Aerial vehicle having incline-controllable wings

1. An aerial vehicle comprising:

a body;

one or more thrust portions connected to the body, wherein each thrust portion comprises a propeller and a rotary shaft;

a first wing disposed on a first side of the body, wherein the first wing is spaced apart from the one or more thrust portions;

a second wing disposed on a second side of the body, wherein the second wing is also spaced apart from the one or more thrust portions; and

a connection assembly comprising:

a first connecting member that is coupled to a servomotor, wherein the servomotor is coupled to the body,

a second connecting member that is coupled to the first and second wings, and

a third connecting member that connects the first connecting member and the second connecting member,

wherein the servomotor is configured to provide a power for changing the first and second wings such that the angle between the rotary shaft and each of the wings is changed,

wherein the first and second wings are pitch-rotated with respect to a horizontal axis of the body such that angles of attack of the first and second wings are adjusted, and

wherein an angle between the rotary shaft of the one or more thrust portions and each of the wings varies based on a pitch rotation of the wings.

2. The aerial vehicle of claim 1 , wherein the one or more thrust portions are fixedly attached to the body such that the rotary shaft of each thrust portion is perpendicular to the body, and

the first and second wings have angles variable within vertical and horizontal ranges with respect to the body.

3. The aerial vehicle of claim 1 , wherein the aerial vehicle is changed to be in a take-off and landing mode, a cruise mode, a high-speed flight mode, and a stationary flight mode,

in the take-off and landing mode, the first and second wings are changed to be parallel to the rotary shaft of the thrust axis so as to be perpendicular to each thrust portion,

in the cruise mode, the first and second wings are changed to be at an inclined angle with respect to the rotary shaft such that an acute angle is formed between each thrust portion and each of the wings,

in the high-speed flight mode, the rotary shaft of each thrust portion is changed to be parallel to the first and second wings such that each thrust portion is perpendicular to the first and second wings, and

in the stationary flight mode, when wind is absent the first and second wings are changed to be perpendicular to the body and when wind is present the first and second wings are changed to be angled in a direction of the wind.

4. The aerial vehicle of claim 3 , wherein a rotation speed of each thrust portion decreases when the angle between the respective thrust portion and the first and second wings is the acute angle, and the rotation speed of each thrust portion increases when the angle between the respective thrust portion and the first and second wings is a right angle.

5. The aerial vehicle of claim 1 , wherein each thrust portion comprises:

at least one first thrust portion having a rotary shaft and disposed away from one side of each of the wings; and

at least one second thrust portion having a rotary shaft and disposed away from a side facing the one side of each of the wings, and

the rotary shaft of the first thrust portion and the rotary shaft of the second thrust portion are perpendicular to the body.

6. The aerial vehicle of claim 1 , wherein

rotation angles of the first wing and the second wing are individually controlled such that a pose and a direction of the aerial vehicle are adjusted.

7. The aerial vehicle of claim 1 , comprising:

a sensor configured to measure information applied to the aerial vehicle; and

a controller configured to control an angle between the rotary shaft and the first and second wings by pitch-rotating the first and second wings based on the information measured by the sensor,

wherein the servomotor is controlled by the controller.

8. The aerial vehicle of claim 7 , wherein the sensor comprises at least one of:

a measurement sensor configured to measure an altitude, a speed, and a flow angle of an air generated in response to the aerial vehicle travelling;

differential pressure sensors disposed on an upper side and a lower side of each of the wings to measure a flow angle using a pressure difference between the upper side and the lower side; and

a flow sensor configured to measure an air flow around the aerial vehicle such that the controller controls the wings to be changed based on the air flow around the aerial vehicle.