CN206087301U - Tandem wing rotor displacement aircraft that verts - Google Patents
Tandem wing rotor displacement aircraft that verts Download PDFInfo
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- CN206087301U CN206087301U CN201621173585.8U CN201621173585U CN206087301U CN 206087301 U CN206087301 U CN 206087301U CN 201621173585 U CN201621173585 U CN 201621173585U CN 206087301 U CN206087301 U CN 206087301U
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Abstract
The utility model relates to a tandem wing rotor displacement aircraft that verts, belong to aircraft technical field, which has the advantages of simple structure, and reasonable design, adopt the overall arrangement of the tandem wing, can adjust the tandem wing rotor displacement aircraft that verts of rotor state of flight, the technical scheme that adopts is provided with wing and a pair of back wing before a pair of on for the cluster fuselage, the distal end of preceding wing and back wing all articulates dynamic arm, be provided with the rotor on the power arm, be provided with drive rotor pivoted power supply on the power arm, the power arm can 90 rotations, and preceding wing, all be provided with the driving power arm pivoted device that verts on the back wing, the utility model discloses extensively be used for various aircraft.
Description
Technical field
This utility model is related to a kind of tandem wing tilting rotor displacement aircraft, belongs to vehicle technology field.
Background technology
At present home and abroad scientific research institution tries to be the first aircraft of the research and development with VTOL function behind hole, but in order to meet more
The demand aircraft takeoff weight of realityization needs to reach several tons of rank, and the take-off weight for working as these aircraft reaches 1 ton
And will go wrong in control and configuration aspects when the above, common many rotors are controlled due to airscrew diameter and quantity
Restriction cannot accomplish big take-off weight, and the structure of tilting wing cannot also adapt to big aircraft.
At present everybody more generally acknowledged a solution is the oil many rotors of dynamic feather, but this scheme is also difficult to
The shortcoming for overcoming：Propeller efficiency is low, and cruising speed is slow, even if classic state also can only be the state of helicopter.
Utility model content
To solve the technical problem that prior art is present, this utility model provides a kind of simple structure, reasonable in design, adopts
With tandem wing layout, the tandem wing tilting rotor displacement aircraft of rotor flying state can be adjusted.
For achieving the above object, the technical scheme that this utility model is adopted is tandem wing tilting rotor displacement aircraft,
Including fuselage, front wing and rear wing, wing after wing and a pair before being provided with a pair on the fuselage, the front wing and after
The distal end of wing is hinged with power arm, and rotor is provided with the power arm, driving rotor is provided with the power arm and is turned
Dynamic power source, the power arm can 90 ° rotation, and be provided with front wing, rear wing drive power arm rotate vert
Device.
Preferably, the reclining device includes fixed plate, drives oil cylinder and cylinder rack, the fixed plate to be fixed on power arm
On, it is provided with the fixed plate and is hinged ear mount, one end of the cylinder rack is hinged on front wing or rear wing, the driving
The cylinder body of oil cylinder is hinged in cylinder rack, and the piston rod of driving oil cylinder is hinged on and is hinged in ear mount.
Preferably, the pitch of the rotor is adjustable.
Compared with prior art, this utility model has following technique effect：This utility model is using tandem wing layout
Fixed-wing fuselage, each wing tip install it is a set of incline turn 90 degrees the variablepiston dynamical system of the above, in the VTOL stage,
Four propellers produce upwards pulling force, and by feather stability contorting is realized, flat winged four propellers of stage tilt forward 90
Degree produces pulling force, and aircraft is changed into fixed wing airplane.This topology layout can adapt to the demand of large aircraft, make VTOL
Aircraft steps further to practical large aircraft.
Description of the drawings
Fig. 1 flies nonstop to the structural representation of state for this utility model.
Fig. 2 puts down the structural representation of winged state for this utility model.
Fig. 3 is the structural representation of reclining device in this utility model.
Specific embodiment
In order that technical problem to be solved in the utility model, technical scheme and beneficial effect become more apparent, with
Lower combination drawings and Examples, are further elaborated to this utility model.It should be appreciated that concrete reality described herein
Example is applied only to explain this utility model, be not used to limit this utility model.
As shown in Figure 1 and Figure 2, tandem wing tilting rotor displacement aircraft, including fuselage 1, front wing 2 and rear wing 3, machine
The distal end of wing 3, front wing 2 and rear wing 3 is hinged with power arm 4 after wing 2 and a pair before being provided with a pair on body 1, moves
Rotor 5 is provided with the arm of force 4, the power source for driving rotor rotational is provided with power arm 4, power arm 4 can 90 ° of rotations, it is and front
The reclining device for driving power arm to rotate is provided with wing 2, rear wing 3.
Wherein, reclining device includes fixed plate 6, drives oil cylinder 7 and cylinder rack 8, fixed plate 6 to be fixed on power arm 4, Gu
It is provided with fixed board 6 and is hinged ear mount 9, one end of cylinder rack 8 is hinged on front wing 2 or rear wing 3, drives the cylinder body of oil cylinder 7
It is hinged in cylinder rack 8, the piston rod of driving oil cylinder 7 is hinged on and is hinged in ear mount 9.
This utility model produces lift using the fixed-wing body of tandem wing normal arrangement by two pairs of wings, can be identical
Reduce the span under conditions of take-off weight, reduce aircraft size.Conversion the verting by wing tip taken off vertically with cruising level flight
Device is completed, and wing is maintained static, and each wing tip has a propeller, totally four, and in the VTOL stage drawing upwards is produced
Power, is rotated by 90 ° in the flat winged stage, produces pulling force forward.The moving component of so whole airplane only has the dynamical system of wing tip
And propeller, technically it is easier to realize, rather than the whole compound movement that wing verts or fuselage verts.This is many
The basic reason that more small-sized VTOL aircraft cannot maximize.Simultaneously the modern the inside of the aircraft with VTOL ability is straight
The machine of liter is one and represents well, but the slow shortcoming of its cruising speed cannot be solved at all, to expect higher flying
Scanning frequency degree and good oil consumption rate and economy, it is necessary to the scheme cruised using fixed-wing, are that we employ fixed-wing this
VTOL scheme, make a kind of aircraft with VTOL ability have in cruise at a high speed and it is economical the characteristics of.
Additionally, control mode of this utility model using feather, the pitch of each propeller can be adjusted individually, by meter
Changing the purpose that its pitch reaches control attitude, this control mode do not limited and propeller size calculation machine by aircraft size
The restriction of weight, is different from the underactuated control of common many rotors, can reach the quick control effect of helicopter.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit this utility model
Any modification, equivalent and improvement made within the spirit and principle of utility model etc., all should wrap in this utility model model
In enclosing.
Claims (3)
1. tandem wing tilting rotor displacement aircraft, including fuselage, front wing and rear wing, it is characterised in that：On the fuselage
The distal end of wing, the front wing and rear wing is hinged with power arm, the power after wing and a pair before being provided with a pair
Rotor is provided with arm, be provided with the power arm drive rotor rotational power source, the power arm can 90 ° rotation, and
The reclining device for driving power arm to rotate is provided with front wing, rear wing.
2. tandem wing tilting rotor displacement aircraft according to claim 1, it is characterised in that：The reclining device includes
Fixed plate, driving oil cylinder and cylinder rack, the fixed plate is fixed on power arm, is provided with the fixed plate and is hinged ear mount,
One end of the cylinder rack is hinged on front wing or rear wing, described to drive the cylinder body of oil cylinder to be hinged in cylinder rack, is driven
The piston rod of oil cylinder is hinged on and is hinged in ear mount.
3. tandem wing tilting rotor displacement aircraft according to claim 1, it is characterised in that：The pitch of the rotor can
Adjust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173585.8U CN206087301U (en) | 2016-10-26 | 2016-10-26 | Tandem wing rotor displacement aircraft that verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621173585.8U CN206087301U (en) | 2016-10-26 | 2016-10-26 | Tandem wing rotor displacement aircraft that verts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206087301U true CN206087301U (en) | 2017-04-12 |
Family
ID=58486265
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621173585.8U Active CN206087301U (en) | 2016-10-26 | 2016-10-26 | Tandem wing rotor displacement aircraft that verts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206087301U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228587A (en) * | 2019-07-03 | 2019-09-13 | 中国人民解放军国防科技大学 | Pitch-varying system and unmanned aerial vehicle |
-
2016
- 2016-10-26 CN CN201621173585.8U patent/CN206087301U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228587A (en) * | 2019-07-03 | 2019-09-13 | 中国人民解放军国防科技大学 | Pitch-varying system and unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder | ||
| CP02 | Change in the address of a patent holder |
Address after: Room 102, floor 1, 3 workshop, No. 6898, Zhuhai Avenue, Hongqi Town, Jinwan District, Zhuhai City, Guangdong Province Patentee after: ZHUHAI TIANQING AEROSPACE TECHNOLOGY CO.,LTD. Address before: 519000 Guangdong Province, Zhuhai city planning exhibition hall on the third floor of the aviation city Jinwan District 312-30 room Patentee before: ZHUHAI TIANQING AEROSPACE TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220627 Address after: 110000 first floor of plant, No. 37-3, Shenbei Road, Shenbei New District, Shenyang City, Liaoning Province Patentee after: Shenyang Tianqing Aerospace Technology Co.,Ltd. Address before: 519000 Room 102, floor 1, No. 3 plant, No. 6898, Zhuhai Avenue, Hongqi Town, Jinwan District, Zhuhai City, Guangdong Province Patentee before: ZHUHAI TIANQING AEROSPACE TECHNOLOGY CO.,LTD. |