CN105711831B - The fixed-wing unmanned plane of VTOL - Google Patents
The fixed-wing unmanned plane of VTOL Download PDFInfo
- Publication number
- CN105711831B CN105711831B CN201610259173.4A CN201610259173A CN105711831B CN 105711831 B CN105711831 B CN 105711831B CN 201610259173 A CN201610259173 A CN 201610259173A CN 105711831 B CN105711831 B CN 105711831B
- Authority
- CN
- China
- Prior art keywords
- wing
- rotor
- fuselage
- slide plate
- fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
Abstract
The present invention provides a kind of fixed-wing unmanned plane of VTOL, including fuselage, and the driving that moves ahead is provided with body, wing is provided with the both sides of fuselage, folding fuselage rotor is provided with fuselage；Fuselage slide plate is provided with the both sides of fuselage rotor；Multiple folding wing rotors are provided with wing, the top of wing rotor is provided with retractable wing skate apparatus.Structure more than, has following beneficial effect：Using forward driving and the combination of fuselage rotor and wing rotor, the switching being easy to implement between VTOL and fixed-wing flight.Thus the unmanned plane of structure, it is easy to hover at any time during execution task, so as to camera energy fixed point observation, while takes off when landing without runway and ejection device.Using the combination of fuselage rotor and wing rotor, it is easy to control the balance of whole body.Using concealed fuselage rotor and wing rotor, make not interfere between VTOL pattern and fixed-wing offline mode, without increasing the volume of wing.Air fluid lifting efficiency is high.
Description
Technical field
The present invention relates to unmanned plane field, the fixed-wing unmanned plane of especially a kind of VTOL.
Background technology
The fixed wing aircraft of VTOL, this kind of aircraft have the function similar to helicopter, it is not necessary to by runway just
Energy vertical and landing takeoff, unlike, this kind of aircraft can vert flat winged acceleration simultaneously from floating state by power in the air
It is transitioned into the offline mode of fixed-wing.For unmanned plane, the fixed-wing scheme of VTOL can drop to unmanned plane
Precalculated position, complete setting task after, automatic takeoff return, make VTOL fixed-wing unmanned plane have it is unrivaled from
Dynamic control advantage.
At present, practical VTOL fixed wing aircraft is mainly AV-8 sparrow hawk formulas fighter plane, V-22 osprey tilting rotors
Aircraft, F-35 opportunities of combat.AV-8 sparrow hawk formula opportunities of combat employ exhaust using flying horse engine on the basis of jet engine
The rotatable thrust vectoring scheme of jet pipe, in actual use, often there is integrity problem in this type aircraft, also referred to as " few
Woman's aircraft ".V-22 osprey formula tiltrotors are a the verting by American Bell Incorporated and Boeing's co-design manufacture
Gyroplane, and a medium transport aircraft.It realizes that rotor exists by two lifting airscrews of tilting wing both ends wing tip
Conversion between vertically and horizontally, so as to which more ideally the characteristics of helicopter and fixed wing aircraft combine together.Hanging down
Under straight landing state, two rotor thrust directions keep the longitudinal attitude stabilization of body perpendicular to ground using auto-bank unit.
V-22 ospreys had both had the ability of pure helicopter VTOL and hovering, had the high speed of turboprop aircraft again
The ability of cruising flight, it is a kind of dual-use new high-tech product.At present, it is mainly used in military requirement, and can assign
Battleficld command official more selects and greater flexibility.It does not need special airport and runway, easy to maintenance, viability
By force, especially suitable for carrying out special operations, military personnel's delivery is greatly improved, is deployed troops on garrison duty, hostile takedown, the action such as disaster relief
Speed.
However, because V-22 ospreys employ two lifting airscrews, under VTOL pattern, rotor needs automatic
Inclinator controls the stabilization of attitude of flight vehicle, adds the difficulty of control, and blade uses feathering device, also increases
Cost；And osprey, under VTOL pattern, rotor slip-stream front is blown on aerofoil surface, causes very big pressure drag
Loss, and force wing to increase structural strength, and then cause the increase of Flight Vehicle Structure weight, reduce the performance of aircraft.
The A of Chinese patent literature CN 105083550 disclose a kind of VTOL Fixed Wing AirVehicle, including fuselage, tail
The wing and the power set with inclining rotary mechanism, the power set with inclining rotary mechanism include fixedpiston propeller, started
Machine, enging cabin, slip-stream rudder, wing, tilting wing and steering wheel, engine are installed in enging cabin, fixedpiston propeller
With the output axis connection of engine, tilting wing one end is fixedly connected on enging cabin, and the other end is rotatablely connected with machine
On the wing, slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving, the power set with inclining rotary mechanism
Fuselage both sides are symmetricly set in, and are horizontally disposed with for wing, the fuselage head is provided with through hole, and ducted fan is set in through hole.This
Invention aircraft rotor and the size of aircraft are smaller, and save the auto-bank unit and feathering device of complexity, structure letter
It is single, the difficulty of trim and the complexity of flight control system are reduced, system reliability is high, cost is low.
But for unmanned plane, the structure is still excessively complicated, and to reach the rigidity with practicality, for structure
Precision and material stiffness require too high, and holistic cost is higher, and organism balance is difficult to control.
In the prior art, also there is a scheme being embedded in rotor in wing, in the program, very large machine is provided with body
The wing, wing are provided with the through hole of up/down perforation, and rotor is arranged in through hole, and program rotor space-consuming is big, the air of wing
Fluid lift efficiency is undesirable, and body is also more heavy.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of fixed-wing unmanned plane of VTOL, have VTOL concurrently
The characteristics of the advantages of being easy to remote operation and fixed-wing are easy to high speed cruise flight, and it is simple in construction, it is easy to accomplish, it is easy to control
The balance of fuselage processed.
In order to solve the above technical problems, the technical solution adopted in the present invention is：A kind of fixed-wing of VTOL nobody
Machine, including fuselage, wing is provided with the both sides of fuselage, preceding rotor is provided with front of fuselage, folding machine is provided with fuselage
Body rotor；Fuselage slide plate is provided with the both sides of fuselage rotor；
Multiple folding wing rotors are provided with wing, the front and top of wing rotor are provided with retractable wing
Skate apparatus.
Described fuselage rotor and the structure of wing rotor are：
Rotary blade is pivotally connected by bearing pin with rotor seat, and the output shaft of rotor seat and rotor motor is fixed
Connection.
Upon deployment, the movement locus of the rotary blade of fuselage rotor extends to the side wall of fuselage both sides to described fuselage rotor
Outside.
The structure of fuselage slide plate is that slide plate is movably arranged in the side wall of fuselage both sides, and can be along fuselage both sides side wall
Slide, slide plate inwall is installed with rack, and fuselage sled motor is connected by fuselage slide plate transmission mechanism with rack.
1 ~ 4 wing rotor is provided with every side wing, wing rotor is arranged in rotor storehouse, and the upside in rotor storehouse is with before
Side opens, and bottom side, the left and right sides and rear side closing, wing rotor are installed in the bottom wall in rotor storehouse.
When wing rotor deploys, the movement locus of the rotary blade of wing rotor is extended to outside the front side of rotor storehouse.
Described wing skate apparatus includes the relative wing front slide and wing tail skid slided；
The both sides of wing front slide positioned at being installed in the wing operating slide guideway rail of rotor storehouse side wall, wing front slide one end with
Wing slide plate preliminary roller is connected, and wing slide plate preliminary roller is connected with drive device, and the other end of wing front slide is taken provided with wing slide plate
Socket part；
The both sides of wing tail skid, which are located at, to be installed in the wing operating slide guideway rail of rotor storehouse side wall, wing tail skid and wing
Slide plate back roller is connected, and wing slide plate back roller is connected with drive device.
The preceding wind spring for driving wing front slide to be closed is provided with wing slide plate preliminary roller；
The rear wind spring for driving wing tail skid to be closed is provided with wing slide plate back roller.
2 fuselage rotors are provided with every side wing, wing left skateboard is provided with the left rack of wing slide plate, and wing slide plate is left
Rack is connected with wing slide plate Left Drive mechanism；
The right slide plate of wing is provided with the right rack of wing slide plate, and the right rack of wing slide plate connects with the right transmission mechanism of wing slide plate
Connect；
Wing slide plate Left Drive mechanism and the right transmission mechanism of wing slide plate are connected with motor.
Multiple louvre blades are provided with the bottom in rotor storehouse, multiple louvre blades are arranged along rotor orlop wall fore-and-aft direction, institute
In the louvre blade stated, blade is connected by blinds bearing pin with rotor storehouse, and the rear portion of blade is provided with blade clinch.
A kind of fixed-wing unmanned plane of VTOL provided by the invention, the structure more than, have following
Beneficial effect：
1st, using forward driving and the combination of fuselage rotor and wing rotor, it is easy to implement VTOL and is flown with fixed-wing
Between switching, obtain the convenience of VTOL and the flying speed of fixed-wing.Thus the unmanned plane of structure, it is easy to perform and appoints
Hover during business, so as to camera energy fixed point observation, while take off when landing without runway and ejection device at any time.
2nd, using the combination of fuselage rotor and wing rotor, it is easy to control the balance of whole body.
3rd, using concealed fuselage rotor and wing rotor, make not having between VTOL pattern and fixed-wing offline mode
There is interference, without increasing the volume of wing.Air fluid lifting efficiency is high.
4th, terminal with compact integral structure, it is easy to accomplish and manufacture, it is easy to control, production cost can be reduced.
Brief description of the drawings
The invention will be further described with reference to the accompanying drawings and examples：
Dimensional structure diagram when Fig. 1 is the VTOL state in the present invention.
Dimensional structure diagram when Fig. 2 is the fixed-wing state of flight in the present invention.
Fig. 3 is the overlooking the structure diagram of middle fuselage slide plate of the present invention.
Fig. 4 is the overlooking the structure diagram of middle fuselage rotor of the present invention and wing rotor.
Fig. 5 is the structural representation of wing skate apparatus in the present invention.
Fig. 6 is the close-up schematic view at A in Fig. 5.
Fig. 7 is the partial structural diagram of wing skate apparatus in the present invention.
Another dimensional structure diagram when Fig. 8 is fixed-wing state of flight in the present invention.
Fig. 9 is another structural representation of wing skate apparatus in the present invention.
Figure 10 is another partial structural diagram of wing skate apparatus in the present invention.
In figure：Body 1, fuselage 2, fuselage rotor 3, fuselage slide plate 4, slide plate 41, rack 42, fuselage sled motor 43, machine
Body slide plate transmission mechanism 44, wing 5, rotor storehouse 6, louvre blade 7, blinds bearing pin 71, blade 72, blade clinch 73, wing rotation
The wing 8, rotary blade 81, bearing pin 82, rotor seat 83, rotor motor 84, wing skate apparatus 9, wing front slide 901 are sliding after wing
Plate 902, wing operating slide guideway rail 903, wing slide plate preliminary roller 904, wing slide plate back roller 905, preceding wind spring 906, rear wind spring 907, point
Disconnected place 908, wing slide plate clinch 909, wing left skateboard 910, the right slide plate 911 of wing, the left rack 912 of wing slide plate, wing
The right rack 913 of slide plate, wing slide plate Left Drive mechanism 914, the right transmission mechanism 915 of wing slide plate, preceding rotor 10.
Embodiment
In the present invention, illustrated with the orientation of body 1, i.e., by taking Fig. 1 as an example, the head of body 1 is front, after afterbody is
Side, the top of body 1 is top.Accompanying drawing in the present invention is schematic diagram, for ease of observation, eliminates part supplementary structure, only
Prominent part-structure related to the present invention, is structure commonly used in the prior art for especially dated part-structure.
In Fig. 1,2, a kind of fixed-wing unmanned plane of VTOL, including fuselage 2, it is provided with wing in the both sides of fuselage 2
5, be provided with preceding rotor 10 in the front of fuselage 2, either the rotor in front or send out below wing or located at turbine below wing
Motivation.
Folding fuselage rotor 3 is provided with fuselage 2；Fuselage slide plate 4 is provided with the both sides of fuselage rotor 3；
Multiple folding wing rotors 8 are provided with wing 5, the front and top of wing rotor 8 are provided with retractable
Wing skate apparatus 9.By the combination of fuselage rotor 3 and wing rotor 8, whole body 1 is set to obtain the lifting force of vertical lift, and
After vertical lift is completed to predetermined altitude, start the driving that moves ahead, then pack up fuselage rotor 3 and wing rotor 8, fuselage is slided
Plate 4 and wing skate apparatus 9 are closed, that is, complete the conversion being flown from vertical lift to fixed-wing.During landing, fuselage is opened
Slide plate 4 and wing skate apparatus 9, start fuselage rotor 3 and wing rotor 8, realize vertical landing.
In preferable scheme such as Fig. 4, the structure of described fuselage rotor 3 and wing rotor 8 is：
Rotary blade 81 is pivotally connected by bearing pin 82 with rotor seat 83, rotor seat 83 and rotor motor 84
Output shaft is fixedly connected.When rotor motor 84 starts, rotary blade 81 opens under the influence of centrifugal force, and obtains lifting force,
When rotor motor 84 stops, rotary blade 81 folds under the action of the forces of the wind, consequently facilitating taking in into fuselage 2 and wing 5
In rotor storehouse 6.Thus structure reduces the space requirement of fuselage rotor 3 and wing rotor 8.
In preferable scheme such as Fig. 1, described fuselage rotor 3 upon deployment, the motion rail of the rotary blade 81 of fuselage rotor 3
Mark is extended to outside the side wall of the both sides of fuselage 2.Thus structure, fuselage rotor 3 is made to obtain enough lifting forces, and required space
Less.
In preferable scheme such as Fig. 3, the structure of fuselage slide plate 4 is that slide plate 41 is movably arranged in the both sides side wall of fuselage 2,
And rack 42 can be installed with along the both sides side walls of fuselage 2, the inwall of slide plate 41, fuselage sled motor 43 passes through fuselage slide plate
Transmission mechanism 44 is connected with rack 42.Fuselage slide plate transmission mechanism 44 in this example is preferably decelerator and gear, specially machine
Body sled motor 43 is connected with decelerator, and the output shaft of decelerator is fixedly connected with gear, the engagement connection of wheel and rack 42, is led to
The rotating of control fuselage sled motor 43 is crossed, the folding of slide plate 41 is controlled, by the folding of slide plate 41, makes the rotation of fuselage rotor 3
Fin 81 is easy to be stretched over outside the side wall of fuselage 2, so as to obtain enough lifting forces.
In preferable scheme such as Fig. 1 ~ 2,1 ~ 4 wing rotor 8 is provided with every side wing 5, is every side wing 5 in this example
2 wing rotors 8 of interior setting, wing rotor 8 are arranged in rotor storehouse 6, and the upside in rotor storehouse 6 and front side open, bottom side, left and right
Both sides and rear side closing, wing rotor 8 are installed in the bottom wall in rotor storehouse 6.The rotor motor 84 of specific wing rotor 8 fixes peace
Bottom wall mounted in rotor storehouse 6 is close to the position of front side, so when rotor motor 84 drives rotary blade 81 to deploy because of rotation, machine
The movement locus of the rotary blade 81 of wing rotor 8 is extended to outside the front side of rotor storehouse 6.Thus structure, larger lifting force is obtained, and
Take less space, without by wing design into bulky structure.
In optional scheme such as Fig. 5,7, described wing skate apparatus 9 includes the relative He of wing front slide 901 slided
Wing tail skid 902；
Positioned at being installed in the wing operating slide guideway rail 903 of the side wall of rotor storehouse 6, wing is advancing slip for the both sides of wing front slide 901
The one end of plate 901 is connected with wing slide plate preliminary roller 904, and wing slide plate preliminary roller 904 is connected with drive device, further preferred scheme
In Fig. 7, wing slide plate clinch 909 is provided with the other end of wing front slide 901；
Slided positioned at being installed in the wing operating slide guideway rail 903 of the side wall of rotor storehouse 6 after wing the both sides of wing tail skid 902
Plate 902 is connected with wing slide plate back roller 905, and wing slide plate back roller 905 is connected with drive device, and the drive device in this example is electricity
Machine and transmission mechanism, motor are connected with transmission mechanism, and transmission mechanism is connected with wing slide plate back roller 905, after driving machine wing slip plate
Roller 905 rotates.The type of drive of wing slide plate preliminary roller 904 is identical.Thus structure, after wing slide plate preliminary roller 904 and wing slide plate
Roller 905 drives wing front slide 901 and the folding of wing tail skid 902, and 908 is combined at disjunction.908 selection wing at disjunction
The position that cross section curve changes greatly.In this example, the length of wing tail skid 902 is more than the length of wing front slide 901, so as to
In the mechanical strength of control wing tail skid 902 and wing front slide 901.In this example, wing tail skid 902 and wing front slide
901 using with flexible material, such as almag plate, titanium alloy sheet or nylon and titanium alloy composite panel.Due to wing
The both sides of tail skid 902 and wing front slide 901 are supported by wing operating slide guideway rail 903, therefore have enough intensity, according to need
Will, it can also be set in the bottom surface of wing tail skid 902 and wing front slide 901 along wing slide plate preliminary roller 904 and wing slide plate
The reinforcing muscle of the axis of back roller 905.
The wing slide plate clinch 909 of setting is the stage bent upward, before making wing tail skid 902 and wing
Overlap joint between slide plate 901 is more reliable, while also enhances the intensity of wing front slide 901.
The preceding wind spring 906 for driving wing front slide 901 to be closed is provided with wing slide plate preliminary roller 904；
The rear wind spring 907 for driving wing tail skid 902 to be closed is provided with wing slide plate back roller 905.Thus structure, can
Quickly from vertical lift State Transferring to fixed-wing state of flight, shorten conversion time, improve the security of body 1.
In another optional structure such as Fig. 8 ~ 9,2 fuselage rotors 3 are provided with every side wing 5, on wing left skateboard 910
Provided with the left rack 912 of wing slide plate, the left rack 912 of wing slide plate is connected with wing slide plate Left Drive mechanism 914；
The right slide plate 911 of wing is provided with the right rack 913 of wing slide plate, the right rack 913 of wing slide plate and the right biography of wing slide plate
Motivation structure 915 connects；
Wing slide plate Left Drive mechanism 914 and the right transmission mechanism 915 of wing slide plate are connected with motor.Thus structure,
In a manner of horizontally slipping, the upside and front side in rotor storehouse 6 are opened.Unmanned plane suitable for the space enlarged relative of wing 5.Due to machine
Thickness of the wing 5 from wing root to wing tip is gradually thinning, therefore wing left skateboard 910 is opening rotor storehouse 6 with the right slide plate 911 of wing
, can be by the arrangement of stacked on top under state.
In further preferred structure such as Figure 10, by by the left rack 912 of wing slide plate it is vertical be arranged on the left cunning of wing
The end of plate 910, the vertical position for being positioned close to the right end of slide plate 911 of wing of the right rack 913 of wing slide plate, wing slide plate
The tooth of the left rack 913 right with wing slide plate of rack 912 is positioned opposite, thus structure, can drive wing simultaneously by a gear
Left skateboard 910 and the right slide plate 911 of wing act.
In preferable scheme such as Fig. 5,6, multiple louvre blades 7 are provided with the bottom in rotor storehouse 6, multiple louvre blades 7 are along rotation
The bottom wall fore-and-aft direction of Wing Tank 6 arranges that in described louvre blade 7, blade 72 is connected by blinds bearing pin 71 with rotor storehouse 6, blade
72 rear portion is provided with blade clinch 73, and blade clinch 73 is a stage portion bent downwards, so that preceding blade 72
The end of posterior blade 72 is overlapped on, the structure of similar fish scale is formed, to reduce windage, and reinforced structure.Louvre blade 7 and hundred
The link position of leaf bearing pin 71 is located at position forward among louvre blade 7, so that by default, louvre blade 7, which is in, to be opened
State.Thus structure, it is easy to make air discharge at louvre blade 7 under vertical lift state, and is flown when being transferred to fixed-wing
During pattern, then overlapped in the effect of wind-force, each louvre blade 7, there is provided lifting force.
In use, wing skate apparatus 9 and fuselage slide plate 4 are opened, fuselage rotor 3 and wing rotor 8 rotate, wing rotor
Wind caused by 8 is discharged from louvre blade 7, rises body 1, and after leaving ground certain altitude, preceding rotor 10 starts, make body 1 to
Preceding flight, the rotating speed of fuselage rotor 3 and wing rotor 8 is gradually reduced until stopping, fuselage rotor 3 and wing rotor 8 are in wind-force
Effect is lower to be folded, and closes wing skate apparatus 9 and fuselage slide plate 4, body 1 are transferred to fixed-wing state of flight.
During landing, wing skate apparatus 9 and fuselage slide plate 4 are opened, and fuselage rotor 3 and wing rotor 8 rotate, and are gradually reduced
For the rotating speed of preceding rotor 10 until stopping, body 1 enters floating state, makes whole body 1 switch to be vertically moved up or down from fixed-wing flight
State is until landing.
The above embodiments are only the preferred technical solution of the present invention, and are not construed as the limitation for the present invention, this Shen
Please in embodiment and embodiment in feature in the case where not conflicting, can mutually be combined.The protection model of the present invention
Enclose the equivalent substitution side of technical characteristic in the technical scheme that should be recorded with claim, including the technical scheme of claim record
Case is protection domain.Equivalent substitution i.e. within this range is improved, also within protection scope of the present invention.
Claims (7)
1. a kind of fixed-wing unmanned plane of VTOL, including fuselage（2）, in fuselage（2）Both sides be provided with wing（5）, in machine
Body（2）Front is provided with preceding rotor（10）, it is characterized in that：In fuselage（2）It is interior to be provided with folding fuselage rotor（3）；Revolved in fuselage
The wing（3）Both sides be provided with fuselage slide plate（4）；
In wing（5）It is interior to be provided with multiple folding wing rotors（8）, wing rotor（8）Front and top be provided with it is retractable
Wing skate apparatus（9）；
Described fuselage rotor（3）With wing rotor（8）Structure be：
Rotary blade（81）Pass through bearing pin（82）With rotor seat（83）Pivotally connect, rotor seat（83）With rotor motor
（84）Output shaft be fixedly connected；
In every side wing（5）Inside it is provided with 1 ~ 4 wing rotor（8）, wing rotor（8）It is arranged at rotor storehouse（6）It is interior, rotor storehouse
（6）Upside and front side open, bottom side, the left and right sides and rear side closing, wing rotor（8）It is installed in rotor storehouse（6）Bottom wall；
Described wing skate apparatus（9）Including the relative wing front slide slided（901）With wing tail skid（902）；
Wing front slide（901）Both sides positioned at being installed in rotor storehouse（6）The wing operating slide guideway rail of side wall（903）It is interior, before wing
Slide plate（901）One end and wing slide plate preliminary roller（904）Connection, wing slide plate preliminary roller（904）It is connected with drive device, wing is advancing slip
Plate（901）The other end be provided with wing slide plate clinch（909）；
Wing tail skid（902）Both sides positioned at being installed in rotor storehouse（6）The wing operating slide guideway rail of side wall（903）It is interior, after wing
Slide plate（902）With wing slide plate back roller（905）Connection, wing slide plate back roller（905）It is connected with drive device.
2. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：Described fuselage rotor
（3）Upon deployment, fuselage rotor（3）Rotary blade（81）Movement locus extend to fuselage（2）Outside the side wall of both sides.
3. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：Fuselage slide plate（4）Knot
Structure is slide plate（41）It is movably arranged on fuselage（2）In the side wall of both sides, and can be along fuselage（2）Both sides side walls, slide plate
（41）Inwall is installed with rack（42）, fuselage sled motor（43）Pass through fuselage slide plate transmission mechanism（44）With rack（42）Even
Connect.
4. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：When wing rotor（8）Exhibition
When opening, wing rotor（8）Rotary blade（81）Movement locus extend to rotor storehouse（6）Outside front side.
5. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：In wing slide plate preliminary roller
（904）Interior be provided with drives wing front slide（901）The preceding wind spring closed（906）；
In wing slide plate back roller（905）Interior be provided with drives wing tail skid（902）The rear wind spring closed（907）.
6. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：In every side wing（5）It is interior
Provided with 2 fuselage rotors（3）, wing left skateboard（910）It is provided with the left rack of wing slide plate（912）, the left rack of wing slide plate
（912）With wing slide plate Left Drive mechanism（914）Connection；
The right slide plate of wing（911）It is provided with the right rack of wing slide plate（913）, the right rack of wing slide plate（913）It is right with wing slide plate
Transmission mechanism（915）Connection；
Wing slide plate Left Drive mechanism（914）With the right transmission mechanism of wing slide plate（915）It is connected with motor.
7. a kind of fixed-wing unmanned plane of VTOL according to claim 1, it is characterized in that：In rotor storehouse（6）Bottom
Portion is provided with multiple louvre blades（7）, multiple louvre blades（7）Along rotor storehouse（6）Bottom wall fore-and-aft direction arrangement, described louvre blade
（7）In, blade（72）Pass through blinds bearing pin（71）With rotor storehouse（6）Connection, blade（72）Rear portion be provided with blade clinch
（73）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259173.4A CN105711831B (en) | 2016-04-25 | 2016-04-25 | The fixed-wing unmanned plane of VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610259173.4A CN105711831B (en) | 2016-04-25 | 2016-04-25 | The fixed-wing unmanned plane of VTOL |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105711831A CN105711831A (en) | 2016-06-29 |
| CN105711831B true CN105711831B (en) | 2018-03-06 |
Family
ID=56162100
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610259173.4A Expired - Fee Related CN105711831B (en) | 2016-04-25 | 2016-04-25 | The fixed-wing unmanned plane of VTOL |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105711831B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379543B (en) * | 2016-09-30 | 2019-06-25 | 顺丰科技有限公司 | The hanger and its stowage of vertical take-off and landing drone |
| CN108944307A (en) * | 2018-07-04 | 2018-12-07 | 天津超算科技有限公司 | Automobile aerocraft |
| CN109018331A (en) * | 2018-09-10 | 2018-12-18 | 观典防务技术股份有限公司 | It is capable of the VTOL fixed-wing unmanned plane of folding and unfolding rotor when a kind of cruise |
| JP6970479B1 (en) * | 2020-09-07 | 2021-11-24 | 株式会社エアロネクスト | Flying object |
| EP4212430A1 (en) * | 2020-09-07 | 2023-07-19 | Aeronext Inc. | Flying vehicle |
| CN112550695A (en) * | 2020-12-07 | 2021-03-26 | 北京航空航天大学 | Vertical take-off and landing wingtip hinged combined unmanned aerial vehicle |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| CN202481309U (en) * | 2012-02-01 | 2012-10-10 | 北京安翔动力科技有限公司 | Vector power vertical take-off and landing aircraft and vector power system thereof |
| CN202923886U (en) * | 2012-10-22 | 2013-05-08 | 夏金暑 | Plane with high safety |
| WO2016018486A2 (en) * | 2014-05-07 | 2016-02-04 | XTI Aircraft Company | Vtol aircraft |
| CN105015770A (en) * | 2015-07-29 | 2015-11-04 | 张飞 | Vertical take-off and landing aircraft with wing body blended with single duct |
| CN205098474U (en) * | 2015-11-18 | 2016-03-23 | 陈佳伟 | Duct formula aircraft that verts with VTOL function |
| CN107745810A (en) * | 2015-12-23 | 2018-03-02 | 钟水龙 | A kind of unmanned plane |
| CN105905294B (en) * | 2016-04-25 | 2018-05-01 | 北京中科遥数信息技术有限公司 | VTOL fixed-wing unmanned plane |
-
2016
- 2016-04-25 CN CN201610259173.4A patent/CN105711831B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105711831A (en) | 2016-06-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105905294B (en) | VTOL fixed-wing unmanned plane | |
| EP3464061B1 (en) | Propeller-hub assembly with folding blades for vtol aircraft | |
| US10293928B2 (en) | Devices and methods for in flight transition VTOL/fixed wing hybrid aircraft structures and flight modes | |
| CN105711831B (en) | The fixed-wing unmanned plane of VTOL | |
| US4469294A (en) | V/STOL Aircraft | |
| JP6191039B2 (en) | VTOL machine | |
| US8733690B2 (en) | Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials | |
| EP3119673B1 (en) | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades | |
| US4828203A (en) | Vertical/short take-off and landing aircraft | |
| US4116405A (en) | Airplane | |
| US9004393B2 (en) | Supersonic hovering air vehicle | |
| US20110031355A1 (en) | Aircraft with dual flight regimes | |
| CN108698690A (en) | UAV with the wing plate component for providing effective vertical takeoff and throwing power | |
| EP2625098A1 (en) | Aircraft with wings and movable propellers | |
| EP3609783A1 (en) | Vertical takeoff and landing aircraft | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN109319112A (en) | It is a kind of to be vertically moved up or down fixed wing aircraft with balance mechanism | |
| US10464667B2 (en) | Oblique rotor-wing aircraft | |
| GB2504369A (en) | Aircraft wing with reciprocating outer aerofoil sections | |
| CN206520752U (en) | Double mode rotary wing aircraft based on folding wing | |
| CN206327567U (en) | A kind of compound unmanned vehicle | |
| CN110510116A (en) | Rotor and vector propulsion system combined type aircraft | |
| CN108128449A (en) | Double mode rotary wing aircraft based on folding wing | |
| CN211996136U (en) | Rotor and vector propulsion system combined aircraft | |
| KR20220137628A (en) | convertible airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180306 |