CN202414163U - Wing of minitype ornithopter - Google Patents

Abstract

The utility model discloses a wing of a miniature flapping wing plane, the main beam is straight, the leading edge points of five wing ribs are fixed on the main beam, and the No. 1 wing rib, the No. 2 wing rib and the No. 3 wing rib are perpendicular to the main beam. Beam, No. 4 rib and No. 5 rib form an acute angle with the direction of the main beam tip; No. 1 rib, No. 2 rib and No. 3 rib have the same chord length, and the chord length of No. 4 rib and No. 5 rib Decrease in turn, all shorter than the No. 1 rib, the auxiliary beam is arc-shaped, the outer edge point is fixed on the main beam between the end point of the main beam tip and the rear edge point of the No. 5 rib, and the root passes through the second half of the No. 1 rib part, the auxiliary beam is in contact with and fixed to the corresponding positions of the five wing ribs; the main beam, auxiliary beam and wing ribs constitute the wing structural frame, and the skin is attached on the frame to form a complete wing. The stiffness distribution and transition of the entire wing are smooth, the structure is continuous, and has good force characteristics, and the structure is simple and easy to manufacture.

Description

A wing of a miniature flapper

technical field

The invention relates to a wing, in particular to a wing of an orthopter.

Background technique

The micro flapping wing aircraft is a new concept aircraft that imitates the flight of birds. It has the advantages of small size, light weight, good concealment, flexible use, and high efficiency. If it is equipped with sensors and related data transmission and flight control systems, it will form a miniature The flapping wing UAV platform will have broad application prospects. Focusing on this topic, various countries have developed flapping-wing aircraft with controllable flight. The more successful ones include the "Microbat" jointly developed by Aero Vironment of the United States and the University of California, and the "Delfly" developed by Delft University in the Netherlands. There is still a big gap, which is mainly reflected in the limited flight time, small payload, and difficult control. Trace it to its cause, the low aerodynamic efficiency of flapping wing aircraft wing, power consumption is big, poor reliability is quite important factor.

At present, the orthopter that has achieved flight mostly adopts flat airfoil wings. Studies have shown that the lift coefficient of this type of wing is small. In order to generate sufficient lift, a larger angle of attack is required, which increases the resistance. Lift-drag Relatively small, resulting in low aerodynamic efficiency, affecting the overall performance of the orthopter.

Chinese Patent Publication No. CN100467347C, published on March 11, 2009, the name of the invention is a two-stage miniature flapping-wing aircraft wing. The application discloses a miniature flapping-wing aircraft wing, which is divided into inner and outer Two sections, the outer wing section is a plane airfoil, the inner wing section is a curved airfoil, the outer wing section has a front main beam and a slanted beam, and the inner wing section has a front main beam and a tail beam parallel to each other. The disadvantage is that the shape and structural rigidity of the inner wing section and the outer wing section change suddenly, which is easy to cause structural damage, poor reliability, and the overall aerodynamic efficiency of the wing will also be reduced.

In recent years, in order to improve the aerodynamic efficiency of orthopter wings, some orthopter wings using mechanisms to passively or actively change the shape of the wings have appeared. The moment of inertia increases the power consumption of the flapping-wing drive system, reducing the life and reliability of the flapping-wing aircraft; realizing the cooperation between shape change and flapping requires precise control, which increases the difficulty of controlling the flapping-wing aircraft.

Chinese Patent Publication No. CN201217500Y, published on April 8, 2009, the name of the invention is bionic aircraft wing. The blades are hinged through the blade shafts in the holes. The blades can open and close passively or actively controlled by the mechanism when the wings flutter up and down, so as to achieve the purpose of reducing drag and increasing lift. The disadvantage is that the blade and its mechanism will increase the weight and moment of inertia of the wing, increase the power required for flapping, and reduce the life of the flapping mechanism and the wing itself; the opening and closing of the blade needs to cooperate with the flapping position to increase control difficulty.

Chinese Patent Publication No. CN2918218Y, date of disclosure July 4th, 2007, the name of the invention is a foldable two-section flapper wing. This application discloses a flapping wing that can be folded into two sections. It is divided into an inner wing section and an outer wing section that can be folded in half. The transmission crankshaft and the tie rod cooperate to generate inner and outer wings when the wing flutters up and down. The relative folding movement of the wing segments simulates the flapping state of birds such as seagulls in flight. Its disadvantage is that the strength and weight of the crankshaft and tie rod structure are sharply contradictory, and it is difficult to have sufficient strength and light weight at the same time, which leads to a decrease in the life of the wing and poor reliability.

Chinese Patent Publication No. CN101492094A, published on July 29, 2009, the name of the invention is a flapping wing of a miniature flapping wing capable of unidirectional bending. This application discloses a flapping wing that can be bent in one direction. Its span beam is broken into two sections, and stretchable elastic materials and connecting pieces that can be deformed in one direction are respectively fixed on the upper and lower surfaces of the disconnection to realize flapping. The fluttering wings are fully unfolded when flying, and partially folded when fluttering upwards. Its shortcoming is that the folding effect is completely passively produced by the elastic material under the action of aerodynamic force. When the flapping frequency of the flapping wing is high, the folding effect will be weakened to a considerable extent; the aging and life of the elastic material directly affect the flapping wing. overall performance and longevity.

Contents of the invention

In order to overcome the disadvantages of low aerodynamic efficiency, unreasonable structure stiffness distribution and poor reliability in the prior art, the present invention provides a wing of a miniature flapper, which can improve the aerodynamic efficiency of the flapper wing and simplify the wing structure , to improve wing reliability.

The technical solution adopted by the present invention to solve the technical problem includes main girders, auxiliary girders, wing ribs and skins. The main beam is straight, and the front edge points of the five wing ribs are fixed on the main beam, starting from the root of the main beam, occupying two-thirds to four-fifths of the spanwise length of the main beam.

No. 1 rib, No. 2 rib and No. 3 rib are perpendicular to the main beam, and No. 4 and No. 5 ribs form an acute angle with the direction of the tip of the main beam; No. 1 rib, No. 2 rib and No. 3 rib The chord lengths of the ribs are equal, and the chord lengths of the No. 4 rib and No. 5 rib decrease successively, and they are both shorter than the No. 1 rib. The front edge is the centerline of the main beam, the root is the chord line of the No. 1 rib, and the side of the root of the trailing edge is a straight line formed by the trailing edge points of the No. 1 rib and No. 3 rib, starting from the No. 3 rib to the tip of the main beam The part at the bottom is a quadratic spline curve, which is tangent to the straight line formed by the trailing edge points of No. 1 rib and No. 3 rib at the trailing edge point of No. Rib trailing edge point and main spar tip end point.

The airfoils of No. 1 rib, No. 2 rib and No. 3 rib are all thin airfoils, No. 5 rib is straight, and No. 4 rib is the transitional airfoil of the former two.

The auxiliary beam is arc-shaped, and the outer edge point is fixed on the main beam between the end point of the main beam tip and the rear edge point of the No. 5 wing rib, and the root passes through the second half of the No. The corresponding position is contacted and fixed.

The chord length of the No. 4 wing rib is 90%-97% of the chord length of the No. 1 wing rib, and the chord length of the No. 5 wing rib is 70%-80% of the chord length of the No. 1 wing rib. The angle between the No. 4 wing rib and the outer direction of the main beam is 70-80°, and the angle between the No. 5 wing rib and the outer direction of the main beam is 55-65°. The leading and trailing points of all ribs lie in the wing reference plane. The contact point between the auxiliary beam and the No. 1 rib is located at 75%-85% of the chord length of the No. 1 rib.

The main spars, auxiliary spars and ribs form the structural frame of the wing, over which the skin is attached to form the complete wing.

Compared with the prior art, the present invention obtains beneficial effects in terms of structure and aerodynamics:

The main and auxiliary beams of the wing and the ribs between them form a relatively rigid area, while the ribs outside this area are in the form of cantilever beams, which can undergo large elastic deformation. The position of the auxiliary beam makes the area where the ribs of the outer section of the wing undergo elastic deformation larger, and the area where the inner section undergoes elastic deformation is smaller, which is beneficial for the outer section to generate thrust and the inner section to generate lift. The stiffness distribution and transition of the entire wing are smooth, the structure is continuous, and has good force characteristics, and the structure is simple and easy to manufacture.

By adjusting the aspect ratio, the inclination angle and chord length ratio of No. 4 rib 4 and No. 5 rib 5, and the position of the positioning point of auxiliary beam 7 within a given range, the aircraft can be changed to a certain extent on the basis of meeting the basic flight requirements. The stiffness distribution of the wing can change the size and distribution of elastic deformation during flapping to meet different flight performance requirements.

Increase the aspect ratio, reduce the angle between No. 4 rib 4 and No. 5 rib 5 and the main beam 6, increase their chord length, move the outer end point of the auxiliary beam 7 outward, and place it in front of the contact position of No. 1 rib 1 can increase the elastic deformation of the outer section of the wing, and obtain greater thrust when fluttering; reduce the aspect ratio, increase the angle between the 4th rib 4, the 5th rib 5 and the main beam 6, and reduce them The length of the chord, moving the outer end point of the auxiliary beam 7 inward, and moving it back with the contact position of the No. 1 rib 1 can reduce the elastic deformation of the outer section of the wing, and obtain a larger lift when fluttering.

The structural stiffness distribution and elastic deformation characteristics of the wing are reasonable, and it can provide greater aerodynamic lift and thrust during the flapping process, and obtain a good combination of aerodynamic lift and thrust, while reducing the energy consumption of the wing flapping, The overall performance is better than the prior art.

Description of drawings

Fig. 1 is the schematic diagram (axonometric view) of embodiment 3

Fig. 2 is the schematic diagram (top view) of embodiment 3.

In the figure: rib 1-1, rib 2-2, rib 3-3, rib 4-4, rib 5-5, 6-main beam, 7-auxiliary beam, 8-skin.

Detailed ways

In order to overcome the disadvantages of low aerodynamic efficiency, unreasonable structure stiffness distribution and poor reliability in the prior art, the present invention provides a wing of a miniature flapper, which can improve the aerodynamic efficiency of the flapper wing and simplify the wing structure , to improve wing reliability. Studies have shown that the inner section of the flapping wing mainly produces lift, and its magnitude is related to the cross-sectional shape and stiffness distribution of the wing. The outer section of the wing mainly produces thrust, and its magnitude is related to the shape of the trailing edge of the outer section of the wing and the It is related to the stiffness distribution determined by the inclination angle of the outer wing ribs.

Below in conjunction with accompanying drawing provide the embodiment of miniature flapping wing.

Example 1:

The present embodiment is that the wing of a pair of miniature flapper aircraft comprises No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, auxiliary beam 7, skin 8 .

Taking the left wing as an example, during implementation:

No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, and auxiliary beam 7 are carbon fiber reinforced resin matrix composite rods, and the aspect ratio is taken as 8, that is The chord length of the No. 1 rib 1 is 25% of the length of the main girder 6 . The main beam 6 is straight, and the front edge points of the five wing ribs 1-5 are fixed on the main beam 6. Starting from the root of the main beam 6, it occupies two-thirds of the spanwise length of the main beam 6. No. 1 ribs 1 and 2 No. 2 rib 2 and No. 3 rib 3 are perpendicular to the main beam, No. 4 rib 4 and No. 5 rib 5 form an acute angle with the direction of the tip of the main beam, and the angles are 70° and 55° respectively. The chord lengths of No. 1 rib 1, No. 2 rib 2, and No. 3 rib 3 are equal, and the chord lengths of No. 4 rib 4 and No. 5 rib 5 decrease in turn, and they are all shorter than No. 1 rib 1, respectively. The chord length of No. 1 rib 1 97% and 80%. The airfoils of No. 1 rib 1, No. 2 rib 2 and No. 3 rib 3 are thin airfoils, No. 5 rib 5 is straight, and No. 4 rib 4 is the transitional airfoil of the former two. The auxiliary beam 7 is arc-shaped, and the outer edge point is fixed between the end point of the main beam 6 and the No. 5 rib, 15% of the length of the main beam from the outer end point of the main beam, and the root passes through the second half of the No. 1 rib 1 from the rear edge point At the position of 75% of the chord length, the radian ensures that the auxiliary beam 7 is in contact with the corresponding positions of the five wing ribs. The fixation between the main beam 6 and the wing ribs 1-5, and between the wing ribs 1-5 and the auxiliary beam 7 is all bound by aramid fibers soaked in glue. Both the main beam 6 and the auxiliary beam 7 extend a certain length at the root of the wing so as to be connected with the fuselage. So far, the wing frame composed of the main beam 6, the auxiliary beam 7 and the ribs 1-5 is completed, the polyester skin 8 is covered on the frame, and the adhesive is bonded to the wing frame to form a complete wing.

The composition of the right wing is the same as that of the left wing.

The wing made in embodiment 1 has a larger amount of elastic deformation when fluttering, and can produce greater thrust.

Example 2:

The present embodiment is that the wing of a pair of miniature flapper aircraft comprises No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, auxiliary beam 7, skin 8 .

Taking the left wing as an example, during implementation:

No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, and auxiliary beam 7 are carbon fiber reinforced resin matrix composite rods, and the aspect ratio is taken as 6, that is The chord length of the No. 1 rib 1 is 33% of the length of the main girder 6 . The main beam 6 is straight, and the front edge points of the five wing ribs 1-5 are fixed on the main beam 6. Starting from the root of the main beam 6, it occupies 4/5 of the spanwise length of the main beam 6. No. 1 ribs 1 and 2 No. 2 rib 2 and No. 3 rib 3 are perpendicular to the main beam, No. 4 rib 4 and No. 5 rib 5 form an acute angle with the direction of the tip of the main beam, and the angles are 80° and 65° respectively. The chord lengths of No. 1 rib 1, No. 2 rib 2, and No. 3 rib 3 are equal, and the chord lengths of No. 4 rib 4 and No. 5 rib 5 decrease in turn, and they are all shorter than No. 1 rib 1, respectively. The chord length of No. 1 rib 1 90% and 70%. The airfoils of No. 1 rib 1, No. 2 rib 2 and No. 3 rib 3 are thin airfoils, No. 5 rib 5 is straight, and No. 4 rib 4 is the transitional airfoil of the former two. The auxiliary beam 7 is arc-shaped, and the outer edge point is fixed between the end point of the main beam 6 and the No. 5 rib, 5% of the length of the main beam from the outer end point of the main beam, and the root passes through the second half of the No. 1 rib 1 to the rear edge point At the position of 85% of the chord length, the radian ensures that the auxiliary beam 7 is in contact with the corresponding positions of the five wing ribs. The fixation between the main beam 6 and the wing ribs 1-5, and between the wing ribs 1-5 and the auxiliary beam 7 is all bound by aramid fibers soaked in glue. Both the main beam 6 and the auxiliary beam 7 extend a certain length at the root of the wing so as to be connected with the fuselage. So far, the wing frame composed of the main beam 6, the auxiliary beam 7 and the ribs 1-5 is completed, the polyester skin 8 is covered on the frame, and the adhesive is bonded to the wing frame to form a complete wing.

The composition of the right wing is the same as that of the left wing.

The wing made in embodiment 2 has a small amount of elastic deformation when fluttering, and can generate greater aerodynamic lift.

Example 3:

The present embodiment is that the wing of a pair of miniature flapper aircraft comprises No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, auxiliary beam 7, skin 8 .

Taking the left wing as an example, during implementation:

No. 1 rib 1, No. 2 rib 2, No. 3 rib 3, No. 4 rib 4, No. 5 rib 5, main beam 6, and auxiliary beam 7 are carbon fiber reinforced resin matrix composite rods, and the aspect ratio is taken as 7, that is The chord length of the No. 1 rib 1 is 28% of the length of the main girder 6 . The main beam 6 is straight, and the front edge points of the five wing ribs 1-5 are fixed on the main beam 6. Starting from the root of the main beam 6, it occupies 73% of the spanwise length of the main beam 6. No. 1 ribs 1 and No. 2 ribs No. 2 and No. 3 ribs 3 are perpendicular to the main beam, No. 4 ribs 4 and No. 5 ribs 5 form an acute angle with the direction of the tip of the main beam, and the angles are 78° and 63° respectively. The chord lengths of No. 1 rib 1, No. 2 rib 2, and No. 3 rib 3 are equal, and the chord lengths of No. 4 rib 4 and No. 5 rib 5 decrease in turn, and they are all shorter than No. 1 rib 1, respectively. The chord length of No. 1 rib 1 95% and 73%. The airfoils of No. 1 rib 1, No. 2 rib 2 and No. 3 rib 3 are thin airfoils, No. 5 rib 5 is straight, and No. 4 rib 4 is the transitional airfoil of the former two. The auxiliary beam 7 is arc-shaped, and the outer edge point is fixed between the end point of the main beam 6 and the No. 5 rib, 10.5% of the length of the main beam from the outer end point of the main beam, and the root passes through the second half of the No. 1 rib 1 to the rear edge point 78% of the chord length position, the radian ensures that the auxiliary beam 7 is in contact with the corresponding positions of the five wing ribs. The fixation between the main beam 6 and the wing ribs 1-5, and between the wing ribs 1-5 and the auxiliary beam 7 is all bound by aramid fibers soaked in glue. Both the main beam 6 and the auxiliary beam 7 extend a certain length at the root of the wing so as to be connected with the fuselage. So far, the wing frame composed of the main beam 6, the auxiliary beam 7 and the ribs 1-5 is completed, the polyester skin 8 is covered on the frame, and the adhesive is bonded to the wing frame to form a complete wing.

The composition of the right wing is the same as that of the left wing.

When the wing made in embodiment 3 flutters, it obtains a good combination of aerodynamic lift and thrust, and has outstanding comprehensive performance.

Claims (8)

1. the wing of a miniature ornithopter comprises girder, floor stringer, rib and covering, it is characterized in that: said girder is straight, and the leading edge point of five ribs is fixed on the girder, is begun by the girder root, occupies the girder exhibition to 2/3rds to 4/5ths of length; No. 1 rib, No. 2 ribs and No. 3 ribs are perpendicular to girder, and No. 4 ribs and No. 5 ribs and girder taper direction acutangulate; No. 1 rib, No. 2 ribs and No. 3 rib chord lengths equate; The chord length of No. 4 ribs and No. 5 ribs reduces successively, all is shorter than rib No. 1, and the wing planform of formation is a wing tip trailing edge corner cut; Floor stringer is curved; The outer rim point is fixed on the girder between girder taper end points and No. 5 rib trailing edge points, and root is through number rib latter half, and its radian guarantees that floor stringer contacts with five rib correspondence positions and fixes; Girder, floor stringer and rib constitute the wing structure framework, and the covering of above framework, fitting forms complete wing.

2. the wing of miniature ornithopter according to claim 1 is characterized in that: the aspect ratio 6～8 of described wingpiston.

3. the wing of miniature ornithopter according to claim 1; It is characterized in that: the leading edge of described wingpiston is that girder line of centers, root are No. 1 rib string of a musical instrument; Trailing edge root one side is the straight line that the trailing edge point of No. 1 rib and No. 3 ribs constitutes; Part from No. 3 ribs to the girder taper is the quadratic spline curve; It is tangent with straight line of No. 1 ribs and No. 3 rib trailing edge point formations at No. 3 rib trailing edge points, connects No. 4 rib trailing edge points, No. 5 rib trailing edge points and girder taper end points successively.

4. the wing of miniature ornithopter according to claim 1, it is characterized in that: the aerofoil profile of described No. 1 rib, No. 2 ribs and No. 3 ribs all adopts thin airfoil, and No. 5 rib is straight, and No. 4 ribs are the above two transition aerofoil profile.

5. the wing of miniature ornithopter according to claim 1, it is characterized in that: the chord length of described No. 4 ribs is the 90%-97% of No. 1 rib chord length, the 70%-80% of No. 1 rib chord length of chord length of No. 5 ribs.

6. the wing of miniature ornithopter according to claim 1, it is characterized in that: described No. 4 ribs and the girder angle of direction laterally are 70-80 °, the angle of No. 5 ribs and girder lateral direction is 55-65 °.

7. the wing of miniature ornithopter according to claim 1, it is characterized in that: the leading edge point of described all ribs and trailing edge point all are positioned at the wing reference plane.

8. the wing of miniature ornithopter according to claim 1, it is characterized in that: the contact point of described floor stringer and No. 1 rib is positioned at rib 75%-85% chord length position No. 1.

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