CN205221104U - A motor for having more rotor unmanned aerial vehicle power device - Google Patents
A motor for having more rotor unmanned aerial vehicle power device Download PDFInfo
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- CN205221104U CN205221104U CN201521089166.1U CN201521089166U CN205221104U CN 205221104 U CN205221104 U CN 205221104U CN 201521089166 U CN201521089166 U CN 201521089166U CN 205221104 U CN205221104 U CN 205221104U
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Abstract
The utility model discloses a motor for having more rotor unmanned aerial vehicle power device, the rotor of motor is hollow transmission shaft, the inside rotation isolation hollow shaft that is of hollow transmission shaft, hollow transmission shaft cup joints the class bearing parts of constitution that links to each other with the rotatory hollow shaft of keeping apart, install the pitch that to carry out piston push -and -pull campaign in the rotatory isolation hollow shaft and adjust the pole, hollow transmission shaft constitutes electric motor rotor as type bearing parts's outer loop, rotatory inner ring of keeping apart hollow shaft conduct type bearing parts links to each other with motor stator is fixed, the outer loop with place two holders between the inner ring, place the ball in the holder. The utility model discloses design into hollow structure with electric motor rotor, through at the pitch change of motor internally mounted pitch regulation pole with push -and -pull piston motion drive motor screw, realize changing the lift that the screw produced fast, showing the mobility, maneuverability and the security that improve many rotors.
Description
Technical field
The utility model relates to a kind of electric machine, particularly relates to a kind of motor for many rotor wing unmanned aerial vehicles engine installation.
Background technology
Robot airplane is called for short " unmanned plane ", and english abbreviation is " UAV ", is the not manned aircraft utilizing radio robot to handle with the process controller provided for oneself.Can be divided into from technical standpoint definition: depopulated helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol etc.Unmanned plane at present taking photo by plane, agricultural plant protection, the field such as mapping obtain widespread use.
In recent years, because of the handling that many rotor structures are simple and excellent, develop into the main flow unmanned plane type in Small and micro-satellite market, the flying power of many rotor wing unmanned aerial vehicles and pose adjustment have been coordinated by multiple rotor, and the lift variation of each rotor depends on the velocity variations of screw propeller, when paddle size is larger, inertia is larger, propeller speed change is slower, manoevreability and road-holding property poorer, this becomes one of key factor that the many rotor of restriction large scale develops.Therefore, be necessary to improve existing many rotor wing unmanned aerial vehicles engine installation.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of motor for many rotor wing unmanned aerial vehicles engine installation, use this motor can realize many rotor wing unmanned aerial vehicles engine installation of variable-pitch easily, the lift that quick change screw propeller produces, significantly improve the manoevreability of many rotors, road-holding property and safety, and structure is simple, easy to implement.
The utility model is solve the problems of the technologies described above the technical scheme adopted to be to provide a kind of motor for many rotor wing unmanned aerial vehicles engine installation, the rotor of described motor is Hollow Transmission Shafts, described Hollow Transmission Shafts inside is for rotating isolation hollow shaft, described Hollow Transmission Shafts is isolated hollow shaft with rotation and is socketed the formation class bearing parts that are connected, and is provided with the pitch control rod that can carry out piston push-and-pull campaign in described rotation isolation hollow shaft.
The above-mentioned motor for many rotor wing unmanned aerial vehicles engine installation, wherein, described Hollow Transmission Shafts forms rotor as the outer shroud of class bearing parts, the described isolation hollow shaft that rotates is fixedly linked as the inner ring of class bearing parts and motor stator, two retainers are placed between described outer shroud and described inner ring, described two retainers, near the two ends of Hollow Transmission Shafts, place ball in described retainer, thus isolate the passage of rotor turns Hollow Transmission Shafts Inner Constitution one.
The above-mentioned motor for many rotor wing unmanned aerial vehicles engine installation, wherein, described pitch control rod comprises synchronous pivoted arm and pull bar, one end of described synchronous pivoted arm connects the first gangbar by the first single degree of freedom rotary joint, the other end connects the second gangbar by the second single degree of freedom rotary joint, the centre of described synchronous pivoted arm is rotatedly connected by the upper end of the 4th single degree of freedom rotary joint and pull bar, the lower end of described pull bar connects the 3rd gangbar by the 3rd single degree of freedom rotary joint, described first gangbar, the other end of the second gangbar and the 3rd gangbar is equipped with displacement joint shaft trepanning.
The utility model contrast prior art has following beneficial effect: rotor design is become Hollow Transmission Shafts by the motor for many rotor wing unmanned aerial vehicles engine installation that the utility model provides, change with the pitch of push-and-pull piston movement drive motor screw propeller by installing pitch control rod at Hollow Transmission Shafts motor internal, realize the lift changing screw propeller generation fast, significantly improve the manoevreability of many rotors, road-holding property and safety, and structure is simple, easy to implement.
Accompanying drawing explanation
Fig. 1 is many rotor wing unmanned aerial vehicles engine installation structural representation of the variable-pitch be made up of the utility model motor;
Fig. 2 is the controllable pitch propeller structural representation that the utility model uses;
Fig. 3 a is hollow shaft motor axial section structural representation of the present utility model;
Fig. 3 b is another axial section structural representation of hollow shaft motor of the present utility model;
Fig. 3 c is hollow shaft motor horizontal section structural representation of the present utility model;
Fig. 4 is pitch control rod structural representation of the present utility model;
Fig. 5 is the unmanned structural representation of four rotors of the variable-pitch be made up of the utility model motor.
In figure:
1 frame arm 2 screw propeller 3 motor
The 4 pitch control rod 5 steering wheel 5a steering wheel arm of forces
6 electronic compartment structure 21 blade 22 pitch changing actuators
221 blade geometrical clamp 222 pitch change axes 223 propeller hubs
221a displacement universal driving shaft 31 Hollow Transmission Shafts 32 rotates isolation hollow shaft
33 ball 41 first single degree of freedom rotary joint 42 second single degree of freedom rotary joints
43 the 3rd single degree of freedom rotary joint 44 the 4th single degree of freedom rotary joints
45 first gangbar 46 second gangbar 47 the 3rd gangbar
Synchronous pivoted arm 410 pull bar of 48 displacement joint shaft trepanning 49
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model will be further described.
Fig. 1 is many rotor wing unmanned aerial vehicles engine installation structural representation of the variable-pitch be made up of the utility model motor.
The many rotor wing unmanned aerial vehicles of fixed pitch are by regulating the velocity of rotation of multiple screw propeller to change its lift produced with implementation space maneuvering flight.In fact except rotating speed, the pitch of propeller blades also can change the lift of screw propeller; So how safe and reliablely realize pitch control.The utility model considers the many rotor wing unmanned aerial vehicles engine installation providing a kind of variable-pitch, and will realize variable-pitch, and key to provide a kind of special hollow shaft motor.Refer to Fig. 1, many rotor wing unmanned aerial vehicles of the present utility model are spliced by 4 and above even number many rotor wing unmanned aerial vehicles engine installation and form, symmetrical and axially symmetric structure centered by described multiple engine installation, described engine installation comprises frame arm 1, the end of frame arm 1 is provided with motor 3 and steering wheel 5, the other end of frame arm 1 is fixedly installed in the electronic compartment structure 6 of many rotors geometric centre, wherein, the rotor of described motor 3 is Hollow Transmission Shafts 31, described Hollow Transmission Shafts 31 inside is for rotating isolation hollow shaft 32, in described rotation isolation hollow shaft 32, the pitch control rod 4 that can carry out piston push-and-pull campaign is installed, described pitch control rod 4 is rotatedly connected with screw propeller 2, described screw propeller 2 comprises two panels blade 21 and pitch changing actuator 22, the upper end of described pitch control rod 4 and the pitch changing actuator 22 of screw propeller 2 are rotationally connected, and lower end and the steering wheel arm of force 5a of described pitch control rod 4 are rotationally connected.
As shown in Figure 2, described pitch changing actuator 22 comprises two blade geometrical clamps, 221, two pitch change axes 222 and propeller hub 223 to the spendable pitch changing actuator of the utility model; Described two panels blade 21 is arranged on blade geometrical clamp 221, and described blade geometrical clamp 221 rotates around pitch change axes 222 blade angle changing blade 21; Described two blade geometrical clamps 221 are respectively provided with displacement universal driving shaft 221a, and described displacement universal driving shaft embeds the first gangbar 45 of pitch control rod 4 and the displacement joint shaft trepanning 48 of the second gangbar 46 end respectively, forms single degree of freedom rotary joint; Propeller hub 223 is fixedly mounted in the Hollow Transmission Shafts 31 of motor 3, rotated by Hollow Transmission Shafts 31 carrying screws, steering wheel 5 drives pitch control rod 4 to carry out piston push-and-pull campaign, thus drive blade geometrical clamp 221 to rotate around its pitch change axes 222 to adjust the blade angle of blade 21, realize pitch control.
The motor 3 for many rotor wing unmanned aerial vehicles engine installation that the utility model provides, described Hollow Transmission Shafts 31 is isolated hollow shaft 32 with rotation and is socketed formation class bearing parts, the outer shroud of described class bearing parts is rotor (i.e. Hollow Transmission Shafts 31), inner ring (namely rotating isolation hollow shaft 32) is fixedly linked with motor stator, two retainers are placed between described outer shroud and affiliated inner ring, described two retainers lay respectively at the two ends near Hollow Transmission Shafts, ball is placed in described retainer, thus the passage of rotor turns is isolated Hollow Transmission Shafts Inner Constitution one.Concrete structure is as shown in Fig. 3 a, Fig. 3 b and Fig. 3 c.
Please continue see Fig. 4, the motor for many rotor wing unmanned aerial vehicles engine installation that the utility model provides, described pitch control rod 4 comprises synchronous pivoted arm 49 and pull bar 410, one end of described synchronous pivoted arm 49 connects the first gangbar 45 by the first single degree of freedom rotary joint 41, the other end connects the second gangbar 46 by the second single degree of freedom rotary joint 42, the centre of described synchronous pivoted arm 49 is rotatedly connected by the upper end of the 4th single degree of freedom rotary joint 44 and pull bar 410, the lower end of described pull bar 410 connects the 3rd gangbar 47 by the 3rd single degree of freedom rotary joint 43, described first gangbar 45, the other end of the second gangbar 46 and the 3rd gangbar 47 is equipped with displacement joint shaft trepanning 48, displacement joint shaft trepanning 48 in described first gangbar 45 embeds in a displacement universal driving shaft 221a of screw propeller 2 and forms the 5th single degree of freedom rotary joint, another displacement universal driving shaft 221a that displacement joint shaft trepanning 48 in described second gangbar 46 embeds screw propeller 2 forms the 6th single degree of freedom rotary joint, described 5th single degree of freedom rotary joint, 6th single degree of freedom rotary joint and the first single degree of freedom rotary joint 41, second single degree of freedom rotary joint 42 is all at a rotation with in surface, displacement joint shaft trepanning 48 in described 3rd gangbar 47 and the displacement joint shaft trepanning on steering wheel arm of force 5a are by additional joint shaft composition the 7th single degree of freedom rotary joint, described 7th single degree of freedom rotary joint and the 3rd single degree of freedom rotary joint 43 are at same rotation with in surface, the synchronous pivoted arm 49 of described pitch control rod 4 can rotate around the pull bar 410 of described pitch control rod 4, described synchronous pivoted arm 49 and screw propeller coaxial synchronous axial system in a plane, described steering wheel 5 drives pitch control rod 4 to make pull bar 410 do piston push-and-pull campaign in rotation isolation hollow shaft 32, thus realizes pitch adjustment by driving blade geometrical clamp 221 to rotate to change blade angle around pitch change axes 222.
Many rotor wing unmanned aerial vehicles engine installation of the variable-pitch that the utility model provides, by installing pitch control rod 4 in motor 3 inside, the synchronous pivoted arm 49 of motor 3 carrying screws 2 and pitch control rod 4 carries out co-rotation around Hollow Transmission Shafts with around pull bar 410 respectively, steering wheel 5 drives the pull bar 410 of pitch control rod 4 to do piston push-and-pull campaign the distance of synchronous pivoted arm 49 opposed helical oar 2 is changed in rotation isolation hollow shaft 32, thus cause the first gangbar 45 of positional symmetry and the second gangbar 46 to drive two blade geometrical clamps 221 to rotate to change the blade angle of blade 21 around pitch change axes 222 simultaneously, the pitch of screw propeller 2 is made to change rapidly to change the lift of screw propeller generation and realize fast maneuver.Please continue see Fig. 5, for four rotor wing unmanned aerial vehicles, four rotors by 4 described frame arm 1 with Central Symmetry and axially symmetric structure form, one end of frame arm 1 not mounted motor is fixed in the electronic compartment structure 6 of four rotor geometric centres, therefore there is four symmetry machine booms and propulsion source, the propeller hub 223 of four screw propellers 2 is fixedly installed in the Hollow Transmission Shafts 31 of the motor 3 in frame arm 1 respectively, adjacent screw propeller 2 hand of rotation is contrary, screw propeller 2 hand of rotation on diad is identical, fixed pitch four rotor regulates 4 motor speeds to change the lift of screw propeller generation by control algorithm, thus implementation space 6DOF maneuvering flight, propeller rotational inertia is larger, speed changes slower, manoevreability and road-holding property are also poorer, totally unfavorable to stabilized flight.And the motor speed of variable-pitch four rotor of the present utility model is constant, pitch adjustment is realized by the pitch changing actuator 22 of propeller blades 2, thus change the lift of screw propeller generation, owing to not being subject to the impact of propeller rotational inertia, screw propeller lift will reach expectation value rapidly, significantly improves manoevreability and the road-holding property of unmanned plane; In addition, blade angle is adjusted to the blowing direction that negative value can also change blade, make unmanned plane not only can to canyon, also can to up-draught, when to up-draught, four rotors fly with the attitude turned upside down, such as, when unmanned plane due to mission requirements or attitude maneuver excessive and cause upset and reverse time, still can normally control, thus enable four rotors all controlled under any attitude, substantially increase the flight safety of four rotors.
Although the utility model discloses as above with preferred embodiment; so itself and be not used to limit the utility model; any those skilled in the art; not departing from spirit and scope of the present utility model; when doing a little amendment and perfect, therefore protection domain of the present utility model is when being as the criterion of defining with claims.
Claims (3)
1. the motor for many rotor wing unmanned aerial vehicles engine installation, it is characterized in that, the rotor of described motor is Hollow Transmission Shafts (31), described Hollow Transmission Shafts (31) inside is for rotating isolation hollow shaft (32), described Hollow Transmission Shafts (31) is isolated hollow shaft (32) with rotation and is socketed the formation class bearing parts that are connected, and is provided with the pitch control rod (4) that can carry out piston push-and-pull campaign in described rotation isolation hollow shaft (32).
2. as claimed in claim 1 for the motor of many rotor wing unmanned aerial vehicles engine installation, it is characterized in that, described Hollow Transmission Shafts (31) forms rotor as the outer shroud of class bearing parts, describedly rotate isolation hollow shaft (32) and be fixedly linked as the inner ring of class bearing parts and motor stator, two retainers are placed between described outer shroud and described inner ring, described two retainers are near the two ends of Hollow Transmission Shafts (31), ball (33) is placed in described retainer, thus the passage of rotor turns is isolated Hollow Transmission Shafts (31) Inner Constitution one.
3. as claimed in claim 1 for the motor of many rotor wing unmanned aerial vehicles engine installation, it is characterized in that, described pitch control rod (4) comprises synchronous pivoted arm (49) and pull bar (410), one end of described synchronous pivoted arm (49) connects the first gangbar (45) by the first single degree of freedom rotary joint (41), the other end connects the second gangbar (46) by the second single degree of freedom rotary joint (42), the centre of described synchronous pivoted arm (49) is rotatedly connected by the upper end of the 4th single degree of freedom rotary joint (44) and pull bar (410), the lower end of described pull bar (410) connects the 3rd gangbar (47) by the 3rd single degree of freedom rotary joint (43), described first gangbar (45), the other end of the second gangbar (46) and the 3rd gangbar (47) is equipped with displacement joint shaft trepanning (48).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521089166.1U CN205221104U (en) | 2015-12-24 | 2015-12-24 | A motor for having more rotor unmanned aerial vehicle power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521089166.1U CN205221104U (en) | 2015-12-24 | 2015-12-24 | A motor for having more rotor unmanned aerial vehicle power device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205221104U true CN205221104U (en) | 2016-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521089166.1U Active CN205221104U (en) | 2015-12-24 | 2015-12-24 | A motor for having more rotor unmanned aerial vehicle power device |
Country Status (1)
| Country | Link |
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| CN (1) | CN205221104U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105383691A (en) * | 2015-12-24 | 2016-03-09 | 上海埃威航空电子有限公司 | Motor used for multi-rotor-wing unmanned aerial vehicle power device |
| CN110127038A (en) * | 2019-05-27 | 2019-08-16 | 安徽卓尔航空科技有限公司 | A kind of propeller hub of adjustable-piston |
-
2015
- 2015-12-24 CN CN201521089166.1U patent/CN205221104U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105383691A (en) * | 2015-12-24 | 2016-03-09 | 上海埃威航空电子有限公司 | Motor used for multi-rotor-wing unmanned aerial vehicle power device |
| CN105383691B (en) * | 2015-12-24 | 2017-07-28 | 上海埃威航空电子有限公司 | Motor for multi-rotor unmanned aerial vehicle power set |
| CN110127038A (en) * | 2019-05-27 | 2019-08-16 | 安徽卓尔航空科技有限公司 | A kind of propeller hub of adjustable-piston |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |