CN109552622A

CN109552622A - A kind of aircraft

Info

Publication number: CN109552622A
Application number: CN201910074210.8A
Authority: CN
Inventors: 李铁
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-01-25
Filing date: 2019-01-25
Publication date: 2019-04-02
Also published as: JP2022517844A; WO2020151479A1

Abstract

The present invention provides a kind of aircraft, are related to airmanship field.The characteristics of aircraft, is: including by swinging up and down or vibrating the one-way ventilating structure for being distributed with and only flowing to above fin for air-flow below fin on fin to provide the fin of flying power.In this way, air-flow is only capable of flowing to the another side of fin from the one side of fin in fin during being oscillated or vibrated repeatedly, and then obtain the lift of aircraft flight.

Description

A kind of aircraft

Technical field

The present invention relates to airmanship fields, refer in particular to a kind of aircraft.

Background technique

In the prior art, the flight lift of aircraft leans on the rotation of propeller or jet-propelled combination to have specific substantially The wing of appearance curve is to obtain lift.In addition, there are also the flapping wing structures that structure is complicated but efficiency is extremely low.

Summary of the invention

The technical problems to be solved by the present invention are: providing a kind of novel flight instruments.

In order to solve the above-mentioned technical problem, the invention discloses a kind of aircraft, including by swing up and down or vibrate with The fin of flying power is provided, the one-way ventilating structure only flowed to above fin for air-flow below fin is distributed on fin.

In further embodiment, the one-way ventilating structure includes framework, and the lower surface of framework, which is covered with, prevents air-flow The baffle of framework upper surface is flowed to from framework lower surface, the part of baffle is connected with framework, and the rest part of baffle can be with air-flow And with framework contact free or separate.

In further embodiment, the baffle be light flexible material made of flexible sheets, the part of the baffle with Framework is connected.

In further embodiment, the baffle is made of EVA, non-woven fabrics, class brown paper or film.

In further embodiment, the shape of the baffle is round, rectangle or irregular shape, the shape of the framework It is adapted with baffle, framework can be completely covered in baffle from shape.

In further embodiment, the aircraft further includes a base, and the fin is connected with base, and the fin is whole Body is symmetric relative to base.

In further embodiment, the fin includes minor flap and auxiliary fin, and base, minor flap, auxiliary fin successively connect It connects, is elastic connection between auxiliary fin and minor flap.

In further embodiment, the fin is in circular ring shape, and the base is located at the center point in circular ring shape fin, institute It is concentric with minor flap to state auxiliary fin；

Or the fin is rounded or rectangular, all fins are axisymmetricly distributed in the two sides of the base.

It further include the fuselage sections as main body in further embodiment, the fin is set to body upper, fin One linear motor/Linear internal combustion engine is connected with to provide the driving force that fin is oscillated or vibrated, linear motor/Linear internal combustion engine Axis is vertical with fin and is connected.

In further embodiment, it is connected with sets simultaneously to drag-line, drag-line is connected between end at the middle part of the fin The drive shaft being placed on base, drive shaft can periodical positive and negative rotation and the swings of synchronous drive fin.

The lift unit of existing aircraft is changed to the fin with specific structure, passes through the wing by the aircraft in the present invention The one-way ventilating structure of on piece distribution, so that the fin, when swinging up and down or vibrating repeatedly up and down, air-flow only can be unidirectional Pass through, and then can get enough lift.

Detailed description of the invention

Specific structure of the invention is described in detail with reference to the accompanying drawing

Fig. 1 is a kind of tab construction top view of aircraft of the present invention；

Fig. 2 is the front view of an aircraft；

Fig. 3 is the one-way ventilating structure closed state schematic diagram of Fig. 1 fin；

Fig. 4 is the one-way ventilating structure opening state schematic diagram of Fig. 1 fin；

Fig. 5 is the tab construction top view of another aircraft of the present invention；

Fig. 6 is the tab construction top view of another aircraft of the invention；

Fig. 7 is the tab construction top view of another aircraft of the invention；

Fig. 8 is aircraft swinging structure schematic diagram；

Fig. 9-12 is that aircraft is oscillated or vibrated structural schematic diagram.

In figure, including 10- base, 11- axis, 20- fin, 201- baffle, 202- framework, the side's 21- minor flap, the side 22- are auxiliary Fin, the auxiliary fin of 23- degree, 31- circle minor flap, the auxiliary fin of 32- circle, 41- ring minor flap, the auxiliary fin of 42- ring, 50- fuselage, 61- fan minor flap, 71- drag-line, 72- drive shaft, 81- pendulum the wing, 82- drag-line, 83- drive shaft, the longitudinal direction 84- bearing, 91- pendulum the wing, 92- bearing, 93- composite bearing.

Specific embodiment

In order to describe the technical content, the structural feature, the achieved object and the effect of this invention in detail, below in conjunction with embodiment And attached drawing is cooperated to be explained in detail.

The invention discloses a kind of aircraft, swing up and down or are vibrated to provide the fin 20 of flying power including passing through, The one-way ventilating structure for only flowing to 20 lower section of fin above fin 20 for air-flow is distributed on fin 20.That is, by existing flight The lift unit of device (such as helicopter, flapping-wing aircraft) is changed to the fin 20 with specific structure, passes through the list being distributed on fin 20 To ventilating structure, so that the fin 20 when being oscillated or vibrated repeatedly up and down, air-flow only can unidirectionally pass through, and then can get Enough lift.

In conjunction with Fig. 3, Fig. 4, the one-way ventilating structure includes framework 202, and the lower surface of framework 202, which is covered with, prevents air-flow The baffle 201 of 202 upper surface of framework is flowed to from 202 lower surface of framework, the part of baffle 201 is connected with framework 202, baffle 201 Rest part can contact or separate with framework 202 with air-flow.Also i other words, when fin 20 is oscillated or vibrated downwards, root According to active force and reaction force, air-flow can be to 201 1 upward power of baffle on fin 20, so that baffle 201 can be with It is tightly bonded upper frame body 202, air-flow can not be passed through from framework 202.And when fin 20 is swung up or vibrates, according to work Firmly and reaction force, air-flow can be to 201 1 downward power of baffle on fin 20, so that baffle 201 can be with frame Body 202 separates, and air-flow can be passed through from framework 202.In this way, fin 20 is during being oscillated or vibrated repeatedly, (other conditions In identical, close situation) air drag (reaction force, support force) that is downwardly and upwardly subject to is different, obtain lift.

In addition, the baffle is flexible sheets made of light flexible material, part and the framework of the baffle are fixedly linked. And baffle is preferably that EVA, non-woven fabrics, class brown paper or film are made, and more preferably Du Pont's paper.As aircraft, used in Structural material, guarantee material intensity meet the requirements under the premise of, can be made of light material, can so be subtracted as far as possible The gravity of few aircraft itself, reduces power needed for flying and energy consumption.

In addition, the shape of the baffle is circle, rectangle, sector, polygon or irregular shape etc., more preferably For rectangle, but also be designed according to the shape of fin entirety, can be distributed on guarantee fin it is enough by Framework and baffle are formed by one-way ventilating structure.The shape of the framework is adapted with baffle, and baffle can be complete from shape Framework is covered, only can cover all framework in baffle shape, just can guarantee complete as much as possible when baffle is bonded with framework Air-flow is hindered to pass through from framework.

In one embodiment, the aircraft further includes a base, and the fin is connected with base, and the fin is whole Body is symmetric relative to base.Base is connected with fin, is for the ease of driving fin swinging up and down relative to base Or vibration.It can be set on base that fin is connected and the driving device for swinging up and down or vibrating fin can be driven, it can also Manpower, or auxiliary manpower realization swing up and down or vibrate.And the symmetric design of fin, then it is in order to enable being moved provided by fin Power or lift distribution are uniform.

In addition, the fin includes minor flap and auxiliary fin, minor flap is directly connect with the base, auxiliary fin and main wing Elastic connection between piece, such as spring can be used or elastic piece elastic component is attached, from the center to being followed successively by base, main wing outside Piece, auxiliary fin, auxiliary fin multistage can be arranged.When minor flap is oscillated or vibrated rising, auxiliary fin asynchronous can be swung, with slow Solve the vibration of aircraft.

In conjunction with Fig. 6, the fin is integrally in circular ring shape, and the base is located at the center point in circular ring shape fin, described auxiliary Fin is concentric with minor flap.I.e. from the center to outer, it is followed successively by base 10, ring minor flap 41, minor flaps 42.Base 10 and ring master Fin 41 connects, and is connected between ring minor flap 41 and the auxiliary fin 42 of ring by elastic component, such as spring or elastic slice.

Combined with Figure 1 and Figure 2, in one embodiment, the fin is square, and all fins are axisymmetricly distributed in institute State the two sides of base.I.e. from the center to outer, it is followed successively by base 10, square minor flap 21, the auxiliary fin 22 in side, the auxiliary fin 23 of degree, machine Seat 10 is connect with square minor flap 21, is connected in elastic connection, such as spring between the auxiliary fin 22 in side and square minor flap 21, the auxiliary fin 23 of degree Or elastic slice.Certainly, it can also continue to that greater number of auxiliary fin is arranged to outer in the auxiliary fin 23 of degree.

In conjunction with Fig. 5, in one embodiment, the fin is rounded, and all fins are axisymmetricly distributed in the machine The two sides of seat.Base 10 is connect with circle minor flap 31, and circle minor flap 31 and auxiliary 32 elastic connection of fin of circle such as pass through spring or bullet Piece is connected.

In conjunction with Fig. 7, in one embodiment, the fin is fan-shaped, and fans 61 entirety of minor flap and be symmetric, and Both the symmetrical wing 1, the wing 3 can be synchronized to drive, i.e., be oscillated or vibrated upwards or downwards simultaneously simultaneously.And symmetrical The wing 2, the wing 4 can be synchronized to drive, i.e., the two is oscillated or vibrated upwards or downwards simultaneously simultaneously.

In conjunction with Fig. 2, in one embodiment, aircraft further includes 50 part of fuselage as main body, this should be calculated It is the basic structure for constituting aircraft integrality, belongs to the justice that should have, the fin is set to 50 top of fuselage, and fin is also connected with There is one linear motor/Linear internal combustion engine to provide the driving force that fin is oscillated or vibrated relative to base, in linear motor/straight line The axis of combustion engine is vertically connected with fin.Linear motor/Linear internal combustion engine, in the course of work, corresponding line shaft be along from Body axial cyclic translates back and forth repeatedly, is connected by the line shaft with fin, and this axial reciprocating of line shaft may make to move It is dynamic to be converted into being oscillated or vibrated repeatedly for fin, form flying power.

In conjunction with Fig. 8, in one embodiment, it is fixedly connected between fin midpoint and endpoint using 71 one end of drag-line Some position, while drag-line 71 is also connected with the drive shaft 72 being set on base 10, and can be real under the action of drive shaft 72 The relaxation and tension of existing drag-line 71 are put repeatedly when drive shaft 72 periodically drives drag-line 71 and be further driven to fin along reversion It is dynamic, to obtain the lift of flight.And drag-line 71 herein is preferably cable wire.Drive shaft herein can be motor drive Dynamic, internal combustion engine driving, is also possible to manpower driving.

In conjunction with Figure 12, in one embodiment, for the swing for realizing fin, it is also possible to put the wing 91 and is connected to one and can turn On the outer ring of dynamic bearing 92, the axis of bearing 92 is horizontally disposed, specific to Figure 12, similar can be considered the axis of bearing 92 The vertical paper setting of line, such bearing 92 can be in clockwise or counterclockwise, 92 outer ring of bearing is also connected with one laterally on paper The composite bearing 93 vertically vertically fixed, composite bearing 93 are sheathed on the axis 11 on base 10.In this way, composite bearing 93 Place can along the periodically sliding back and forth of about 11 axis, and can the swing for putting the wing 91 that is connected with bearing 92 of synchronous drive, at bearing 92 It is also similar to that a moving fulcrum, makes to put the wing 91 with the branch spot wobble.

In conjunction with Fig. 9, in one embodiment, for the vibration for realizing fin, it is also possible to flutter 81 and connects a drag-line 82, while drag-line 82 is connected to drive shaft 83, and can be realized in 81 periodicity of flutter by the periodical positive and negative rotation of drive shaft 83 Lower swing.

In conjunction with Figure 10 and Figure 11, in one embodiment, for the vibration for realizing fin, it is also possible to the connection of flutter 81 Longitudinal bearing 84, meanwhile, 84 sets of longitudinal bearing on the axis 11 being arranged on base 10, so as to pass through 84 edge of longitudinal bearing Axial periodicity move repeatedly and realize swinging up and down for flutter 81.

Aircraft in the present invention, fuselage, base and loading (including driver, similarly hereinafter) quality are greater than wing quality, greatly More satisfactory again in wing mass number, when wing is swung relative to base, when wing is to lower swing, wing is downwards by larger (relative to upwards) resistance, for base in opposite directions by upward power, fuselage, base and loading stress are more than gravity, fuselage, base and loading It moves up, is moving up the later half period, waggle transfers upwards, because of wing structure, to remove gravity etc., be swung up resistance Power is less, and the energy needed is less, and fuselage, base and the kinetic energy of loading subtract gravity acting, and rest part offsets the upward institute of wing The acting needed, resets wing.And so on, realization rises overally.On the basis of the present invention, it can be arranged and pass according to traditional technology Dynamic device, can adjust part or all of power wing angle, to control heading etc..Meanwhile appropriate figure and physical efficiency personage, also Wing can be manipulated by mechanical mechanism to swing, realize human-powered flight.Also in combination with some existing human-powered flight's technologies and material Expect skill upgrading, reduces and realize human-powered flight in the case where requiring figure and physical efficiency.Furthermore, it may also be used for aerodone wing, Promote its in-flight lift.

It should be noted that herein, up, down, left, right, before and after only represents its relative position without indicating its absolute position It sets.The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize explanation of the invention Equivalent structure or equivalent flow shift made by book and accompanying drawing content is applied directly or indirectly in other relevant technology necks Domain is included within the scope of the present invention.

Claims

1. a kind of aircraft, it is characterised in that: including by swinging up and down or vibrating to provide the fin of flying power, on fin The one-way ventilating structure only flowed to above fin for air-flow below fin is distributed with.

2. aircraft as described in claim 1, it is characterised in that: the one-way ventilating structure includes framework, the following table of framework Face is covered with the baffle for preventing air-flow from flowing to framework upper surface from framework lower surface, and the part of baffle is connected with framework, baffle Rest part can with air-flow and with framework contact free or separate.

3. aircraft as claimed in claim 2, it is characterised in that: the baffle is flexible sheets made of light flexible material, The part of the baffle is connected with framework.

4. aircraft as claimed in claim 3, it is characterised in that: the baffle is by EVA, non-woven fabrics, class brown paper or film It is made.

5. aircraft as claimed in claim 3, it is characterised in that: the shape of the baffle is round, rectangle or irregular shape The shape of shape, the framework is adapted with baffle, and framework can be completely covered in baffle from shape.

6. aircraft as described in any one in claim 1-5, it is characterised in that: the aircraft further includes a base, described Fin is connected with base, and the fin is integrally symmetric relative to base.

7. aircraft as claimed in claim 6, it is characterised in that: the fin includes minor flap and auxiliary fin, base, main wing Piece, auxiliary fin are sequentially connected, and are elastic connection between auxiliary fin and minor flap.

8. aircraft as claimed in claim 7, it is characterised in that: the fin is in circular ring shape, and it is in annulus that the base, which is located at, The center point of shape fin, the auxiliary fin and minor flap are concentric；

9. aircraft as claimed in claim 6, it is characterised in that: further include the fuselage sections as main body, the fin is set It is placed in body upper, fin is connected with one linear motor/Linear internal combustion engine to provide the driving force that fin is oscillated or vibrated, straight line Motor/Linear internal combustion engine axis is vertical with fin and is connected.

10. aircraft as claimed in claim 6, it is characterised in that: at the middle part of the fin to being connected with drag-line between end, Drag-line is connected with the drive shaft being set on base simultaneously, and drive shaft can periodical positive and negative rotation and the swing of synchronous drive fin.