CN106585982A - Combined type micro air vehicle driven by flapping wings - Google Patents

Abstract

The invention provides a composite micro-aircraft driven by a flapping wing, comprising: a fixed-wing lifting surface, a flapping-wing drive system, a V-shaped tail and a connecting rod; the fixed-wing lifting surface includes: a wing, a left aileron rudder surface and a right The aileron rudder surface is mainly used to provide lift and roll control required for aircraft flight; the flapping wing drive system includes: left flapping wing, right flapping wing, mechanism mounting frame and flapping mechanism, mainly used to provide aircraft flight The required thrust; the V-shaped tail includes: left tail, right tail, left tail and right tail rudder, used to provide stability and pitch and yaw control when the aircraft is flying. The advantages are: the present invention adopts the flapping wing drive to replace the traditional propeller drive, which can improve the propulsion efficiency of the micro-aircraft under the condition of low Reynolds number, and at the same time improve the lift characteristics of the whole machine to a certain extent, thereby improving the flight performance of the micro-aircraft.

Description

Composite micro air vehicle driven by flapping wings

technical field

The invention belongs to the technical field of micro-aircraft, and in particular relates to a composite micro-aircraft driven by flapping wings.

Background technique

Micro air vehicle is an aircraft with a size of less than 15cm. It is considered to be an important weapon for close-range reconnaissance and attack on the future battlefield.

In the prior art, the micro air vehicle mainly adopts propulsion propellers as the propulsion mechanism. Compared with large aircraft, MAVs are much more affected by air viscosity, which makes the low Reynolds number characteristics of MAVs particularly prominent. Affected by this, the propulsion efficiency is greatly reduced when a small-sized propulsion propeller is traditionally used, which directly restricts the flight performance of the MAV. Therefore, how to effectively improve the propulsion efficiency of the MAV and ensure the flight performance of the MAV is an urgent problem to be solved at present.

Contents of the invention

Aiming at the defects in the prior art, the present invention provides a composite micro-aircraft driven by flapping wings, which can effectively solve the above problems.

The technical scheme that the present invention adopts is as follows:

The invention provides a composite micro-aircraft driven by a flapping wing, comprising: a fixed wing lifting surface, a flapping wing drive system, a V-shaped tail and a connecting rod (8);

The front end of the connecting rod (8) is equipped with the fixed wing lifting surface; the tail end of the connecting rod (8) is equipped with the V-shaped tail; the flapping wing drive system is installed on the connecting rod (8) , and is located between the fixed-wing lifting surface and the V-tail;

Wherein, the fixed-wing lifting surface is used to generate the lift required for aircraft flight and the rolling moment required for aircraft attitude control; the fixed-wing lifting surface includes wing (1), left aileron rudder surface (2) and Right aileron rudder surface (3); described wing (1) is a rectangular wing, and its aspect ratio is in the scope of 6-10, and the center of described wing (1) and the front end of described connecting rod (8) fixed connection, and the leading edge of the wing (1) is perpendicular to the axis of the connecting rod (8); the left aileron rudder surface (2) and the right aileron rudder surface (3) are located at the The left and right sides of the trailing edge of the wing (1), the left aileron rudder surface (2) and the right aileron rudder surface (3) can respectively deflect up and down around their respective leading edges;

The flapping wing drive system is used to provide the required thrust when the aircraft flies forward; the flapping wing drive system includes a left flapping wing (4), a right flapping wing (5), a mechanism mounting frame (6) and a flapping wing mechanism (7); the mechanism mounting bracket (6) is fixedly connected with the connecting rod (8), and is located between the fixed wing lifting surface and the V-shaped tail; the flapping mechanism (7) is fixed connected to the mechanism mounting frame (6); the left flapping wing (4) and the right flapping wing (5) are symmetrically located on both sides of the connecting rod (8), and are respectively connected to the flapping The left and right fluttering rocker arms of moving mechanism (7) are fixedly connected;

The V-shaped tail is used to provide stability and maneuverability when the aircraft is flying; the V-shaped tail includes a left tail (9), a right tail (10), a left tail rudder (11) and a right tail rudder (12); The left empennage (9) and the right empennage (10) are arranged in a V shape, and their lower edges are respectively fixedly connected with the rear end of the connecting rod (8) along the direction of the connecting rod (8). The tail rudder (11) and the right tail rudder (12) are arranged symmetrically on the trailing edges of the left tail (9) and the right tail (10) respectively, and can deflect up and down around their respective leading edges.

Preferably, the vertical deflection angle range of the left aileron control surface (2) and the right aileron control surface (3) is within ±40°.

Preferably, the vertical deflection angle range of the left tail rudder (11) and the right tail rudder (12) is within ±40°.

Preferably, the flapping wing driving system is located at a position of 40%-60% of the total front and rear length of the micro air vehicle.

The composite micro air vehicle driven by flapping wings provided by the present invention has the following advantages:

(1) The present invention adopts the flapping wing drive instead of the traditional propeller drive as the driving mode of the micro-aircraft. propulsion efficiency of the aircraft;

(2) In addition to generating thrust to drive the aircraft forward, the flapping wing can also generate a certain amount of lift. In the process of flapping, it will drive the air in front to flow backwards, thereby improving the lift characteristics of the fixed wing. This composite layout can improve the lift characteristics of the entire micro air vehicle to a certain extent.

Description of drawings

Fig. 1 is the schematic diagram of the three-dimensional structure of the hybrid micro-aircraft driven by flapping wings provided by the present invention;

Fig. 2 is a top view of the composite micro air vehicle driven by flapping wings provided by the present invention.

detailed description

In order to make the technical problems, technical solutions and beneficial effects solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

Aiming at the problem of low propulsion efficiency of small-sized propellers in low Reynolds number environments, the present invention uses flapping wings instead of traditional propellers as the driving device of the micro-aircraft, and provides a composite micro-aircraft driven by flapping wings. According to the research results of aerodynamics, under the condition of low Reynolds number, the flapping wing has higher driving efficiency, so the performance of the MAV can be improved by using the flapping wing drive instead of the propeller drive.

1 and 2, the composite micro-aircraft using the flapping wing drive provided by the present invention includes a fixed-wing lifting surface, a flapping wing drive system, a V-shaped tail and a connecting rod 8 . The front end of the connecting rod 8 is equipped with a fixed-wing lifting surface; the tail end of the connecting rod 8 is equipped with a V-shaped tail; Between 40% and 60% of the total front and rear length, the specific position needs to be determined through relevant aerodynamic analysis and tests. Thus constitute the whole aircraft. The following is a detailed introduction to each component:

(1) Fixed wing lifting surface

The fixed-wing lifting surface is used to generate the lift required for aircraft flight and the roll moment required for aircraft attitude control; the fixed-wing lifting surface includes wing 1, left aileron control surface 2 and right aileron control surface 3; wing 1 It is a rectangular wing with a certain airfoil profile, its aspect ratio is in the range of 6-10, the center of the wing 1 is fixedly connected with the front end of the connecting rod 8, and the leading edge of the wing 1 is perpendicular to the axis of the connecting rod 8 ; The left aileron rudder surface 2 and the right aileron rudder surface 3 are respectively located on the left and right sides of the rear edge of the wing 1, and the left aileron rudder surface 2 and the right aileron rudder surface 3 can deflect up and down around their respective leading edges respectively, and the deflection The angle range is within ±40°.

(2) Flapping wing drive system

The flapping wing drive system is used to provide the required thrust when the aircraft flies forward; the flapping wing drive system includes the left flapping wing 4, the right flapping wing 5, the mechanism mounting frame 6 and the flapping mechanism 7; the mechanism mounting frame 6 and the connecting rod 8 are fixedly connected, and are located between the fixed wing lifting surface and the V-shaped tail; the flapping mechanism 7 is fixed on the mechanism mounting frame 6; the left flapping wing 4 and the right flapping wing 5 are symmetrically located on both sides of the connecting rod 8, And respectively with the left and right flapping rocking arms of flapping mechanism 7.

(3) V-shaped tail

The V-shaped empennage is used to provide stability and maneuverability when the aircraft is flying; the V-shaped empennage comprises a left empennage 9, a right empennage 10, a left empennage 11 and a right empennage 12; the left empennage 9 and the right empennage 10 are V-shaped arrangements, Its lower edge is fixedly connected with the rear end of the connecting rod 8 respectively along the direction of the connecting rod 8, and the left tail rudder 11 and the right tail rudder 12 are arranged symmetrically on the trailing edges of the left tail 9 and the right tail 10 respectively, and can be wound around the respective leading edges. Up and down deflection, the deflection angle range is within ±40°.

The composite micro air vehicle driven by flapping wings provided by the present invention has the flight principle as follows:

The fixed-wing lift surface is mainly used to generate the lift required for the flight of the aircraft, and at the same time provide the rolling moment required for the attitude control of the aircraft through the differential deflection of the left aileron rudder surface 2 and the right aileron rudder surface 3 at the trailing edge; The wing drive system is mainly used to provide the thrust required for the forward flight of the aircraft; the V-shaped tail is mainly used to provide the stability and maneuverability of the aircraft during flight, wherein when the left tail rudder 11 and the right tail rudder are deflected in tandem, the attitude of the aircraft can be provided. Control the required pitching moment, when the left tail rudder 11 and the right tail rudder are deflected differentially, the yaw moment required for aircraft attitude control can be provided; connected together to form the entire aircraft.

In summary, the hybrid micro-aircraft driven by flapping wings provided by the present invention has the following advantages:

(1) The present invention adopts the flapping wing drive instead of the traditional propeller drive as the driving mode of the micro-aircraft. propulsion efficiency of the aircraft;

(2) In addition to generating thrust to drive the aircraft forward, the flapping wing can also generate a certain amount of lift. In the process of flapping, it will drive the air in front to flow backwards, thereby improving the lift characteristics of the fixed wing. This composite layout can improve the lift characteristics of the entire micro air vehicle to a certain extent.

The above is only a preferred embodiment of the present invention, and it should be pointed out that for those of ordinary skill in the art, some improvements and modifications can be made without departing from the principle of the present invention. It should be regarded as the protection scope of the present invention.

Claims (4)

1. A composite micro air vehicle driven by flapping wings is characterized in that it comprises: fixed wing lifting surface, flapping wing drive system, V-shaped empennage and connecting rod (8); The front end of the connecting rod (8) is equipped with the fixed wing lifting surface; the tail end of the connecting rod (8) is equipped with the V-shaped tail; the flapping wing drive system is installed on the connecting rod (8) , and is located between the fixed-wing lifting surface and the V-tail; Wherein, the fixed-wing lifting surface is used to generate the lift required for aircraft flight and the rolling moment required for aircraft attitude control; the fixed-wing lifting surface includes wing (1), left aileron rudder surface (2) and Right aileron rudder surface (3); described wing (1) is a rectangular wing, and its aspect ratio is in the scope of 6-10, and the center of described wing (1) and the front end of described connecting rod (8) fixed connection, and the leading edge of the wing (1) is perpendicular to the axis of the connecting rod (8); the left aileron rudder surface (2) and the right aileron rudder surface (3) are located at the The left and right sides of the trailing edge of the wing (1), the left aileron rudder surface (2) and the right aileron rudder surface (3) can respectively deflect up and down around their respective leading edges; The flapping wing drive system is used to provide the required thrust when the aircraft flies forward; the flapping wing drive system includes a left flapping wing (4), a right flapping wing (5), a mechanism mounting frame (6) and a flapping wing mechanism (7); the mechanism mounting bracket (6) is fixedly connected with the connecting rod (8), and is located between the fixed wing lifting surface and the V-shaped tail; the flapping mechanism (7) is fixed connected to the mechanism mounting frame (6); the left flapping wing (4) and the right flapping wing (5) are symmetrically located on both sides of the connecting rod (8), and are respectively connected to the flapping The left and right fluttering rocker arms of moving mechanism (7) are fixedly connected; The V-shaped tail is used to provide stability and maneuverability when the aircraft is flying; the V-shaped tail includes a left tail (9), a right tail (10), a left tail rudder (11) and a right tail rudder (12); The left empennage (9) and the right empennage (10) are arranged in a V shape, and their lower edges are respectively fixedly connected with the rear end of the connecting rod (8) along the direction of the connecting rod (8). The tail rudder (11) and the right tail rudder (12) are arranged symmetrically on the trailing edges of the left tail (9) and the right tail (10) respectively, and can deflect up and down around their respective leading edges. 2. the composite micro-aircraft that adopts flapping wings to drive according to claim 1, is characterized in that, the angle range that described left aileron rudder surface (2) and described right aileron rudder surface (3) deflect up and down is Within ±40°. 3. The composite micro air vehicle driven by flapping wings according to claim 1, characterized in that, the angle range of the up and down deflection of the left tail rudder (11) and the right tail rudder (12) is within ±40° . 4. The composite micro air vehicle driven by flapping wings according to claim 1, wherein the flapping wing drive system is located at a position of 40%-60% of the total length of the front and rear of the micro air vehicle.