CN207712292U - A kind of tilting rotor wing unmanned aerial vehicle - Google Patents
A kind of tilting rotor wing unmanned aerial vehicle Download PDFInfo
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- CN207712292U CN207712292U CN201721800380.2U CN201721800380U CN207712292U CN 207712292 U CN207712292 U CN 207712292U CN 201721800380 U CN201721800380 U CN 201721800380U CN 207712292 U CN207712292 U CN 207712292U
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Abstract
The utility model discloses a kind of tilting rotor wing unmanned aerial vehicles, mounting surface including head bay section described in head bay section is equipped with major part screw, the front and back mounting surface of the fuselage compartment section is equipped with U-type groove, the front and rear part of the fuselage compartment section is separately installed with No.1 inclining rotary mechanism and No. two inclining rotary mechanisms, and it is fixed by mounting screw in No.1 inclining rotary mechanism and the U-type groove of No. two inclining rotary mechanisms insertion, the No.1 inclining rotary mechanism and No. two inclining rotary mechanisms are equipped with rotor horn, rotor horn is equipped with electric machine assembly, foldable assembly is installed on the rotor horn, the electric machine assembly includes motor, retarder, pitch-changing mechanism and propeller, the motor is connect by retarder with shaft, the shaft is connect by pitch-changing mechanism with propeller.The tilting rotor wing unmanned aerial vehicle may be implemented VTOL and relax place limitation, while can fly so that fixed-wing pattern is flat, flying speed is fast, and endurance is long using tilting rotor topology layout.
Description
Technical field
The utility model belongs to air vehicle technique field, and in particular to a kind of tilting rotor wing unmanned aerial vehicle.
Background technology
Miscellaneous unmanned plane occurred one after another in recent years, the main Liang great branches of unmanned plane be multi-rotor unmanned aerial vehicle,
Fixed-wing unmanned plane.Multi-rotor unmanned aerial vehicle can require take-off venue low, but the low endurance of speed with VTOL and hovering
Short, cruise duration often only has dozens of minutes, it is difficult to meet mission requirements.Fixed-wing unmanned plane possesses faster speed and longer
Endurance, but high to takeoff and anding site requirements, runway is often difficult to find.So tilting rotor wing unmanned aerial vehicle in recent years
Research and development are also such as emerged rapidly in large numbersBamboo shoots after a spring rain, and various tilting rotor wing unmanned aerial vehicle is also developed in succession, however designing and developing for tilting rotor is gone back
Much prematurities, airscrew pitch is smaller efficient when taking off vertically, and flat winged pattern airscrew pitch is larger efficient, two kinds of moulds
Formula is difficult to take into account.
A kind of tilting rotor wing unmanned aerial vehicle is proposed thus.
Utility model content
The purpose of this utility model is to provide a kind of tilting rotor wing unmanned aerial vehicles, mentioned above in the background art to solve
Problem.
To achieve the above object, the utility model provides the following technical solutions：A kind of tilting rotor wing unmanned aerial vehicle, including head
The mounting surface of bay section, ventral bay section, wing, tail bay section and empennage, the head bay section is equipped with major part screw, the ventral cabin
The mounting surface of section be equipped with it is interior bury nut, the head bay section by burying nut plugged and fixed in major part screw and fuselage compartment section,
The front and back mounting surface of the fuselage compartment section is equipped with U-type groove, and the front and rear part of the fuselage compartment section is separately installed with No.1 and verts machine
Structure and No. two inclining rotary mechanisms, and fixed by mounting screw in No.1 inclining rotary mechanism and the U-type groove of No. two inclining rotary mechanisms insertion, institute
It states No.1 inclining rotary mechanism and No. two inclining rotary mechanisms is equipped with rotor horn, rotor horn is equipped with electric machine assembly, the gyroplane
Foldable assembly is installed, the electric machine assembly includes motor, retarder, pitch-changing mechanism and propeller, and the motor passes through on arm
Retarder is connect with shaft, and the shaft is connect by pitch-changing mechanism with propeller, and the wing is fixed on fuselage by intubation
On, the tail bay section is plugged in the tail portion mounting surface of fuselage compartment section by carbon pipe and is fixed with major part screw, and the empennage is logical
It crosses intubation and is fixed on the both sides of tail bay section and fixed again by eye-splice and major part screw.
Further, the head bay section is made of head hatchcover and head cabin main body, equipped with for solid on head hatchcover
Fixed head cabin plug, the head hatchcover are fixed with head cabin main body by head cabin plug attachment screw, head cabin main body
On carbon plate for fixing gondola is installed, the carbon plate is equipped with gondola mounting hole, and gondola mounting hole passes through the company on gondola
Fitting attachment screw is fixed.
Further, the ventral bay section is by ventral bay section main body, front hatch cover, rear hatchcover, umbrella hatchcover and main landing gear group
At the front hatch cover and rear hatchcover are inserted into the slot of ventral bay section body top by plug connector and are consolidated by stainless steel hasp
Fixed, the umbrella cabin is installed on by umbrella storehouse geometrical clamp in the empty slot in the middle part of ventral bay section main body, and umbrella hatchcover is equipped on empty slot,
The front of the ventral bay section main body is fixed with antenna by antenna fixing piece, and the bottom of the ventral bay section main body passes through fixation
Screw is equipped with main landing gear, and the inside of ventral bay section main body is equipped with gas cylinder and pile.
Further, the tail bay section is made of tail bay section main body and rear undercarriage, and the rear undercarriage is screwed on
Below tail bay section main body.
Further, the wing is made of wing-body, wing flap, aileron and winglet, and the wing flap and aileron are logical
Hinge connection is crossed, the tail portion of the wing-body is fixed with winglet by screw, and the surface of wing-body is equipped with steering engine
Lid.
Further, the empennage by empennage main body, empennage tail vane, empennage intubation and eye-splice plate, the empennage main body
Side is equipped with empennage tail vane, and eye-splice plate is equipped in empennage main body, and one end of the empennage intubation passes through eye-splice plate to be inserted into tail
In wing main body.
The technique effect and advantage of the utility model：
1. using tilting rotor topology layout, VTOL may be implemented and relax place limitation, while can be with fixed-wing mould
Formula is flat to fly, and flying speed is fast, and endurance is long.
2. using hydrogen fuel cell and lithium battery as the energy, the energy density of hydrogen fuel cell is high, can extend endurance.
3. rotor horn can fold, fuselage is divided into three sections, and wing, empennage can dismount, make in this way aircraft can with Quick Release,
It is more portable.
4. propeller can change screw pitch by pitch-changing mechanism, propeller efficiency in fine pitch under more rotor modes
Height, propeller is efficient in big screw pitch under fixed-wing pattern.
Description of the drawings
Fig. 1 is the decomposition texture schematic diagram of the utility model；
Fig. 2 is the assembling figure of the utility model；
Fig. 3 is the status diagram that takes off vertically of the utility model；
Fig. 4 is the flat winged status diagram of the utility model；
Fig. 5 is the vertical view of the utility model；
Fig. 6 is the side view of the utility model.
In figure：1 ventral bay section main body, 2 No.1 inclining rotary mechanisms, 3 rotor horns, 4 electric machine assemblies, 5 head hatchcovers, 6 heads
Undercarriage, 14 tail bay sections behind cabin main body, 7 gondolas, 8 main landing gears, 9 front hatch covers, 10 wing-bodies, 11 ailerons, 12 wing flaps, 13
Hatchcover behind main body, 15 empennage main bodys, 16 empennage tail vanes, 17 No. two inclining rotary mechanisms, 18.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
The utility model provides a kind of tilting rotor wing unmanned aerial vehicle as shown in figures 1 to 6, including head bay section, ventral cabin
The mounting surface of section, wing, tail bay section and empennage, the head bay section is equipped with major part screw, the mounting surface of the ventral bay section
Nut is buried equipped with interior, the head bay section is by burying nut plugged and fixed, the fuselage compartment in major part screw and fuselage compartment section
The front and back mounting surface of section is equipped with U-type groove, and the front and rear part of the fuselage compartment section is separately installed with No.1 inclining rotary mechanism 2 and No. two are inclined
Rotation mechanism 17, and fixed by mounting screw in No.1 inclining rotary mechanism 2 and the U-type groove of No. two inclining rotary mechanisms 17 insertion, described one
Number inclining rotary mechanism 2 and No. two inclining rotary mechanisms 17 are equipped with rotor horn 3, and rotor horn 3 is equipped with electric machine assembly 4, the rotor
Foldable assembly is installed, the electric machine assembly 4 includes motor, retarder, pitch-changing mechanism and propeller, the motor on horn 3
It is connect with shaft by retarder, the shaft is connect by pitch-changing mechanism with propeller, and the wing is fixed on by intubation
On fuselage, the tail bay section is plugged in the tail portion mounting surface of fuselage compartment section by carbon pipe and is fixed with major part screw, the tail
The both sides that the wing is fixed on tail bay section by intubation are fixed again by eye-splice and major part screw.
The head bay section is made of head hatchcover 5 and head cabin main body 6, and head for fixing is housed on head hatchcover 5
Cabin plug, the head hatchcover 5 are fixed by head cabin plug attachment screw with head cabin main body 6, are pacified in head cabin main body 6
Equipped with the carbon plate for fixing gondola 7, the carbon plate is equipped with gondola mounting hole, and gondola mounting hole passes through the connection on gondola 7
Part attachment screw is fixed.
The ventral bay section is made of ventral bay section main body 1, front hatch cover 9, rear hatchcover 18, umbrella hatchcover and main landing gear 8, institute
Front hatch cover 9 and rear hatchcover 18 is stated to be inserted into the slot on 1 top of ventral bay section main body by plug connector and by stainless steel hasp consolidate
Fixed, the umbrella cabin is installed on by umbrella storehouse geometrical clamp in the empty slot at 1 middle part of ventral bay section main body, and umbrella cabin is equipped on empty slot
The front of lid, the ventral bay section main body 1 is fixed with antenna by antenna fixing piece, and the bottom of the ventral bay section main body 1 is logical
It crosses fixing screws and main landing gear 8 is installed, the inside of ventral bay section main body 1 is equipped with gas cylinder and pile.
The tail bay section is made of tail bay section main body and rear undercarriage 13, and the rear undercarriage 13 is screwed on tail cabin
Below section main body.
The wing is made of wing-body 10, wing flap 12, aileron 11 and winglet, and the wing flap 12 and aileron 11 are logical
Hinge connection is crossed, the tail portion of the wing-body 10 is fixed with winglet by screw, and the surface of wing-body is equipped with rudder
Cover.
The empennage is by empennage main body 15, empennage tail vane 16, empennage intubation and eye-splice plate, the side of the empennage main body 15
Empennage tail vane 16 is installed, eye-splice plate is installed in empennage main body 15, one end of the empennage intubation passes through eye-splice plate to be inserted into tail
In wing main body 15.
It takes off vertically：
As shown in Figure 3-4：Aircraft provides upward pulling force in four rotor rotationals, and aircraft vertical takes off.
It takes off vertically after reaching certain altitude, fuselage gradually adjusts posture to level, and propeller and horizontal plane is made to have centainly
Angle forms the component of horizontal direction, carries out horizontal direction acceleration.Simultaneously as the speed of horizontal direction increases, the machine of aircraft
The lift of the wing can gradually increase.
In order to accelerate the process of horizontal acceleration, propeller can further vert certain angle.The process is mainly by inclining
Rotation mechanism is completed, and linear motor drives tiliting axis rotation, is further driven to propeller and verts certain angle.
It is flown to from this stage, propeller is in fine pitch state, this is because the screw pitch of propeller exists in low speed
It is more efficient when smaller.
Finally it should be noted that：The above descriptions are merely preferred embodiments of the present invention, is not limited to this
Utility model, although the utility model is described in detail with reference to the foregoing embodiments, for those skilled in the art
For, it still can be with technical scheme described in the above embodiments is modified, or to which part technical characteristic
Equivalent replacement is carried out, within the spirit and principle of the utility model, any modification, equivalent replacement, improvement and so on,
It should be included within the scope of protection of this utility model.
Claims (6)
1. a kind of tilting rotor wing unmanned aerial vehicle, including head bay section, ventral bay section, wing, tail bay section and empennage, feature exist
In：The mounting surface of the head bay section is equipped with major part screw, and the mounting surface of the ventral bay section buries nut, the head equipped with interior
Bay section is equipped with U by burying nut plugged and fixed, the front and back mounting surface of the fuselage compartment section in major part screw and fuselage compartment section
The front and rear part of type groove, the fuselage compartment section is separately installed with No.1 inclining rotary mechanism（2）With No. two inclining rotary mechanisms（17）, and No.1 is inclined
Rotation mechanism（2）With No. two inclining rotary mechanisms（17）It is fixed by mounting screw in the U-type groove of insertion, the No.1 inclining rotary mechanism（2）
With No. two inclining rotary mechanisms（17）Rotor horn is installed（3）, rotor horn（3）Electric machine assembly is installed（4）, the rotor horn
（3）On foldable assembly, the electric machine assembly are installed（4）Including motor, retarder, pitch-changing mechanism and propeller, the motor
It is connect with shaft by retarder, the shaft is connect by pitch-changing mechanism with propeller, and the wing is fixed on by intubation
On fuselage, the tail bay section is plugged in the tail portion mounting surface of fuselage compartment section by carbon pipe and is fixed with major part screw, the tail
The both sides that the wing is fixed on tail bay section by intubation are fixed again by eye-splice and major part screw.
2. a kind of tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that：The head bay section is by head hatchcover
（5）With head cabin main body（6）Composition, head hatchcover（5）It is upper that head cabin for fixing plug, the head hatchcover are housed（5）With
Head cabin main body（6）It is fixed by head cabin plug attachment screw, head cabin main body（6）On be equipped with for fixing gondola
（7）Carbon plate, the carbon plate is equipped with gondola mounting hole, and gondola mounting hole passes through gondola（7）On connector attachment screw it is solid
It is fixed.
3. a kind of tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that：The ventral bay section is by ventral bay section
Main body（1）, front hatch cover（9）, rear hatchcover（18）, umbrella hatchcover and main landing gear（8）Composition, the front hatch cover（9）With rear hatchcover
（18）It is inserted into ventral bay section main body by plug connector（1）It is fixed in the slot on top and by stainless steel hasp, the umbrella cabin is logical
It crosses umbrella storehouse geometrical clamp and is installed on ventral bay section main body（1）Umbrella hatchcover, the ventral cabin are installed in the empty slot at middle part, and on empty slot
Section main body（1）Front antenna, the ventral bay section main body are fixed with by antenna fixing piece（1）Bottom pass through fixing screws
Main landing gear is installed（8）, ventral bay section main body（1）Inside gas cylinder and pile are installed.
4. a kind of tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that：The tail bay section is by tail bay section
Main body and rear undercarriage（13）Composition, the rear undercarriage（13）It is screwed below tail bay section main body.
5. a kind of tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that：The wing is by wing-body
（10）, wing flap（12）, aileron（11）It is formed with winglet, the wing flap（12）And aileron（11）It is connected through the hinge, it is described
Wing-body（10）Tail portion winglet is fixed with by screw, and the surface of wing-body is equipped with steering engine lid.
6. a kind of tilting rotor wing unmanned aerial vehicle according to claim 1, it is characterised in that：The empennage is by empennage main body
（15）, empennage tail vane（16）, empennage intubation and eye-splice plate, the empennage main body（15）Side empennage tail vane is installed（16）,
Empennage main body（15）Eye-splice plate is inside installed, one end of the empennage intubation passes through eye-splice plate to be inserted into empennage main body（15）It is interior.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721800380.2U CN207712292U (en) | 2017-12-21 | 2017-12-21 | A kind of tilting rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721800380.2U CN207712292U (en) | 2017-12-21 | 2017-12-21 | A kind of tilting rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207712292U true CN207712292U (en) | 2018-08-10 |
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ID=63056715
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721800380.2U Active CN207712292U (en) | 2017-12-21 | 2017-12-21 | A kind of tilting rotor wing unmanned aerial vehicle |
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| CN (1) | CN207712292U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| WO2020107099A1 (en) * | 2018-11-30 | 2020-06-04 | Sky Canoe Inc. | Aerial vehicle with enhanced pitch control and interchangeable components |
| CN112278313A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Landing arresting rope mechanism of sliding unmanned aerial vehicle |
| CN116750226A (en) * | 2023-08-22 | 2023-09-15 | 陕西德鑫智能科技有限公司 | Modularized unmanned aerial vehicle |
-
2017
- 2017-12-21 CN CN201721800380.2U patent/CN207712292U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020107099A1 (en) * | 2018-11-30 | 2020-06-04 | Sky Canoe Inc. | Aerial vehicle with enhanced pitch control and interchangeable components |
| US10787255B2 (en) | 2018-11-30 | 2020-09-29 | Sky Canoe Inc. | Aerial vehicle with enhanced pitch control and interchangeable components |
| EP3887248A4 (en) * | 2018-11-30 | 2022-08-24 | Sky Canoe Inc. | Aerial vehicle with enhanced pitch control and interchangeable components |
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| CN112278313A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Landing arresting rope mechanism of sliding unmanned aerial vehicle |
| CN116750226A (en) * | 2023-08-22 | 2023-09-15 | 陕西德鑫智能科技有限公司 | Modularized unmanned aerial vehicle |
| CN116750226B (en) * | 2023-08-22 | 2023-10-31 | 陕西德鑫智能科技有限公司 | Modularized unmanned aerial vehicle |
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