Tilting rotor aircraft

Abstract

The invention provides an inclined rotor aircraft which comprises an aircraft body and a rotor assembly, the rotor assembly comprises blades, a rotating shaft and a motor, aircraft arms are symmetrically arranged on the two sides of the aircraft body, mounting frames are arranged on the aircraft arms, the rotor assembly is arranged on the mounting frames, and the rotor assembly is arranged on the mounting frames. A rotating shaft of the rotor wing assembly is obliquely arranged relative to the aircraft body, and the inclined rotor wing aircraft is an unmanned aircraft.

Description

Technical Field

[0001] The present application relates to an aircraft, in particular to a rotary-wing aircraft. Background Art

[0002] The background description provided here is used to generally introduce the background of this application. The work of the presently named inventors described in this background section to the extent that it does not constitute prior art at the time of filing is neither explicitly nor implicitly admitted to be prior art that conflicts with this application.

[0003] Rotorcraft are widely used due to their ability to take off and land vertically, their low landing and takeoff area requirements, their excellent maneuverability, and their high speed. With the development of unmanned aerial vehicle (UAV) technology, rotorcraft are playing an increasingly important role in transportation, disaster relief, monitoring, and military applications. However, existing rotorcraft suffer from short flight time and low efficiency due to factors such as high air resistance, low power, and heavy weight. Small UAVs, in particular, typically adopt a frame-shaped structure, which results in significant air resistance during flight. Existing approaches to address this issue typically involve increasing power and reducing weight, but these approaches fail to improve flight endurance by reducing air resistance, particularly the air vortices generated by the rotors. Furthermore, the rotor axis of existing rotorcraft is perpendicular to the fuselage, requiring the aircraft to tilt at a certain angle to the horizontal after takeoff to ensure the rotors provide forward propulsion. This not only increases the aircraft's projected area in the forward direction, thereby increasing air resistance, but also easily causes the passengers or cargo on board to sway or swing, creating a safety hazard.

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

[0005] This section introduces a selection of inventive concepts in a simplified form that are further described in the detailed description below. This section is not intended to identify 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 response to the problems existing in the prior art, the present application provides a tilt-rotor aircraft, comprising a fuselage and a rotor assembly, wherein the rotor assembly includes blades, a rotating shaft and a motor, and arms are symmetrically arranged on both sides of the fuselage, wherein a mounting frame is provided on the arm, and the rotor assembly is arranged on the mounting frame, and wherein the rotating shaft of the rotor assembly is tilted relative to the fuselage, and the tilt-rotor aircraft is an unmanned aerial vehicle.

[0007] Preferably, the mounting frame includes a first mounting portion close to the front portion of the fuselage and a second mounting portion close to the rear portion of the fuselage, and both the first mounting portion and the second mounting portion are provided with rotor assemblies.

[0008] Preferably, the first mounting portion extends along the first direction toward the lower side of the arm, and the second mounting portion extends along the second direction toward the upper side of the arm, or the first mounting portion extends along the second direction toward the upper side of the arm, and the second mounting portion extends along the first direction toward the lower side of the arm, wherein the first direction is opposite to the second direction.

[0009] Preferably, a fairing is provided on the motor, and the fairing has a streamlined shape.

[0010] Preferably, the lower side of the fuselage is provided with a first support frame and a second support frame extending rearwards at an angle to the axis of the fuselage.

[0011] Preferably, the first support frame and the second support frame are cylindrical, and the appearance of the first support frame and the second support frame is streamlined.

[0012] Preferably, the two sides of the tail portion of the fuselage approach each other and eventually intersect to form the tail.

[0013] Preferably, the end of the tail is straight.

[0014] Preferably, the ends of the first support frame and the second support frame are both provided with a support surface, and the support surface and the end of the tail are located in the same plane.

[0015] Preferably, the fairing includes a first part and a second part, wherein the first part is connected to the motor and extends along the direction of the rotation axis, and the second part is connected to the first part and is parallel to the fuselage.

[0016] Preferably, when the tilt-rotor aircraft is in a ready-to-fly state, the rotation axis is perpendicular to the horizontal plane.

[0017] Preferably, when the tilt-rotor aircraft is in a ready-to-fly state, the fairing provided on the second mounting portion can provide support for the fuselage.

[0018] Preferably, the lower surface of the arm is a plane, and the upper surface of the arm is a curved surface.

[0019] Preferably, at least two rotor assemblies are respectively provided on the first mounting portion and the second mounting portion.

[0020] Preferably, the fairing is a hollow structure.

[0021] Preferably, communication antennas are provided in the first supporting frame and the second supporting frame.

[0022] Preferably, the tilt-rotor aircraft is made of a material having a hollow array inside.

[0023] Preferably, the body and the arms are both streamlined in shape. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] 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:

[0025] Figure 1 A tilt-rotor aircraft according to the principles of the present application is shown;

[0026] Figure 2 shows a side view of a tilt-rotor aircraft according to the principles of the present application;

[0027] Figure 3 shows a front view of a tilt-rotor aircraft according to the principles of the present application;

[0028] Figure 4 shows a top view of a tilt-rotor aircraft according to the principles of the present application; and

[0029] Figure 5 FIG2 shows a view of a tilt-rotor aircraft according to the principles of the present application in a ready-to-fly state. DETAILED DESCRIPTION

[0030] The following description is merely exemplary in nature and is not intended to limit the present application, applications, or uses. Furthermore, no intention is to be bound by any expressed or implied theory presented in the preceding technical field, background, and summary or the following detailed description. It should be understood that throughout the drawings, corresponding reference numerals identify similar or corresponding parts or features.

[0031] The present application will now be further elaborated. In the following paragraphs, different aspects of the present application are defined in more detail. Unless clearly indicated to the contrary, each aspect so defined may be combined with any other (multiple) aspects. In particular, any feature indicated as preferred or advantageous may be combined with any other (multiple) features indicated as preferred or advantageous.

[0032] Refer to the attached Figure 1 and attached Figure 2, shows a tilt-rotor aircraft 100 according to the principles of the present application. Tilt-rotor aircraft 100 includes a fuselage 110 and a rotor assembly 120. Rotor assembly 120 provides power for tilt-rotor aircraft 100 and includes blades 121, a rotating shaft 122, and a motor (not shown). Arms 130 are symmetrically disposed on either side of fuselage 110, with mounting brackets 140 disposed on each arm 130. Rotor assembly 120 is mounted on mounting brackets 140, and rotating shaft 122 is tilted relative to fuselage 110. That is, rotating shaft 122 is angled relative to the axis of fuselage 110, rather than perpendicular or parallel. This allows tilt-rotor aircraft 100 to be driven forward by the horizontal thrust provided by rotor assembly 120 without tilting fuselage 110 during flight. Advantageously, both fuselage 110 and arms 130 are streamlined, effectively reducing air resistance. Advantageously, lower surface 131 of arm 130 is flat, while upper surface 132 of arm 130 is curved. This allows tilt-rotor aircraft 100 to generate airflows of different velocities on the upper and lower surfaces of arm 130 during flight, thereby generating a pressure differential and providing lift for tilt-rotor aircraft 100. Advantageously, a cockpit (not shown) is provided at nose portion 111 of the fuselage. The cockpit houses a control system and a navigation system for controlling and navigating tilt-rotor aircraft 100.

[0033] Refer to the attached Figure 2 Mounting bracket 140 includes a first mounting portion 141 near the nose 111 of the fuselage and a second mounting portion 142 near the tail 112 of the fuselage. Both first and second mounting portions 141, 142 are equipped with rotor assemblies 120. Placing rotor assemblies 120 on different mounting portions helps reduce airflow interference between rotor assemblies 120 during operation. Advantageously, first mounting portion 141 extends in a first direction toward the underside of arm 130, while second mounting portion 142 extends in a second direction toward the upper side of arm 130. The first and second directions are opposite. This allows rotor assemblies 120 mounted on first and second mounting portions 141, 142 to be spaced apart from each other, further reducing airflow interference between rotor assemblies 120 during operation. Alternatively, first mounting portion 141 can extend in the second direction toward the upper side of arm 130, while second mounting portion 142 can extend in a first direction, opposite to the second direction, toward the underside of arm 130. Other technical effects brought about by the first mounting portion 141 and the second mounting portion 141 extending in opposite directions will be described in detail later. Advantageously, there is no limit to the number of rotor assemblies 120 that can be mounted on the first mounting portion 141 and the second mounting portion 142. For example, at least two rotor assemblies 120 can be mounted on each of the first mounting portion 141 and the second mounting portion 142, thereby providing greater power to the tilt-rotor aircraft 100.

[0034] Refer to the attached Figure 1 and attached Figure 2 The rotor assembly 120 is provided with a fairing 123, so that the fairing 123 is located behind the blades 121, wherein the fairing 123 is mounted on the motor of the rotor assembly (not shown), and the shape of the fairing 123 is streamlined, for example, it can be drop-shaped or roughly conical. As a result, the fairing 123 can convert the vortex generated by the rotation of the blades 121 into laminar flow, thereby reducing the resistance of the vortex to the tilt-rotor aircraft 100. In addition, the fairing 123 is mounted on the motor to protect the motor. Preferably, the fairing 123 includes a first part 124 and a second part 125, wherein the first part 124 is connected to the motor and extends in the direction of the rotation axis 122, and the second part 125 is connected to the first part 124, and the second part 125 and the first part 124 form a certain angle so that the second part 125 is parallel to the fuselage 110. Second portion 125 is parallel to the fuselage, which can reduce the horizontal projection of tilt-rotor aircraft 100, thereby reducing the area affected by wind force and reducing flight resistance. Advantageously, fairing 123 is a hollow structure, which can reduce the weight of tilt-rotor aircraft 100 and extend flight time.

[0035] Refer to the attached Figure 2-3 and attached Figure 5 The lower side of the fuselage 110 is provided with a first support frame 151 and a second support frame 152. The first support frame 151 and the second support frame 152 extend rearward at an angle to the axis of the fuselage, that is, extend toward the tail portion 112 of the fuselage. This can reduce the horizontal projection of the first support frame 151 and the second support frame 152, thereby reducing flight resistance. Advantageously, the first support frame 151 and the second support frame 152 also form an angle (e.g. Figure 3 , thereby providing more stable support for the tilt-rotor aircraft 100. Advantageously, the appearance of the first support frame 151 and the second support frame 152 is streamlined, so that their respective cross-sections are elliptical, which can further reduce flight resistance. Advantageously, the ends of the first support frame 151 and the second support frame 152 are provided with support surfaces 153 so as to contact the ground or the parking plane, thereby providing supporting force. Advantageously, the support surface 153 is set at an angle to the length direction of the support frame. Advantageously, communication antennas are provided in the first support frame 151 and the second support frame 152, thereby providing protection for the communication antennas to prevent the communication antennas from shaking or deforming during flight, and making the appearance of the tilt-rotor aircraft 100 simpler, further reducing flight resistance.

[0036] Refer to the attached Figure 2 and attached Figure 4The two sides of the tail section 112 approach each other and eventually intersect to form tail 113. The end of tail 113 is straight and advantageously angled with the upper and lower edges of the tail. This simple and retractable design of tail 113 further reduces the area affected by wind force and reduces flight resistance.

[0037] Refer to the attached Figure 5 Support surface 153 and the end of tail 113 are coplanar. This allows both support surface 153 and the end of tail 113 to contact the ground or a parking surface when tilt-rotor aircraft 100 is parked, i.e., in a ready-to-fly state, thereby providing stable support for fuselage 110. Advantageously, fairing 123 disposed on second mounting portion 142 also supports fuselage 110 when tilt-rotor aircraft 100 is parked, thereby ensuring more stable parking of tilt-rotor aircraft 100. Furthermore, because first mounting portion 141 and second mounting portion 142 are located on opposite sides of the arm and extend in opposite directions, tilt-rotor aircraft 100 is more evenly balanced, preventing it from tipping over due to a shift in its center of gravity when parked. Advantageously, when tilt-rotor aircraft 100 is in a ready-to-fly state, rotation axis 122 is perpendicular to the horizontal plane. This allows rotor assembly 120 to provide maximum upward lift during takeoff, allowing tilt-rotor aircraft 100 to quickly ascend. Advantageously, tilt-rotor aircraft 100 is made of lightweight materials, such as foam or materials with hollowed-out interiors. This reduces the weight of the aircraft while maintaining its strength, thereby increasing its flight time.

[0038] It is easy for those skilled in the art to understand that the tilt-rotor aircraft 100 according to the principles of the present application can be either a human-piloted aircraft or an unmanned aircraft.

[0039] The tilt-rotor aircraft based on the principles of the present application effectively reduces flight resistance and the impact of vortices generated by the rotor on flight through its streamlined appearance and the provision of a fairing; at the same time, its rotor is at an angle to the fuselage relative to its rotation axis, so that the aircraft can generate forward thrust during flight without tilting the fuselage; in addition, the support frame, tail end and fairing also provide multi-point support for the fuselage, so that the tilt-rotor aircraft can be stably parked when in a ready-to-fly state to prevent tipping over.

[0040] 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 the exemplary embodiment or embodiments described herein are merely examples and are not intended to limit the scope, applicability, or configuration of the present application in any way. On the contrary, the foregoing detailed description will provide a convenient guide for those skilled in the art to implement an exemplary embodiment or embodiments. It should be understood that various changes, modifications, or alterations may be made to the functions and arrangements of the elements without departing from the scope of the present application as set forth in the appended claims and their equivalents.

Claims

1. A tilt-rotor aircraft comprising a fuselage and a rotor assembly, wherein the rotor assembly comprises blades, a rotating shaft, and a motor, wherein: The arms are symmetrically arranged on both sides of the fuselage, wherein a mounting frame is provided on the arms, the rotor assembly is provided on the mounting frame, and wherein the rotation axis of the rotor assembly is tilted relative to the fuselage, and the tilt-rotor aircraft is an unmanned aerial vehicle.

2. The tilt-rotor aircraft according to claim 1, wherein: The mounting frame includes a first mounting portion close to the front portion of the fuselage and a second mounting portion close to the rear portion of the fuselage, and both the first mounting portion and the second mounting portion are provided with the rotor assembly.

3. The tilt-rotor aircraft according to claim 2, wherein: The first mounting portion extends along a first direction toward the lower side of the arm, and the second mounting portion extends along a second direction toward the upper side of the arm, or the first mounting portion extends along the second direction toward the upper side of the arm, and the second mounting portion extends along the first direction toward the lower side of the arm, wherein the first direction is opposite to the second direction.

4. The tilt-rotor aircraft according to claim 3, wherein: The motor is sleeved with a fairing with a streamlined shape.

5. The tilt-rotor aircraft according to any one of claims 1 to 4, characterized in that: A first support frame and a second support frame are provided on the lower side of the fuselage and extend toward the tail of the fuselage in a manner of forming an angle with the axis of the fuselage.

6. The tilt-rotor aircraft according to claim 5, wherein: The first support frame and the second support frame are cylindrical, and the appearance of the first support frame and the second support frame is streamlined.

7. The tilt-rotor aircraft according to claim 6, wherein: The two sides of the tail portion of the fuselage approach each other and eventually intersect to form the tail.

8. The tilt-rotor aircraft according to claim 7, wherein: The end of the tail is straight.

9. The tilt-rotor aircraft according to claim 8, wherein: The ends of the first support frame and the second support frame are both provided with a support surface, and the support surface and the end of the tail are located in the same plane.

10. The tilt-rotor aircraft according to claim 9, wherein: The fairing includes a first portion and a second portion, wherein the first portion is connected to the motor and extends along the direction of the rotation axis, and the second portion is connected to the first portion and parallel to the fuselage.

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