A type of aircraft without exposed blades

Abstract

The present invention provides a bladeless aircraft, comprising a fuselage (4), two front wings (3), two rear wings (5), two front propellers (2) and two rear propellers (1), wherein the fuselage (4) is located in the middle of the entire aircraft, the two front wings (3) are arranged at the front end of the aircraft and rotate together through a transmission shaft, the two rear wings (5) are arranged at the end of the aircraft and rotate together through a transmission shaft, the two front propellers (2) and the two front wings (3) are integrated, the two rear propellers (1) and the two rear wings (5) are integrated, and both the front propellers (2) and the rear propellers (1) are designed without exposed blades. The aircraft of the present invention adopts a bladeless design, which can prevent foreign objects from being sucked in, enhances safety during flight, and improves flight efficiency by utilizing an airflow multiplication effect.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, in particular to an aircraft without exposed blades. Background Art

[0002] Low-altitude flight holds great commercial potential, attracting widespread market interest and strong government support. However, current aircraft typically feature exposed blades, resulting in high noise levels and poor structural stability. Foreign objects such as branches and debris can easily damage the blades during flight, significantly impacting flight safety and even rendering the aircraft useless. Therefore, it is crucial to design a bladeless aircraft that overcomes these shortcomings while maintaining high flight efficiency. Summary of the Invention

[0003] In order to overcome the above-mentioned problems existing in the prior art, the present invention provides an aircraft without exposed blades, which can ensure the safe and reliable flight of the aircraft while having high flight efficiency.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions:

[0005] A bladeless aircraft comprises a fuselage 4, two front wings 3, two rear wings 5, two front propellers 2 and two rear propellers 1, wherein the fuselage 4 is located in the middle of the entire aircraft, the two front wings 3 are arranged at the front end of the aircraft and rotate together through a transmission shaft, the two rear wings 5 ​​are arranged at the end of the aircraft and rotate together through a transmission shaft, the two front propellers 2 and the two front wings 3 are integrated into one design, the two rear propellers 1 and the two rear wings 5 ​​are integrated into one design, and both the front propellers 2 and the rear propellers 1 are designed without exposed blades.

[0006] Preferably, the two front wings 3 are distributed symmetrically on the left and right, and the two rear wings 5 ​​are distributed symmetrically on the left and right.

[0007] Preferably, a revolute pair is used between the front wing 3, the rear wing 5 and the fuselage 4, so that the front wing and the rear wing can rotate together with the connecting shaft.

[0008] Preferably, when the aircraft takes off vertically, the front wing 3 and the rear wing 5 are both perpendicular to the ground, thereby reducing air resistance during takeoff; when the aircraft flies level, the front wing 3 and the rear wing 5 are parallel to the ground, thereby reducing flight resistance; when the aircraft climbs, climbing at different angles can be achieved by adjusting the angles of the front wing 3 and the rear wing 5.

[0009] Preferably, the rotation and attitude control of the front wing 3 and the rear wing 5 are controlled by a flight control system to realize the flight operation of the aircraft; the two front propellers 2 and the rear propeller 1 are independently controlled and are controlled by the flight control system.

[0010] Preferably, the fuselage 4 adopts a low wind resistance appearance design, the fuselage material adopts lightweight and high-strength aviation material, the fuselage bottom adopts soft material, and the landing gear and taxiing wheels are installed inside.

[0011] Preferably, the motor air inlet 6 is located below the fuselage 4 , and a high-speed motor and blades 9 are installed in the internal air inlet channel 10 .

[0012] Preferably, the air flow enters from the motor air inlet 6, and the high-speed motor and blades 9 drive the air flow to flow in the internal air inlet channel 10 and reach the natural wind air inlet 7, and the air flow is multiplied through the Coanda effect, so that the air flow in the natural wind inlet 7 flows out from the air outlet 8 at a wind speed of more than 15 times.

[0013] Preferably, the high-speed motor and the blades 9 are configured to have 13 blades, and the high-speed motor is located inside the central hole of the blade.

[0014] Preferably, all blades are made of carbon fiber material.

[0015] Compared with the prior art, the advantages of the present invention are as follows:

[0016] 1) The propeller has no exposed blades, which can prevent foreign objects from being sucked in, thereby damaging the blades and affecting flight safety;

[0017] 2) The front wing and front propeller, as well as the rear wing and rear propeller, are integrated into one design, which greatly improves the structural strength and utilizes the airflow multiplication effect to generate lift, making the aircraft highly efficient.

[0018] 3) A revolute pair is used between the front wing, rear wing and fuselage, that is, the front wing and rear wing can rotate around the connecting axis, which can realize vertical take-off and landing, as well as taxiing take-off and landing, and can flexibly realize various aerial flight posture adjustments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the present invention, the following briefly introduces the drawings used in the invention.

[0020] Figure 1 This is a perspective structural diagram of a blade-less aircraft in level flight according to the present invention;

[0021] Figure 2 This is a left side view of a blade-less aircraft in level flight according to the present invention;

[0022] Figure 3This is a cross-sectional view of a bladeless aircraft propeller according to the present invention;

[0023] Figure 4 The present invention is a perspective structural diagram of an enlarged fuselage and propeller of a bladeless aircraft during level flight.

[0024] Among them, 1 is the rear propeller, 2 is the front propeller, 3 is the front wing, 4 is the fuselage, 5 is the rear wing, 6 is the motor air inlet, 7 is the natural wind air inlet, 8 is the air outlet, 9 is the high-speed motor and blades, and 10 is the internal air inlet channel. DETAILED DESCRIPTION

[0025] To better understand the technical solutions of the present invention, the present invention includes but is not limited to the specific embodiments described below. Similar technologies and methods should be considered within the scope of protection of the present invention. To further clarify the technical problems, technical solutions, and advantages to be solved by the present invention, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments.

[0026] like Figure 1 As stated,

[0027] The following is combined with Figure 1-4 An embodiment of the present invention is described.

[0028] A bladeless aircraft comprises a fuselage 4, two front wings 3, two rear wings 5, two front propellers 2, and two rear propellers 1. The fuselage 4 is located in the middle of the entire aircraft. The two front wings 3 are arranged at the front end of the aircraft and rotate together via a transmission shaft. The two rear wings 5 ​​are arranged at the end of the aircraft and rotate together via a transmission shaft. The rotation and attitude control of the front wings 3 and rear wings 5 ​​are controlled by a flight control system, helping the aircraft to flexibly climb and descend. The two front wings 3 are arranged symmetrically, and the two rear wings 5 ​​are arranged symmetrically. The two front propellers 2 are integrated with the two front wings 3, and the two rear propellers 1 are integrated with the two rear wings 5. Revolute pairs are used between the front wings 3, the rear wings 5, and the fuselage 4, allowing the front wings and rear wings to rotate together with the connecting shaft. The two front thrusters and the rear thruster are independently controlled and are controlled by the flight control system, so that the aircraft can flexibly perform flight operations including turning, acceleration, deceleration, climbing and descending.

[0029] The fuselage 4 features a low-drag exterior design and is constructed from lightweight, high-strength aviation-grade materials. The fuselage bottom is constructed from a soft material and houses the landing gear and runners. The system operates as follows: when the aircraft needs to land vertically, the landing gear and runners remain in place, achieving a soft landing thanks to the soft material on the fuselage bottom. When the aircraft needs to taxi on a runway for takeoff or landing, the landing gear and runners are lowered for a taxiing takeoff or landing.

[0030] The two front wings 3 are arranged symmetrically, and the two rear wings 5 ​​are also arranged symmetrically. The two front propellers 2 are integrated with the two front wings 3, and the two rear propellers 1 are integrated with the two rear wings 5. Revolute joints are used between the front wings 3, the rear wings 5, and the fuselage 4, allowing the front and rear wings to rotate along the connecting shaft. The two front and rear propellers are independently controlled and controlled by the flight control system, allowing the aircraft to flexibly perform flight operations including turning, acceleration, deceleration, climbing, and descending.

[0031] The specific operating process is as follows: During vertical takeoff, the front wing 3 and the rear wing 5 are perpendicular to the ground, thereby reducing air resistance during takeoff. During level flight, the front wing 3 and the rear wing 5 are parallel to the ground, thereby reducing flight resistance. During climb, the front wing 3 and the rear wing 5 can be adjusted to achieve different climb angles.

[0032] The front propeller 2 and the rear propeller 1 both adopt a non-exposed blade design, and their cross-sectional views are as follows: Figure 3 As shown, a high-speed motor and blades 9 are installed in the internal air inlet channel 10, and the motor air inlet 6 is located below the fuselage 4. Figure 2 and 3 As shown, air enters through the motor air inlet 6. The high-speed motor and blades 9 drive the airflow through the internal air inlet duct 10 in the direction of the arrow, reaching the natural wind inlet 7. The Coanda effect multiplies the airflow, causing the airflow in the natural wind inlet 7 to flow out of the air outlet 8 at a speed 15 times greater than the wind speed. The Coanda effect refers to the tendency of a fluid (water or airflow) to deviate from its original flow direction and instead follow the surface of a protruding object. When there is surface friction (also known as fluid viscosity) between the fluid and the surface of the object it flows over, the fluid will follow the surface as long as the curvature is not large. Utilizing this fluid's "viscosity," the high-speed motor and blades 9 drive the airflow through the motor air inlet 6. The high-speed airflow then flows through the internal air inlet duct 10 and is ejected through a narrow slit, driving the surrounding air along with it and forming a larger airflow ejection volume. This multiplication effect creates significant lift, meeting the aircraft's takeoff and landing requirements.

[0033] Specifically, the high-speed motor and the blades 9 are made of 13 pieces, the high-speed motor is inside the center hole of the blade, and all the blades are made of carbon fiber material. Figure 3 As shown, lift is generated by the airflow multiplication effect, the aircraft is highly efficient and can achieve low-noise flight.

[0034] The present invention adopts a propeller without exposed blades, which can prevent foreign objects from being sucked in, thereby damaging the blades and affecting the safety of flight; by utilizing the airflow multiplication effect, it can achieve both vertical take-off and landing, as well as gliding take-off and landing, and can flexibly realize various aerial flight posture adjustments.

[0035] Finally, it should be noted that the above embodiments are intended only to illustrate the technical solutions of the present invention and are not intended to limit the same. Persons skilled in the art may modify the technical solutions described herein or substitute equivalent features for some of the technical features, and such modifications or substitutions do not deviate from the scope of the present invention.

Claims

1. A bladeless aircraft, comprising a fuselage (4), two front wings (3), two rear wings (5), two front propellers (2) and two rear propellers (1), wherein the fuselage (4) is located in the middle of the entire aircraft, the two front wings (3) are arranged at the front end of the aircraft and rotate together through a transmission shaft, the two rear wings (5) are arranged at the end of the aircraft and rotate together through a transmission shaft, the two front propellers (2) and the two front wings (3) are integrated, the two rear propellers (1) and the two rear wings (5) are integrated, and the front propellers (2) and the rear propellers (1) are both designed without exposed blades; a revolute pair is used between the front wings (3), the rear wings (5) and the fuselage (4), so that the front wings and the rear wings can rotate together; when the aircraft takes off vertically, the front wings (3) and the rear wings (5) are both perpendicular to the ground, and the front wings (3) and the rear wings (5) are both perpendicular to the ground. The invention relates to a method for controlling the rotation and attitude of the front wing (3) and the rear wing (5) of the aircraft so as to reduce the air resistance during take-off. When the aircraft is flying level, the front wing (3) and the rear wing (5) are parallel to the ground, thereby reducing the flight resistance. When the aircraft climbs, different climbing angles can be achieved by adjusting the angles of the front wing (3) and the rear wing (5). The rotation and attitude control of the front wing (3) and the rear wing (5) are controlled by the flight control system to realize the flight operation of the aircraft. The two front propellers (2) and the rear propeller (1) are independently controlled and are controlled by the flight control system. The motor air inlet (6) is located below the fuselage (4). A high-speed motor and blades (9) are installed in the internal air inlet channel (10). The air flow enters from the motor air inlet (6). The high-speed motor and blades (9) drive the air flow to flow in the internal air inlet channel (10) and reach the natural wind inlet (7). The air flow is multiplied by the Coanda effect, so that the air flow in the natural wind inlet (7) flows out from the air outlet (8) at a speed of more than 15 times the wind speed.

2. The bladeless aircraft according to claim 1, wherein: The two front wings (3) are distributed symmetrically on the left and right, and the two rear wings (5) are distributed symmetrically on the left and right.

3. The bladeless aircraft according to claim 1, wherein: The fuselage (4) adopts a low wind resistance appearance design, and the fuselage material adopts a lightweight and high-strength aviation material. The bottom of the fuselage adopts a soft material, and a landing gear and a taxiing wheel are installed inside.

4. The bladeless aircraft according to claim 1, wherein: All blades are made of carbon fiber.

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