CN105711831A - Vertical take-off and landing type fixed-wing unmanned aerial vehicle - Google Patents
Vertical take-off and landing type fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN105711831A CN105711831A CN201610259173.4A CN201610259173A CN105711831A CN 105711831 A CN105711831 A CN 105711831A CN 201610259173 A CN201610259173 A CN 201610259173A CN 105711831 A CN105711831 A CN 105711831A
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- 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
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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Abstract
The invention provides a vertical take-off and landing type fixed-wing unmanned aerial vehicle. The vertical take-off and landing type fixed-wing unmanned aerial vehicle comprises a vehicle body, wherein a forwarding drive is arranged on the vehicle body, wings are arranged at two sides of the vehicle body, a foldable vehicle body rotor wing is arranged in the vehicle body, vehicle body sliding plates are arranged at two sides of the foldable vehicle body rotor wing, a plurality of foldable rotor wings of the wing are arranged in the wing, and an openable wing sliding plate device is arranged at the top part of the rotor wing of the wing. With adoption of the above structure, the vertical take-off and landing type fixed-wing unmanned aerial vehicle has the following beneficial effects that the forwarding drive and the vehicle body rotor wing are combined with the rotor wings of the wing to conveniently realize switching between the vertical take-off and landing mode and the fixed wing flight mode; the unmanned aerial vehicle can hover at any time when performing a task so as to make a camera observe at a fixed point, and does not require a runway and ejection equipment when taking off and landing; the vehicle body rotor wing is combined with the rotor wings of the wing to conveniently control the balance of the whole vehicle; the hidden vehicle body rotor wing and the rotor wings of the wing are adopted to make no interference between the vertical take-off and landing mode and the fixed wing flight mode, and the volume of the wing is not required to be increased; and the air stream 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 airplane of VTOL, this kind of aircraft has the function similar to helicopter, need not by runway just can vertical and landing takeoff, the difference is that, this kind of aircraft aloft can be verted the flat offline mode flying acceleration and being transitioned into fixed-wing from floating state by power.For unmanned plane, the fixed-wing scheme of VTOL can make unmanned plane drop to precalculated position, and after completing setting task, automatic takeoff returns, and makes the fixed-wing unmanned plane of VTOL have and unrivaled automatically controls advantage.
At present, practical VTOL fixed wing airplane is mainly AV-8 sparrow hawk formula fighter plane, V-22 osprey tilt rotor aircraft, F-35 opportunity of combat.What AV-8 sparrow hawk formula opportunity of combat adopted is flying horse electromotor, have employed the rotatable thrust vectoring scheme of ejector exhaust pipe on jet engine basis, and in actual use, integrity problem often occurs in this type aircraft, is also referred to as " widow's aircraft ".V-22 osprey formula tiltrotor is a tiltrotor manufactured by American Bell Incorporated and Boeing's co-design, is also a medium transport aircraft.It realizes rotor conversion between vertically and horizontally by two lifting airscrews of tilting wing two ends wing tip, thus more ideally the feature of helicopter and fixed wing airplane being combined together.Under VTOL state, two rotor thrust directions are perpendicular to ground, utilize the attitude stabilization that auto-bank unit keeps body longitudinal.V-22 osprey had both had the ability of pure helicopter VTOL and hovering, had again the ability of the high speed cruise flight of turboprop aircraft, was a kind of dual-use new high-tech product.At present, it is mainly used in military requirement, and can give battleficld command official and more select and greater flexibility.It does not need special airport and runway, easy to maintenance, and viability is strong, is particularly well-suited to carry out special operations, is greatly improved military personnel and delivers, deploys troops on garrison duty, hostile takedown, the speed of the action such as disaster relief.
But, owing to V-22 osprey have employed two lifting airscrews, under VTOL pattern, rotor needs auto-bank unit to control stablizing of attitude of flight vehicle, adds the difficulty of control, and blade adopts feathering device, too increases cost；And osprey is under VTOL pattern, the positive top blast of rotor slip-stream, on aerofoil surface, causes very big pressure drag to lose, and forces wing to increase structural strength, and then causes that Flight Vehicle Structure weight increases, and reduces the performance of aircraft.
Chinese patent literature CN105083550A discloses a kind of VTOL Fixed Wing AirVehicle, including fuselage, empennage and the power set with inclining rotary mechanism, the described power set with inclining rotary mechanism include fixedpiston propeller, electromotor, enging cabin, slip-stream rudder, wing, tilting wing and steering wheel, electromotor is installed in enging cabin, fixedpiston propeller is connected with the output shaft of electromotor, tilting wing one end is fixedly connected on enging cabin, the other end is rotatablely connected with on wing, slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving, the described power set with inclining rotary mechanism are symmetricly set in fuselage both sides, and be horizontally disposed with for wing, described fuselage head is provided with through hole, ducted fan is set in through hole.Aircraft rotor of the present invention and aircraft smaller, and save auto-bank unit and feathering device, the simple in construction of complexity, reducing the difficulty of trim and the complexity of flight control system, system reliability is high, cost is low.
But for unmanned plane, this structure is still excessively complicated, and for reaching the rigidity with practicality, requires too high for structure precision and material stiffness, and holistic cost is higher, and organism balance is difficult to control to.
In prior art, also there is the scheme being embedded in wing by rotor, in the program, being provided with very large wing on body, wing is provided with the through hole of up/down perforation, and rotor is arranged in through hole, program rotor takes up room greatly, and the air fluid lifting efficiency of wing is undesirable, and body is also comparatively heavy.
Summary of the invention
The technical problem to be solved is to provide the fixed-wing unmanned plane of a kind of VTOL, has VTOL concurrently and is prone to remote-operated advantage and fixed-wing is easy to the feature of high speed cruise flight and simple in construction, it is easy to accomplish, it is simple to control the balance of fuselage.
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: the fixed-wing unmanned plane of a kind of VTOL, including fuselage, is provided with wing in the both sides of fuselage, and rotor before fuselage front is provided with is provided with folding fuselage rotor in fuselage；It is provided with fuselage slide plate in the both sides of fuselage rotor；
Being provided with multiple folding wing rotor in wing, the front of wing rotor and top are provided with can the wing skate apparatus of folding.
Described fuselage rotor and the structure of wing rotor be:
Rotary blade is pivotally connected with rotor seat by bearing pin, and rotor seat is fixing with the output shaft of rotor motor to be connected.
Upon deployment, the movement locus of the rotary blade of fuselage rotor extends to outside the sidewall of fuselage both sides described fuselage rotor.
The structure of fuselage slide plate is, slide plate is movably arranged on the sidewall of fuselage both sides, and can along fuselage both sides side walls, and slide plate inwall is installed with tooth bar, and fuselage sled motor is connected with tooth bar by fuselage slide plate drive mechanism.
Being provided with 1 ~ 4 wing rotor in the wing of every side, wing rotor is arranged in rotor storehouse, and the upside in rotor storehouse and front side are open, and bottom side, the left and right sides and rear side are closed, and wing rotor is installed in the diapire in rotor storehouse.
When wing rotor launches, the movement locus of the rotary blade of wing rotor extends to outside on front side of rotor storehouse.
Described wing skate apparatus includes wing front slide and the wing tail skid of relative sliding；
The both sides of wing front slide are positioned at the wing operating slide guideway rail being installed in rotor storehouse sidewall, and wing front slide one end is connected with wing slide plate preliminary roller, and wing slide plate preliminary roller is connected with driving device, and the other end of wing front slide is provided with wing slide plate clinch；
The both sides of wing tail skid are positioned at the wing operating slide guideway rail being installed in rotor storehouse sidewall, and wing tail skid is connected with wing slide plate back roller, and wing slide plate back roller is connected with driving device.
It is provided with in wing slide plate preliminary roller and orders about the front wind spring that wing front slide is closed；
It is provided with in wing slide plate back roller and orders about the rear wind spring that wing tail skid is closed.
Being provided with 2 fuselage rotors in the wing of every side, wing left skateboard is provided with the left tooth bar of wing slide plate, and the left tooth bar of wing slide plate is connected with wing slide plate Left Drive mechanism；
The right slide plate of wing is provided with the right tooth bar of wing slide plate, and the right tooth bar of wing slide plate is connected with the right drive mechanism of wing slide plate；
Wing slide plate Left Drive mechanism and the right drive mechanism of wing slide plate are connected with drive motor.
Be provided with multiple louvre blade in the bottom in rotor storehouse, multiple louvre blades are arranged along rotor storehouse diapire fore-and-aft direction, and in described louvre blade, blade is connected with rotor storehouse by BAIYE bearing pin, and the rear portion of blade is provided with blade clinch.
The fixed-wing unmanned plane of a kind of VTOL provided by the invention, by adopting above structure, has following beneficial effect:
1, the combination of row cutting and fuselage rotor and wing rotor before adopting, it is simple to realize the switching between VTOL and fixed-wing flight, it is thus achieved that the convenience of VTOL and the flight speed of fixed-wing.The thus unmanned plane of structure, it is simple to hover at any time when performing task, in order to camera energy fixed point observation, takes off when landing without runway and ejection device simultaneously.
2, the combination of fuselage rotor and wing rotor is adopted, it is simple to control the balance of whole body.
3, adopt concealed fuselage rotor and wing rotor, make not interfere between VTOL pattern and fixed-wing offline mode, it is not necessary to increase the volume of wing.Air fluid lifting efficiency is high.
4, terminal with compact integral structure, it is easy to accomplish and manufacture, it is simple to control, it is possible to reduce production cost.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the invention will be further described:
Fig. 1 is the perspective view during VTOL state in the present invention.
Fig. 2 is the perspective view during fixed-wing state of flight in the present invention.
Fig. 3 is the plan structure schematic diagram of fuselage slide plate in the present invention.
Fig. 4 is the plan structure schematic diagram of fuselage rotor and wing rotor in the present invention.
Fig. 5 is the structural representation of wing skate apparatus in the present invention.
Fig. 6 is the close-up schematic view at A place in Fig. 5.
Fig. 7 is the partial structurtes schematic diagram of wing skate apparatus in the present invention.
Fig. 8 is another perspective view during 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 structurtes schematic 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, tooth bar 42, fuselage sled motor 43, fuselage slide plate drive mechanism 44, wing 5, rotor storehouse 6, louvre blade 7, BAIYE bearing pin 71, blade 72, blade clinch 73, wing rotor 8, rotary blade 81, bearing pin 82, rotor seat 83, rotor motor 84, wing skate apparatus 9, wing front slide 901, wing tail skid 902, wing operating slide guideway rail 903, wing slide plate preliminary roller 904, wing slide plate back roller 905, front wind spring 906, rear wind spring 907, disjunction place 908, wing slide plate clinch 909, wing left skateboard 910, the right slide plate 911 of wing, the left tooth bar 912 of wing slide plate, the right tooth bar 913 of wing slide plate, wing slide plate Left Drive mechanism 914, the right drive mechanism 915 of wing slide plate, front rotor 10.
Detailed description of the invention
In the present invention, illustrating with the orientation of body 1, namely for Fig. 1, the head of body 1 is front, and afterbody is rear, and body 1 top is top.Accompanying drawing in the present invention is schematic diagram, for ease of observing, eliminates part supplementary structure, only prominent part-structure related to the present invention, for the part-structure indicated especially, for structure conventional in prior art.
Such as Fig. 1, in 2, the fixed-wing unmanned plane of a kind of VTOL, including fuselage 2, it is provided with wing 5 in the both sides of fuselage 2, rotor 10 before fuselage 2 front is provided with, or it is located at below wing or the rotor in front, or it is located at turbogenerator below wing.
Folding fuselage rotor 3 it is provided with in fuselage 2；It is provided with fuselage slide plate 4 in the both sides of fuselage rotor 3；
Being provided with multiple folding wing rotor 8 in wing 5, the front of wing rotor 8 and top are provided with can the wing skate apparatus 9 of folding.Combination by fuselage rotor 3 and wing rotor 8, whole body 1 is made to obtain the lifting force of vertical lift, and when completing vertical lift to after predetermined altitude, row cutting before starting, then fuselage rotor 3 and wing rotor 8 is made to pack up, fuselage slide plate 4 and wing skate apparatus 9 are closed, and namely complete the conversion between flight from vertical lift to fixed-wing.During landing, open fuselage slide plate 4 and wing skate apparatus 9, start fuselage rotor 3 and wing rotor 8, it is achieved vertical landing.
In preferred scheme such as Fig. 4, described fuselage rotor 3 and the structure of wing rotor 8 be:
Rotary blade 81 is pivotally connected with rotor seat 83 by bearing pin 82, and rotor seat 83 is fixing with the output shaft of rotor motor 84 to be connected.When rotor motor 84 starts, rotary blade 81 opens under the influence of centrifugal force, and obtains lifting force, and when rotor motor 84 stops, rotary blade 81 folds under the action of the forces of the wind, consequently facilitating income is in fuselage 2 and in the rotor storehouse 6 of wing 5.Thus structure reduces the space requirement of fuselage rotor 3 and wing rotor 8.
In preferred scheme such as Fig. 1, upon deployment, the movement locus of the rotary blade 81 of fuselage rotor 3 extends to outside the sidewall of fuselage 2 both sides described fuselage rotor 3.Thus structure, makes fuselage rotor 3 obtain enough lifting forces, and required space is little.
In preferred scheme such as Fig. 3, the structure of fuselage slide plate 4 is, slide plate 41 is movably arranged on the sidewall of fuselage 2 both sides, and can along fuselage 2 both sides side walls, slide plate 41 inwall is installed with tooth bar 42, and fuselage sled motor 43 is connected with tooth bar 42 by fuselage slide plate drive mechanism 44.Fuselage slide plate drive mechanism 44 in this example is preferably decelerator and gear, it is specially fuselage sled motor 43 to be connected with decelerator, the output shaft of decelerator is fixing with gear to be connected, wheel and rack 42 engagement connects, by controlling the rotating of fuselage sled motor 43, control the folding of slide plate 41, by the folding of slide plate 41, the rotary blade 81 making fuselage rotor 3 is easy to be stretched over outside the sidewall of fuselage 2, thus obtaining enough lifting forces.
In preferred scheme such as Fig. 1 ~ 2,1 ~ 4 wing rotor 8 it is provided with in every side wing 5, this example arranges 2 wing rotors 8 in every side wing 5, wing rotor 8 is arranged in rotor storehouse 6, the upside in rotor storehouse 6 and front side are open, bottom side, the left and right sides and rear side are closed, and wing rotor 8 is installed in the diapire in rotor storehouse 6.The rotor motor 84 of concrete wing rotor 8 is fixedly mounted on the diapire position near front side in rotor storehouse 6, and so when rotor motor 84 drives rotary blade 81 to launch because of rotation, the movement locus of the rotary blade 81 of wing rotor 8 extends to outside on front side of rotor storehouse 6.Thus structure, it is thus achieved that bigger lifting force, and take less space, it is not necessary to wing design is become heavy structure.
Optional scheme such as Fig. 5, in 7, described wing skate apparatus 9 includes wing front slide 901 and the wing tail skid 902 of relative sliding；
The both sides of wing front slide 901 are positioned at the wing operating slide guideway rail 903 being installed in rotor storehouse 6 sidewall, wing front slide 901 one end is connected with wing slide plate preliminary roller 904, wing slide plate preliminary roller 904 is connected with driving device, it is preferred that scheme such as Fig. 7 in, the other end at wing front slide 901 is provided with wing slide plate clinch 909；
The both sides of wing tail skid 902 are positioned at the wing operating slide guideway rail 903 being installed in rotor storehouse 6 sidewall, wing tail skid 902 is connected with wing slide plate back roller 905, wing slide plate back roller 905 is connected with driving device, driving device in this example is motor and drive mechanism, motor is connected with drive mechanism, drive mechanism is connected with wing slide plate back roller 905, drives wing slide plate back roller 905 to rotate.The type of drive of wing slide plate preliminary roller 904 is identical.Thus structure, wing slide plate preliminary roller 904 and wing slide plate back roller 905 drive wing front slide 901 and wing tail skid 902 folding, and combine in disjunction place 908.Disjunction place 908 selects the position that Airfoil Sections curvilinear motion is bigger.In this example, the length of wing tail skid 902 is more than the length of wing front slide 901, in order to control the mechanical strength of wing tail skid 902 and wing front slide 901.In this example, wing tail skid 902 and wing front slide 901 adopt the material with flexibility, for instance almag plate, titanium alloy sheet or nylon and titanium alloy composite panel.Owing to the both sides of wing tail skid 902 and wing front slide 901 are supported by wing operating slide guideway rail 903, therefore there is enough intensity, as required, it is also possible to the strengthening muscle along wing slide plate preliminary roller 904 and wing slide plate back roller 905 axis is set in the bottom surface of wing tail skid 902 and wing front slide 901.
The wing slide plate clinch 909 arranged is the stage bent upward, makes the overlap joint between wing tail skid 902 and wing front slide 901 more reliable, also enhances the intensity of wing front slide 901 simultaneously.
It is provided with in wing slide plate preliminary roller 904 and orders about the front wind spring 906 that wing front slide 901 is closed；
It is provided with in wing slide plate back roller 905 and orders about the rear wind spring 907 that wing tail skid 902 is closed.Thus structure, it is possible to quickly from vertical lift State Transferring to fixed-wing state of flight, shortens the conversion time, improves the safety of body 1.
In another optional structure such as Fig. 8 ~ 9, being provided with 2 fuselage rotors 3 in every side wing 5, wing left skateboard 910 is provided with the left tooth bar 912 of wing slide plate, and the left tooth bar 912 of wing slide plate is connected with wing slide plate Left Drive mechanism 914；
The right slide plate of wing 911 is provided with the right tooth bar 913 of wing slide plate, and the right tooth bar of wing slide plate 913 is connected with the right drive mechanism 915 of wing slide plate；
Wing slide plate Left Drive mechanism 914 and the right drive mechanism 915 of wing slide plate are connected with drive motor.Thus structure, in the way of horizontally slipping, opens upside and the front side in rotor storehouse 6.Be suitable to the unmanned plane of wing 5 space enlarged relative.Owing to wing 5 is thinning gradually from wing root to the thickness of wing tip, therefore wing left skateboard 910 and the right slide plate 911 of wing are when opening rotor storehouse 6, it is possible to by the layout of stacked on top.
It is preferred that structure such as Figure 10 in, by by the end being arranged on wing left skateboard 910 vertical for left for wing slide plate tooth bar 912, what wing slide plate right tooth bar 913 was vertical is positioned close to the position of wing right slide plate 911 end, the left tooth bar of wing slide plate 912 is positioned opposite with the tooth of the right tooth bar of wing slide plate 913, thus structure, it is possible to simultaneously driven wing left skateboard 910 and wing right slide plate 911 action by a gear.
Preferred scheme such as Fig. 5, in 6, multiple louvre blade 7 it is provided with in the bottom in rotor storehouse 6, multiple louvre blades 7 are arranged along rotor storehouse 6 diapire fore-and-aft direction, and in described louvre blade 7, blade 72 is connected with rotor storehouse 6 by BAIYE bearing pin 71, the rear portion of blade 72 is provided with blade clinch 73, blade clinch 73 is the stage portion of a downward bending, so that preceding blade 72 is overlapped on the end of posterior blade 72, forms the structure of similar fish scale, to reduce windage, and reinforced structure.Louvre blade 7 is positioned at position forward in the middle of louvre blade 7 with the link position of BAIYE bearing pin 71, so that by default, louvre blade 7 is in the state of unlatching.Thus structure, it is simple to make air discharge from louvre blade 7 under vertical lift state, and when proceeding to fixed-wing offline mode, then in the effect of wind-force, each louvre blade 7 overlaps, it is provided that lifting force.
During use, wing skate apparatus 9 and fuselage slide plate 4 are opened, and fuselage rotor 3 and wing rotor 8 rotate, and the wind that wing rotor 8 produces is discharged from louvre blade 7, body 1 is made to rise, after leaving ground certain altitude, front rotor 10 starts, and makes body 1 flight forward, it is gradually lowered the rotating speed of fuselage rotor 3 and wing rotor 8 until stopping, fuselage rotor 3 and wing rotor 8 are folding under wind-force effect, close wing skate apparatus 9 and fuselage slide plate 4, and body 1 proceeds 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 lowered the rotating speed of front rotor 10 until stopping, and body 1 enters floating state, make whole body 1 transfer vertical lift state to from fixed-wing flight until landing.
The above embodiments are only the preferred technical solution of the present invention, and are not construed as the restriction for the present invention, and the embodiment in the application and the feature in embodiment be not when conflicting, it is possible to combination in any mutually.The technical scheme that protection scope of the present invention should be recorded with claim, is protection domain including the equivalents of technical characteristic in the technical scheme that claim is recorded.Namely equivalent replacement the within the scope of this is improved, also within protection scope of the present invention.
Claims (10)
1. a fixed-wing unmanned plane for VTOL, including fuselage (2), is provided with wing (5) in the both sides of fuselage (2), is provided with front rotor (10) in fuselage (2) front, it is characterized in that: be provided with folding fuselage rotor (3) in fuselage (2)；It is provided with fuselage slide plate (4) in the both sides of fuselage rotor (3)；
Being provided with multiple folding wing rotor (8) in wing (5), the front of wing rotor (8) and top are provided with can the wing skate apparatus (9) of folding.
2. the fixed-wing unmanned plane of a kind of VTOL according to claim 1, is characterized in that: described fuselage rotor (3) and the structure of wing rotor (8) be:
Rotary blade (81) is pivotally connected with rotor seat (83) by bearing pin (82), and rotor seat (83) is fixing with the output shaft of rotor motor (84) to be connected.
3. the fixed-wing unmanned plane of a kind of VTOL according to claim 1, is characterized in that: upon deployment, the movement locus of the rotary blade (81) of fuselage rotor (3) extends to outside the sidewall of fuselage (2) both sides described fuselage rotor (3).
4. the fixed-wing unmanned plane of a kind of VTOL according to claim 1, it is characterized in that: the structure of fuselage slide plate (4) is, slide plate (41) is movably arranged on the sidewall of fuselage (2) both sides, and can along fuselage (2) both sides side walls, slide plate (41) inwall is installed with tooth bar (42), and fuselage sled motor (43) is connected with tooth bar (42) by fuselage slide plate drive mechanism (44).
5. the fixed-wing unmanned plane of a kind of VTOL according to claim 1, it is characterized in that: in every side wing (5), be provided with 1 ~ 4 wing rotor (8), wing rotor (8) is arranged in rotor storehouse (6), the upside in rotor storehouse (6) and front side are open, bottom side, the left and right sides and rear side are closed, and wing rotor (8) is installed in the diapire of rotor storehouse (6).
6. the fixed-wing unmanned plane of a kind of VTOL according to claim 5, is characterized in that: when wing rotor (8) launches, and the movement locus of the rotary blade (81) of wing rotor (8) extends to outside front side, rotor storehouse (6).
7. the fixed-wing unmanned plane of a kind of VTOL according to claim 5, is characterized in that: described wing skate apparatus (9) includes wing front slide (901) and the wing tail skid (902) of relative sliding；
The both sides of wing front slide (901) are positioned at the wing operating slide guideway rail (903) being installed in rotor storehouse (6) sidewall, wing front slide (901) one end is connected with wing slide plate preliminary roller (904), wing slide plate preliminary roller (904) is connected with driving device, and the other end of wing front slide (901) is provided with wing slide plate clinch (909)；
The both sides of wing tail skid (902) are positioned at the wing operating slide guideway rail (903) being installed in rotor storehouse (6) sidewall, and wing tail skid (902) is connected with wing slide plate back roller (905), and wing slide plate back roller (905) is connected with driving device.
8. the fixed-wing unmanned plane of a kind of VTOL according to claim 5, is characterized in that: is provided with in wing slide plate preliminary roller (904) and orders about the front wind spring (906) that wing front slide (901) is closed；
It is provided with in wing slide plate back roller (905) and orders about the rear wind spring (907) that wing tail skid (902) is closed.
9. the fixed-wing unmanned plane of a kind of VTOL according to claim 1, it is characterized in that: in every side wing (5), be provided with 2 fuselage rotors (3), wing left skateboard (910) is provided with the left tooth bar of wing slide plate (912), and the left tooth bar of wing slide plate (912) is connected with wing slide plate Left Drive mechanism (914)；
The right slide plate of wing (911) is provided with the right tooth bar of wing slide plate (913), and the right tooth bar of wing slide plate (913) is connected with the right drive mechanism of wing slide plate (915)；
Wing slide plate Left Drive mechanism (914) and the right drive mechanism of wing slide plate (915) are connected with drive motor.
10. the fixed-wing unmanned plane of a kind of VTOL according to claim 5, it is characterized in that: be provided with multiple louvre blade (7) in the bottom of rotor storehouse (6), multiple louvre blades (7) are arranged along rotor storehouse (6) diapire fore-and-aft direction, in described louvre blade (7), blade (72) is connected with rotor storehouse (6) by BAIYE bearing pin (71), and the rear portion of blade (72) is provided with blade clinch (73).
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| CN201610259173.4A CN105711831B (en) | 2016-04-25 | 2016-04-25 | The fixed-wing unmanned plane of VTOL |
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| CN201610259173.4A CN105711831B (en) | 2016-04-25 | 2016-04-25 | The fixed-wing unmanned plane of VTOL |
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| CN105711831A true CN105711831A (en) | 2016-06-29 |
| CN105711831B CN105711831B (en) | 2018-03-06 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106379543A (en) * | 2016-09-30 | 2017-02-08 | 顺丰科技有限公司 | Hanging rack of vertical take-off and landing unmanned plane and loading method of hanging rack |
| 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 |
| 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 |
| JP6970479B1 (en) * | 2020-09-07 | 2021-11-24 | 株式会社エアロネクスト | Flying object |
| JPWO2022049764A1 (en) * | 2020-09-07 | 2022-03-10 | ||
| CN117906897A (en) * | 2024-03-18 | 2024-04-19 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
| CN117906897B (en) * | 2024-03-18 | 2024-06-11 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
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| 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 |
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| CN105015770A (en) * | 2015-07-29 | 2015-11-04 | 张飞 | Vertical take-off and landing aircraft with wing body blended with single duct |
| CA2947974A1 (en) * | 2014-05-07 | 2016-02-04 | XTI Aircraft Company | Vtol aircraft |
| CN205098474U (en) * | 2015-11-18 | 2016-03-23 | 陈佳伟 | Duct formula aircraft that verts with VTOL function |
| CN105501440A (en) * | 2015-12-23 | 2016-04-20 | 徐洪恩 | Unmanned aerial vehicle |
| CN105905294A (en) * | 2016-04-25 | 2016-08-31 | 荆州翔天科技有限公司 | Vertical take-off and landing fixed-wing unmanned aerial vehicle |
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- 2016-04-25 CN CN201610259173.4A patent/CN105711831B/en not_active Expired - Fee Related
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| 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 |
| 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 |
| CN202923886U (en) * | 2012-10-22 | 2013-05-08 | 夏金暑 | Plane with high safety |
| CA2947974A1 (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 |
| CN105501440A (en) * | 2015-12-23 | 2016-04-20 | 徐洪恩 | Unmanned aerial vehicle |
| CN105905294A (en) * | 2016-04-25 | 2016-08-31 | 荆州翔天科技有限公司 | Vertical take-off and landing fixed-wing unmanned aerial vehicle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379543A (en) * | 2016-09-30 | 2017-02-08 | 顺丰科技有限公司 | Hanging rack of vertical take-off and landing unmanned plane and loading method of hanging rack |
| 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 |
| JPWO2022049764A1 (en) * | 2020-09-07 | 2022-03-10 | ||
| 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 |
| CN117906897A (en) * | 2024-03-18 | 2024-04-19 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
| CN117906897B (en) * | 2024-03-18 | 2024-06-11 | 西安羚控电子科技有限公司 | Simulated wind load control method and system of wing folding driving device |
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| CN105711831B (en) | 2018-03-06 |
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