CN110588966A - Hybrid lift tandem vector double-rotor aircraft - Google Patents
Hybrid lift tandem vector double-rotor aircraft Download PDFInfo
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- CN110588966A CN110588966A CN201910977773.8A CN201910977773A CN110588966A CN 110588966 A CN110588966 A CN 110588966A CN 201910977773 A CN201910977773 A CN 201910977773A CN 110588966 A CN110588966 A CN 110588966A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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Abstract
The invention provides a hybrid lift longitudinal vector double-rotor aircraft which comprises a machine frame, a door structure steering engine, a first wing, a second wing, a wing fixing rod, a wing control mechanism, a main carbon rod, a first flying mechanism and a second flying mechanism, wherein the first wing and the second wing are fixedly installed on two sides of the wing fixing rod through a first bearing respectively, two ends of the top surface of the machine frame are fixedly installed with the wing control mechanisms respectively, the middle of the top surface of the machine frame is fixedly installed with the main carbon rod, and two ends of the main carbon rod are fixedly installed with the first flying mechanism and the second flying mechanism respectively. The hybrid lift longitudinal vector dual-rotor aircraft has the advantages of low cost, excellent stability and maneuverability and high energy utilization rate.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a hybrid lift longitudinal vector double-rotor aircraft.
Background
To the commodity circulation transportation trade that gradually develops day by day, unmanned aerial vehicle transportation has been the trend of future development, at the last stage of commodity circulation transportation, market needs a section ability VTOL, it is stable to cruise, the task load is big, the long novel unmanned aerial vehicle of time of endurance, the unmanned aerial vehicle scheme of leading to this market at present is the combination of four rotors and fixed wings, comparatively ripe 18 years of following abundance Manta Ray unmanned aerial vehicle, though the demand in market is tentatively reached to this type of scheme, but such combination mode makes the aircraft have unnecessary waste on function and energy: 1. the manufacturing cost is high, the combination of the four rotor wings and the fixed wings requires at least 4 motors in terms of power, and for example, a Manta Ray unmanned aerial vehicle is provided with 4 motors and two ducts; 2. the unmanned aerial vehicle is large in size and poor in maneuvering performance, and is not suitable for delivery at the tail end of transportation, because the unmanned aerial vehicle makes wings large for increasing endurance, for example, the wing span adopted by a Manta Ray unmanned aerial vehicle is as long as 3.5m, so that the unmanned aerial vehicle needs a large landing space, and the design of the unmanned aerial vehicle has certain defects aiming at a final-stage transportation-pedestrian flow dense area in order to ensure that the unmanned aerial vehicle needs at least 4m by 4m landing space; 3. energy utilization is low, and the aircraft dead weight is higher, and more energy sources are used in self load, causes energy utilization not high, and in the aspect of its dead weight, firstly need a large amount of motors for increasing power, secondly big span aircraft requires highly to wing intensity, uses high strength material also can increase the dead weight for the increase intensity.
Disclosure of Invention
In view of the above, the invention aims to provide a hybrid lift longitudinal vector dual-rotor aircraft to solve the problems of high manufacturing cost, poor maneuvering performance and low energy utilization rate of the aircraft.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the mixed lift longitudinal vector double-rotor aircraft comprises a machine frame, a door structure steering engine, a first wing, a second wing, a wing fixing rod, a wing control mechanism, a main carbon rod, a first flying mechanism and a second flying mechanism, wherein the machine frame is formed by splicing a plurality of connecting rods and is of a rectangular frame structure, the machine frame forms a first surface, a second surface, a third surface, a fourth surface, a top surface and a bottom surface, the first surface, the second surface, the third surface, the fourth surface, the top surface and the bottom surface are of a rectangular structure consisting of four connecting rods, the first surface and the second surface are opposite surfaces, cross rods are respectively and fixedly installed on the first surface and the second surface and are formed by cross connection of two connecting rods, the third surface and the fourth surface are opposite surfaces, the third surface and the fourth surface are respectively and fixedly installed with one connecting rod, and an installation rod is fixedly installed on the bottom surface of the machine frame, the central part of the steering engine mounting rod is fixedly provided with a door structure steering engine, the door structure steering engine is connected to a deflector rod through a first transmission rod, two ends of the bottom surface are respectively hinged with a first door and a second door, the wing fixing rod penetrates through the machine frame and is placed at the intersection of the two cross rods and is fixedly connected with the two cross rods, the first wing and the second wing are respectively and fixedly arranged at two sides of the wing fixing rod through a first bearing, two ends of the top surface of the machine frame are respectively and fixedly provided with a wing control mechanism, the wing control mechanism comprises a wing steering engine, a wing steering wheel and a pull rod, the wing steering engine is fixedly connected with the wing steering wheel through a second transmission rod, the wing steering wheel is fixedly connected to the wings through two pull rods, the middle part of the top surface of the machine frame is fixedly provided with a main carbon rod, and two ends of the main carbon rod are respectively and fixedly provided with a first flying mechanism and a second flying, the first flying mechanism and the second flying mechanism are identical in structure and symmetrically installed, the first flying mechanism comprises a propeller, a motor, a fixing frame, a steel shaft, a robot steering wheel, a fixing part, a second fixing part and a third fixing part, the fixing frame is identical in structure with the second fixing frame, the propeller is fixedly connected with the motor, the bottom of the motor is fixedly connected with the fixing frame, the cross section of the fixing frame is of a U-shaped structure, two through holes are formed in two sides of the fixing frame respectively, a second bearing is arranged in each through hole respectively, the steel shaft penetrates through the two bearings and the fixing frame, one end of the fixing frame is fixedly connected with the robot steering wheel, and a main carbon rod is fixedly installed with the first fixing part, the second fixing part and the third fixing part from the end part inwards in sequence, The main carbon rod is connected with the steel shaft through the first fixing part and the second fixing part, the fixing frame is rotatable relative to the steel shaft under the control of the robot steering engine, the main carbon rod is fixedly connected with the robot steering engine through the third fixing part, a controller is fixedly installed on the machine frame, the door structure steering engine, the wing steering engine, the motor and the robot steering engine are respectively connected with the controller through signals, the controller is connected with an external remote controller through signals, and a lithium battery is fixedly installed on the machine frame.
Further, main carbon pole pass through the rope with frame fixed connection, the rope drips into 502 glue.
Further, the wing fixing rod is fixedly connected with the cross rod through a rope, and 502 glue is dripped into the rope.
Further, the rope is made of Kevlar.
Furthermore, the main carbon rod, the wing fixing rod, the propeller, the first door and the second door are made of carbon fibers.
Further, the propeller is a double-blade propeller.
Furthermore, the first door comprises a first main rod, a first short rod, a first middle rod and a first long rod, two ends of the first short rod are respectively and fixedly connected to the upper parts of the two first main rods, two ends of the first middle rod are respectively and fixedly connected to the middle parts of the two first main rods, the first long rod is fixedly connected to the end parts of the two first main rods, the second door comprises a second main rod, a second short rod, a second middle rod and a second long rod, two ends of the second short rod are respectively and fixedly connected to the upper parts of the two second main rods, two ends of the second middle rod are respectively and fixedly connected to the middle parts of the two second main rods, no. two stock fixed connection to two No. two mobile jib tip, two a mobile jib, two No. two the mobile jib respectively with the frame passes through the rubber band to be connected, the length of dial rod is greater than a quarter butt No. two length between the quarter butt.
Further, a mounting, No. two mountings with No. three mountings are printed through 3D and are formed.
Further, the length of the first short rod is greater than that of the second short rod.
Further, the controller is a SPracing F3 flight controller.
Compared with the prior art, the hybrid lift longitudinal vector dual-rotor aircraft has the following advantages:
(1) the hybrid lift longitudinal vector dual-rotor aircraft is low in cost, four rotors are replaced by the vector dual rotors, the control performance is basically the same as that of the four rotors, and the efficiency of the dual rotors is higher than that of the four rotors, so that the cost is greatly reduced by adopting a vector dual-rotor scheme.
(2) The mixed lift longitudinal vector dual-rotor aircraft has excellent stability and maneuverability, and in the aspect of maneuverability, the longitudinal design can improve the maneuverability of the aircraft, and the wing span of the full-motion wing can be properly reduced, so that the maneuverability is improved; in the aspect of stability, the full-motion wing is utilized to assist flight control to adjust the flying attitude, so that the self-adjusting capacity of the aircraft is more outstanding, and the flight is more stable.
(3) The hybrid lift longitudinal vector dual-rotor aircraft has high energy utilization rate, adopts dual rotors on power, and can properly reduce the wingspan of a full-motion wing on the wing, so that the requirement on the strength of the wing is reduced, the weight increase on materials can be reduced, the weight reduction is realized on two aspects, the energy is less used on the self consumption, and the energy utilization rate is improved; the design of the full-motion wing in the mixed lift force enables the lift force characteristic of the aircraft to be increased, and therefore the energy utilization rate is further improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a hybrid lift tandem vector twin rotor aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a machine frame according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a door according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a second door according to an embodiment of the present invention;
FIG. 5 is a schematic view of a hybrid lift tandem vector twin rotor aircraft according to an embodiment of the present invention;
FIG. 6 is an enlarged view of a portion of the circle in FIG. 5 according to an embodiment of the present invention;
FIG. 7 is a schematic view of a hybrid lift tandem vector twin rotor aircraft according to an embodiment of the present invention;
fig. 8 is a partially enlarged view of the circle in fig. 7 according to the embodiment of the present invention.
Description of reference numerals:
1-machine frame; 11-a first side; 12-a second face; 13-a third face; 14-fourth face; 15-top surface; 16-a bottom surface; 161-steering engine mounting rod; 17-a crossbar; 18-door number one; 181-first main bar; 182-short rod number one; 183-first middle rod; 184-long rod number one; 19-door No. two; 191-second main pole; 192-second short rod; 193-second middle rod; 194-long rod number two; 2-door structure steering engine; 21-a deflector rod; 3-first wing; 4-second wing; 5-a wing fixing rod; 6-wing control mechanism; 61-wing steering engine; 62-wing rudder disk; 63-a pull rod; 7-a primary carbon rod; 8-a first flight mechanism; 81-propeller; 82-a motor; 83-a fixed mount; 84-steel shaft; 85-a robot tiller; 86-robot steering gear; 87-number one fastener; 88-number two fastener; 89-third fastener; 9-second flying mechanism.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "first," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
A hybrid lift longitudinal vector dual-rotor aircraft is shown in figures 1 to 8 and comprises a machine frame 1, a door structure steering engine 2, a first wing 3, a second wing 4, a wing fixing rod 5, a wing control mechanism 6, a main carbon rod 7, a first flight mechanism 8 and a second flight mechanism 9, wherein the machine frame 1 is formed by splicing a plurality of connecting rods and is of a rectangular frame structure, the machine frame 1 forms a first surface 11, a second surface 12, a third surface 13, a fourth surface 14, a top surface 15 and a bottom surface 16, the first surface 11, the second surface 12, the third surface 13, the fourth surface 14, the top surface 15 and the bottom surface 16 are of rectangular structures formed by four connecting rods, the first surface 11 and the second surface 12 are opposite surfaces, cross rods 17 are fixedly installed on the first surface 11 and the second surface 12 respectively, the cross rods 17 are formed by cross-connecting two connecting rods, the third surface 13 and the fourth surface 14 are opposite surfaces, a connecting rod is fixedly arranged on the third surface 13 and the fourth surface 14 respectively, a steering engine mounting rod 161 is fixedly arranged on the bottom surface 16 of the machine frame 1, a door structure steering engine 2 is fixedly arranged at the central part of the steering engine mounting rod 161, the door structure steering engine 2 is connected to a shifting rod 21 through a first transmission rod, two ends of the bottom surface 16 are respectively hinged with a first door 18 and a second door 19, when the shifting rod 21 rotates to a position parallel to the steering engine mounting rod 161, the first door 18 and the second door 19 can be opened, when the shifting rod 21 rotates to a position perpendicular to the steering engine mounting rod 161, the shifting rod 21 blocks the first door 18 and the second door 19, so that the first door 18 and the second door 19 are in a locked state, the wing fixing rod 5 penetrates through the machine frame 1 and is placed at the intersection of the two cross rods 17, and the cross rods 17 can well support the wing fixing rod 5, the first wing 3 and the second wing 4 are fixedly mounted on two sides of the wing fixing rod 5 through a first bearing respectively, so that the first wing 3 and the second wing 4 rotate relative to the wing fixing rod 5, two ends of the top surface 15 of the machine frame 1 are fixedly mounted with a wing control mechanism 6 respectively, the wing control mechanism 6 comprises a wing steering engine 61, a wing steering wheel 62 and a pull rod 63, the wing steering engine 61 is fixedly connected with the wing steering wheel 62 through a second transmission rod, the wing steering wheel 62 is fixedly connected to the wings through two pull rods 63, the wing steering engine 61 is controlled to rotate the wing steering wheel 62, so that the first wing 3 and the second wing 4 rotate through driving the pull rod 63, a main carbon rod 7 is fixedly mounted in the middle of the top surface 15 of the machine frame 1, two ends of the main carbon rod 7 are fixedly mounted with a first flying mechanism 8 and a second flying mechanism 9 respectively, the first flying mechanism 8 and the second flying mechanism 9 are identical in structure and symmetrically installed, the first flying mechanism 8 comprises a propeller 81, a motor 82, a fixing frame 83, a steel shaft 84, a robot steering wheel 85, a robot steering wheel 86, a fixing member 87, a second fixing member 88 and a third fixing member 89, the first fixing frame 83 is identical in structure with the second fixing frame 83, the propeller 81 is fixedly connected with the motor 82, the bottom of the motor 82 is fixedly connected with the fixing frame 83, the cross section of the fixing frame 83 is of a U-shaped structure, through holes are respectively arranged on two sides of the fixing frame 83, a second bearing is respectively arranged in each through hole, the steel shaft 84 penetrates through the two second bearings and is fixedly connected with the fixing frame 83, the fixing frame 83 can rotate around the steel shaft 84, one end of the fixing frame 83 is fixedly connected with the robot steering wheel 86 through the robot steering wheel 85, the main carbon rod 7 is fixedly provided with a first fixing piece 87, a second fixing piece 88 and a third fixing piece 89 from the end part inwards in sequence, the main carbon rod 7 is connected with the steel shaft 84 through the first fixing piece 87 and the second fixing piece 88, the fixing frame 83 can rotate relative to the steel shaft 84 under the control of the robot steering gear 86, the main carbon rod 7 is fixedly connected with the robot steering gear 86 through the third fixing piece 89 to control the robot steering gear 86, so that the robot steering gear 85 rotates, the robot steering gear 85 drives the fixing frame 83 to rotate, then the propeller 81 changes the angle, the machine frame 1 is fixedly provided with a controller, the door structure 2, the wing steering gear 61, the motor 82 and the robot steering gear 86 are respectively connected to the controller through signals, the controller is connected to an external remote controller through signals, and the lithium battery is fixedly arranged on the machine frame 1, and supplying power to the hybrid lift tandem vector dual-rotor aircraft.
Main carbon pole 7 pass through the rope with frame 1 fixed connection, 502 glue are dripped into to the rope, and glue can make the rope solidify, avoids the fracture.
The wing fixing rod 5 is fixedly connected with the cross rod 17 through a rope, 502 glue is dripped into the rope, and the glue can solidify the rope to avoid breakage.
The rope is made of Kevlar, the Kevlar is light in weight and firm in structure, and the rope can be prevented from being broken when used as the rope.
The main carbon rod 7, the wing fixing rod 5, the propeller 81, the first door 18 and the second door 19 are made of carbon fibers, the carbon fibers have the characteristics of high temperature resistance, friction resistance, electric conduction, heat conduction, corrosion resistance and the like, and the graphite microcrystalline structure of the carbon fibers is preferentially oriented along the fiber axis, so that the carbon fibers have high strength and modulus along the fiber axis direction.
The propeller 81 is a double-blade propeller, so that the weight can be reduced.
The first door 18 comprises a first main rod 181, a first short rod 182, a first middle rod 183 and a first long rod 184, two ends of the first short rod 182 are respectively and fixedly connected to the upper parts of the first main rods 181, two ends of the first middle rod 183 are respectively and fixedly connected to the middle parts of the first main rods 181, the first long rod 184 is fixedly connected to the end parts of the first main rods 181, the second door 19 comprises a second main rod 191, a second short rod 192, a second middle rod 193 and a second long rod 194, two ends of the second short rod 192 are respectively and fixedly connected to the upper parts of the second main rods 191, two ends of the second middle rod 193 are respectively and fixedly connected to the middle parts of the second main rods 191, the second long rod 194 is fixedly connected to the end parts of the second main rods 191, the first main rod 181, the second main rod 191 are respectively connected with the machine frame 1 through rubber bands, the length of the shift lever 21 is greater than the length between the first short rod 182 and the second short rod 192.
A mounting 87 No. two mounting 88 with No. three mounting 89 forms through 3D printing, need not grinding apparatus and machining and can make, shortens the development cycle of product, reduction in production cost.
The length of the first short rod 182 is greater than that of the second short rod 192, so that the first short rod 182 and the second short rod 192 are clamped by the shifting lever 21, and the first door 18 and the second door 19 are locked.
The controller is a SPracing F3 flight controller.
The hybrid lift tandem vector dual-rotor aircraft has the working principle that the pitching operation of the hybrid lift tandem vector dual-rotor aircraft is realized by the differential rotation of the motor 82 on the first flying mechanism 8 and the motor on the second flying mechanism 9, and the rolling operation is realized by the simultaneous deflection of the motor 82 on the first flying mechanism 8 and the motor on the second flying mechanism 9 towards a side vector; the motor 82 on the first flying mechanism 8 and the motor on the second flying mechanism 9 deflect the same angle towards different directions simultaneously to realize yawing operation; in the flying process, the first wing 3 and the second wing 4 can be controlled by a remote controller to automatically adjust the elevation angle according to the flying controller.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. Mix lift tandem formula vector bispin wing aircraft, its characterized in that: comprises a machine frame (1), a door structure steering engine (2), a first wing (3), a second wing (4), a wing fixing rod (5), a wing control mechanism (6), a main carbon rod (7), a first flying mechanism (8) and a second flying mechanism (9),
the frame (1) is formed by a plurality of connecting rods through splicing, and is a rectangular frame structure, the frame (1) forms a first face (11), a second face (12), a third face (13), a fourth face (14), a top face (15) and a bottom face (16), the first face (11), the second face (12), the third face (13), a fourth face (14), the top face (15) and the bottom face (16) are rectangular structures formed by four connecting rods, the first face (11) and the second face (12) are opposite faces, the first face (11) and the second face (12) are respectively provided with a fixed mounting cross rod (17), the cross rod (17) is formed by cross connection of two connecting rods, the third face (13) and the fourth face (14) are opposite faces, the third face (13) and the fourth face (14) are respectively provided with a connecting rod of fixed mounting, steering wheel installation pole (161) of bottom surface (16) fixed mounting of frame (1), steering wheel installation pole (161) central part fixed mounting door structure steering wheel (2), door structure steering wheel (2) are connected to driving lever (21) through a transfer line, bottom surface (16) both ends are articulated with door (18) and No. two door (19) respectively, wing dead lever (5) are passed frame (1) is placed two on the intersect of crossbar (17), with two crossbar (17) fixed connection, wing (3) No. two wing (4) respectively through a bearing fixed mounting extremely wing dead lever (5) both sides, a wing control mechanism (6) of fixed mounting respectively at top surface (15) both ends of frame (1), wing control mechanism (6) include wing steering wheel (61), Wing steering wheel (61) through No. two transfer lines with wing steering wheel (62) fixed connection, wing steering wheel (62) is through two pull rod (63) fixed connection to the wing, top surface (15) middle part fixed mounting main carbon rod (7) of frame (1), main carbon rod (7) both ends are fixed mounting flight mechanism (8) and No. two flight mechanism (9) respectively, No. one flight mechanism (8) and No. two flight mechanism (9) the same and symmetrical installation of structure, No. one flight mechanism (8) include screw (81), motor (82), mount (83), steel axle (84), robot steering wheel (85), robot steering wheel (86), a mounting (87), No. two mounting (88) and No. three mounting (89), No. one mounting (83) with No. two mounting (83) the structure is the same, the propeller (81) is fixedly connected with the motor (82), the bottom of the motor (82) is fixedly connected with the fixing frame (83), the cross section of the fixing frame (83) is of a U-shaped structure, two sides of the fixing frame (83) are respectively provided with a through hole, each through hole is internally provided with a second bearing, the steel shaft (84) penetrates through the two second bearings and is fixedly connected with the fixing frame (83), one end of the fixing frame (83) is fixedly connected with the robot steering gear (86) through the robot steering gear (85), the main carbon rod (7) is fixedly provided with a first fixing piece (87), a second fixing piece (88) and a third fixing piece (89) from the end part inwards in sequence, the main carbon rod (7) is connected with the steel shaft (84) through the first fixing piece (87) and the second fixing piece (88), and the fixing frame (83) is rotatable relative to the steel shaft (84) under the control of the robot steering gear (86), main carbon pole (7) through No. three mounting (89) with robot steering wheel (86) fixed connection, fixed installation controller on frame (1), door structure steering wheel (2) wing steering wheel (61) motor (82) with robot steering wheel (86) signal connection respectively to the controller, controller signal connection is to outside remote controller, fixed mounting lithium cell on frame (1).
2. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: main carbon pole (7) pass through the rope with frame (1) fixed connection, the rope drips into glue.
3. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the wing fixing rod (5) is fixedly connected with the cross rod (17) through a rope, and glue is dripped into the rope.
4. The hybrid lift tandem vector twin rotor aircraft of claim 2 or 3, wherein: the rope is made of Kevlar.
5. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the main carbon rod (7), the wing fixing rod (5), the propeller (81), the first door (18) and the second door (19) are made of carbon fibers.
6. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the propeller (81) is a double-blade propeller.
7. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the first door (18) comprises a first main rod (181), a first short rod (182), a first middle rod (183) and a first long rod (184), two ends of the first short rod (182) are fixedly connected to the upper parts of the first main rods (181) respectively, two ends of the first middle rod (183) are fixedly connected to the middle parts of the first main rods (181) respectively, the first long rod (184) is fixedly connected to the end parts of the first main rods (181), the second door (19) comprises a second main rod (191), a second short rod (192), a second middle rod (193) and a second long rod (194), two ends of the second short rod (192) are fixedly connected to the upper parts of the second main rods (191) respectively, two ends of the second middle rod (193) are fixedly connected to the middle parts of the second main rods (191), and the second long rod (194) is fixedly connected to the end parts of the second main rods (191), two mobile jib (181), two No. two mobile jib (191) respectively with frame (1) passes through the rubber band and connects, the length of driving lever (21) is greater than short-rod (182) No. two length between short-rod (192).
8. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the fixing piece (87) is formed by 3D printing of the fixing piece (87), the fixing piece (88) and the fixing piece (89).
9. The hybrid lift tandem vector twin rotor aircraft of claim 7, wherein: the length of the first short rod (182) is greater than that of the second short rod (192).
10. The hybrid lift tandem vector twin rotor aircraft of claim 1, wherein: the controller is a SPracing F3 flight controller.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910977773.8A CN110588966B (en) | 2019-10-15 | 2019-10-15 | Hybrid lift tandem vector double-rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910977773.8A CN110588966B (en) | 2019-10-15 | 2019-10-15 | Hybrid lift tandem vector double-rotor aircraft |
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| CN110588966A true CN110588966A (en) | 2019-12-20 |
| CN110588966B CN110588966B (en) | 2022-12-02 |
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