CN112849401A - Steering engine control's two wing unmanned aerial vehicle - Google Patents
Steering engine control's two wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN112849401A CN112849401A CN202110313250.0A CN202110313250A CN112849401A CN 112849401 A CN112849401 A CN 112849401A CN 202110313250 A CN202110313250 A CN 202110313250A CN 112849401 A CN112849401 A CN 112849401A
- Authority
- CN
- China
- Prior art keywords
- steering engine
- rotor
- unmanned aerial
- aerial vehicle
- flight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
A steering engine controlled double-wing unmanned aerial vehicle relates to the field of unmanned aerial vehicle control. The aircraft comprises an aircraft body and steering engines (500), two flight rods (110) are symmetrically fixed on two sides of the aircraft body, the flight rods (110) are arranged obliquely upwards, a rotor motor (400) is movably connected to one end, far away from the aircraft body, of each flight rod (110), the steering engines are further arranged at one ends, far away from the aircraft body, of the flight rods (110), the adjusting bracket (200) is fixedly connected to one end, far away from the aircraft body, of each flight rod (110), and the steering engines (500) control the rotation of the rotor motor (400) and the rotors (300) thereof through the adjusting bracket (200); the unmanned aerial vehicle system realizes the integration of the drive of the steering engine (500) and the rotor motor (400) at one end of the flight rod, avoids the weak part of the connection part of the flight rod and the vehicle body from becoming the drive connection, and improves the control efficiency of the unmanned aerial vehicle system.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle control, in particular to a steering engine controlled double-wing unmanned aerial vehicle.
Background
When two rotor unmanned aerial vehicle fly forward, the oar face verts forward, and unmanned aerial vehicle in flight can change lift force into forward traction force fast, and two rotor unmanned aerial vehicle efficiency can be higher, and the acceleration also can be faster. During turning, the steering engine is controlled in a differential mode, the steering engine can turn by means of lift force components, more force can be applied to corner force, the turning speed can be higher, and the flight can be more flexible.
At present, the flight control algorithm of the double-rotor unmanned aerial vehicle is very complex, the control of rotors is considered, the coordination of structures such as tilting of steering engines is combined, the existing double-rotor structure is still unreasonable, and the setting requirement on the flight control algorithm and the control system of the double-rotor unmanned aerial vehicle is high.
Specifically, a motor corresponding to a middle rotor of the existing dual-rotor unmanned aerial vehicle can only be used for controlling the starting speed and the starting speed of the rotor, so that the unmanned aerial vehicle can move up and down and left and right, and the pitching steering of the unmanned aerial vehicle can be realized only by further combining a steering engine for controlling the rotation of the rotor, in a specific steering engine application mode, the steering engine is more commonly arranged in a machine body, and a flight rod, the rotor motor and the like are driven by the steering engine, and when the mode is implemented, it is not difficult to find that the distance between the steering engine and the rotor comprises a flight rod structure, the common flight rod structure is almost symmetrically designed in an oblique upward direction and is arranged on two sides of the machine body, in the implementation mode, the force arm of the steering engine during driving at least comprises the distance of one section of the flight rod and the gravity required to be overcome during driving, the efficiency of controlling the rotation angle of the rotor is, the emergency property of steering engine control is not ideal, and the energy consumption is higher.
Disclosure of Invention
The invention aims to overcome at least one defect (deficiency) of the prior art, and provides a steering engine controlled double-wing unmanned aerial vehicle, which structurally simplifies the control mode of the unmanned aerial vehicle on the double rotors and improves the control efficiency of the unmanned aerial vehicle, especially the angle control efficiency.
The technical scheme adopted by the invention is that,
a steering engine controlled double-wing unmanned aerial vehicle comprises a fuselage and a steering engine, wherein two flight rods are symmetrically fixed on two sides of the fuselage, the flight rods are arranged obliquely upwards, one ends, far away from the fuselage, of the flight rods are movably connected with a rotor motor for driving the rotors to rotate, the steering engine is further arranged at one ends, far away from the fuselage, of the flight rods and used for controlling the rotation of the rotor motors and the rotors, one ends, far away from the fuselage, of the flight rods are fixedly connected with an adjusting bracket, and the steering engine controls the rotation of the rotor motors and the rotors through the adjusting bracket;
the aircraft body is provided with a power supply, and the rotor motor and the steering engine are electrically connected along the flight rod;
when the rotor motor starts, the rotor receives rotor motor drive drives the fuselage goes up and down or turns to about, works as when the steering wheel starts, steering wheel drive the rotor motor with the rotor makes its certain angle of upset, combines the drive of rotor motor, further realizes the every single move of fuselage turns to.
When the control mode of the steering engine is designed, the corresponding relation between the flight rod and the steering engine control is considered, and the steering engine is creatively arranged at the tail end of the flight, namely one end of the flight rod, which is far away from the machine body, so that the lower end of the flight rod can be fixedly connected with the machine body, specifically can be rigidly connected, and the flight stability of the unmanned aerial vehicle is improved; meanwhile, by arranging the adjusting bracket which is fixedly connected with the tail end of the flight rod, the adjusting bracket can be regarded as two fixed connection points on the flight rod in the unmanned aerial vehicle, so that the influence of the flight rod on the control of the motor or the steering engine is reduced; the installation rotor and the rotor motor are arranged on the adjusting support, and the steering engine which is also arranged at the tail end of the flight rod controls the rotation of the rotor and the rotor motor, so that the control end of the rotor can be positioned at the same end of the flight rod, the force arm driven by the steering engine is minimized, the energy consumption of the steering engine is reduced, and the follow-up design of an unmanned aerial vehicle control system is facilitated.
As a preferred embodiment, the adjusting bracket is provided with an adjusting block and a vertical part, the adjusting block is connected with the vertical part in a rotating mode and used for providing a rotatable horizontal supporting surface, the rotor motor is fixedly connected with the horizontal supporting surface and used for rotatably supporting the rotor motor, the steering engine is provided with an output shaft, and the adjusting block is connected with the output shaft and used for driving the horizontal supporting surface to turn over.
In order to realize the connection of the adjusting bracket with the rotor and the rotor motor thereof, when the adjusting block designed by the invention is rotatably connected with the vertical part, a horizontal supporting surface is provided, the horizontal supporting surface comprises a horizontal supporting shaft, namely the support of the rotor motor comprises but is not limited to the support in the horizontal direction, namely the horizontal supporting surface limited by the invention is a surface which can turn over on the basis of the horizontal supporting shaft, and the structure for driving the rotor to turn over by the steering engine is provided through the fixed connection of the output shaft and the adjusting block.
As a preferred embodiment, the vertical portion includes a first protrusion and a second protrusion, the first protrusion and the second protrusion are respectively connected to the adjusting block in a rotating manner, the adjusting bracket is further provided with a base, the base is fixedly connected to the first protrusion and the second protrusion, and the lower side of the base is rigidly connected to one end of the flight bar, which is far away from the fuselage.
In order to realize the turnover of the adjusting block, the invention further limits the structure of the vertical part into two bulges which are rotatably connected with the adjusting block, suspends the rotor wing structure in the flying rod and rotatably supports the flying rod on the adjusting bracket for realizing the rotation of the rotor wing, and simultaneously, the invention is further limited to the base structure fixedly connected with the flying rod, and the driving part of the rotor wing is intensively limited at one end of the flying rod far away from the machine body through the rigid connection of the base and the flying rod, thereby overcoming the possibility that the flying rod is used as a driving force arm.
Furthermore, first arch is equipped with first rotatory hole, the second arch is equipped with the rotatory hole of second, the regulating block respectively with first rotatory hole, the rotatory hole swing joint of second.
As a preferred embodiment, the first protrusion of the adjusting bracket is a movable block which is detachably mounted, and the base is provided with a second threaded hole corresponding to the first threaded hole and a mounting groove for mounting and limiting the movable block, so as to realize the fixed connection between the movable block and the adjusting bracket.
Furthermore, for realizing the rotation transmission connection of steering wheel and regulating block, the regulating block is equipped with first column spinner, the rotatory piece of second, first column spinner is located regulating block one side, the rotatory piece fixed connection of second in the other end of regulating block, first column spinner second rotatory piece all is less than the top face of regulating block, first column spinner with first rotatory hole rotates to be connected, the rotatory piece of second with the rotatory hole of second rotates to be connected, the rotatory piece of second is close to one side of steering wheel is equipped with the upset hole, the output shaft is output nut, the upset hole with output nut corresponds the setting, through the rotatory piece of second the movable block realizes the horizontal flip structure of regulating block.
As a preferred embodiment, the base is further provided with a limiting surface for limiting the turning angle of the supporting surface.
The invention further considers the extreme condition that the rotor wing is out of control, if the turning angle of the rotor wing has no related limit structure, and the turning angle is infinitely close to 90 degrees or more, the flight path of the unmanned aerial vehicle becomes disordered and has the risk of crash, the difficulty is further increased for identifying and controlling the steering engine, and various problems can be brought to the routing of various motors in the flight lever.
As a preferred embodiment, the distance between the limiting surface and the turning central shaft of the adjusting block ranges from 5 mm to 20 mm.
As a preferred embodiment, one end of the first protrusion close to the rotor is provided with an arc surface for adapting to the flight and the overturn of the rotor.
As a preferred embodiment, the second protrusion includes a branch portion, the branch portion protrudes and is disposed obliquely upward, and the branch portion is used for achieving vertical fixation of the steering engine.
In order to realize vertical fixation of the steering engine, in one implementation mode, the steering engine can be fixed on the flight rod and is arranged close to the adjusting support to realize rotary connection with the adjusting block device, but the mode can cause that the steering engine fixing structure and the adjusting support are not compact in structure and have certain influence on the flight of the airplane body; therefore, in order to overcome the defects, the invention further designs a flight rod structure which enables the adjusting bracket and the steering engine to be installed and fixed into a whole, the branch part is protruded and obliquely upwards arranged, so that enough space is reserved at the top end of the branch part to fix the steering engine, the protruded and obliquely upwards arranged flight rod structure can be well suitable for oblique arrangement, and meanwhile, the rear steering engine can be well vertically fixed; the steering engine fixing mode of vertical fixation can better match the rotation of the adjusting block.
As a preferable embodiment, the steering engine is provided with a mounting plate, the mounting plate is provided with a mounting hole, the second protrusion is provided with a fixing hole corresponding to the mounting hole, the steering engine is fixedly connected to the second protrusion through screw connection, and/or the mounting plate is arranged at one end of the support part, which is inclined upwards.
In a preferred embodiment, the mounting plate is provided with a concave structure.
As a preferred embodiment, the mounting plate is provided with a turnover hole for realizing the transmission connection between the output shaft and the adjusting block.
In order to realize the fixation of the steering engine on the top end of the branch part, the invention further designs a mounting plate capable of being used for fixation, the mounting plate is provided with a fixing plate with a bulge and a mounting hole, the steering engine is fixed on the mounting plate through a screw connection with better fixing effect and better rigid connection, the transmission is further realized through a turnover hole, and the steering engine drives the adjusting block and the rotor wing thereof to turn over on the basis of fixing the steering engine; for further strengthening the fixed strength of the steering engine and protecting the structure of the output shaft part at the front end of the steering engine, an installing plate with an inner concave is arranged, the structure of the output shaft part at the front end of the steering engine is embedded into the inner concave structure, and the force for fixing the steering engine is increased by combining the mode of screw connection.
In a preferred embodiment, the bottom of the adjusting bracket is a sleeve structure with a first opening, and the first opening is adapted to the flight bar.
In a preferred embodiment, an adjusting slit is arranged on one side of the sleeve close to the rotor wing, and a plurality of adjusting holes are formed in the adjusting slit.
In a preferred embodiment, the sleeve is provided with a first positioning hole, and the flight bar is provided with a second positioning hole corresponding to the first positioning hole.
Compared with the prior art, the invention has the beneficial effects that:
1) through setting up adjusting bracket and concrete structure, realized the drive integration of steering wheel, rotor motor in the one end of flight pole, avoided the position that flight pole and fuselage are connected to become the weak portion of drive connection, improved the efficiency of steering wheel to rotor structural control, be favorable to further the design to unmanned aerial vehicle control system.
2) The invention realizes a structure with a turning effect through the movable block and the rotating block, namely, the distance range between the limiting surface and the turning central shaft of the adjusting block is 5-20mm, and the movable installation and the adjustment of the adjusting block on the adjusting bracket are also realized.
Drawings
Fig. 1 is an overall structure diagram of a steering engine controlled two-wing drone of the invention.
Fig. 2 is a structural diagram of the end part of a flight rod of a steering engine controlled double-wing unmanned aerial vehicle.
Fig. 3 is a structural diagram of an adjusting block of a steering engine controlled double-wing unmanned aerial vehicle.
Fig. 4 is a schematic view of the output shaft connection of the steering engine controlled two-wing drone.
Fig. 5 is a partial front view of the flight bar end of a steering engine controlled two wing drone of the present invention.
Fig. 6 is a front view of a steering engine controlled twin wing drone of the present invention.
Detailed Description
The drawings are only for purposes of illustration and are not to be construed as limiting the invention. For a better understanding of the following embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
Example 1
As shown in fig. 1, a steering engine controlled two-wing unmanned aerial vehicle comprises a fuselage and a steering engine 500, two flight bars 110 are symmetrically fixed on two sides of the fuselage, the flight bars 110 are arranged obliquely upward, a rotor motor 400 is movably connected to one end of each flight bar 110 far away from the fuselage and is used for driving the rotor 300 to rotate, the steering engine 500 is further arranged at one end of each flight bar 110 far away from the fuselage and is used for controlling the rotation of the rotor motor 400 and the rotor 300, the adjusting bracket 200 is fixedly connected to one end of each flight bar 110 far away from the fuselage, the steering engine 500 controls the rotation of the rotor motor 400 and the rotor 300 through the adjusting bracket 200,
the fuselage is equipped with power 600, follows the flight bar 110 electricity is connected rotor motor 400 steering wheel 500 works as when rotor motor 400 starts, rotor 300 receives rotor motor 400 drives the fuselage goes up and down or control and turn to, works as when steering wheel 500 starts, steering wheel 500 drives rotor motor 400 with rotor 300 makes its certain angle of upset, combines rotor motor 400's drive, further realizes the every single move of fuselage turns to.
When the control mode of the steering engine 500 is designed, the corresponding control relation between the flight rod 110 and the steering engine 500 is considered, and the steering engine 500 is creatively arranged at the tail end of the flight, namely one end of the flight rod 110 far away from the machine body, so that the starting end of the flight rod 110 can be fixedly connected with the machine body, specifically can be rigidly connected, and the flight stability of the unmanned aerial vehicle is improved; meanwhile, by arranging the adjusting bracket 200, the adjusting bracket 200 is fixedly connected with the tail end of the flight rod 110, so that the tail end of the flight rod 110 can be regarded as two fixed connection points on the flight rod 110 in the unmanned aerial vehicle, and the influence of the flight rod 110 on the control of the motor or the steering engine 500 is reduced; through setting up installation rotor 300 and rotor motor 400 on adjusting bracket 200, by installing the upset of steering wheel 500 control rotor 300 and rotor motor 400 at the terminal flight pole 110 equally to can realize that the control end of rotor 300 all is located the same end on flight pole 110, make steering wheel 500 driven arm of force minimize, reduce steering wheel 500's energy consumption, also be favorable to follow-up design to unmanned aerial vehicle control system.
As shown in fig. 2, as a preferred embodiment, the adjusting bracket 200 is provided with an adjusting block 210 and a vertical portion, the adjusting block 210 is rotatably connected to the vertical portion for providing a rotatable horizontal supporting surface, the rotor motor 400 is fixedly connected to the horizontal supporting surface for rotatably supporting the rotor motor 400, the steering engine 500 has an output shaft 510, and the adjusting block 210 is connected to the output shaft 510 for driving the horizontal supporting surface to turn over.
In order to realize the connection between the adjusting bracket 200 and the rotor 300 and the rotor motor 400 thereof, when the adjusting block 210 is rotatably connected with the vertical part, providing a horizontal support surface, wherein the horizontal support surface comprises a horizontal support shaft, i.e., support of rotor motor 400, includes, but is not limited to, support in a horizontal direction, i.e., the horizontal support plane defined by the present invention is based on a reversible surface on the horizontal support shaft, moreover, a specific structure that the steering engine 500 drives the rotor 300 to turn over is provided through the fixed connection of the output shaft 510 and the adjusting block 210, wherein, the design of steering wheel 500 and regulation support 200 in this scheme, can be that steering wheel 500 snap-on is in the part that the midway of flight pole 110 is close to the part of adjusting support 200, also can be with steering wheel 500 setting on adjusting support 200, and it can to all be used for driving the rotation of adjusting block 210 that one end of equal fixed connection regulating block 210 is used for at last.
As a preferred embodiment, the vertical portion includes a first protrusion 220 and a second protrusion 230, the first protrusion 220 and the second protrusion 230 are respectively connected to the adjusting block 210 in a rotating manner, the adjusting bracket 200 is further provided with a base 240, the base 240 is fixedly connected to the first protrusion 220 and the second protrusion 230, and a lower side of the base 240 is rigidly connected to an end of the flight bar 110 away from the fuselage.
In order to realize the turnover of the adjusting block 210, the invention further defines the structure of the vertical part as two protrusions which are rotatably connected with the adjusting block 210, the structure of the rotor wing 300 is suspended in the air in the flying bar 110 and rotatably supported on the adjusting bracket 200 for realizing the rotation of the rotor wing 300, and simultaneously, the invention is further defined in the structure of the base 240 fixedly connected with the flying bar 110, and the driving part of the rotor wing 300 is intensively limited at one end of the flying bar 110 far away from the fuselage through the rigid connection of the base 240 and the flying bar 110, thereby overcoming the possibility that the flying bar 110 is used as a driving arm.
As shown in fig. 3 and 4, further, the first protrusion 220 is provided with a first rotating hole, the second protrusion 230 is provided with a second rotating hole, and the adjusting block 210 is movably connected to the first rotating hole and the second rotating hole respectively.
As a preferred embodiment, the first protrusion 220 of the adjusting bracket 200 is a movable block which is detachably mounted, the movable block is provided with a plurality of first threaded holes, the base 240 is provided with second threaded holes corresponding to the first threaded holes and a mounting groove for mounting the movable block in a limiting manner, so as to fixedly connect the movable block and the adjusting bracket 200.
Further, for realizing the rotation transmission connection of the steering engine 500 and the adjusting block 210, the adjusting block 210 is provided with a first rotating column 211 and a second rotating block 212, the first rotating column 2111 is arranged on one side of the adjusting block 210, the second rotating block 212 is fixedly connected to the other end of the adjusting block 210, the first rotating column 211 and the second rotating block 212 are both lower than the top end face of the adjusting block 210, the first rotating column 211 is rotatably connected with the first rotating hole, the second rotating block 212 is rotatably connected with the second rotating hole, one side of the second rotating block close to the steering engine 500 is provided with a turnover hole, the output shaft 510 is an output nut, the turnover hole corresponds to the output nut, and the horizontal turnover structure of the adjusting block 210 is realized through the second rotating block 212 and the movable block.
As shown in fig. 5, as a preferred embodiment, the base 240 is further provided with a limiting surface 241 for limiting the turning angle of the supporting surface.
The invention further considers the extreme condition that the rotor 300 is out of control, if the turning angle of the rotor 300 has no relevant limit structure, and the turning angle is infinitely close to 90 degrees or more, the flight path of the unmanned aerial vehicle becomes disordered and has the risk of crash, so that the difficulty is further increased for identifying and controlling the steering engine 500, and various problems can be brought to the routing of various motors in the flight bar 110.
In a preferred embodiment, the distance between the limiting surface 241 and the turning center axis of the adjusting block 210 is 5-20 mm.
In a preferred embodiment, an end of the first protrusion 220 close to the rotor 300 is provided with a cambered surface for adapting to the flight and the overturn of the rotor 300.
As a preferred embodiment, the second protrusion 230 includes a branch portion, the branch portion protrudes and is disposed obliquely upward, and the branch portion is used for realizing vertical fixation of the steering engine 500.
In order to vertically fix the steering engine 500, in one embodiment, the steering engine 500 may be fixed on the flight rod 110, and is arranged close to the adjusting bracket 200 to realize the rotary connection with the adjusting block 210 device, but the mode may cause the structure of the steering engine 500 fixing structure and the adjusting bracket 200 to be not compact, and may have a certain influence on the flight of the fuselage; therefore, in order to overcome the defects, the adjusting bracket 200 and the steering engine 500 are further designed to be installed and fixed to be integrated, the branch part is arranged in a protruding and inclined upward mode, the top end of the branch part is provided with enough space to fix the steering engine 500, the flight rod 110 structure which can be well suitable for inclined arrangement is arranged in a protruding and inclined upward mode, and meanwhile the rear steering engine 500 can be well fixed vertically; the steering engine 500 is fixed vertically, so that the rotation of the adjusting block 210 can be better matched.
As a preferable embodiment, the steering engine 500 is provided with a mounting plate, the mounting plate is provided with a mounting hole, the second protrusion 230 is provided with a fixing hole corresponding to the mounting hole, and the steering engine 500 is fixedly connected to the second protrusion 230 through a screw connection, and/or the mounting plate is arranged at one end of the branch part inclined upwards.
In a preferred embodiment, the mounting plate is provided with a concave structure.
In a preferred embodiment, the mounting plate is provided with a turnover hole for realizing the transmission connection between the output shaft 510 and the adjusting block 210.
In order to realize the fixation of the steering engine 500 on the top end of the branch part, the invention further designs a mounting plate which can be used for fixation, a fixing plate with a bulge and a mounting hole is arranged, the steering engine 500 is fixed on the mounting plate through a screw connection with better fixing effect and better rigid connection, the transmission is further realized through a turnover hole, and the steering engine 500 is further realized to drive the adjusting block 210 and the rotor 300 thereof to turn over on the basis of fixing the steering engine 500; for further strengthening the fixed intensity of steering wheel 500 and protecting the structure of steering wheel 500 front end output shaft 510 part, set up the mounting panel that has the indent, with steering wheel 500 front end output shaft 510 part structure embedding indent structure, combine the mode of screw connection, increased fixed steering wheel 500's dynamics.
In a preferred embodiment, the bottom of the adjusting bracket 200 is a sleeve structure having a first opening, and the first opening is adapted to the flight bar 110.
In a preferred embodiment, an adjusting slit is provided at a side of the sleeve close to the rotor 300, and the adjusting slit is provided with a plurality of adjusting holes.
In a preferred embodiment, the sleeve is provided with a first positioning hole, and the end of the flight bar 110 is provided with a second positioning hole corresponding to the first positioning hole.
As shown in fig. 6, as a preferred embodiment, the fuselage further includes a positioning instrument 700, the unmanned aerial vehicle is provided with a control system, the power supply 600 is provided inside the fuselage, the fuselage is provided with a positioning instrument 700 connected with the power supply 600, the positioning instrument 700 is further wirelessly connected with the control system, and is used for transmitting the three-dimensional position information of the unmanned aerial vehicle to the control system.
Illustratively, the installation of the inventive product at the end of the flight bar 110 is: firstly, assembling the rotor motor 400 and the rotor 300 on the adjusting block 210, then embedding the sleeve structure of the base 240 into the flight bar 110, fixing the base 240 at the end of the flight bar 110 through the matching of the first positioning hole and the second positioning hole, and adjusting or reinforcing the connection between the base and the flight bar through the matching of the adjusting holes; through the structure of mounting panel, steering wheel 500 and its output shaft 510 fixed mounting are in one side of adjusting bracket 200, make output shaft 510 connect the rotatory piece 212 of second through the upset hole at the mounting panel, align the first rotatory hole of first arch 220 with the first column spinner of regulating block 210, arrange rotor 300, rotor motor 400, regulating block 210, the integrated configuration that first arch 220 formed in base 240 top, fix regulating block 210 at the rotatory piece 212 of second, make first arch 220 fix the mounting groove at base 240, accomplish the installation of flight pole 110 end structure.
The "fit" of the various holes described includes the manner in which the screws fit the holes.
The invention has the following beneficial effects:
1) through setting up adjusting bracket 200 and concrete structure, realized the drive integration of steering wheel 500, rotor motor 400 in the one end of flight pole 110, avoided the position that flight pole 110 is connected with the fuselage to become the weak part of drive connection, improved steering wheel 500 efficiency to rotor 300 structural control, be favorable to further design to unmanned aerial vehicle control system.
2) The invention realizes a structure with a turning effect through the movable block and the rotating block, namely, the distance range between the limiting surface 241 and the turning central shaft of the adjusting block 210 is 5-20mm, and the movable installation and the adjustment of the adjusting block 210 on the adjusting bracket 200 are also realized.
It should be understood that the examples are merely for clearly illustrating the technical solutions of the present invention, and are not intended to limit the specific embodiments of the present invention. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention claims should be included in the protection scope of the present invention claims.
Claims (10)
1. A steering engine controlled double-wing unmanned aerial vehicle comprises a fuselage and a steering engine (500), wherein two flying rods (110) are symmetrically fixed on two sides of the fuselage, the flying rods (110) are arranged obliquely upwards, one ends, far away from the fuselage, of the flying rods (110) are movably connected with a rotor motor (400) and used for driving the rotation of a rotor wing (300), one ends, far away from the fuselage, of the flying rods (110) are also provided with the steering engine (500) and used for controlling the overturning of the rotor motor (400) and the rotor wing (300), and the steering engine is characterized in that one ends, far away from the fuselage, of the flying rods (110) are fixedly connected with an adjusting bracket (200), the steering engine (500) controls the overturning of the rotor motor (400) and the rotor wing (300) through the adjusting bracket (200),
the aircraft body is provided with a power supply (600), the rotor motor (400) and the steering engine (500) are electrically connected along the flight rod (110),
when rotor motor (400) starts, rotor (300) receive rotor motor (400) drive drives the fuselage goes up and down or turns to about, works as when steering wheel (500) start, steering wheel (500) drive rotor motor (400) with rotor (300) make its certain angle of upset, combine rotor motor (400)'s drive, further realize the every single move of fuselage turns to.
2. The steering engine controlled double-wing unmanned aerial vehicle according to claim 1, wherein the adjusting bracket (200) is provided with an adjusting block (210) and a vertical portion, the adjusting block (210) is rotatably connected with the vertical portion and used for providing a rotatable horizontal supporting surface, the rotor motor (400) is fixedly connected with the horizontal supporting surface and used for rotatably supporting the rotor motor (400), the steering engine (500) is provided with an output shaft (510), and the adjusting block (210) is connected with the output shaft (510) and used for driving the horizontal supporting surface to turn over.
3. The steering engine controlled double-wing unmanned aerial vehicle of claim 2, wherein the vertical portion comprises a first protrusion (220) and a second protrusion (230), the first protrusion (220) and the second protrusion (230) are respectively connected with the adjusting block (210) in a rotating manner, the adjusting bracket (200) is further provided with a base (240), the base (240) is fixedly connected with the first protrusion (220) and the second protrusion (230), and the lower side of the base (240) is rigidly connected with one end, far away from the fuselage, of the flying rod (110).
4. The steering engine controlled double-wing unmanned aerial vehicle of claim 3, wherein the base (240) is further provided with a limiting surface (241) for limiting the turning angle of the supporting surface.
5. The steering engine controlled double-wing unmanned aerial vehicle of claim 3, wherein one end of the first protrusion (220) close to the rotor (300) is provided with an arc surface for adapting to the flight and overturn of the rotor (300).
6. The steering engine controlled double-wing unmanned aerial vehicle according to claim 3, wherein the second protrusion (230) comprises a branch portion, the branch portion protrudes and is arranged obliquely upwards, and the branch portion is used for achieving vertical fixation of the steering engine (500).
7. The steering engine controlled double-wing unmanned aerial vehicle according to claim 6, wherein the steering engine (500) is provided with a mounting plate, the mounting plate is provided with mounting holes, the second protrusions (230) are provided with fixing holes corresponding to the mounting holes, the steering engine (500) is fixedly connected to the second protrusions (230) through screw connection, and/or the mounting plate is arranged at one end of the branch part, which is inclined upwards.
8. The steering engine controlled double-wing unmanned aerial vehicle of claim 7, wherein the mounting plate is provided with an indent structure.
9. The steering engine controlled double-wing drone according to any one of claims 1 to 8, characterized in that the bottom of the adjusting bracket (200) is a sleeve structure with a first opening, which is adapted to the flight bar (110).
10. The steering engine controlled double-wing unmanned aerial vehicle of claim 9, wherein one side of the sleeve near the rotor (300) is provided with an adjusting slit.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202110313250.0A CN112849401A (en) | 2021-03-24 | 2021-03-24 | Steering engine control's two wing unmanned aerial vehicle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202110313250.0A CN112849401A (en) | 2021-03-24 | 2021-03-24 | Steering engine control's two wing unmanned aerial vehicle |
Publications (1)
Publication Number | Publication Date |
---|---|
CN112849401A true CN112849401A (en) | 2021-05-28 |
Family
ID=75992569
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202110313250.0A Pending CN112849401A (en) | 2021-03-24 | 2021-03-24 | Steering engine control's two wing unmanned aerial vehicle |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN112849401A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110510101A (en) * | 2019-10-08 | 2019-11-29 | 漳州鹰航电子科技有限公司 | A kind of aircraft |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN202128911U (en) * | 2011-07-07 | 2012-02-01 | 广州大学 | Remote-control electric side-by-side twin rotor helicopter model airplane |
US20170137122A1 (en) * | 2013-08-14 | 2017-05-18 | Bell Helicopter Textron Inc. | Maintaining Drive System Alignment in Tiltrotor Aircraft |
CN108357674A (en) * | 2018-04-17 | 2018-08-03 | 山东农业大学 | It can small more rotor unmanned aircrafts of paddle outside big paddle in tilted propeller |
CN211618110U (en) * | 2019-12-17 | 2020-10-02 | 黑龙江科技大学 | Diaxon VTOL unmanned aerial vehicle |
-
2021
- 2021-03-24 CN CN202110313250.0A patent/CN112849401A/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN202128911U (en) * | 2011-07-07 | 2012-02-01 | 广州大学 | Remote-control electric side-by-side twin rotor helicopter model airplane |
US20170137122A1 (en) * | 2013-08-14 | 2017-05-18 | Bell Helicopter Textron Inc. | Maintaining Drive System Alignment in Tiltrotor Aircraft |
CN108357674A (en) * | 2018-04-17 | 2018-08-03 | 山东农业大学 | It can small more rotor unmanned aircrafts of paddle outside big paddle in tilted propeller |
CN211618110U (en) * | 2019-12-17 | 2020-10-02 | 黑龙江科技大学 | Diaxon VTOL unmanned aerial vehicle |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110510101A (en) * | 2019-10-08 | 2019-11-29 | 漳州鹰航电子科技有限公司 | A kind of aircraft |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8544787B2 (en) | High performance tilt rotor aircraft in which nacelle tilt angle and flaperon angle mechanically interwork with each other | |
EP2353684B1 (en) | VTOL model aircraft | |
JP2021522111A (en) | Electric tilt rotor aircraft | |
US20210323661A1 (en) | Coaxial helicopter and control method thereof | |
CN107336833B (en) | Composite unmanned aerial vehicle and control method | |
CN106477032A (en) | Multi-axis aircraft | |
US7644887B2 (en) | Yaw control system and method | |
CN110171568A (en) | One kind can hover flapping wing aircraft | |
JP2006518246A (en) | A horizontal tail structure capable of fast and stable turning in a remotely adjusted vehicle. | |
JP2014076674A (en) | Co-axial reversing type unmanned helicopter | |
CN112644701A (en) | Transverse double-rotor unmanned aerial vehicle | |
CN112849401A (en) | Steering engine control's two wing unmanned aerial vehicle | |
CN109131866A (en) | The compound unmanned plane of multiaxis fixed-wing and its flight control method | |
WO2021047988A1 (en) | Attitude control mechanism for a flapping wing aerial vehicle | |
CN105480414A (en) | Coaxial double-rotor helicopter core and helicopter | |
CN216102767U (en) | Unmanned aerial vehicle rotor control structure | |
CN114619817A (en) | Flight power system and hovercar | |
CN214383413U (en) | Steering engine control's two wing unmanned aerial vehicle | |
CN212195888U (en) | Dual-rotor unmanned aerial vehicle | |
KR20090067686A (en) | Tilt-duct aircraft and attitude-control of same | |
KR102134746B1 (en) | Removable Coaxial Reversal Drones | |
CN111319762A (en) | Biax rotor unmanned vehicles that verts | |
CN214451820U (en) | Transverse double-rotor unmanned aerial vehicle | |
CN111846220B (en) | Flapping wing aircraft | |
CN212980530U (en) | Flapping wing aircraft |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210528 |
|
RJ01 | Rejection of invention patent application after publication |