CN214356676U

CN214356676U - Flapping wing aircraft with adjustable wing pitch

Info

Publication number: CN214356676U
Application number: CN202120427253.2U
Authority: CN
Inventors: 许娜; 周帅至; 牟晓蕾
Original assignee: Yantai University
Current assignee: Yantai University
Priority date: 2021-02-26
Filing date: 2021-02-26
Publication date: 2021-10-08
Anticipated expiration: 2031-02-26

Abstract

The utility model relates to a wing is apart from adjustable flapping wing aircraft belongs to miniature flapping wing aircraft field. The flapping wing aircraft comprises an aircraft body, wings, a flapping mechanism, a hollow cup motor and a steering engine, wherein the flapping mechanism and the hollow cup motor are directly arranged on the aircraft body and consist of a gear, a connecting rod and a rocker arm; the gear, duplicate gear and gear intermeshing to with the high rotational speed reduction of motor output, the gear drives the connecting rod lower extreme and does the unidirectional rotation, the upper end of connecting rod restricts mutually with the slot of fuselage, and drive connecting rod one end and do reciprocating linear motion, thereby drive connecting rod and rocking arm and do reciprocating motion, the arm links firmly with the wing realizes flapping of wing, the fuselage comprises first fuselage and second fuselage, the second fuselage is installed on the slide bar of first fuselage and fixed mounting has the steering wheel, the steering wheel is from taking the gear and meshing with the rack on the first fuselage, thereby control the steering wheel to realize the slip of second fuselage on first fuselage and change the distance between two pairs of wings.

Description

Flapping wing aircraft with adjustable wing pitch

Technical Field

The utility model relates to a miniature flapping wing aircraft field particularly, is a wing distance adjustable flapping wing aircraft.

Background

The miniaturization and miniaturization of man-made aircraft has been the focus of research, and due to the development of manufacturing processes and micro-electromechanical systems, the micro-flapping wing aircraft has made great progress in manufacturing, but the micro-flapping wing aircraft still faces many problems in aerodynamic performance, especially the unsteady aerodynamic problems faced by flying in low reynolds number environment. The previous aerodynamic research on the tandem wings under the low Reynolds number shows that the airflows generated by the front and rear wings during flapping affect each other, the front edge vortex generated by the rear wing can improve the propulsion efficiency of the front wing, the shedding vortex of the front wing and the action of the rear wing can also enable the rear wing to obtain better aerodynamic performance, the influence is related to the distance between the front and rear wings and the phase difference of flapping, and the distance between the front and rear wings and the flapping phase difference are reasonably controlled to enable the micro flapping wing aircraft to obtain better aerodynamic performance.

SUMMERY OF THE UTILITY MODEL

The utility model discloses to the distance of wing and the problem of flapping the phase difference around current miniature flapping wing aircraft can not adjust when adopting the tandem wing overall arrangement, provided a wing apart from adjustable flapping wing aircraft, the flapping of wing is realized through gear connecting rod structure to adjust the distance of front and back wing and flap the phase difference through the control motor, the interact of air current between the wing before can the rational utilization, with this increase aerodynamic lift.

The utility model provides an above-mentioned technical problem's technical scheme as follows:

a flapping wing aircraft with adjustable wing pitch comprises a first aircraft body 9, a second aircraft body 10, wings 8, a flapping mechanism 100, a hollow cup motor 11, a steering engine 12, a transmission gear 13 and a rack 14;

the flapping mechanism 100 comprises a power gear 1, a duplicate gear 2, a gear 3, a first connecting rod 4, a second connecting rod 5, a third connecting rod 6 and a rocker arm 7; the second connecting rod 5, the third connecting rod 6, the rocker arm 7 and the wing 8 are symmetrically distributed in pairs; the power gear 1, the duplicate gear 2, the gear 3, the second connecting rod 5 and the rocker arm 7 on the flapping mechanism 100 are all installed through corresponding installation holes on the machine body, the power gear 1 is fixedly installed on an output shaft of the coreless motor 11, the power gear 1 is meshed with the duplicate gear 2, the duplicate gear 2 is meshed with the gear 3 to reduce the high rotating speed output by the coreless motor 11, the gear 3 is hinged with the lower end of the first connecting rod 4, the upper end of the first connecting rod 4 is constrained with a first groove 101 on the machine body, the upper end of the first connecting rod 4 is constrained with second grooves 51 of the two second connecting rods 5, the other ends of the second connecting rods 5 are respectively hinged with a third connecting rod 6, the third connecting rod 6 is hinged with the rocker arm 7, and the rocker arm 7 is used as an output end of the flapping mechanism 100 and is fixedly connected with the wing 8 so as to realize flapping of the wing 8 driven by the rocker arm 7;

the flapping mechanisms 100 are respectively arranged on the first machine body 9 and the second machine body 10, and the coreless motors 11 are respectively arranged on the first machine body 9 and the second machine body 10 to provide power output for the flapping mechanisms 100; a steering gear 12 and a rack 14 are mounted on the second machine body 10, a transmission gear 13 is fixed on an output shaft of the steering gear 12, the transmission gear 13 is in meshed transmission with the rack 14, and the first machine body 9 and the second machine body 10 are mounted in a clearance fit mode through sliding rods, so that the second machine body 10 and the first machine body 9 can move back and forth relatively along the sliding rod direction.

Preferably, wings 8 comprise a main beam 802, an auxiliary beam 801 and a wing membrane 803; wherein the main beam 802 is fixedly connected with the rocker arm 7 in an interference fit manner; the main beam 802 and the auxiliary beam 801 both adopt carbon rods with the same diameter, and the auxiliary beam 801 is vertically fixed on the main beam 802 through glue; the wing membranes are made of thin film materials and are fixed on the main beams 802 and the auxiliary beams 801 through glue.

Has the advantages that:

1. the flapping wing aircraft with the adjustable wing pitch adopts a design mode of two pairs of wings, and has larger aerodynamic lift force compared with the pair of wings.

2. The flapping wing aircraft with the adjustable wing pitch adopts a gear connecting rod structure to realize flapping of wings, and has the advantages of simple structure and high reliability.

3. The flapping wing aircraft with the adjustable wing distance can change flapping phase difference between front and rear wings through differential motion of two hollow cup motors, can adjust the distance between the front and rear wings through reciprocating rotation of a steering engine, and can improve the pneumatic performance by reasonably utilizing the interaction of airflow between the front and rear wings.

Drawings

FIG. 1 is a schematic view of an angle of an ornithopter with adjustable wing pitch;

FIG. 2 is a general schematic view of another angle of an ornithopter with adjustable wing pitch;

FIG. 3 is a schematic structural diagram of a flapping mechanism 100 of an ornithopter with adjustable wing pitch;

FIG. 4 is a schematic structural diagram of a first fuselage 9 of an ornithopter with adjustable wing pitch;

FIG. 5 is a schematic structural diagram of a second fuselage 10 of an ornithopter with adjustable wing pitch;

FIG. 6 is a schematic structural diagram of a second connecting rod 5 of an ornithopter with adjustable wing pitch;

FIG. 7 is a schematic structural diagram of a third link 6 of an ornithopter with adjustable wing pitch;

FIG. 8 is a schematic structural diagram of a swing arm 7 of an ornithopter with adjustable wing pitch;

FIG. 9 is a schematic structural view of a wing 8 of an ornithopter with adjustable wing pitch;

FIG. 10 is a schematic view of the adjustment of the shortest pitch of an ornithopter with adjustable pitch;

fig. 11 is a schematic diagram of the adjustment of the longest pitch of an ornithopter with adjustable pitch.

The reference numbers are recorded as follows:

the flapping-wing aircraft comprises a power gear 1, a duplicate gear 2, a gear 3, a first connecting rod 4, a second connecting rod 5, a third connecting rod 6, a rocker arm 7, wings 8, a first machine body 9, a second machine body 10, a flapping mechanism 100, a coreless motor 11, a steering engine 12, a transmission gear 13 and a rack 14.

Main beam 802, auxiliary beam 801, wing membrane 803.

A first slide bar 906, a second slide bar 907, a third slide bar 908.

Detailed Description

The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.

Example 1

As shown in fig. 1-11: a flapping wing aircraft with adjustable wing pitch comprises a first aircraft body 9, a second aircraft body 10, four wings 8, two flapping mechanisms 100, two coreless motors 11, a steering engine 12, a transmission gear 13 and a rack 14;

the four wings 8 are symmetrically distributed in pairs;

the flapping mechanism 100 comprises a power gear 1, a duplicate gear 2, a gear 3, a first connecting rod 4, two second connecting rods 5, two third connecting rods 6 and two rocker arms 7, wherein the two second connecting rods 5, the two third connecting rods 6 and the two rocker arms 7 are symmetrically distributed in pairs,

the power gear 1, the duplicate gear 2, the gear 3, the two second connecting rods 5 and the two rocker arms 7 on the flapping mechanism 100 are all assembled and installed with the machine body through corresponding installation holes on the first machine body 9 and the second machine body 10, the power gear 1 is fixedly installed on an output shaft of the coreless motor, the power gear 1 is meshed with the duplicate gear 2, the duplicate gear 2 is meshed with the gear 3 to reduce the high rotating speed output by the driving motor to a speed suitable for flapping, the gear 3 is hinged with the lower end of the first connecting rod 4, the upper end of the first connecting rod 4 is constrained with a first groove 101 on the machine body, the upper end of the first connecting rod 4 is constrained with second grooves 51 of the two second connecting rods 5, the other ends of the two second connecting rods 5 are respectively hinged with the two third connecting rods 6, the two third connecting rods 6 are respectively hinged with the two rocker arms 7, the two rocker arms 7 are respectively fixedly connected with a wing 8 as output ends of the flapping mechanism 100, thereby realizing flapping of the wings 8 driven by the rocker arm 7.

The flapping mechanism 100 is respectively arranged on the first machine body 9 and the second machine body 10, and the two coreless motors 11 are respectively arranged on the first machine body 9 and the second machine body 10 to provide power output for the flapping mechanism 100; the second machine body 10 is provided with a steering engine 12 and a rack 14, an output shaft of the steering engine 12 is fixedly provided with a transmission gear 13, the transmission gear 13 is meshed with the rack 14 for transmission, and the first machine body 9 and the second machine body 10 are installed through a first sliding rod 906, a second sliding rod 907 and a third sliding rod 908 in a clearance fit manner, so that the second machine body 10 and the first machine body 9 can move back and forth relatively along the sliding rod direction.

Wings 8 include main beams 802, auxiliary beams 801 and a wing membrane 803; wherein the main beam 802 is fixedly connected with the rocker arm 7 in an interference fit manner; the main beam 802 and the auxiliary beam 801 both adopt carbon rods with the same diameter, and the auxiliary beam 801 is vertically fixed on the main beam 802 through glue; the wing membranes are made of thin film materials and are fixed on the main beams 802 and the auxiliary beams 801 through glue.

The process of adjusting the distance between the front and rear wings in this example is as follows:

the second body 10 and the first body 9 are in clearance fit through a first sliding rod 906, a second sliding rod 907 and a third sliding rod 908, the second body 10 is driven to slide back and forth on the first body 9 through the reciprocating rotation of the steering engine 12, and therefore the distance between the front wing and the rear wing between the second body 10 and the first body 9 is adjusted, and the shortest distance between the front wing and the rear wing is 0.25cMaximum distance of 2cWherein, in the step (A),cis the chord length.

In summary, the flapping wing aircraft with the adjustable wing pitch of the embodiment realizes flapping of wings through a gear connecting rod structure, the flapping phase difference between the front wing and the rear wing is changed through the differential motion of the two coreless motors, and the distance between the front wing and the rear wing is adjusted through the reciprocating rotation of the steering engine, so that the interaction of airflow between the front wing and the rear wing is reasonably utilized, and the aerodynamic performance of the miniature flapping wing aircraft is improved.

The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.

Claims

1. A flapping wing aircraft with adjustable wing pitch is characterized by comprising a first aircraft body, a second aircraft body, wings, a flapping mechanism, a hollow cup motor, a steering engine, a transmission gear and a rack;

the flapping mechanism comprises a power gear, a duplicate gear, a first connecting rod, a second connecting rod, a third connecting rod and a rocker arm; the second connecting rod, the third connecting rod, the rocker arm and the wing are symmetrically distributed in pairs; the power gear, the duplicate gear, the second connecting rods and the rocker arm on the flapping mechanism are all installed through corresponding installation holes in the machine body, the power gear is fixedly installed on an output shaft of the coreless motor and is meshed with the duplicate gear, the duplicate gear is meshed with the gear to reduce the high rotating speed output by the coreless motor, the gear is hinged with the lower end of the first connecting rod, the upper end of the first connecting rod is constrained with a first groove in the machine body, the upper end of the first connecting rod is constrained with second grooves of the two second connecting rods, the other ends of the second connecting rods are respectively hinged with third connecting rods, the third connecting rods are hinged with the rocker arm, and the rocker arm is used as an output end of the flapping mechanism and fixedly connected with a wing so as to realize flapping of the wing driven by the rocker arm;

the flapping mechanisms are respectively arranged on the first machine body and the second machine body, and the hollow cup motors are respectively arranged on the first machine body and the second machine body to provide power output for the flapping mechanisms; the second machine body is provided with a steering engine and a rack, a transmission gear is fixed on an output shaft of the steering engine and is in meshed transmission with the rack, and the first machine body and the second machine body are installed in a clearance fit mode through a sliding rod, so that the second machine body and the first machine body can move back and forth relatively along the direction of the sliding rod.