Aircraft without exposed blades

Abstract

The invention provides a non-exposed blade type aircraft which comprises an aircraft body (4), two front wings (3), two rear wings (5), two front propellers (2) and two rear propellers (1), the aircraft body (4) is located in the middle of the whole aircraft, the two front wings (3) are arranged at the front end of the aircraft and rotate together through a transmission shaft, and the two rear wings (5) are arranged at the rear end of the aircraft. The two rear wings (5) are arranged at the tail end of the aircraft and rotate together through a transmission shaft, the two front propellers (2) and the two front wings (3) are integrally designed, the two rear propellers (1) and the two rear wings (5) are integrally designed, and the two rear propellers (1) and the two rear wings (5) are integrally designed. The front thruster (2) and the rear thruster (1) are both designed to be free of exposed blades. According to the aircraft, the design without exposed blades is adopted, foreign objects can be prevented from being sucked in, the safety in the flight process is enhanced, and the flight efficiency is improved through the airflow multiplication effect.

Description

Technical Field

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

[0002] Low-altitude flight has great commercial application prospects, is highly favored by the market, and is strongly supported by the government. However, most aircraft on the market currently have exposed blades, which make a lot of noise during flight and have poor structural stability. If branches, debris, and other foreign objects invade during flight, the blades are easily damaged, which will greatly affect flight safety and even cause the aircraft to be scrapped. Therefore, it is necessary to design an aircraft without exposed blades to overcome the above shortcomings and at the same time have higher 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 the front propellers 2 and the rear propellers 1 both adopt a bladeless design.

[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 take-off; 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 thrusters 2 and the rear thruster 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 a landing gear and a taxiing wheel 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 to 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 air inlet 7 flows out from the air outlet 8 at a wind speed more than 15 times.

[0013] Preferably, the high-speed motor and the blades 9 use 13 blades, and the high-speed motor is inside the center 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 with no exposed blades 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 solution of the present invention, the drawings used in the present invention are briefly introduced below.

[0020] Figure 1 It is a perspective structural schematic diagram of a blade-free aircraft of the present invention in level flight;

[0021] Figure 2 It is a left side view of a blade-free aircraft of the present invention in level flight;

[0022] Figure 3A cross-sectional view of an aircraft propeller without exposed blades according to the present invention;

[0023] Figure 4 The present invention is a perspective structural schematic diagram of an enlarged fuselage and a propeller of a blade-free 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] In order to better understand the technical solution of the present invention, the content of the present invention includes but is not limited to the specific implementation methods described below, and similar technologies and methods should be considered to be within the scope of protection of the present invention. In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to 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, 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 are rotated together through a transmission shaft, and the two rear wings 5 ​​are arranged at the end of the aircraft, and are rotated together through a transmission shaft, and the rotation and attitude control of the front wings 3 and the rear wings 5 ​​are controlled by a flight control system, which helps the aircraft to climb and descend flexibly; the two front wings 3 are symmetrically distributed, the two rear wings 5 ​​are symmetrically distributed, the two front propellers 2 and the two front wings 3 are integrated, and the two rear propellers 1 and the two rear wings 5 ​​are integrated. 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 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, accelerating, decelerating, climbing and descending.

[0029] The fuselage 4 adopts a low wind resistance appearance design, the fuselage material adopts a lightweight and high-strength aviation material, the fuselage bottom adopts a soft material, and a landing gear and a taxiing wheel are installed inside. The working process is: when the aircraft needs to land vertically, the landing gear and the taxiing wheel are not lowered, and a soft landing is achieved by the soft material at the bottom of the fuselage; when the aircraft needs to taxi on the runway for takeoff or landing, the landing gear and the taxiing wheel are lowered to achieve taxiing takeoff or landing.

[0030] The two front wings 3 are symmetrically distributed, the two rear wings 5 ​​are symmetrically distributed, the two front propellers 2 and the two front wings 3 are integrated, and the two rear propellers 1 and the two rear wings 5 ​​are integrated. 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 with the connecting shaft. The two front propellers and the rear propeller are independently controlled and controlled by the flight control system, so that the aircraft can flexibly realize flight operations including turning, acceleration, deceleration, climbing and descending.

[0031] The specific working process is as follows: when the aircraft takes off vertically, the front wing 3 and the rear wing 5 are both perpendicular to the ground, thereby reducing the air resistance during takeoff. When the aircraft flies horizontally, the front wing 3 and the rear wing 5 are parallel to the ground, thereby reducing the flight resistance. When the aircraft climbs, different angles of climbing can be achieved by adjusting the angles of the front wing 3 and the rear wing 5.

[0032] The front propeller 2 and the rear propeller 1 are both designed without exposed blades, 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, the airflow enters from the motor air inlet 6, and the high-speed motor and blades 9 drive the airflow to flow in the internal air inlet channel 10 in the direction of the arrow, reaching the natural wind air inlet 7, and the airflow is multiplied by the Coanda effect, so that the airflow in the natural wind air inlet 7 flows out from the air outlet 8 at a wind speed of more than 15 times. The Coanda effect refers to the tendency of the fluid (water flow or airflow) to deviate from the original flow direction and flow along the protruding surface of the object. When there is surface friction between the fluid and the surface of the object it flows through (it can also be said to be fluid viscosity), as long as the curvature is not large, the fluid will flow along the surface of the object. Using the "fluid viscosity" of the fluid, the high-speed motor and blades 9 drive the airflow to enter from the motor air inlet 6, and then the high-speed airflow passes through the internal air inlet channel 10 and is ejected out through a narrow slit, driving the surrounding air to move together, forming a larger volume of airflow. Thereby achieving the multiplication effect of the airflow, generating huge lift, and meeting the take-off and landing requirements of the aircraft.

[0033] Specifically, the high-speed motor and the blades 9 are made of 13 pieces, the high-speed motor is inside the central hole of the blade, and all the blades are made of carbon fiber material. Figure 3 As shown, lift is generated through 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 multiplier effect, it can achieve both vertical take-off and landing and gliding take-off and landing, and can flexibly achieve various aerial flight posture adjustments.

[0035] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. A person skilled in the art may modify the technical solutions described in the present invention, or replace some of the technical features therein with equivalents, and these modifications or replacements do not make the corresponding technical solutions deviate from the scope described in 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 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.

2. The bladeless aircraft according to claim 1, characterized in that: The two front wings (3) are distributed in a left-right symmetrical manner, and the two rear wings (5) are distributed in a left-right symmetrical manner.

3. The bladeless aircraft according to claim 1, characterized in that: A revolving 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.

4. The bladeless aircraft according to claim 3, characterized in that: 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 take-off; 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).

5. The bladeless aircraft according to claim 1, characterized in that: 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 thrusters (2) and the rear thruster (1) are independently controlled and are controlled by the flight control system.

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

7. The airborne aircraft without exposed blades according to claim 1, characterized in that: 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).

8. The bladeless aircraft according to claim 7, characterized in that: The airflow enters from the motor air inlet (6), and the high-speed motor and blades (9) drive the airflow to flow in the internal air inlet channel (10) and reach the natural wind air inlet (7). The airflow is multiplied through the Coanda effect, so that the airflow in the natural wind air inlet (7) flows out from the air outlet (8) at a wind speed 15 times higher than that of the natural wind air inlet (7).

9. The bladeless aircraft according to claim 7, characterized in that: The high-speed motor and the blades (9) have 13 blades, and the high-speed motor is inside the central hole of the blade.

10. The bladeless aircraft according to claim 7, characterized in that: All blades are made of carbon fiber.

Images