Unmanned aerial vehicle with inclined rotor wings

Abstract

The invention provides an unmanned aerial vehicle which comprises a fuselage and rotors, and the rotors are obliquely arranged relative to the fuselage, so that the fuselage does not need to be rotated when the unmanned aerial vehicle advances, the projection area of the unmanned aerial vehicle in the horizontal direction is reduced, the flight resistance and energy consumption are reduced, and the cruise mileage is increased.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and particularly to an unmanned aircraft with tilt rotors. Background Art

[0002] The background art provided here is for generally introducing the background of the present application. The work of the currently named inventors to the extent described in this background art section, and aspects of this description that do not constitute prior art at the time of the application, are neither expressly nor impliedly admitted to be prior art conflicting with the present application.

[0003] Most existing rotorcraft adopt a vertical rotor arrangement, that is, the axis of rotation of the rotor is fixedly perpendicular to the aircraft body. When such an aircraft moves in space, it needs to generate a certain inclination relative to the horizontal direction to provide forward thrust to achieve the movement of the aircraft. However, when the aircraft is inclined, it will cause the projected area of the fuselage in the forward direction to increase, which will increase the force-bearing area of the aircraft, increase the air resistance, and reduce the flight range of the aircraft. In the prior art, to solve this problem, it is usually to increase the number of batteries or the amount of fuel of the aircraft to increase the flight range, but this method increases the weight and volume of the aircraft, further increasing the resistance and weight, resulting in a further increase in the energy consumption of the aircraft and limited efficiency improvement.

[0004] Therefore, a new type of rotorcraft is needed to solve the above problems. Summary of the Invention

[0005] This section introduces the selected inventive concepts in a simplified form, which will be further embodied in the following detailed description. This section is not intended to identify the key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.

[0006] In view of the problems existing in the prior art, the present application provides an unmanned aircraft, including a fuselage and a rotor, and the rotor is inclined relative to the fuselage.

[0007] Preferably, the unmanned aircraft further includes a base, wherein the base is mounted to the fuselage, and the rotor is mounted to the base through a mounting surface provided on the base.

[0008] Preferably, the angle between the axis of rotation of the rotor and the fuselage is between 5° and 89°.

[0009] Preferably, the angle between the axis of rotation of the rotor and the fuselage is between 40° and 50°.

[0010] Preferably, the base is vertically mounted to the fuselage, and the mounting surface is an inclined mounting surface.

[0011] Preferably, the base is mounted to the fuselage at an angle.

[0012] Preferably, the fuselage comprises a fuselage body and a mounting arm extending outwardly from the fuselage body, and the base is mounted at one end of the mounting arm extending outwardly.

[0013] Preferably, the number of the mounting arms is four, wherein two mounting arms extend outwardly from the front end of the fuselage body, and the other two mounting arms extend outwardly from the rear end of the fuselage body.

[0014] Preferably, the height of the base at the rear end of the fuselage body is greater than the height of the base installed at the front end of the fuselage body.

[0015] Preferably, the base is a hollow columnar structure or is provided with hollowing.

[0016] The unmanned aerial vehicle based on the principle of the present application does not need to tilt the fuselage when moving forward, thereby reducing the force area of ​​the aircraft in the horizontal direction and reducing flight resistance. The structure is simple and there is no additional load on the unmanned aerial vehicle, thereby reducing energy consumption and increasing cruising range. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Other or additional features, advantages and details are presented by way of example only in the following detailed description of the embodiments. In the drawings:

[0018] Figure 1 The figure schematically shows the posture of an aircraft when hovering in the prior art;

[0019] Figure 2 The figure schematically shows the posture of an aircraft when it is moving forward in the prior art;

[0020] Figure 3 The structure of an aircraft according to the principles of the present application is schematically shown;

[0021] Figure 4 Schematically shows the structure of an aircraft according to the principles of the present application from another perspective;

[0022] Figure 5 The projected areas in the horizontal direction of an aircraft in the prior art and an aircraft according to the principles of the present application when flying are shown. DETAILED DESCRIPTION

[0023] The following description is merely exemplary in nature and is not intended to limit the present application, application, or uses. Furthermore, there is no intention to be limited by any express or implied theory presented in the preceding technical field, background technology and invention content or the following detailed description. It should be understood that throughout the drawings, corresponding reference numerals identify similar or corresponding parts or features.

[0024] The present application will now be further elaborated. In the following paragraphs, different aspects of the present application are defined in more detail. Unless explicitly indicated to the contrary, each aspect so defined can be combined with any other aspect(s). In particular, any feature indicated as being preferred or advantageous can be combined with any other feature(s) indicated as being preferred or advantageous.

[0025] Referring to the attached Figure 1 and Figure 2 , the attitudes of the rotary-wing aircraft 10 in the prior art during hovering and forward flight are respectively shown, in which the rotation axis 12 of the rotor 11 is vertically arranged with respect to the aircraft fuselage 13. When the aircraft is in the hovering state, the vertically upward thrust generated by the rotation of the rotor 11 balances the gravity acting on the aircraft 10 itself, so that the aircraft 10 can be in the hovering state. When the aircraft 10 moves forward, the aircraft fuselage 13 will tilt at a certain angle. At this time, the rotor can provide a horizontal component force for the aircraft, thereby propelling the aircraft 10 forward. However, since the tilt of the aircraft 10 will increase its projected area in the horizontal direction, thus increasing the force-bearing area in the horizontal direction, and further increasing the forward resistance, which affects the flight range of the aircraft.

[0026] In view of the problems existing in the rotary-wing aircraft in the prior art, the present application provides a Figure 3The novel rotorcraft 100 shown includes a fuselage 110 and a rotor 120. Among them, the rotor 120 is arranged to be inclined relative to the fuselage 110. In other words, the rotation axis 121 of the rotor 120 is arranged to be inclined relative to the fuselage 110. In one embodiment, the rotorcraft 100 has a base 130. Among them, the base 130 is mounted on the fuselage 110, and the rotor 120 is mounted on the base 130 through a mounting surface 131 provided on the base 130, so that the rotor 120 is inclined relative to the fuselage 110, that is, the rotation axis 121 of the rotor 120 is inclined relative to the fuselage 110. This way of arranging the rotor inclined relative to the fuselage enables the following: when the aircraft moves forward, there is no need to tilt the fuselage, thereby reducing the projected area of the aircraft in the horizontal direction, further reducing the resistance, and improving the range. When hovering, only need to tilt the fuselage so that the rotation axis 121 of the rotor 120 is in a vertical state. Preferably, the base 130 is a cylindrical structure, so that the rotor 120 mounted on it can maintain a certain distance from the fuselage 110, avoiding the rotor 120 colliding with the fuselage 110 during the rotation process due to the inclined setting of the rotor 120, and further causing damage to the aircraft. Those skilled in the art can easily understand that the rotorcraft 100 may not be provided with a base 130. At this time, as long as it can be ensured that the rotor 120 is inclined relative to the fuselage 110 and does not collide with the fuselage 110. For example, grooves or hollow-outs can be provided at the intersection of the movement trajectories of the fuselage 110 and the rotor blades of the rotor 120 to avoid the inclined rotor 120 colliding with or contacting the fuselage 110.

[0027] The included angle a between the rotation axis 121 of the rotor 120 and the fuselage 110 can be between 5° and 89°. In actual use, a suitable included angle can be selected according to the use of the aircraft and the requirements for speed, etc. Preferably, the included angle between the rotation axis 121 of the rotor 120 and the fuselage 110 is between 40° and 50°, such as 45°. Thus, it can ensure that the hovering performance and the forward performance are in a better balanced state, meeting the requirements of most application scenarios.

[0028] Advantageously, the base 130 is vertically mounted on the fuselage 110, and the mounting surface 131 is an inclined mounting surface. That is, the mounting surface 131 is inclined relative to the axis of the base 130 and the fuselage 110, so that the rotor mounted on the mounting surface 131 is inclined relative to the fuselage 110. In an alternative embodiment, the base 130 can also be inclinedly mounted on the fuselage 110. At this time, the mounting surface 131 does not need to be an inclined mounting surface, and it can also ensure that the rotor 120 is inclined relative to the fuselage 110. Advantageously, the base 130 can be a hollow cylindrical structure or provided with hollow-outs to reduce the load of the aircraft and further improve the range.

[0029] Refer to the appendix Figure 4, Advantageously, the fuselage 110 includes a fuselage body 111 and mounting arms 112 extending outward from the fuselage body 111. The base 130 is mounted at an end of the mounting arm 112 extending outward. Thereby, not only can a sufficient safety distance be maintained between the rotors 120 mounted on the base 130, but also the weight of the fuselage 110 can be minimized. Advantageously, the number of mounting arms 112 is four, two of which extend outward from the front end of the fuselage body 111, and the other two extend outward from the rear end of the fuselage body 111, which is conducive to maintaining the overall balance of the fuselage 110. Return to reference attachment Figure 3 , Advantageously, the height of the base 130b mounted at the rear end of the fuselage body is greater than the height of the base 130a mounted at the front end of the fuselage body. It is easy for those skilled in the art to understand that since the base 130a is mounted at the end of the mounting arm extending outward, the rotor 120a inclined at the front end will not collide with the fuselage during rotation. While the inclination direction of the rotor 120b on the base 130b at the rear end is the same as that of the rotor 120a, so it is easy to collide with the fuselage 110 during rotation. The height of the base 130b is set to be greater than that of 130a to avoid the rotor 120b colliding with the fuselage 110 during rotation. It is easy for those skilled in the art to understand that the number of mounting arms 112 can also be other numbers.

[0030] Advantageously, the aircraft according to the principle of the present application can be an unmanned aircraft.

[0031] Reference attachment Figure 5 , Respectively shown are the projections 200 and 300 in the horizontal direction during flight of an aircraft in the prior art with the same-sized fuselage and the aircraft 100 according to the principle of the present application. It can be seen that the projected area 300 in the horizontal direction during flight of the aircraft according to the principle of the present application is significantly smaller than the projection 200 in the horizontal direction during flight of the aircraft in the prior art. This indicates that the aircraft according to the principle of the present application can effectively reduce flight resistance and energy consumption and increase the cruising range.

[0032] Although at least one exemplary embodiment has been described in the foregoing detailed description, it should be understood that there are a large number of variations. It should also be understood that one exemplary embodiment or multiple exemplary embodiments described herein are merely examples and are not intended to limit the scope, applicability, or construction of the present application in any way. On the contrary, the foregoing detailed description will provide those skilled in the art with a convenient guide for implementing one exemplary embodiment or multiple exemplary embodiments. It should be understood that various changes, variations, or alterations can be made to the functions and arrangements of the elements without departing from the scope of the present application as set forth by the appended claims and their equivalents.

Claims

1. An unmanned aerial vehicle, comprising a fuselage and a rotor, characterized in that, The rotor is inclined relative to the fuselage.

2. The unmanned aerial vehicle according to claim 1, characterized in that, The aircraft further includes a base, wherein the base is mounted to the fuselage, and the rotor is mounted to the base through a mounting surface provided on the base.

3. The unmanned aerial vehicle according to claim 2, characterized in that, The included angle between the rotation axis of the rotor and the fuselage is between 5° and 89°.

4. The unmanned aerial vehicle according to claim 3, characterized in that, The included angle between the rotation axis of the rotor and the fuselage is between 40° and 50°.

5. The unmanned aerial vehicle according to claim 4, characterized in that, The base is vertically mounted to the fuselage, and the mounting surface is an inclined mounting surface.

6. The unmanned aerial vehicle according to claim 4, characterized in that, The base is inclinedly mounted to the fuselage.

7. The unmanned aerial vehicle according to claim 5, characterized in that, The fuselage includes a fuselage body and a mounting arm extending outward from the fuselage body, and the base is mounted at an end of the mounting arm extending outward.

8. The unmanned aerial vehicle according to claim 7, characterized in that, The number of the mounting arms is four, wherein two mounting arms extend outward from the front end of the fuselage body, and the other two mounting arms extend outward from the rear end of the fuselage body.

9. The unmanned aerial vehicle according to claim 8, characterized in that, The height of the base mounted at the rear end of the fuselage body is greater than the height of the base mounted at the front end of the fuselage body.

10. The unmanned aerial vehicle according to any one of claims 1-9, characterized in that, The base is a hollow columnar structure or provided with a hollow out.

Images