CN105564641A - Vector aircraft - Google Patents
Vector aircraft Download PDFInfo
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- CN105564641A CN105564641A CN201610067048.3A CN201610067048A CN105564641A CN 105564641 A CN105564641 A CN 105564641A CN 201610067048 A CN201610067048 A CN 201610067048A CN 105564641 A CN105564641 A CN 105564641A
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- tailspin
- power unit
- duct power
- flight vector
- preamble
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- 230000001360 synchronised effect Effects 0.000 claims abstract description 39
- 238000009434 installation Methods 0.000 claims description 23
- 238000010586 diagram Methods 0.000 description 8
- 230000002153 concerted effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
- Toys (AREA)
Abstract
The invention provides a vector aircraft, comprising: a body; the rear power device comprises two rear duct power units; the two rear duct power units are respectively hinged to the left side and the right side of the rear half part of the fuselage; the rear synchronous mechanism comprises a rear synchronous steering engine, a rear synchronous swing arm and two rear synchronous connecting rods; the starting end of the rear synchronous swing arm is connected with the rear synchronous steering engine, and the tail end of the rear synchronous swing arm is hinged with the starting ends of the two rear synchronous connecting rods; the tail ends of the two rear synchronous connecting rods are respectively hinged with the two rear duct power units. According to the invention, the rotation angle of the rear duct power unit is controlled through the rear synchronization mechanism, so that the rear duct power unit can incline at a certain angle to generate a horizontal component force, thereby realizing yawing, and the yawing does not need to incline the aircraft body, does not increase the flight resistance, and ensures the flexibility of the flying.
Description
Technical field
The present invention relates to a kind of flight vector device.
Background technology
Four-axle aircraft is a kind of Multi-axis aircraft with four rotors, also known as quadrotor, four-rotor helicopter, is called for short four axles, four rotors.
Chinese patent 200920318470.7 discloses one and can to vert quadrotor, be included in aircraft body and be provided with wing and some floors, tiliting axis and rear tiliting axis before being provided with in the floor strengthened before and after wing, front tiliting axis is connected with wheel word with rear tiliting axis, by connecting rod associated synchronisation, the two ends of front tiliting axis are separately installed with 1# power pack, 2# power pack, the two ends of rear tiliting axis are separately installed with 3# power pack, 4# power pack, 1# power pack, 2# power pack, 3# power pack, 4# power pack is provided with a set of rotor separately, each adjacent rotor hand of rotation is contrary between two, 1# power pack, the rotor wing rotation of 2# power pack is in same plane, 3# power pack, the rotor wing rotation of 4# power pack is in same plane.
Chinese patent application 201310310717.1 discloses a kind of quadrotor, it comprises body, avionics system, take-off and landing device, working load module, be connected with avionics system the driver element of four hold-down arms angularly launching along the axial surrounding of body center and end thereof, hold-down arm and 0 ° < α < 90 ° equal with body center's axle clamp angle, hold-down arm xoy plane be projected as rotational symmetry intersect two straight lines, driver element lays respectively in four quadrants or x in the projection of xoy plane, on the positive and negative semiaxis of y, the rotation axis of driver element becomes angle theta with z-axis respectively in the projection of yoz or xoz plane,-65 °≤θ≤65 °, do not comprise 0, the rotation axis of driver element is vertical in the projection of xoy plane to the line of body axis system initial point with centre of gration in the projection of xoy plane.
Chinese patent application 201410558617.5 discloses a kind of quadrotor, comprise fuselage, the front end of fuselage is symmetrically installed with first, second rotor, the rear end of fuselage is symmetrically installed with the 3rd, the 4th rotor, first, second, third, fourth rotor difference one is connected with brshless DC motor, brshless DC motor connects a machine governor respectively, and machine governor regulates the rotating speed of brshless DC motor; Machine governor is all connected with a flight controller, and flight controller controls the adjustment of machine governor; Also comprise angular velocity sensor and angular transducer, angular velocity sensor is connected with line control unit respectively with angular transducer.
Above-mentioned the deficiencies in the prior art part is, existing four-axle aircraft usually adopts screw propeller and is fixed in same working face space, and the air-flow causing screw propeller to produce is constant across face, and flight course turnover is to dumb, poor stability, turns to flight resistance larger.
Summary of the invention
For prior art Problems existing, object of the present invention provides that a kind of dogled is flexible, safety is high, possess the flight vector device of good manoevreability and stability.
To achieve these goals, the invention provides a kind of flight vector device, this flight vector device comprises:
Fuselage;
Rear engine installation, duct power unit after it comprises two; After two, duct power unit is articulated with the latter half of left and right sides of fuselage respectively;
Rear synchronizer gear, after being driven by connecting rod, duct power unit is verting perpendicular to the plane inter-sync along fuselage fore-and-aft direction.
In the present invention, one end (top) of rear synchronous swing arm is rotated by rear synchronous servo driving, the other end (end) with two after synchronising (connecting) rod hinged.When rear synchronous steering wheel rotates, after two synchronising (connecting) rod synchronous left or synchronous to the right, duct power unit left avertence or right avertence simultaneously simultaneously after driving two, to realize going off course.It should be noted that, rear synchronous steering wheel is used for realizing left and right non-symmetrical synchronous (i.e. left avertence or simultaneously right avertence simultaneously), and preamble steering wheel is hereinafter used for realizing symmetrical synchronously (such as one to left avertence another to right avertence).
In the present invention, after two, the angle of duct power unit in the vertical direction deflection can be the scope of positive and negative 8 degree.Such as, flight vector device left-handed turning to time, duct power unit negative 8 degree deflections simultaneously after rear synchronous steering wheel makes two, the horizontal wind-force realization produced left is gone off course.
In the present invention, the inclination of rear duct power unit is mainly in order to realize driftage, and secondly in order to overcome some natural cause as flight effect more stable under high wind, but rear duct power unit is in vertical direction, and it is most effective.
According to another detailed description of the invention of the present invention, rear synchronizer gear comprises rear synchronous steering wheel, rear synchronous swing arm, synchronising (connecting) rod after two; The top of rear synchronous swing arm connects described rear synchronous steering wheel, and after the end of rear synchronous swing arm and two, the top of synchronising (connecting) rod is hinged; After two the end of synchronising (connecting) rod respectively with two after duct power unit hinged.
According to another detailed description of the invention of the present invention, rear duct power unit is articulated with on fuselage by erecting frame; After two the end of synchronising (connecting) rod respectively with two after the erecting frame of duct power unit hinged.
According to another detailed description of the invention of the present invention, fuselage comprises frame and tailspin plate; Tailspin plate is positioned at the rear end of frame, and hinged with frame.Like this, tailspin plate can depart from horizontal direction relative to frame and rotates to an angle (such as, about horizontal direction rotate 45 degree).
According to another detailed description of the invention of the present invention, rear synchronizer gear is arranged on tailspin plate, and after two, duct power unit is articulated with the left and right sides of tailspin plate respectively.Like this, rear duct power unit can depart from horizontal direction and rotate to an angle (such as, rotating 45 degree after taking off about horizontal direction), flies to accelerate flight vector device, the stability of maintenance and manoevreability.
According to another detailed description of the invention of the present invention, flight vector device comprises tailspin control mechanism further, and tailspin control mechanism comprises tailspin steering wheel, tailspin swing arm, tailspin connecting rod; The top of tailspin swing arm connects tailspin steering wheel, the end of tailspin swing arm and the top of tailspin connecting rod hinged; The end tailspin plate of tailspin connecting rod is hinged.In this tailspin control mechanism, three shaft parallels that three places are hinged.The swing arm of tailspin servo driving tailspin swings, and then drives tailspin plate to rotate by tailspin connecting rod.
According to another detailed description of the invention of the present invention, flight vector device comprises front engine installation further, and front engine installation comprises two front duct power units; Two front duct power units are connected to the left and right sides of fuselage forebody.Front duct power unit is verted and can be driven by screw body.
According to another detailed description of the invention of the present invention, flight vector device comprises preamble mechanism further; Preamble mechanism comprises preamble steering wheel, preamble rocking arm, two preamble connecting rods; The center of preamble rocking arm connects preamble steering wheel, and the two ends of preamble rocking arm are hinged with the top of two preamble connecting rods respectively; The end of two preamble connecting rods respectively with two front duct power unit hinged.The center of preamble rocking arm is rotated by preamble servo driving, its two ends and two preamble rod hinge connections.When current sync steering wheel rotates, after two, synchronising (connecting) rod is synchronous outwards or synchronously inside, drives two front duct power units to deflect (such as one to left avertence another to right avertence) symmetrically.
According to another detailed description of the invention of the present invention, preamble connecting rod comprises: steering wheel connecting rod, transfer rocking arm, duct connecting rod; The center of transfer rocking arm is articulated on fuselage; The head end of steering wheel connecting rod is articulated with the end of preamble rocking arm; Steering wheel connecting rod, transfer rocking arm, duct connecting rod are hinged end to end; The end of two duct connecting rods respectively with two front duct power unit hinged.When current sync steering wheel rotates, two steering wheel connecting rods are synchronous outwards or synchronously inside, and then drive two transfer rocking arms to deflect symmetrically, and then drive two front duct power units to deflect symmetrically by two duct connecting rods.
Adopt independent synchronising (connecting) rod can take more fuselage space, synchronising (connecting) rod is become the relation of many anatomical connectivity, can taking fuselage be reduced, make more compact structure, differentiation on the whole stressed, improve parts by force intensity.
Front duct power unit can be the scope of positive and negative 8 degree at the deflection angle of vertical direction.When taking off, front duct power unit is in the position of interior eight (rotating negative 8 degree), the now power that tilted of front duct power unit, form making a concerted effort and component horizontally outward of vertical direction, horizontal component of force is cancelled out each other and is made flight vector device more stable for takeoff phase, vertical resultant force makes flight vector device accelerate to take off, and manoevreability is good.In flight course, front duct power unit is in the position of outer eight (rotating positive 8 degree), even if such flight vector device also can take into account manoevreability and stability in the rapid flight stage, because the stressed of front duct power unit is decomposed into the power of vertical direction and the power of level sensing fuselage, the power of horizontal direction is cancelled out each other but is maintained the stable of fuselage, and vertical direction is supplied to the lift of flight vector device flight.During decline, before front duct power unit, duct power unit is in the position of outer eight (rotating positive 8 degree) with held stationary.
According to another detailed description of the invention of the present invention, verting of front duct power unit is driven by screw body.
According to another detailed description of the invention of the present invention, front duct power unit comprises installation portion; The installation portion of front duct power unit is articulated with on fuselage; The end of two duct connecting rods respectively with two the installation portion of front duct power unit hinged.
According to another detailed description of the invention of the present invention, flight vector device comprises detent mechanism further; Detent mechanism comprises limiting stopper, locates steering wheel, by the locating dowel pin of locating servo driving; Limiting stopper is provided with knock hole (such as upper, middle and lower three knock holees are distinguished positive 8 degree of correspondence, zero degree, born 8 degree); Limiting stopper is fixed on installation portion; Location steering wheel is arranged on fuselage.Location steering wheel can drive the position of locating dowel pin to front duct power unit to carry out locked.Because forebody is stressed comparatively large, can prevent front duct power unit from dislocating (preventing front duct power unit from departing from predetermined angle) by limiting stopper location.
According to another detailed description of the invention of the present invention, be provided with alighting gear at fuselage bottom, alighting gear is made up of damper element and foot rest.
According to another detailed description of the invention of the present invention, be provided with two cameras at front fuselage, be provided with 1 camera in battery retaining boards bottom, the power supply providing flight vector device to fly is arranged on battery retaining boards.
In the present invention, controlled by the rotational angle of rear synchronizer gear to rear duct power unit, rear duct power unit can be made to tilt at an angle, produce horizontal component of force, realize driftage, without the need to the fuselage that tilts during driftage, can not flight resistance be increased, ensure that the alerting ability of flight; Rear duct power unit is distributed in the both sides of fuselage axis second half section, for flight vector device provides larger air supporting span under the prerequisite not increasing power of motor, thus can improve flight stability; Rear duct power unit vertically can vert positive and negative 8 degree, can ensure stable taking off during vertical acceleration; After taking off, horizontal direction rotates 45 degree, accelerates the flight of flight vector device, the stability of maintenance and manoevreability.
Accompanying drawing explanation
Fig. 1 is the integral structure schematic diagram of the flight vector device of embodiment 1;
Fig. 2 is the part-structure schematic diagram of the flight vector device of embodiment 1, and it mainly shows preamble mechanism;
Fig. 3 is the part-structure schematic diagram of the flight vector device of embodiment 1, and it mainly shows detent mechanism;
Fig. 4 is the part-structure schematic diagram of the flight vector device of embodiment 1, and it mainly shows rear synchronizer gear;
Fig. 5 is the part-structure schematic diagram of the flight vector device of embodiment 1, and it mainly shows tailspin control mechanism;
Fig. 6 is in the flight vector device of embodiment 2, the part-structure schematic diagram of rear synchronizer gear;
Fig. 7 is in the flight vector device of embodiment 3, the part-structure schematic diagram of rear synchronizer gear;
Fig. 8 is in the flight vector device of embodiment 4, the part-structure schematic diagram of rear synchronizer gear;
Fig. 9 is in the flight vector device of embodiment 5, the structural representation of front engine installation.
Detailed description of the invention
Embodiment 1
As Figure 1-Figure 5, the flight vector device of the present embodiment comprises: fuselage 1, front engine installation 2, preamble mechanism 3, detent mechanism 4, rear engine installation 5, rear synchronizer gear 6, tailspin control mechanism 7.
Fuselage 1 comprises frame 101 and tailspin plate 102; Tailspin plate 102 is positioned at the rear end of frame 101, and hinged with frame 101.Be provided with alighting gear 103 at fuselage bottom, alighting gear 103 is made up of damper element and foot rest.Be provided with two cameras 104 in fuselage 1 front end, be provided with 1 camera in battery retaining boards 105 bottom, the power supply providing flight vector device to fly is arranged on battery retaining boards 105.
As Figure 1-Figure 2, front engine installation 2 comprises two front duct power units 201; Two front duct power units 201 are connected to the left and right sides of fuselage 1 forebody.Front duct power unit 201 comprises installation portion; The installation portion of front duct power unit 201 is articulated with on fuselage 1; The end of two duct connecting rods 304 respectively with two the installation portion of front duct power unit 201 hinged.
As shown in Figure 2, preamble mechanism 3 comprises preamble steering wheel, preamble rocking arm 301, two preamble connecting rods; The center of preamble rocking arm 301 connects preamble steering wheel, and the two ends of preamble rocking arm 301 are hinged with the top of two preamble connecting rods respectively; The end of two preamble connecting rods respectively with two front duct power unit 201 hinged.The center of preamble rocking arm 301 is rotated by preamble servo driving, its two ends and two preamble rod hinge connections.Preamble connecting rod comprises: steering wheel connecting rod 302, transfer rocking arm 303, duct connecting rod 304; The center of transfer rocking arm 302 is articulated on fuselage 1; The head end of steering wheel connecting rod 302 is articulated with the end of preamble rocking arm 301; Steering wheel connecting rod 302, transfer rocking arm 303, duct connecting rod 304 are hinged end to end; The end of two duct connecting rods 304 respectively with two front duct power unit 201 hinged.
As shown in Figure 3, detent mechanism 4 comprises limiting stopper 401, locates steering wheel, by the locating dowel pin 402 of locating servo driving; Limiting stopper 401 is provided with upper, middle and lower three knock holees 403, distinguishes positive 8 degree of correspondence, zero degree, bears 8 degree; Limiting stopper 401 is fixed on installation portion; Location steering wheel is arranged on fuselage 1.Location steering wheel 1 can drive the position of locating dowel pin 402 to front duct power unit 201 to carry out locked.Because forebody is stressed comparatively large, can be prevented by limiting stopper 401 location that front duct power unit is stressed to wave.Detent mechanism 4 has a spring 404, when its effect is detent mechanism inefficacy, prevents the excessive direct impact fuselage 1 of front duct power unit 201 anglec of rotation.
Comprise motor and deceleration group in the steering wheel of location, deceleration group is generally straight-tooth wheels, worm-and-wheel gear or its combination, and when deceleration group is worm-and-wheel gear, location steering wheel has auto-lock function.
As shown in Figure 1, shown in Figure 5, duct power unit 501 after rear engine installation 5 comprises two; After two, duct power unit 501 is articulated with the left and right sides of tailspin plate 102 respectively; Rear duct power unit 501 comprises erecting frame; The erecting frame of rear duct power unit 501 is articulated with on fuselage 1; After two the end of synchronising (connecting) rod 602 respectively with two after the erecting frame of duct power unit hinged.
As shown in Figure 4, rear synchronizer gear 6 is arranged on tailspin plate 102, and it comprises synchronising (connecting) rod 602 after rear synchronous steering wheel, rear synchronous swing arm 601, two; Synchronous steering wheel after the top of rear synchronous swing arm 601 connects, after the end of rear synchronous swing arm 601 and two, the top of synchronising (connecting) rod 602 is hinged; After two the end of synchronising (connecting) rod 602 respectively with two after duct power unit 501 hinged.
As shown in Figure 5, tailspin control mechanism 7 comprises tailspin steering wheel, tailspin swing arm 701, tailspin connecting rod 702; The top of tailspin swing arm 701 connects tailspin steering wheel, the end of tailspin swing arm and the top of tailspin connecting rod 702 hinged; End and the tailspin plate 102 of tailspin connecting rod 702 are hinged.In this tailspin control mechanism, three shaft parallels that three places are hinged.Tailspin servo driving tailspin swing arm 701 swings, and then drives tailspin plate to rotate by tailspin connecting rod 702.
Below the present embodiment flight vector device is taken off vertically, in flight course, decline process is described.
When 1, taking off vertically, by the rotation of preamble steering wheel, preamble mechanism driving, and location steering wheel positions the position making front duct power unit be in interior eight (negative 8 degree).Rear duct power unit is in vertical direction.
When taking off, front duct power unit is in the position of interior eight (rotating negative 8 degree), the now power that tilted of front duct power unit, form making a concerted effort and component horizontally outward of vertical direction, horizontal component of force is cancelled out each other and is made flight vector device more stable for takeoff phase, vertical resultant force makes flight vector device accelerate to take off, and manoevreability is good.
2, during rapid flight, in order to obtain good manoevreability, rear duct power unit rotates 45 degree in the horizontal direction by tailspin steering wheel, at this moment thrust forward and component is upwards produced, power upwards makes tail balance, thrust forward accelerates the flight of flight vector device, and the flight vector device speed of a ship or plane is improved.
Now, front duct power unit is in the position of outer eight (rotating positive 8 degree), even if such flight vector device also can take into account manoevreability and stability in the rapid flight stage, because the stressed of front duct power unit is decomposed into the power of vertical direction and the power of level sensing fuselage, the power of horizontal direction is cancelled out each other but is maintained the stable of fuselage, and vertical direction is supplied to the lift of flight vector device flight.
3, during driftage, rear duct power unit realizes the rotation of positive and negative 8 degree by rear synchronous steering wheel, flight vector device left-handed turning to time, after rear synchronous steering wheel makes two, duct power unit deflects negative 8 degree horizontal wind-force realizations produced left simultaneously and goes off course.
When 4, declining, rear duct power unit is rotated by tailspin plate and becomes vertical direction again, realizes quick deceleration; Front duct power unit is in the position of outer eight (rotating positive 8 degree) with held stationary.
Embodiment 2
As shown in Figure 6, the present embodiment is with the difference of embodiment 1: rear synchronous swing arm 601 is discoid runner, which is provided with a point of connection 603; This point of connection 603 is between the rotating shaft and edge of runner; After two, the top of synchronising (connecting) rod 602 is connected to point of connection 603, and its end is connected with rear duct power unit.
Embodiment 3
As shown in Figure 7, the present embodiment is with the difference of embodiment 2: rear synchronous swing arm 601 is discoid runner, and its edge is provided with two point of connection 604, and these two point of connection 604 are radially symmetrical about runner; After two, the top of synchronising (connecting) rod 602 is connected to point of connection 604, and its end is connected with rear duct power unit.
Embodiment 4
As shown in Figure 8, the difference of the present embodiment and embodiment 2 is: rear synchronising (connecting) rod 602 is pole, and it comprises galianconism 606 and long-armed 607, and the angle between galianconism 606 and long-armed 607 is 90 °, the end of galianconism 606 connects rear synchronous swing arm 601, and the end of long-armed 607 connects rear duct power unit.
Embodiment 5
As shown in Figure 9, the difference of the present embodiment and embodiment 2 is: verting of front duct power unit 201 is driven by screw body 209.
Be more than the exemplary description done the present invention, all simple deformation of making when not departing from core of the present invention or amendment all fall into protection scope of the present invention.
Claims (11)
1. a flight vector device, is characterized in that, described flight vector device comprises:
Fuselage;
Rear engine installation, duct power unit after it comprises two; After described two, duct power unit is articulated with the latter half of left and right sides of described fuselage respectively;
Rear synchronizer gear, drives described rear duct power unit verting perpendicular to the plane inter-sync along fuselage fore-and-aft direction by connecting rod.
2. flight vector device as claimed in claim 1, is characterized in that, described rear synchronizer gear comprises rear synchronous steering wheel, rear synchronous swing arm, synchronising (connecting) rod after two; The top of described rear synchronous swing arm connects described rear synchronous steering wheel, and after the end of described rear synchronous swing arm and described two, the top of synchronising (connecting) rod is hinged; After described two the end of synchronising (connecting) rod respectively with described two after duct power unit hinged.
3. flight vector device as claimed in claim 1, it is characterized in that, described rear duct power unit is articulated with on described fuselage by erecting frame; After described two the end of synchronising (connecting) rod respectively with described two after the erecting frame of duct power unit hinged.
4. flight vector device as claimed in claim 1, it is characterized in that, described fuselage comprises frame and tailspin plate; Described tailspin plate is positioned at the rear end of described frame, and hinged with described frame.
5. flight vector device as claimed in claim 4, it is characterized in that, described rear synchronizer gear is arranged on described tailspin plate, and after described two, duct power unit is articulated with the left and right sides of described tailspin plate respectively.
6. flight vector device as claimed in claim 5, it is characterized in that, described flight vector device comprises tailspin control mechanism further, and described tailspin control mechanism comprises tailspin steering wheel, tailspin swing arm, tailspin connecting rod; The top of described tailspin swing arm connects described tailspin steering wheel, the end of described tailspin swing arm and the top of described tailspin connecting rod hinged; Described in the end of described tailspin connecting rod, tailspin plate is hinged.
7. flight vector device as claimed in claim 1, it is characterized in that, described flight vector device comprises front engine installation further, and described front engine installation comprises two front duct power units; Described two front duct power units are connected to the left and right sides of described fuselage forebody.
8. flight vector device as claimed in claim 7, it is characterized in that, described flight vector device comprises preamble mechanism further; Described preamble mechanism comprises preamble steering wheel, preamble rocking arm, two preamble connecting rods; The center of described preamble rocking arm connects described preamble steering wheel, and the two ends of described preamble rocking arm are hinged with the top of described two preamble connecting rods respectively; The end of described two preamble connecting rods is hinged with described two front duct power units respectively.
9. flight vector device as claimed in claim 8, is characterized in that, verting of described front duct power unit is driven by screw body.
10. flight vector device as claimed in claim 8, it is characterized in that, described front duct power unit comprises installation portion; The installation portion of described front duct power unit is articulated with on described fuselage; The end of described two duct connecting rods is hinged with the installation portion of described two front duct power units respectively.
11. flight vector devices as claimed in claim 10, it is characterized in that, described flight vector device comprises detent mechanism further; Described detent mechanism comprises limiting stopper, location steering wheel, locating dowel pin by described location servo driving; Described limiting stopper is provided with knock hole; Described limiting stopper is fixed on described installation portion; Described location steering wheel is arranged on described fuselage.
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|---|---|---|---|
| CN201610067048.3A CN105564641B (en) | 2016-01-29 | 2016-01-29 | Vector aircraft |
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| CN201610067048.3A CN105564641B (en) | 2016-01-29 | 2016-01-29 | Vector aircraft |
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| CN105564641B CN105564641B (en) | 2019-01-25 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106585952A (en) * | 2016-12-20 | 2017-04-26 | 深圳市元征科技股份有限公司 | Multi-rotor unmanned aerial machine |
| CN106628160A (en) * | 2016-12-12 | 2017-05-10 | 成都育芽科技有限公司 | Two-layer coaxial multi-rotor unmanned aerial vehicle |
| CN106741918A (en) * | 2017-01-14 | 2017-05-31 | 陕西捷恒新材料有限责任公司 | The axle flying vehicles control structure of skew product vector two |
| CN106995052A (en) * | 2017-03-23 | 2017-08-01 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| CN107264780A (en) * | 2017-06-27 | 2017-10-20 | 何漠 | Tandem vectored thrust drives aircraft and its design method entirely |
| CN107757897A (en) * | 2017-07-01 | 2018-03-06 | 珠海磐磊智能科技有限公司 | Three axle aircraft and mobile takeoff method |
| CN109131857A (en) * | 2018-05-04 | 2019-01-04 | 江国春 | Petrol engine drives more rotor fire extinguishment rescue manned vehicles |
| CN114348252A (en) * | 2022-03-01 | 2022-04-15 | 成都纵横大鹏无人机科技有限公司 | Multi-rotor aircraft |
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