CN204527636U

CN204527636U - A kind of novel cross flapping wing aircraft

Info

Publication number: CN204527636U
Application number: CN201520216209.1U
Authority: CN
Inventors: 赵永亮; 周超英; 彭月辉; 谢鹏
Original assignee: Shenzhen Graduate School Harbin Institute of Technology
Current assignee: Shenzhen Graduate School Harbin Institute of Technology
Priority date: 2015-04-10
Filing date: 2015-04-10
Publication date: 2015-08-05
Anticipated expiration: 2025-04-10

Abstract

The utility model provides a kind of novel cross flapping wing aircraft, it is characterized in that: it comprises four wings, four wing composition criss-cross flapping wings, each wing adopts slider-crank mechanism, each wing comprises fork, crank, frame, primary speed-down gear, motor, clutch shaft bearing, the second bearing, and described primary speed-down gear comprises the first gear and the second gear.The utility model utilizes the crank block structure improved to realize fluttering of wing and provide lift, and becomes cross and be arranged symmetrically with, and makes flapping wing aircraft can realize the flying in multi-direction of pitching roll all around, and can realize the function of hovering.

Description

A kind of novel cross flapping wing aircraft

Technical field

The utility model relates to aircraft field, particularly relates to cross flapping wing aircraft.

Background technology

The maneuverability of flapping wing aircraft, good concealment, in anti-terrorism task, close to terrorist, can monitor it and even attacks, and effectively reduces the injures and deaths of hostage.Flapping wing aircraft, in accident process, is understood express highway, the condition of a disaster, forest fire protection in real time, the collection etc. of noxious gas and smog, and near airports expulsion flying bird, ensures that the safety of rising and falling of aircraft is all widely used.

Existing flapping wing aircraft can realize wing single degree of freedom and flutter, and heading is fixed, or wing can roll over exhibition, in upper process of flutterring, alleviate air resistance.Mostly be dipteron symmetrical structure, mechanism mostly is single crank double rocker mechanism or double crank double rocker mechanism.The present invention can realize the hovering of flapping wing aircraft and pitching (front and back), roll (left and right) flight, is more suitable for carrying out the hidden tracking of target.

Because the wing design of most of flapping wing aircraft has the angle of attack, so be difficult to the hovering realizing aircraft.Single flapping wing aircraft can not be realized there is the ability of carrying out pitching, roll, hovering campaign simultaneously.No matter be single crank double rocker mechanism or double crank double rocker mechanism, all can occur that wing is fluttered nonsynchronous problem.

Existing flapping wing aircraft mostly is single to wing, and lift is little, and can not realize the hovering of aircraft, and heading is single.

Utility model content

In order to solve problem in prior art, the utility model provides a kind of novel cross flapping wing aircraft, it comprises four wings, four wing composition criss-cross flapping wings, each wing adopts slider-crank mechanism, each wing comprises fork, crank, frame, primary speed-down gear, motor, clutch shaft bearing, the second bearing, and described primary speed-down gear comprises the first gear and the second gear;

Electric machine rotation drives the first gear, first gear driven second gear 60, second gear driven crank, crank first end is provided with clutch shaft bearing, crank second end is arranged in the draw-in groove of fork, by crank, the circular-rotation of the second gear is converted to the horizontal hunting of fork, the action that the level realizing wing is fluttered.

As further improvement of the utility model, the end of described fork is connected with swinging mounting by the second bearing.

As further improvement of the utility model, described crank first end is arranged on the center position of described second gear.

As further improvement of the utility model, the length of the outside radius of described second gear is 4 to 10 times of the length of described first gear outside radius.

As further improvement of the utility model, the length of described first gear outside radius be 2 to 5 times of the length of the inside radius of described second gear.

The beneficial effects of the utility model are:

The utility model utilizes the crank block structure improved to realize fluttering of wing and provide lift, and becomes cross and be arranged symmetrically with, and makes flapping wing aircraft can realize the flying in multi-direction of pitching roll all around, and can realize the function of hovering.

Accompanying drawing explanation

Fig. 1 is the utility model cross flapping wing aircraft plan structure schematic diagram;

Fig. 2 is the cross flapping wing aircraft block diagram of the utility model;

Fig. 3 is the cross flapping wing aircraft of the utility model single wing structural blast figure;

Fig. 4 is the utility model cross flapping wing aircraft structure cutaway view;

Fig. 5 is the B-B section-drawing in Fig. 4.

Detailed description of the invention

Below in conjunction with accompanying drawing, the utility model is described further.

As shown in Figures 1 to 5, aircraft with flapping wings adopts cruciform symmetry structure, can realize the actions such as lifting hovering, pitching, roll.When with the first fork 101 direction for head time: roll to the second fork 102 or the 4th fork 104 direction flight, pitching namely to the first fork 101 or the 3rd fork 103 direction flight.

As Fig. 1, when with the first fork 101 direction for head time: when four fork hunting frequencies increase simultaneously time aircraft rise, time frequency reduces simultaneously aircraft decline, realize the hovering of aircraft, height-lock control.

When the first fork 101 hunting frequency reduces, the 3rd fork 103 hunting frequency increases, and aircraft will pitching flight forward, and contrary aircraft will fly backward in pitching.

When the second fork 102 hunting frequency reduces, the 4th fork 104 hunting frequency increases, and flight will be flown left in roll, and contrary aircraft will fly to the right in roll.

Each wing adopts the slider-crank mechanism redesigning improvement to realize.As Fig. 3, each wing comprises motor 500, primary speed-down gear (comprising the first gear 400 and the second gear 600), crank 200, clutch shaft bearing 800, fork 100, second bearing 700 and frame 300.

Because fork 100 is in swing process, the fork be arranged symmetrically with can produce certain anti-twisted moment, makes aircraft off the course.In order to avoid anti-twisted moment is on the impact of aircraft, adopts primary speed-down mechanism, the hunting frequency of fork will be made like this to increase, thus reduce the impact of anti-twisted moment.

Because it is slightly low that slider-crank mechanism efficiency compares quadric linkage, so adopt clutch shaft bearing 800 and the second bearing 700 to reduce friction, replace slide block with clutch shaft bearing 800 simultaneously, cliding friction is become the efficiency that friction of rolling improves aircraft further.

As Fig. 4 and Fig. 5, electric machine rotation drives first stage decelerator gear, and the second gear 600 drives crank 200 to rotate.Clutch shaft bearing 800 is equipped with in crank 200 front end, clutch shaft bearing 800 is arranged in the draw-in groove of fork 100, crank 200 converts circular-rotation the horizontal hunting of fork 100 to, the action that the level realizing wing is fluttered by clutch shaft bearing 800 horizontal rolling in the draw-in groove of fork 100.

Above content is in conjunction with concrete preferred implementation further detailed description of the utility model, can not assert that concrete enforcement of the present utility model is confined to these explanations.For the utility model person of an ordinary skill in the technical field, without departing from the concept of the premise utility, some simple deduction or replace can also be made, all should be considered as belonging to protection domain of the present utility model.

Claims

1. a novel cross flapping wing aircraft, it is characterized in that: it comprises four wings, four wing composition criss-cross flapping wings, each wing adopts slider-crank mechanism, each wing comprises fork (100), crank (200), frame (300), primary speed-down gear, motor (500), clutch shaft bearing (800), the second bearing (700), and described primary speed-down gear comprises the first gear (400) and the second gear (600);

Motor (500) rotates drive first gear (400), first gear (400) drives the second gear 60, second gear (600) drives crank (200) to rotate, crank (200) first end is provided with clutch shaft bearing (800), crank (200) second end is arranged in the draw-in groove of fork (100), by crank (200), the circular-rotation of the second gear (600) is converted to the horizontal hunting of fork (100), the action that the level realizing wing is fluttered.

2. the novel cross flapping wing aircraft of one according to claim 1, is characterized in that: the end of described fork (100) is connected with swinging mounting (900) by the second bearing (700).

3. the novel cross flapping wing aircraft of one according to claim 1, is characterized in that: described crank (200) first end is arranged on the center position of described second gear (600).

4. the novel cross flapping wing aircraft of one according to claim 1, is characterized in that: the length of the outside radius of described second gear (600) is 4 to 10 times of the length of described first gear (400) outside radius.

5. the novel cross flapping wing aircraft of one according to claim 1, is characterized in that: the length of described first gear (400) outside radius be 2 to 5 times of the length of the inside radius of described second gear (600).