eight propellers are named as helicopter, tricopter, quadcopter (quadrotor), hexacopter and octocopter respectively as the Romance form. In rotary flaps, body is fixed, and propeller flaps rotate, and therefore, the body does not have to continuously move in order for the vehicle to stay in air in a different manner from the fixed flap. Thanks to this, the movement of rotary flaps in air is more controlled, and they can be suspended at a single point in air and they can realize take off- landing to very small areas. A big part of the design and production of rotary flaps is formed by electronic labor and planning and the works of weight-load-battery balance. The production costs are much higher depending on the number of rotating flaps since the number of expensive electronic materials like motor and driver increases very much. Their flying ranges are short.

In hybrid IHA design, the superior characteristic of having a long range in fixed flaps and having orthogonal take off-landing in rotary flaps are joined. In hybrid IHAs, there are rotary propeller flaps which provide orthogonal take off-landing of the vehicle and at the same time, there are fixed wigs connected to the body and which provide floating of the vehicle in air.

Both lightness and the flight stability are very important characteristics for unmanned air vehicles. The energy need can be met by means of batteries that are provided on IHAs. Batteries can be used only for a specific duration. This condition leads to usage of IHAs in limited areas and the battery must be continuously checked for forming a safe drive.

As a result, because of the abovementioned problems, an improvement is required in the related technical field.

BRIEF DESCRIPTION OF THE INVENTION

The present invention relates to an unmanned air vehicle, for eliminating the abovementioned disadvantages and for bringing new advantages to the related technical field.

An object of the present invention is to provide an unmanned air vehicle which can stay in air for long duration.

Another object of the present invention is to provide a hybrid unmanned air vehicle which can be operated in different flying modes.

In order to realize the abovementioned objects and the objects which are to be deducted from the detailed description below, the present invention is an unmanned air vehicle comprising a body; at least four propellers where at least two of said propellers are provided on a front edge of said body and where at least two of said propellers are provided on a rear edge of the body; a flying mode transition mechanism for providing movement of said propellers between a first flying position, where the body applies substantially parallel thrust to the ground for providing movement of the body in air in a parallel manner to the ground, and a second flying position, where the body applies substantially orthogonal thrust to the ground for providing suspension of the body in air, and a control unit for providing operation of said flying mode transition mechanism. Accordingly, at least one part of the body has flap cross-section for providing floating of the unmanned air vehicle in air when the unmanned air vehicle moves parallel to the ground; at least one body solar panel is provided on a lower surface of the body which faces the ground for providing taking light from a light source which exists on the ground. Thus, continuity of energy production can be provided in conditions where there is no sunlight.

In a possible embodiment of the present invention, the body comprises at least one body solar panel positioned on an upper surface provided against said lower surface.

In another possible embodiment of the present invention, the body comprises a first flap provided on a first side edge thereof and a second flap provided on a second side edge which exists opposite to said first side edge.

In another possible embodiment of the present invention, said first flap and said second flap are provided in a manner forming an angle at any value in the range of ±75 ^e with respect to the body if the orthogonal axis is accepted as 0 ^e .

In another possible embodiment of the present invention, in order to adjust the angle of the first flap and the second flap with respect to the body, a movement mechanism is provided which is associated with the first flap and the second flap.

In another possible embodiment of the present invention, at least one flap solar panel is provided on said first flap and on said second flap.

In another possible embodiment of the present invention, a tail is provided which is connected to the body.

In another possible embodiment of the present invention, at least one tail flap is provided on said tail.

In another possible embodiment of the present invention, a storage unit is provided for storing the energy collected from at least one of said body solar panel and said flap solar panel. In another possible embodiment of the present invention, said control unit is configured to provide:

- taking a movement signal comprising at least one of the first flying position or the second flying position,

- operating the flying mode transition mechanism for the flying position included by said movement signal,

- storing the energy, produced in the body solar panel, in the storage unit,

- operating the movement mechanism for providing positioning of the first flap and the second flap in a manner receiving the solar rays,

- storing the energy, produced in flap solar panels, in the storage unit,

- producing energy by means of an artificial light source by at least one of body solar panels and flap solar panels in cases where there is no sunlight,

- using the energy, stored in the storage unit, as needed.

BRIEF DESCRIPTION OF THE FIGURES

In Figure 1 , a representative view of the unmanned air vehicle while the propellers are at the first flying position is given.

In Figure 2, a representative view of the unmanned air vehicle while the propellers are at the second flying position is given.

In Figure 3, a bottom representative view of the unmanned air vehicle is given.

In Figure 4, a representative view of the operation scenario of the unmanned air vehicle is given.

DETAILED DESCRIPTION OF THE INVENTION

In this detailed description, the subject matter is explained with references to examples without forming any restrictive effect only in order to make the subject more understandable.

The present invention relates to an unmanned air vehicle (10). Said unmanned air vehicle (10) comprises a body (100), which has at least partially aerofoil shaped cross-section, embodied to float in air when said unmanned air vehicle (10) moves in a parallel manner to the ground. Said body (100) has a structure which provides formation of a pressure difference between an upper edge of the body (100) and a lower edge provided against said upper edge. Said structure is embodied in the form of a half water drop, etc. at the first height of the upper edge of the body (100) and in the form of a half water drop, etc. at the second height of the lower edge thereof. Said first height is selected to be greater than said second height. This condition provides movement of the air, which passes through the upper part of the airplane, in a faster manner than the air which passes through the lower part of the airplane. Thus, the pressure, which occurs due to speed difference, forms a lifting force for the unmanned air vehicle (10). By means of the occurring lifting force, the unmanned air vehicle (10) moves in air.

There are at least two propellers (101 ) provided on a front edge of the body (100) and there are at least two propellers (101) provided on a rear edge of the body (100). Said propellers (101 ) comprise rotary elements which provide air thrust and which are in blade/flap form, and a motor which provides movement of sad rotary elements. In a possible embodiment of the present invention, the number of propellers (101) can be increased in a compliant manner to the usage area. In another possible embodiment of the present invention, the number of propellers (101) can be decreased in a compliant manner to the usage area. The unmanned air vehicle (10) comprises a flying mode transition mechanism (103) for providing movement of said propellers (101 ) between a first flying position, where the body (100) applies substantially parallel thrust to the ground for providing movement of the body (100) in air in a parallel manner to the ground, and a second flying position, where the body (100) applies substantially orthogonal thrust to the ground for providing suspension of the body (100) in air. In Figure 1 , a representative view of the unmanned air vehicle (10) while the propellers (101) are at the first flying position is given. In Figure 2, a representative view of the unmanned air vehicle (10) while the propellers (101) are at the second flying position is given. There is a control unit (200) which provides operation of said flying mode transition mechanism (103). Said unmanned air vehicle (10) has been designed with an innovative architecture depending on the usage purpose such that it moves like an airplane, etc. by floating in air or such that it moves like a drone, etc. by staying suspended in air.

As shown in Figure 3, the unmanned air vehicle (10) comprises at least one body solar panel (104) provided in a manner receiving light from a light source, which exists on the ground, to the lower surface of the body (100) which faces the ground. At least one of said body solar panels (104) is provided to the upper surface of the body (100). There is a storage unit (109) for storing the energy produced in said body solar panels (104). There is a tail (102) connected to the body (100). Said tail (102) comprises at least one tail flap (1021). As shown in Figure 1 and 2, the unmanned air vehicle (10) comprises at least one first flap (105) provided at a first side edge of the body (100). At least one second flap (106) is provided at a second side edge provided against said first side edge. Said first flap (105) and said second flap (106) are placed in a manner forming an angle at any value in the range of ±75 ^e with respect to the body (100) if the orthogonal axis is accepted as 0 ^e . This condition provides reduction of the vortex effect. There is a movement mechanism (108) associated with the first flap (105) and the second flap (106) in order to adjust the angle made by the first flap (105) and the second flap (106) with respect to the body (100). In a possible embodiment of the present invention, said movement mechanism (108) can also be used as a landing set in order for the unmanned air vehicle (10) to be able to land to the ground in a comfortable manner. There is at least one flap solar panel (107) provided on the first flap (105) and on the second flap (106). The energy, produced in said flap solar panels (107), is stored in said storage unit (109).

With reference to Figure 4, said control unit (200) is moreover configured to provide storing of the energy produced in at least one of the flap solar panels (107) and the body solar panel (104). The control unit (200) provides usage of the stored energy in the unmanned air vehicle (10) as needed. The control unit (200) moreover provides operation of the movement mechanism (108) which provides changing of the inclination in order for the first flap (105) and the second flap (106) to utilize solar rays. Thus, the angle between the flaps and the body (100) is changed in accordance with solar rays, and thereby energy efficiency is increased. The control unit (200) moreover provides actuation of the propeller (101) flaps by providing operation of the motors provided to the propellers (101).

An exemplary operation scenario of the present invention is described below;

The motor, provided to the unmanned air vehicle (10), is operated for providing taking off of an unmanned air vehicle (10) at the first flying position. A first movement signal, which includes the information indicating that the unmanned air vehicle (10) shall be operated at the first flying position, is transferred to the control unit (200). Depending on said first movement signal, the control unit (200) provides operation of the flying mode transition mechanism (103) for operating the propellers (101) at the first flying position. As the flying mode transition mechanism (103) brings the propellers (101) to the suitable position for the first position, the unmanned air vehicle (10) takes off such that it applies thrust force which is orthogonal to the ground. The unmanned air vehicle (10) stays suspended in air like a drone. In order for the unmanned air vehicle (10) to be operated in the second flying position, the second movement signal, including the second flying position, is sent to the control unit (200). Depending on the second movement signal, the control unit (200) provides operation of the flying mode transition mechanism (103) for bringing the propellers (101), which are at the first flying position, to the second flying position. As the flying mode passage mechanism (103) is operated, by means of the movement of the propellers (101 ) which pass to the second position, the unmanned air vehicle (10) floats in air in a manner exerting thrust force which is parallel to the ground. The flying of the unmanned air vehicle (10) results from the fact that the body of the unmanned air vehicle (10) has aerodynamic flap structure and it has flaps. Since the body (10) has aerodynamic structure, pressure difference occurs between the upper structure and the lower structure of the body (100) when a force, which is parallel to the body (100), is exerted. Said pressure difference provides formation of the needed lifting effect in order for the unmanned air vehicle (10) to fly in air. This leads to reduction of energy consumption.

The energy need of the unmanned air vehicle (10) is met by means of solar panels provided to the surface of the flaps and the body (100). The solar panels, which are provided to the lower surface and to the upper surface of the body (100), provide production of energy all the day. The control unit (200) provides storage of the energy, produced by means of the body solar panels (104), in the storage unit (109). The energy stored in the storage unit (109) is used in the unmanned air vehicle (10) by means of the control unit (200). Since solar panel is provided to the lower surface of the body (100), energy can be produced by means of the energy taken from an artificial light source, even at times where there is no sunlight. Thus, the unmanned air vehicle (10) can produce energy continuously both during the day and during the night. This condition provides meeting the energy need of the unmanned air vehicle (10) in a continuous manner.

Energy is produced also by means of the flap solar panels (107) provided on the first flap (105) and on the second flap (106). The control unit (200) provides storage of the energy, produced in the flap solar panels (107), in the storage unit (109). The energy, stored in the storage unit (109), is used when needed. By means of the movement mechanism (108) provided to the first flap (105) and to the second flap (106), the angle of the flaps with respect to the body (100) is changed such that the solar rays are utilized at the maximum level. The control unit (200) provides operation of the movement mechanism (108). In a possible embodiment of the present invention, the inclination of the flaps can be changed so as to utilize an artificial light source. Thus, continuity of energy production can be provided by means of artificial light source provided at night. This condition provides meeting of the energy need of the unmanned air vehicle (10). Thus, the unmanned air vehicle (10) is used for long distances. In an exemplary embodiment of the present invention, an unmanned air vehicle (10) is primarily used for observation purpose. Said unmanned air vehicle (10) takes off in an orthogonal manner to the ground. During the duration which the unmanned air vehicle (10) takes off, energy is produced in sunlight by means of flap solar panels (107) and the body solar panels (104). The produced energy is utilized as needed during the duration where the unmanned air vehicle (10) stays in air. This condition provides meeting of the energy need. Thus, the unmanned air vehicle (10) can stay in air for long duration. As the sunlight finishes, light is reflected to the unmanned air vehicle (10), which stays suspended in air, by means of artificial light source. By means of the guidance of flaps and solar panels provided to the lower surface of the body (100), energy is produced from solar panels provided on the flaps. The produced energy provides the needed energy in order for the unmanned air vehicle (10) to stay in air. In order for the unmanned air vehicle (10), which stays suspended in air, to advance in air, the propellers (101) are passed from the first flying position to the second flying position. The unmanned air vehicle (10), which passes to the second flying position, is provided to move in air in a parallel manner to the ground. Thus, the unmanned air vehicle (10) can move to a far distance in a faster manner. While the unmanned air vehicle (10) is in the second flying position, sunlight is used during the day, and energy can be produced at night by means of the light reflected from an artificial light source.

The protection scope of the present invention is set forth in the annexed claims and cannot be restricted to the illustrative disclosures given above, under the detailed description. It is because a person skilled in the relevant art can obviously produce similar embodiments under the light of the foregoing disclosures, without departing from the main principles of the present invention.

REFERENCE NUMBERS

10 Unmanned air vehicle

100 Body 101 Propeller

102 Tail

1021 Tail flap

103 Flying mode transition mechanism

104 Body solar panel 105 First flap

106 Second flap

107 Flap solar panel

108 Movement mechanism

109 Storage unit 200 Control unit