CN101513933A

CN101513933A - Circulating flapping wing aerial vehicle

Info

Publication number: CN101513933A
Application number: CNA2009100666670A
Authority: CN
Inventors: 章静
Original assignee: Individual
Current assignee: Individual
Priority date: 2009-03-23
Filing date: 2009-03-23
Publication date: 2009-08-26
Anticipated expiration: 2029-03-23
Also published as: CN101513933B

Abstract

The invention provides a circulating flapping wing aerial vehicle, belonging to the technical field of mechanical manufacture. The aerial vehicle comprises a body, control mechanisms, a power device, an output shaft and a wing plate, wherein the power device is arranged on the body; two sides of the body are symmetrically provided with the control mechanism; the control mechanism comprises a frame, a main gear, a transmission gear, a wing gear and a rudder lever; the main gear is arranged in the middle of the frame, and is engaged with at least two symmetric transmission gears; each transmission gear is engaged with the wing gear; the wing plate is fixed with the axle center of the wing gear through a wing shaft; the power device is fixed with the frame through an output shaft; the output shaft is in rolling connection with the axle center of the main gear, and is sleeved with a shaft housing; and the rudder lever is connected with the main gear through the shaft housing. When the aerial vehicle is operated, the power device is started to lead the wing plate to revolve on the main gear and rotate in reverse direction through the axle center of the wing gear to swat air at different windward angles so as to form an asymmetric air flow, thereby realizing circulating lift-off flapping wing of the aerial vehicle.

Description

Circulating flapping wing aerial vehicle

Technical field:

The invention belongs to machinery manufacturing technology field, the present invention relates to a kind of aircraft specifically.

Background technology:

Human existing aircraft mainly is to rely on screw propeller and fixed-wing to produce aerodynamic force and lift, and its flight theory and technical scheme mainly are the pneumatic mode based on the Magnus theory.But in fact, also have a kind of aerodynamic force pattern often to be left in the basket, that is exactly the flapping wing pneumatic mode of equally freely circling in the air and being relied on to birds, insect, bat.Scientific research shows, the flight efficiency of birds, insect, bat is higher than human existing airmanship far away, they can consume minimum energy and fly higher fartherly, prove that thus the flapping wing pneumatic mode is better than the pneumatic mode based on the Magnus theory under certain condition greatly.Since ancient times, the human step that never stops the research and the exploration of flapping wing aircraft, but owing to fail from understand grasping the flight mechanism of birds in essence, and only be imitation, thereby the research of flapping-wing aircraft is never had considerable progress the simple blindness of the surface phenomena of birds flight.Its reason is the deficiency and the defective of also having imitated the birds flights in imitation birds airmanship, such as, birds have also consumed certain energy when lifting wing last, having produced air resistance is negative lift, offset raising force, and the power consumption of the mechanical fatigue that in the flapping wing process, produces, inertia or the like.

For many years, the inventor is devoted to the research of flapping wing pneumatic mode and flapping wing aircraft and exploration always, by to deep observation, analysis and the research of birds, insect, bat flight behavior and through repeatedly designing, improve and repeatedly model test, its purpose will be invented a kind of flapping wing pneumatic mode, absorption birds, insect and bat flight strong point utilized exactly, abandon its defective and deficiency, only the circulating flapping wing aerial vehicle of air is swatted in circulation downwards.The patent family that I had once invented in 2007 and had been granted patent by State Patent Office, name are called a kind of wheel wing that can lifting flight, and the patent No. is 200720094807.1.

Summary of the invention:

The technical problem to be solved in the present invention is to disclose a kind of circulating flapping wing aerial vehicle that can effectively improve the aircraft pneumatic efficiency.

Aircraft of the present invention is by comprising body, control mechanism, engine installation, output shaft and wing plate constitute, engine installation is contained on the body, there is the control mechanism of symmetry the body both sides, control mechanism is by framework, main gear, transmission gear, wing gear and rudder stock constitute, main gear is contained in the midway location of framework, the transmission gear and the gear that have two symmetries at least, transmission gear is contained on the framework, each transmission gear is connected with a wing gear mesh respectively again, wing gear is contained on the framework, wing plate is captiveed joint with wing gear axis by wing axle, and engine installation is connected with frame fixation by output shaft, and output shaft is connected with the rolling of main gear axle center, be with axle sleeve on the output shaft, rudder stock connects main gear by axle sleeve, and between 65 degree, the revolution ratio of wing gear and main gear is 1: 2 to the crossing angle of wing axle and output shaft at 15 degree.

During operation, start engine installation, make wing plate around the main gear revolution and by the rotation of wing gear axis reversing sense, swat air and form asymmetric air-flow with the difference angle of facining the wind, realize the circulating flapping wing of aircraft lift-off, adjust rudder stock,, can adjust maximum 90 degree of the wing plate position at angle down with the wind by gear transmission.

Experiment shows, because wing plate is in the rotation that also can do deceleration 1/2nd around the main gear revolution, therefore, make the wing plate regularly can reverses direction in revolution, promptly reached maximization when wing plate facing the wind angle and the air resistance of wing plate that circulate when rotating; And when the wing plate circulation was upwards rotated, the angle down with the wind of wing plate and air resistance had reached and have minimized, thereby had produced asymmetric air-flow vertically downward, and its antagonistic force is realized the rising of aircraft.

The optimized angle that intersects of wing axle and engine installation output shaft is between 25 degree are spent to 55.

The best angle that intersects of wing axle and engine installation output shaft is 45 degree.

In order to make aircraft held stationary in flight course, anti-torsion balance bar is housed at the head of body.

As shown in Figure 3, wing plate is being done the process that produces the reversing sense rotation when rotating counterclockwise and change with the angle that facings the wind of main gear tangent line.When wing plate rotates through D, E, F point, its angle maximum of facining the wind, this kind situation is equivalent to birds, bat and swats air downwards, and the angle minimum of when wing plate upwards rotates through H, A, B point, facining the wind, even be 0 degree, this kind situation is similar to the aviation expert bat and upwards lifts wing and dwindle wind area (in fact, this kind solution has surmounted bat), producing thus is the asymmetric air-flow of gravity direction vertically downward, and its antagonistic force has been realized the aircraft rising.And when wing plate process C, G point, all doing the parallel transverse motion approaching in the angle down with the wind with horizontal surface with 45 degree, also produced certain lift, this kind situation is equivalent to swat wing before and after the big emperor honeybee, though the angle of facining the wind is bigger, and can't stall, generation is converted into lift than maelstrom.As shown in Figure 4, the curve of the direction that wing plate rotates, position and the angle change procedure that facings the wind has also illustrated the angle maximum of facining the wind downwards, the angle minimum of facining the wind when wing plate upwards changes when wing plate changes.

Outside body, the control mechanisms that two symmetries are installed when the high speed revolution flapping wing, in below produce the interflow, strengthened the density of air of middle below, produced lift, and increased the stability of aircraft.

By the adjusting control rudder stock, the facing the wind position at angle of maximum 90 degree when changing wing plate and swatting air can change the direction of asymmetric air-flow, thereby realizes advancing or retreating of aircraft.As shown in Figure 5.When the control rudder stock facings the wind angle E point when adjusting downwards with maximum 90 degree, asymmetric air-flow action direction changes, promptly by vertical downward direction transfer to the lower right to, its antagonistic force has realized that aircraft also travels, and just flies forward left in rising.

As shown in Figure 6, maximum is facingd the wind angle 90 degree E points when adjusting upward when adjusting rudder stock, asymmetric air-flow action direction by transfer to vertically downward the lower left to, its antagonistic force also falls back when having realized the aircraft rising backward.

When two groups of control mechanisms during by a driving engine coaxial drive, adjust wherein maximum 90 degree of the side control mechanism wing plate position, angle that facings the wind, because the asymmetric air flow line of aircraft one side changes, can realize that aircraft turns to.

When two groups of flapping wing mechanisms during by engine drive independently, improve or reduce the wherein rotating speed of one group of flapping wing mechanism, also can realize turning to of aircraft.

Aircraft of the present invention has reached the imitation of birds, insect, bat and has surmounted, promptly by the flapping wing of the creationary circular movement that is designed to circulate of flapping wing up and down, improved the aircraft pneumatic efficiency greatly, realized the lifting of aircraft original place, hovered, advanced, fallen back, turned to, safety, stability and the alerting ability of aircraft have been improved, also can be used as underwater scooter, low cost of manufacture is widely used.

Description of drawings:

Fig. 1 is a scheme drawing of the present invention;

Fig. 2 is the cutaway view of control mechanism part;

Wing plate motion state diagram when Fig. 3 is the aircraft uphill process;

Wing plate stress curve figure when Fig. 4 is the aircraft uphill process;

Wing plate motion state diagram when Fig. 5 advances process for aircraft;

Wing plate motion state diagram when Fig. 6 is the aircraft fallback procedures.

The specific embodiment:

Body 1 of the present invention, control mechanism 2, engine installation 3, output shaft 4 and wing plate 5 constitute, engine installation 3 is contained on the body 1, there is the control mechanism 2 of symmetry body 1 both sides, control mechanism 2 is by framework 6, main gear 7, transmission gear 8, wing gear 9 and rudder stock 11 constitute, main gear 7 is contained in the midway location of framework 6, transmission gear 8 and main gear 7 engagements that two symmetries are arranged, transmission gear 8 is contained on the framework 6, each transmission gear 8 is connected with a joggle with a wing gear 9 respectively again, wing gear 9 is contained on the framework 6, wing plate 5 is captiveed joint with wing gear 9 axle center by wing axle 10, engine installation 3 is captiveed joint with framework 6 by output shaft 4, and output shaft 4 rolls with main gear 7 axle center and is connected, be with axle sleeve 12 on the output shaft 4, rudder stock 11 connects main gear 7 by axle sleeve 12, and wing axle 10 is 45 degree with the crossing angle of output shaft 4, wing gear 9 is 1: 2 with the revolution ratio of main gear 7, at the head of body 1 anti-torsion balance bar 13 is housed.

Claims

1, a kind of circulating flapping wing aerial vehicle, it is characterized in that: it is by body, control mechanism, engine installation, output shaft and wing plate constitute, engine installation is contained on the body, there is the control mechanism of symmetry the body both sides, control mechanism is by framework, main gear, transmission gear, wing gear and rudder stock constitute, main gear is contained in the midway location of framework, the transmission gear and the gear that have two symmetries at least, transmission gear is contained on the framework, each transmission gear is connected with a wing gear mesh respectively again, wing gear is contained on the framework, wing plate is captiveed joint with wing gear axis by wing axle, engine installation is connected with frame fixation by output shaft, and output shaft rolls with the main gear axle center and is connected, and is with axle sleeve on the output shaft, and rudder stock connects main gear by axle sleeve, to between 65 degree, the revolution ratio of wing gear and main gear is 1: 2 to the crossing angle of wing axle and output shaft at 15 degree.

2, aircraft according to claim 1 is characterized in that: the angle that intersects of wing axle and engine installation output shaft is between 25 degree are spent to 55.

3, aircraft according to claim 2 is characterized in that: the angle that intersects of wing axle and engine installation output shaft is 45 degree.

4, according to claim 1,2 or 3 described aircraft, it is characterized in that: the head of body is equipped with anti-torsion balance bar.