CN207274984U - A kind of aircraft - Google Patents
A kind of aircraft Download PDFInfo
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- CN207274984U CN207274984U CN201721329483.5U CN201721329483U CN207274984U CN 207274984 U CN207274984 U CN 207274984U CN 201721329483 U CN201721329483 U CN 201721329483U CN 207274984 U CN207274984 U CN 207274984U
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- vertical
- canard
- fuselage
- connecting rod
- main wing
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Abstract
The utility model belongs to technical field of aerospace, a kind of more particularly to aircraft, including fuselage, the main wing being arranged on fuselage, the connecting rod for being fixedly connected with main wing and being set along fuselage length direction is respectively equipped with the both sides of fuselage, vertical tail is respectively equipped with the rear end of two connecting rods, tailplane is connected between two vertical tails, vertical rotor is respectively equipped with two connecting rods, be rotatably connected to respectively between the front end of two connecting rods and fuselage canard and with the undercarriage that canard rotates coaxially, tilting rotor is installed on undercarriage；The canard of Three-wing-surface, main wing, tailplane composition frame structure, it can ensure integrally-built rigidity and realize lightweight, exhibition is reduced to size, reduce influence of the crosswind to whole aircraft, main wing can avoid the strong jamming of canard downwash flow higher than canard, using vertical tail as rear undercarriage, reducing weight reduces flight aerodynamic drag, solves the problems, such as that existing Flight Vehicle Structure is complicated and flight pneumatic efficiency is poor.
Description
Technical field
The utility model belongs to technical field of aerospace, more particularly to a kind of aircraft.
Background technology
At present, rotor and the vertically taking off and landing flyer of fixed-wing composite layouts, are all simple rotor and fixed-wing superpositions,
Two sets of dynamical systems either hang down the winged stage still it is flat fly the stage have it is a set of be it is idle, it is not only complicated, and
And reduce the pneumatic efficiency of aircraft.
Utility model content
The purpose of this utility model is to provide a kind of aircraft, it is intended to solves existing Flight Vehicle Structure complexity and flight gas
The problem of efficiency of movement is poor.
The utility model is realized in this way a kind of aircraft, the aircraft includes fuselage, is arranged on the fuselage
Main wing, it is characterised in that be respectively equipped with and be fixedly connected with the main wing and along fuselage length direction in the both sides of the fuselage
The connecting rod of setting, is respectively equipped with vertical tail in the rear end of two connecting rods, water is connected between two vertical tails
The horizontal tail wing, vertical rotor is respectively equipped with two connecting rods, is turned respectively between the front end of two connecting rods and the fuselage
It is dynamic to be connected with canard and the undercarriage rotated coaxially with the canard, tilting rotor is installed on the undercarriage.
As an improvement the main wing is arranged on the upside of the fuselage afterbody, in the main wing and the institute of respective side
State and the support of the main wing wing is connected between connecting rod.
As an improvement the vertical rotor is arranged on the shaft portion between the main wing and the vertical tail
On.
As an improvement being equipped with mounting groove in the front end of the connecting rod, the undercarriage is installed in the mounting groove
And it is rotatablely connected with it.
As an improvement the rear end of the connecting rod is fixedly connected with the center of the vertical tail, the horizontal tail
The wing is connected between the center of two vertical tails.
As an improvement the direction of rotation of two vertical rotors is on the contrary, the direction of rotation phase of two tilting rotors
Instead, the vertical rotor positioned at homonymy is opposite with the direction of rotation of the tilting rotor.
As an improvement it is respectively equipped with rudder face on the canard, the main wing and the vertical tail.
As an improvement the rudder face of the vertical tail includes upper rudder face above the connecting rod, positioned at described
Lower rudder face below connecting rod.
As an improvement it is separately installed with wheel on the undercarriage, on the bottom of the vertical tail..
By adopting the above-described technical solution, the aircraft of the utility model includes fuselage, the main wing being arranged on fuselage,
The connecting rod for being fixedly connected with main wing and being set along fuselage length direction is respectively equipped with the both sides of fuselage, in the rear end of two connecting rods
Vertical tail is respectively equipped with, tailplane is connected between two vertical tails, vertical rotor is respectively equipped with two connecting rods,
Canard and the undercarriage rotated coaxially with canard are rotatably connected between the front end of two connecting rods and fuselage respectively, in undercarriage
On tilting rotor is installed.The canard of Three-wing-surface, main wing, tailplane composition frame structure, frame structure pass through canard and machine
Connection, connecting rod and the connection realization of main wing of body and fuselage are connected as one, and can be ensured integrally-built rigidity and be realized light
Quantify, canard, tailplane are located at the lower section of main wing and are arranged along fuselage anteroposterior direction, reduce exhibition to size, reduce
Influence of the crosswind to whole aircraft, main wing avoids the strong jamming of canard downwash flow higher than canard, after vertical tail is used as
Undercarriage instead of single landing gear structure, has not only reduced the weight of full machine but also has reduced flight aerodynamic drag, solve existing
The problem of Flight Vehicle Structure complexity and poor flight pneumatic efficiency.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the aircraft of the utility model；
Fig. 2 is the side structure schematic view of the aircraft of the utility model；
Fig. 3 is the transition state of the aircraft of the utility model, short take-off and landing status architecture schematic diagram；
Fig. 4 is the flat winged status architecture schematic diagram of the aircraft of the utility model；
Wherein, 11, fuselage, 12, main wing, 13a, connecting rod, 13b, connecting rod, 14a, vertical tail, 14b, vertical tail, 15,
Tailplane, 16a, canard, 16b, canard, 17a, tilting rotor, 17b, tilting rotor, 18a, vertical rotor, 18b, vertical rotation
The wing, 19, the main wing wing support, 20a, undercarriage, 20b, undercarriage, 21a, rudder face, 21b, rudder face, 21c, rudder face, 21d, rudder face.
Embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, is further elaborated the utility model.It should be appreciated that specific embodiment described herein is only explaining
The utility model, is not used to limit the utility model.
From Fig. 1 and Fig. 2, which includes fuselage 11, the main wing 12 being arranged on fuselage 11, the two of fuselage 11
Side be respectively equipped be fixedly connected with main wing 12 and along 11 length direction of fuselage set connecting rod 13a, connecting rod 13b, connecting rod 13a,
The rear end of connecting rod 13b is respectively equipped with vertical tail 14a, vertical tail 14b, between vertical tail 14a and vertical tail 14b
Tailplane 15 is connected with, vertical rotor 18a, vertical rotor 18b are respectively equipped with connecting rod 13a, on connecting rod 13b, in connecting rod
Be rotatably connected to respectively between the front end of 13a and fuselage 11, between the front end of connecting rod 13b and fuselage 11 canard 16a, canard 16b,
And the undercarriage 20b that the undercarriage 20a and canard 16b rotated coaxially with canard 16a is rotated coaxially, in undercarriage 20a, rise
Fall to be separately installed with tilting rotor 17a, tilting rotor 17b on frame 20b.
Canard 16a and canard 16b, main wing 12, the tailplane 15 of Three-wing-surface form frame structure, and frame structure passes through duck
Connection realizations and fuselage 11 of connection, connecting rod 13a and the connecting rod 13b of wing 16a and canard 16b and fuselage 11 with main wing 12 are connected as
One, can ensure integrally-built rigidity and realize lightweight, canard 16a and canard 16b, tailplane 15 are located at main wing 12
Lower section and also along 11 anteroposterior direction of fuselage arrange, reduce exhibition to size, reduce influence of the crosswind to whole aircraft, main wing
12 avoid the strong jamming of canard 16a and canard 16b downwash flows higher than canard 16a and canard 16b, by vertical tail 14a, hang down
Straight tail 14b instead of single landing gear structure as rear undercarriage, has not only reduced the weight of full machine but also has reduced flight gas
Dynamic resistance, solves the problems, such as that existing Flight Vehicle Structure is complicated and flight pneumatic efficiency is poor.
In the present embodiment, main wing 12 is arranged on the upside at 11 rear portion of fuselage, further reduces canard 16a and canard 16b
The strong jamming of downwash flow, is connected to main wing wing support 19, just between main wing 12 and the connecting rod 13a of respective side, connecting rod 13b
In the installation and fixation of the frame structure that canard 16a and canard 16b, main wing 12, tailplane 15 form.
In the present embodiment, vertical rotor 18a, vertical rotor 18b are separately positioned between main wing 12 and vertical tail 14a
Connecting rod 13a on, on the connecting rod 13b between main wing 12 and vertical tail 14b, when VTOL and flight, easy to maintain to fly
The balance of device, beneficial to the control of flight attitude.
In the present embodiment, on undercarriage 20a, undercarriage 20b, on the bottom of vertical tail 14a and vertical tail 14b
Wheel (not shown) is separately installed with, vertical tail 14a, vertical tail 14b instead of individually as rear undercarriage
Landing gear structure, had not only reduced the weight of full machine but also had reduced flight aerodynamic drag.
Further, mounting groove is respectively equipped with the front end of connecting rod 13a, connecting rod 13b, undercarriage 20a is installed on connecting rod 13a
Be rotatablely connected in the mounting groove of front end and with it, undercarriage 20b is installed in the mounting groove of connecting rod 13b front ends and with its company of rotation
Connect, easy to the installation of undercarriage 20a, undercarriage 20b, while coupling stiffness can be improved.
In the present embodiment, connecting rod 13a is fixedly connected with the center of vertical tail 14a, connecting rod 13b and vertical tail
The center of 14b is fixedly connected, and tailplane 15 is connected between the center of vertical tail 14a and vertical tail 14b.
In the present embodiment, vertical rotor 18a and vertical rotor 18b direction of rotation on the contrary, tilting rotor 17a with verting
The direction of rotation of rotor 17b on the contrary, positioned at homonymy vertical rotor 18a is opposite with the direction of rotation of tilting rotor 17a, vertical rotation
The direction of rotation of wing 18b and tilting rotor 17b is on the contrary, easy to maintain balance.
In the present embodiment, canard 16a and canard 16b, main wing 12 and vertical tail 14a and vertical tail 14b,
Rudder face 21a, rudder face 21b, rudder face 21c, rudder face 21d are respectively equipped with tailplane 15；Further, the rudder of vertical tail 14a
Face 21c includes the upper rudder face above the connecting rod 13a, the lower rudder face below connecting rod 13a, the rudder face on vertical tail 14b
21c includes being located at the upper rudder face above connecting rod 13b, the lower rudder face below connecting rod 13b.
In order to make it easy to understand, make to say as follows with reference to the VTOL of Fig. 1, Fig. 2, Fig. 3 and Fig. 4 to aircraft and flight progress
It is bright：
Take off vertically the stage：Before taking off, the tilting rotor 17a, canard 16a and undercarriage 20a of side are rotated to vertical
In the state of connecting rod 13a, rotated by the tilting rotor 17b of opposite side, canard 16b and with undercarriage 20b to perpendicular to connecting rod 13b
State, as shown in Figure 1 and Figure 2, the tilting rotor 17a of four rotors, tilting rotor 17b, vertical rotor 18a, vertical rotor
18b rotations, which produce, overcomes the lift force of gravity aircraft is gone up to the air, and is controlled and flown by the rudder face 21a on canard 16a, canard 16b
Row posture.
Vertical flight flies transition stage to flat：After aircraft vertical climbs to safe altitude, tilting rotor 17a, canard
16a forward at a slow speed rotation to parallel to connecting rod 13a state, tilting rotor 17b, canard 16b forward at a slow speed rotation to parallel to
The state of connecting rod 13b, undercarriage 20a, undercarriage 20b (nose-gear) are with packing up, as shown in figure 4, aircraft begins with water
Square to acceleration, vertical rotor 18a, the vertical rotor 18b of rear end still rotate the height and posture for keeping aircraft.
The flat winged stage：It can be carried when aircraft reaches three aerofoil canard 16a and canard 16b, main wing 12, tailplane 15
When keeping putting down winged speed for enough lift, vertical rotor 18a, the vertical rotor 18b of rear end are closed, aircraft flies as fixed-wing
Machine equally flies.
It is flat to fly to vertical flight transition stage：Tilting rotor 17a is rotated with canard 16a, tilting rotor 17b and canard 16b,
Respectively with connecting rod 13a, connecting rod 13b at an angle, as shown in figure 3, rear end vertical rotor 18a, vertical rotor 18b start at the same time
Rotation, four rotors (tilting rotor 17a, tilting rotor 17b, vertical rotor 18a, vertical rotor 18b) and two canard (canards
16a, canard 16b) keep aircraft posture and height, with tilting rotor 17a, tilting rotor 17b and canard 16a, canard
Close to when being respectively perpendicular to connecting rod 13a, connecting rod 13b, aircraft can fly 16b as more helighros.
Landing：Undercarriage 20a, undercarriage 20b (nose-gear) frame are put down, and aircraft can be as more helighros one
Sample is dropped on ground, by undercarriage 20a, undercarriage 20b (nose-gear) and vertical tail 14a and vertical tail 14b (after
Undercarriage) support landing.
In order to make it easy to understand, the short take-off and landing and flight progress of aircraft are made to say as follows with reference to Fig. 1, Fig. 2, Fig. 3 and Fig. 4
It is bright, short range landing need undercarriage 20a, undercarriage 20b, vertical tail 14a and vertical tail 14b bottom on install respectively
Wheel.
Takeoff phase：Before taking off, by tilting rotor 17a, canard 16a, undercarriage 20a rotate to connecting rod 13a be in 45 degree
Left and right angle, tilting rotor 17b, canard 16b, undercarriage 20b is rotated to being in 45 degree or so angles with connecting rod 13b, aircraft
Tilting rotor 17a, tilting rotor 17b driving under pass through undercarriage 20a, undercarriage 20b, vertical tail 14a and vertical end
Wheel on the bottom of wing 14b, which is slided, to be run, while vertical rotor 18a, vertical rotor 18b rotation overcome a part of gravity, in main wing
12nd, aircraft is lifted away from by tilting rotor 17a and tilting rotor 17b and vertical rotor 18a and vertical rotor 18b collective effects
Ground, after flying away from ground, tilting rotor 17a, canard 16a are rotated at a slow speed forward to the state parallel to connecting rod 13a, tilting rotor
17b, canard 16b forward at a slow speed rotation to parallel to connecting rod 13b state, as shown in Figure 4.
The flat winged stage：It can be carried when aircraft reaches three aerofoil canard 16a and canard 16b, main wing 12, tailplane 15
When keeping putting down winged speed for enough lift, vertical rotor 18a, the vertical rotor 18b of rear end are closed, aircraft flies as fixed-wing
Machine equally flies.
Landing：Tilting rotor 17a, canard 16a, undercarriage 20a are rotated to being in 45 degree or so angles with connecting rod 13a, are verted
Rotor 17b, canard 16b, undercarriage 20b are rotated to being in 45 degree or so angles with connecting rod 13b, while vertical rotor 18a and vertical
Rotor 18b, which starts to work, ensures aircraft balance, this stage aircraft has forward speed to fly to landing place always
Overhead finally drops to ground, and tilting rotor 17a, canard 16a, undercarriage 20a are vertical with connecting rod 13a after landing is contacted to earth, and vert
Rotor 17b, canard 16b, undercarriage 20b are vertical with connecting rod 13b, and vertical rotor 18a, vertical rotor 18b stop operating, can be compared with
It is fast to stop sliding running.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (9)
1. a kind of aircraft, including fuselage, the main wing that is arranged on the fuselage, it is characterised in that in the both sides of the fuselage
The connecting rod for being fixedly connected with the main wing and being set along fuselage length direction is respectively equipped with, is distinguished in the rear end of two connecting rods
Equipped with vertical tail, tailplane is connected between two vertical tails, vertical rotation is respectively equipped with two connecting rods
The wing, is rotatably connected to canard and is rotated coaxially with the canard respectively between the front end of two connecting rods and the fuselage
Undercarriage, tilting rotor is installed on the undercarriage.
2. aircraft according to claim 1, it is characterised in that the main wing is arranged on the upside of the fuselage afterbody,
The support of the main wing wing is connected between the main wing and the connecting rod of respective side.
3. aircraft according to claim 2, it is characterised in that the vertical rotor is arranged on the main wing and hangs down with described
In shaft portion between straight tail.
4. aircraft according to claim 1, it is characterised in that it is equipped with mounting groove in the front end of the connecting rod, described
Fall frame to be rotatablely connected in the mounting groove and with it.
5. aircraft according to claim 1, it is characterised in that the rear end of the connecting rod and the middle part of the vertical tail
Place is fixedly connected, and the tailplane is connected between the center of two vertical tails.
6. aircraft according to claim 1, it is characterised in that the direction of rotation of two vertical rotors is on the contrary, two institutes
The direction of rotation of tilting rotor is stated on the contrary, the vertical rotor positioned at homonymy is opposite with the direction of rotation of the tilting rotor.
7. aircraft according to claim 1, it is characterised in that in the canard, the main wing and the vertical end
Rudder face is respectively equipped with the wing.
8. aircraft according to claim 7, it is characterised in that the rudder face of the vertical tail includes being located at the connecting rod
The upper rudder face of top, the lower rudder face below the connecting rod.
9. according to claim 1 to 8 any one of them aircraft, it is characterised in that on the undercarriage, the vertical end
Wheel is separately installed with the bottom of the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721329483.5U CN207274984U (en) | 2017-10-14 | 2017-10-14 | A kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721329483.5U CN207274984U (en) | 2017-10-14 | 2017-10-14 | A kind of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207274984U true CN207274984U (en) | 2018-04-27 |
Family
ID=61979427
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721329483.5U Active CN207274984U (en) | 2017-10-14 | 2017-10-14 | A kind of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207274984U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107571994A (en) * | 2017-10-14 | 2018-01-12 | 上海歌尔泰克机器人有限公司 | A kind of aircraft |
| CN109720553A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | A kind of fixed-wing unmanned plane, control method and medium with VTOL function |
| CN113955092A (en) * | 2021-12-01 | 2022-01-21 | 中航金城无人系统有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout |
-
2017
- 2017-10-14 CN CN201721329483.5U patent/CN207274984U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107571994A (en) * | 2017-10-14 | 2018-01-12 | 上海歌尔泰克机器人有限公司 | A kind of aircraft |
| CN109720553A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | A kind of fixed-wing unmanned plane, control method and medium with VTOL function |
| CN109720553B (en) * | 2019-02-13 | 2021-07-27 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned aerial vehicle with vertical take-off and landing function, control method and medium |
| CN113955092A (en) * | 2021-12-01 | 2022-01-21 | 中航金城无人系统有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout |
| CN113955092B (en) * | 2021-12-01 | 2023-09-26 | 中航金城无人系统有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout |
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