CN208360498U - One kind is verted double-rotor aerobat - Google Patents
One kind is verted double-rotor aerobat Download PDFInfo
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- CN208360498U CN208360498U CN201821019163.4U CN201821019163U CN208360498U CN 208360498 U CN208360498 U CN 208360498U CN 201821019163 U CN201821019163 U CN 201821019163U CN 208360498 U CN208360498 U CN 208360498U
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Abstract
It verts double-rotor aerobat, including fuselage the utility model discloses one kind, the two sides of the fuselage are symmetrically arranged with fixed-wing, and the tail portion of the fuselage is provided with fixed empennage；The end of each fixed-wing is rotatably equipped with rotor assemblies, is equipped with the component that verts between the fixed-wing and rotor assemblies, is tilted with the rotor for adjusting rotor assemblies facing towards along fuselage front and back for driving rotor assemblies to rotate.The double-rotor aerobat that verts of the utility model has many advantages, such as that structure is simple, route speed is fast and can hover.
Description
Technical field
The utility model relates generally to vehicle technology field, refers in particular to one kind and verts double-rotor aerobat.
Background technique
Currently, small aircraft is used to carry various measuring instruments (such as camera) mostly, aerological sounding or high-altitude are carried out
On object is thrown, it can apply in various fields such as agricultural, detection, meteorological, hazard forecasting and rescues.
Existing aircraft is divided into Fixed Wing AirVehicle and two kinds of rotor craft.Fixed Wing AirVehicle mainly passes through acquisition
Larger initial velocity forms lift in aerofoil and realizes flight, but can not hover, and stability is poor when low speed, be easy because stall and
Air crash, and need biggish ground run distance.In addition Fixed Wing AirVehicle generally uses two methods to be turned to, a kind of pure
It is turned to by vertical tail, one is wing aileron cooperation tailplanes to turn to.Wherein the case where ratio purely is turned to by vertical tail
It is more rare because vertical tail in addition to have control aircraft turn function other than, there are one most important function be just to maintain it is winged
The stabilization of machine, it is impossible to significantly be turned using vertical tail.And wing aileron cooperation tailplane turns to, and is to pass through pair
The lifting of the wing, fuselage is tilted, and is turned round by the effect of centrifugal force, and this mode needs aircraft itself to have inclined effect,
It applies on personal aircraft, will increase the security risk of driver, be not suitable for personal aircraft and use.
Another is rotor craft, and wherein rotor is primarily used to form lift, and flying speed needs by adjusting appearance
State forms lateral resultant force and is just able to achieve, larger so as to cause energy consumption and route speed is lower.In addition rotor craft is big
It is mostly all to realize that attitude of flight vehicle changes by change of flight device engine output, or change blade screw pitch；And it is
Make aircraft smooth flight, when adjusting each flight attitude, needs to accurately calculate revolving speed and the change of engine
The screw pitch of blade, process is cumbersome, is not suitable for flight environment of vehicle complicated and changeable, and still will appear inclination in flight course,
The same security risk for increasing driver.
Utility model content
The technical problems to be solved in the utility model is that for technical problem of the existing technology, this is practical new
Type provides the double-rotor aerobat that verts that a kind of structure is simple, speed is fast and can hover.
In order to solve the above technical problems, the utility model proposes technical solution are as follows:
One kind is verted double-rotor aerobat, including fuselage, and the two sides of the fuselage are symmetrically arranged with fixed-wing, the fuselage
Tail portion be provided with fixed empennage；The end of each fixed-wing is rotatably equipped with rotor assemblies, the fixed-wing and rotor
The component that verts is installed, for driving rotor assemblies to rotate to adjust the rotor of rotor assemblies facing towards before fuselage between component
Back sweep.
As a further improvement of the above technical scheme:
The rotor assemblies include mounting rack, rotor and force piece, and the force piece is installed on the mounting rack, described
The output shaft of force piece is connect with the rotor.
The force piece is internal combustion engine or motor；When the force piece is internal combustion engine, oil is provided on the fuselage
Case carries out fuel feeding to each internal combustion engine for unified；When the force piece is motor, the fuselage is equipped with electric energy unit,
Electric energy is provided to each motor for unified.
The component that verts includes actuator and link mechanism, and one end of the link mechanism is connected with the actuator,
The other end is connected with the rotor assemblies.
The link mechanism includes cursor, first connecting rod and second connecting rod, is fixed in the middle part of the cursor described
On the output shaft of actuator, one end of the first connecting rod and one end of the cursor are hinged, one end of the second connecting rod
Hinged with the other end of the cursor, the other end of the first connecting rod and second connecting rod is hinged on the rotor assemblies
On.
The first connecting rod and second connecting rod are ball head connecting rod, and ball screw is provided in the rotor assemblies, described
Ball head connecting rod and ball screw are cooperatively connected.
The actuator is servo motor or stepper motor or steering engine.
The fixing axle for running through fuselage two sides fixed-wing is provided on the fuselage, the both ends of the fixing axle are arranged with
Bearing is equipped with bearing block in the rotor assemblies, and the bearing is installed in the bearing block.
The bottom of the fuselage is provided with undercarriage.
The rotor includes rotor seat and muti-piece rotary blade, and rotary blade described in muti-piece is evenly distributed on rotor seat.
Compared with the prior art, the advantages of the utility model are:
The double-rotor aerobat that verts of the utility model, by Fixed Wing AirVehicle in conjunction with rotor craft progress depth,
Rotor assemblies are rotatably equipped in the end of fixed-wing, the advantage of Fixed Wing AirVehicle and rotor craft can be gathered, are navigated
Scanning frequency degree is fast, can hover, can be suitably used for flight environment of vehicle complicated and changeable；And structure is simple, is easily achieved；In fixed-wing and respectively
The component that verts is mounted between rotor assemblies, for driving rotor assemblies to rotate so that the direction in rotor face is along the front and back of fuselage
Side's inclination, to realize the adjustment of the various state of flights such as aircraft landing, steering, translation and hovering, in the process, fuselage
Always it is in stable horizontality, guarantees the traffic safety and riding comfort of driver or passenger.
Detailed description of the invention
Fig. 1 is the three-dimensional structure diagram of the utility model.
Fig. 2 is the overlooking structure figure of the utility model.
Fig. 3 is the structural schematic diagram of rotor and the component that verts in the utility model.
Figure label indicates: 1, fuselage；101, fixed-wing；102, empennage；103, fixing axle；2, rotor assemblies；201, pacify
It shelves；202, force piece；203, rotor；3, vert component；301, actuator；302, cursor；303, first connecting rod；304,
Two connecting rods；305, ball screw.
Specific embodiment
The utility model is further described below in conjunction with Figure of description and specific embodiment.
As depicted in figs. 1 and 2, the double-rotor aerobat that verts of the present embodiment, including fuselage 1, the bottom of fuselage 1 are equipped with
Undercarriage (not shown), the two sides of fuselage 1 are symmetrically arranged with fixed-wing 101, and the tail portion of fuselage 1 is provided with fixed empennage
102；The end of each fixed-wing 101 is rotatably equipped with rotor assemblies 2, is fixedly installed between fixed-wing 101 and rotor assemblies 2
Vert component 3, for driving the rotation of rotor assemblies 2 to tilt with the rotor for adjusting rotor assemblies 2 facing towards along 1 front and back of fuselage,
To realize the adjustment of the state of flights such as aircraft landing, steering, translation and hovering.The DCB Specimen flight of verting of the utility model
Device is rotatably equipped with rotor group in the end of fixed-wing 101 by Fixed Wing AirVehicle in conjunction with rotor craft progress depth
Part 2 can gather the advantage of Fixed Wing AirVehicle and rotor craft, and route speed is fast, can hover, suitable for complicated and changeable
Flight environment of vehicle；And structure is simple, is easily achieved.
In the present embodiment, rotor assemblies 2 include mounting rack 201, rotor 203 and force piece 202, and force piece 202 is installed on
On mounting rack 201, the output shaft of force piece 202 is connect with rotor 203.One is provided in its middle fuselage 1 through 1 two sides of fuselage
The fixing axle 103 of fixed-wing 101, the both ends of fixing axle 103 are arranged with bearing, are equipped with axis on the mounting rack 201 of rotor assemblies 2
Seat is held, bearing is installed in bearing block, i.e., mounting rack 201 can be rotated around fixing axle 103.In addition, force piece 202 be internal combustion engine or
Motor；When force piece 202 is internal combustion engine, such as gasoline engine, the unified fuel tank by fuselage 1 of each gasoline engine is carried out
Unified fuel feeding, the mode of independent oil tank is configured relative to each gasoline engine, can guarantee fuel tank weight at each rotor assemblies 2
Consistency, consequently facilitating carrying out flight control.Certainly, force piece 202 or motor, by installing on the fuselage 1
Battery to provide the mode that electric energy or gasoline engine drive generator to produce electricl energy to each motor be that each motor mentions
For electric energy, and suitable battery is assisted to carry out the work such as electric energy feedback, redundancy protecting.In the present embodiment, rotor 203 includes rotation
Wing seat and three pieces of rotary blades, three pieces of rotary blades are evenly distributed on rotor seat.It is understood that herein not to rotary blade
Quantity is defined, in other embodiments, can also be using two panels, four or more rotary blades.
As shown in figure 3, the component 3 that verts includes actuator 301 and link mechanism in the present embodiment, wherein actuator 301 is
Steering engine, stepper motor or servo motor, wherein it is preferred that steering engine, link mechanism then include cursor 302,303 and of first connecting rod
Second connecting rod 304, the middle part of cursor 302 are fixed on the output shaft of steering engine and rotate with it, one end of first connecting rod 303 with
One end of cursor 302 is hinged, and one end of second connecting rod 304 and the other end of cursor 302 are hinged, first connecting rod 303 and
The other end of two connecting rods 304 is hinged in mounting base；Wherein first connecting rod 303 and second connecting rod 304 are ball head connecting rod, peace
Dress seat is provided with ball screw 305 in the two sides of bearing block, and ball head connecting rod and ball screw 305 are cooperatively connected.When steering engine receives
When to control command, predetermined angular is rotated, corresponding cursor 302 rotates, exists by first connecting rod 303 and second connecting rod 304
Pullling in opposite direction drives mounting rack 201 to rotate, thus make rotor 203 on mounting rack 201 towards the front of fuselage 1 or
Back sweep.
The double-rotor aerobat that verts of the utility model, corresponding attitude adjusting method are as follows:
When needing makes aircraft be in forward travel state, the angle of two sides rotor assemblies 2 is adjusted by the component 3 that verts, is made
Rotor faces the front inclination of fuselage 1, so that aircraft is had a forward motive force, pushes aircraft forward flight.
When needing makes aircraft be in retrogressing or braking state, passes through the component 3 that verts and adjust two sides rotor assemblies 2
Angle makes the rotor of two sides rotor assemblies 2 face the back sweep of fuselage 1, and aircraft is made to have a motive force backward, pushes
Aircraft flies or brakes backward
When needing makes aircraft bend to right, the rotor assemblies 2 in left side is made to turn forward, while making the rotor group on right side
Part 2 tilts backwards, i.e., has forward thrust on the left of aircraft, there is thrust backward on right side, and collective effect makes it in aircraft
It turns to the right.
When needing makes aircraft turn to the left, the rotor assemblies 2 in left side are tilted backwards, while making the rotor group on right side
Part 2 turns forward, i.e., has thrust backward on the left of aircraft, and there is forward thrust on right side, and collective effect makes it in aircraft
It turns to the left.
Above are merely preferred embodiments of the utility model, the protection scope of the utility model is not limited merely to above-mentioned
Embodiment, technical solution belonging to the idea of the present invention belong to the protection scope of the utility model.It should be pointed out that pair
For those skilled in the art, several improvements and modifications without departing from the principle of the utility model,
It should be regarded as the protection scope of the utility model.
Claims (10)
- The double-rotor aerobat 1. one kind is verted, which is characterized in that including fuselage (1), the two sides of the fuselage (1) are symmetrically arranged with The tail portion of fixed-wing (101), the fuselage (1) is provided with fixed empennage (102)；The end of each fixed-wing (101) turns It is dynamic to be equipped with rotor assemblies (2), the component that verts (3) are installed between the fixed-wing (101) and rotor assemblies (2), for driving Dynamic rotor assemblies (2) rotation is tilted with the rotor for adjusting rotor assemblies (2) facing towards along fuselage (1) front and back.
- 2. the double-rotor aerobat according to claim 1 that verts, which is characterized in that the rotor assemblies (2) include installation Frame (201), rotor (203) and force piece (202), the force piece (202) are installed on the mounting rack (201), described dynamic The output shaft of power part (202) is connect with the rotor (203).
- 3. the double-rotor aerobat according to claim 2 that verts, which is characterized in that the force piece (202) is internal combustion engine Or motor；When the force piece (202) are internal combustion engine, it is provided with fuel tank on the fuselage (1), for unified to each internal combustion Machine carries out fuel feeding；When the force piece (202) are motor, the fuselage (1) is equipped with electric energy unit, for unified to each Motor provides electric energy.
- 4. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that the component that verts (3) packet Include actuator (301) and link mechanism, one end of the link mechanism is connected with the actuator (301), the other end with it is described Rotor assemblies (2) are connected.
- 5. the double-rotor aerobat according to claim 4 that verts, which is characterized in that the link mechanism includes cursor (302), first connecting rod (303) and second connecting rod (304) are fixed on the actuator (301) in the middle part of the cursor (302) Output shaft on, one end of the first connecting rod (303) and one end of the cursor (302) are hinged, the second connecting rod (304) other end of one end and the cursor (302) is hinged, the first connecting rod (303) and second connecting rod (304) it is another One end is hinged on the rotor assemblies (2).
- 6. the double-rotor aerobat according to claim 5 that verts, which is characterized in that the first connecting rod (303) and second Connecting rod (304) is ball head connecting rod, is provided with ball screw (305), the ball head connecting rod and bulb on the rotor assemblies (2) Screw (305) is cooperatively connected.
- 7. the double-rotor aerobat according to claim 4 that verts, which is characterized in that the actuator (301) is servo electricity Machine or stepper motor or steering engine.
- 8. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that be arranged on the fuselage (1) There is the fixing axle (103) for running through fuselage (1) two sides fixed-wing (101), the both ends of the fixing axle (103) are arranged with axis It holds, bearing block is installed on the rotor assemblies (2), the bearing is installed in the bearing block.
- 9. the double-rotor aerobat according to claim 1 or 2 or 3 that verts, which is characterized in that the bottom of the fuselage (1) It is provided with undercarriage.
- 10. the double-rotor aerobat according to claim 2 or 3 that verts, which is characterized in that the rotor (203) includes rotation Wing seat and muti-piece rotary blade, rotary blade described in muti-piece are evenly distributed on rotor seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821019163.4U CN208360498U (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821019163.4U CN208360498U (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
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| Publication Number | Publication Date |
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| CN208360498U true CN208360498U (en) | 2019-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201821019163.4U Active CN208360498U (en) | 2018-06-29 | 2018-06-29 | One kind is verted double-rotor aerobat |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
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2018
- 2018-06-29 CN CN201821019163.4U patent/CN208360498U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
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