CN109625246B - Internal excitation automatic balancing device for propeller - Google Patents
Internal excitation automatic balancing device for propeller Download PDFInfo
- Publication number
- CN109625246B CN109625246B CN201811378231.0A CN201811378231A CN109625246B CN 109625246 B CN109625246 B CN 109625246B CN 201811378231 A CN201811378231 A CN 201811378231A CN 109625246 B CN109625246 B CN 109625246B
- Authority
- CN
- China
- Prior art keywords
- plate
- coil
- balancing device
- propeller
- balance weight
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/008—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft characterised by vibration absorbing or balancing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/15—Propellers having vibration damping means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/28—Other means for improving propeller efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Balance (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an internal excitation automatic balancing device for a propeller, which is designed to be installed at a propeller shaft and can realize the online suppression of the unbalanced vibration of the propeller. The internal excitation automatic balancing device is of an annular structure and mainly comprises a static ring and a dynamic ring. The static ring comprises an excitation coil and a counterweight plate positioning Hall sensor; the movable ring comprises two counterweight plates embedded with permanent magnets and counterweight blocks, and the position self-locking is realized through the side magnetic plates when no external magnetic field exists; the static ring is connected with the dynamic ring through a bearing. When the coil is electrified, the counterweight plate can generate stepping rotation to perform unbalance compensation. The invention can design the mounting structure according to the actual requirements of the propeller, and is respectively suitable for different mounting modes and different balancing capability requirements. The invention has advantages in the aspects of the weight of the excitation coil, the balance capability, the installation convenience and the like.
Description
Technical Field
The invention belongs to the technical field of automatic balance of rotating machinery, and particularly relates to an automatic balance device which is suitable for automatic balance of a propeller and can be used for real-time online vibration suppression.
Background
The propeller generates power by the rotation of the blades in the air or water, and in the field of current general aviation and marine transportation, the propeller power device is widely applied with good economy and high propulsion efficiency, such as propellers of propeller airplanes and ships. The propeller is used as a high-speed rotating part, and errors of manufacturing, assembling and the like can cause the propeller to inevitably generate mass center deviation after being assembled, or mass center deviation caused by mass change of blades in flight and the like can cause the propeller to generate unbalanced vibration in the high-speed rotating process. In actual use, the problem of propeller vibration caused by mass unbalance is prominent, structural fatigue damage of related parts is caused, and even blade breakage accidents happen in severe cases, so that the propeller must be trimmed to reduce the vibration value level. Therefore, how to more conveniently and effectively realize the dynamic balance of the propeller is a difficult problem to be solved urgently in the engineering science and technology field.
Researches are carried out on the automatic balance of the propeller at home and abroad, and the researches are as follows.
An automatic balancing device for a rotating main shaft of an airplane is invented by Hofmann company in Germany in 2012. Solid or liquid material with thixotropic property is adopted, and the position of the solid or liquid material is automatically adjusted by centrifugal force and is filled in a cavity surrounding a rotating main shaft. Automatic balancing is achieved by changing the position of the thixotropic material. The balancing mode is a passive automatic balancing mode, and strict requirements are imposed on thixotropic materials and the rotating speed of a main shaft of an airplane in the balancing process. The difference from the invention lies in: the balancing method used by the invention is to achieve dynamic balance by driving the position of a balancing weight in the automatic balancing device through internal excitation, and belongs to an active balancing device.
The american Lord company, as the earliest published patents in 2008 and 2009, WO2008127362A3 and US20090306829a1, propose a propeller automatic balancing system for aeroengines. The automatic balance actuator is arranged at the inner side position close to the paddle in a shaft penetrating mode. Different from the invention, the static ring of the automatic balancing device is arranged outside the dynamic ring, namely the excitation mechanism is arranged outside along the radius direction, and the balancing weight is arranged inside. Balance capability the present invention provides greater balance capability for an equivalent counterweight mass. The company proposed patents US20110197703a1 and WO2012051475a1 in 2012, and a slip ring structure was added to the original automatic balancing device for data transmission. EP2647567a2 in 2013 and US8961140B2 in 2015 disclose an internal excitation automatic balancing device with a slip ring structure. However, due to the introduction of the slip ring structure, the structure of the balancing device is complex, and the service life of the whole machine is influenced to a certain extent. The invention is characterized in that: and a slip ring is not used for data transmission, so that the hidden danger caused by the wear of the slip ring is avoided.
In 2014, domestic patent CN206654184U discloses a paddle seat of adjustable foldable screw dynamic balance, can realize the focus adjustable function of screw, but this patent belongs to off-line dynamic balance technical field, can not realize online dynamic balance.
In 2016, domestic patent CN205931235U discloses an amphibious aircraft with an automatic balancing tail wing, which has the function of smooth flight by arranging a horizontal tail wing in a propeller for flight adjustment. The invention provides automatic balancing aiming at mass unbalance vibration, and belongs to the field of different research objects and balancing.
In 2018, domestic patent CN106312821B proposes a side-excited electromagnetic slip ring type automatic balancing device, which realizes real-time suppression of unbalanced vibration by changing the counterweight mass position. The structure is characterized in that the excitation coil is arranged on two axial sides, but the structure is not suitable for being applied to the field of dynamic balance of a large-diameter propeller, and the mass and the volume of the structure are large.
In short, the automatic balancing device involved in related research at home and abroad is different from the invention.
Disclosure of Invention
In order to solve the problems of large size, heavy weight and limited balancing capacity of the existing external excitation automatic balancing device, the invention designs an internal excitation automatic balancing device which can be arranged on a propeller shaft of a propeller to realize real-time suppression of unbalanced vibration by a mode of arranging an electromagnetic drive copper coil inside and arranging a balancing weight outside, and the system has an integrated structural design with larger balancing capacity, stable magnetic driving capacity and light weight.
The technical scheme adopted by the invention for solving the technical problems is as follows: according to the structural characteristics of the propeller, the inner side of a blade close to the propeller is provided with the inner excitation automatic balancing device in a shaft penetrating mode or the outer side of the blade close to the propeller is provided with the inner excitation automatic balancing device in an end part mode.
The automatic balancing device comprises a movable ring which can synchronously rotate along with the turboprop rotor and a static ring which is static relative to the casing; the movable ring consists of a left support plate 1, a right support plate 30, an intermediate disc bracket 29, a counterweight disc a14 and a counterweight disc b 17; the static ring is composed of a coil rack a9, a coil rack b23, a magnetism isolating ring 21, a transition sleeve 8 and a transition sleeve end cover 24; the static ring is respectively assembled with an external ultrathin bearing c7 and an ultrathin bearing d25 through the left support plate 1 and the right support plate 30 and forms a follow-up structure with the movable ring, bosses are arranged on the left support plate 1 and the right support plate 30, the radial positioning of the assembly of the left support plate 1 and the assembly of the right support plate 30 and the intermediate tray support 29 can be realized, and the left support plate 1 and the right support plate 30 are fixed through bolts so as to ensure the axial stability of the left support plate 1, the right support plate 30 and the intermediate tray support 29.
The installation ensures the integrated stable structure of the automatic balancer, and simultaneously, the distribution of the movable ring outside and the static ring inside is adopted on the whole structure, so that the distribution can increase the balancing capacity.
The left support plate 1 is provided with a side magnetic plate a12, the right support plate 30 is provided with a side magnetic plate b19, and the left side and the right side of the intermediate disk bracket 29 are respectively provided with a side magnetic plate c13 and a side magnetic plate d 18.
The movable ring comprises two rotatable weight plates a14 and b17, wherein the weight plates a14 and b17 are respectively provided with a counter weight a3 and a counter weight b27, and the weight plates a14 and b17 can independently rotate according to the specified size and direction and synthesize compensation masses with different sizes and directions. Cylindrical permanent magnets are arranged on the counterweight disk a14 and the counterweight disk b17 in the circumferential direction corresponding to the through holes in the side magnetic plate a12, the side magnetic plate c13, the side magnetic plate d18 and the side magnetic plate b19, the number of the cylindrical permanent magnets is half of that of the through holes, the polarities of the adjacent magnets are opposite, and the cylindrical permanent magnets are installed in a crossed mode, so that the self-locking function of the counterweight disk is guaranteed, and the counterweight disk is stabilized at the position after dynamic balance.
The balance weight disk a14 and the balance weight disk b17 are respectively matched with the intermediate disk bracket 29 through an ultrathin bearing a15, an ultrathin bearing b16 and an intermediate disk bracket 29, and a balance weight end cover a2 and a balance weight disk end cover b28 are arranged to realize the axial orientation of the balance weight disk a14, the balance weight disk b17, the ultrathin bearing a15 and the ultrathin bearing b16, the selection of the ultrathin bearing reduces the axial size of the automatic balancer, and meanwhile, as the radial thickness of the ultrathin bearing is reduced, the balance weight on the balance weight disk can be installed in a region with a larger radius, and the balancing capacity is further increased.
The static ring is composed of a coil rack a9, a coil rack b23, a transition sleeve 8 and a transition sleeve end cover 24, wherein the coil rack a9 and the coil rack b23 are of a U-shaped groove structure, the materials are pure iron materials, a copper coil a10 and a copper coil b22 are respectively wound in the U-shaped groove, pulse direct current is conducted to the copper coil a10 and the copper coil b22, the permanent magnet 20 can generate driving force under the action of magnetic fields of a surrounding side magnetic plate a12, a side magnetic plate c13, a side magnetic plate d18, a side magnetic plate b19, the coil rack a9 and the coil rack b23, stepping rotation is instantly generated on the counterweight disk a14 and the counterweight disk b17, the pulse direct current disappears, and the counterweight disk a14 and the counterweight disk b17 are self-locked at a certain stable position relative to the propeller rotor, namely, the rotational motion with the same rotational speed as that of the propeller is kept.
Coil former a9, magnetic shield 21 and coil former b23 are placed in transition cover 8 in turn, and transition cover end cover 24 is assembled with transition cover 8 through bolts, so that the assembly structure of internal coil former a9 and coil former b23 is further stable.
The left support plate 1 is provided with a reference magnet 6 which corresponds to a Hall sensor a5 on a coil rack a9, and the Hall sensor a5 obtains a pulse signal every time the moving ring rotates one circle; the counterweight plate a14 and the counterweight plate b17 are both provided with positioning magnets which respectively correspond to the Hall sensor b4 and the Hall sensor c26, and the Hall sensor b4 and the Hall sensor c26 acquire a pulse signal every time the counterweight plate a14 and the counterweight plate b17 rotate for one circle. The coil frames a9 and b23 are internally provided with wire grooves 11 to ensure that the Hall sensor b4, the Hall sensor a5, the Hall sensor c26, the copper coil a10 and the copper coil b22 are connected with an external controller.
Each side magnetic plate is made of pure iron material with high magnetic permeability, and a certain number of through holes are formed in the circumferential direction of the side magnetic plate.
Because the density of the coil and the pure iron material is higher, the weight of the part is reduced to the maximum extent due to the built-in static ring, and the magnetism isolating plate 21 is made of hard aluminum material with low magnetic permeability.
The two balancing weights are positioned through the three Hall sensors, the permanent magnet 20 generates driving force through impressed current, and the two balancing weights are accurately moved by combining reference signals provided by the three Hall sensors.
The internal excitation automatic balancing device provided by the invention can be designed into automatic balancing actuators with various structural forms such as a drawing 3 and an end face drawing 4 arranged in a shaft penetrating shaft according to different structural forms and balancing capacity requirements of a controlled turboprop rotor.
The invention can obtain the following beneficial effects:
1. the rotating ring is externally arranged, and the static ring is internally arranged with a structure.
The invention has the advantages that the movable ring is externally arranged, the static ring is internally arranged, the sizes of the coil and the coil rack are reduced, and the total amount of the balance head is reduced. Compared with a static ring external balance actuator, the dynamic ring external structure can obtain higher balance capacity. Under the condition of the same counterweight weight, the acting radius of the counterweight block is increased. The built-in excitation structure of the copper coil can reduce the weight of the copper coil to a greater extent, and a light-weight automatic balancing device is obtained. The invention adopts an internal excitation structure, designs a follow-up structure to realize the static state of the static ring relative to the dynamic ring, is beneficial to data and electric energy transmission, and powerfully ensures the stability of signal transmission. Meanwhile, for a large-diameter hollow rotor, the built-in coil excitation structure is more favorable for engineering application.
2. The balance weight plate is arranged outside, so that the balance capacity is greatly increased.
The balancing capacity of the automatic balancing device is equal to the product of the mass of the counterweight and the radius of the counterweight. Therefore, the balance weight plate is arranged externally, and the balance capacity is greatly increased on the premise of the same weight.
3. And the ultra-thin bearing is adopted, so that the axial size is reduced, the installation is convenient, and the ultra-thin bearing is particularly suitable for narrow spaces.
The four bearings required in the device are all ultrathin bearings on the premise of meeting the bearing capacity, so that the axial size is reduced, and the installation under the actual narrow working condition is facilitated. Meanwhile, the wall thickness of the ultrathin bearing is smaller, so that the mounting radius of the balancing weight can be further enlarged, and the balancing weight capacity is increased.
4. The transition sleeve type compact structure design reduces the complexity of the balance head structure, so that the dynamic and static rings form a whole.
The invention adopts the transition sleeve to connect the dynamic ring and the static ring, and the fixed axial parts form a whole, so that the whole automatic balance actuator has a more compact integral structure.
The automatic balance actuator can be designed into a shaft penetrating shaft inner mounting mode or an end face mounting mode according to the mounting requirements of controlled equipment, and has high flexibility in design and application.
Drawings
Fig. 1 is a schematic structural diagram of an internal excitation automatic balancing device for a propeller.
Figure 2 is a schematic view of a weight plate.
Fig. 3 is a schematic diagram of an internal excitation automatic balancing device installed in a shaft penetrating shaft.
Fig. 4 is a schematic view of an end-face mounting type internal excitation automatic balancing apparatus.
In the figure: 1. the device comprises a left support plate, a right support plate, a balance weight plate end cover, a balance weight plate a, a balance weight plate 4, a Hall sensor b, a Hall sensor 5, a Hall sensor a, a reference magnet 7, an ultrathin bearing c, 8, a transition sleeve 9, a coil rack a, 10, a copper coil a, 11, a wire slot 12, a side magnetic plate a, 13, a side magnetic plate c, 14, a balance weight plate a, 15, an ultrathin bearing a, 16, an ultrathin bearing b, 17, a balance weight plate b, 18, a side magnetic plate d, 19, a side magnetic plate b, 20, a permanent magnet, 21, a middle magnetic isolation plate, 22, a copper coil b, 23, a coil rack b, 24, a transition sleeve end cover, 25, an ultrathin bearing d, 26, a Hall sensor c, 27, a balance weight plate b, 28, a balance weight plate end cover b, 29, a middle plate support, 30 and a right support plate.
Detailed Description
For the actual use condition of the propeller shaft, the installation mode of the automatic balancing device can be divided into two types: one is a shaft penetrating shaft inner mounting mode; the other is end face mounting. The automatic balancing device provided by the invention can meet the two installation modes. The following is a more detailed description of the embodiments with reference to the drawings.
The first embodiment is as follows:
as shown in fig. 1, 2 and 3, the automatic balancing device of the present invention is an integrated structure, and the device can be assembled to the propeller after being assembled.
The mounting sequence of the movable ring is as follows:
s1, referring to fig. 1 and 2, the permanent magnets are alternately mounted on the weight plate a14 and the weight plate b17 in the opposite magnetic sequence, in this example, 60 magnets are selected, the number of the magnets is determined according to the calculated self-locking force and driving force relationship, then the weight block a3 and the weight block b27 are fixed on the weight plate a14 and the weight plate b17 by bolts, and the positioning magnets are mounted on the weight plate a14 and the weight plate b 17;
s2, respectively installing a weight plate a14 and a weight plate b17 on an ultrathin bearing a15 and an ultrathin bearing b16, and connecting a weight end cover a2, a weight end cover b28, the weight plate a14 and the weight plate b17 by bolts to axially fix the weight plate a14, the weight plate b17 and the weight end cover a2, the weight end cover b28, the ultrathin bearing a15 and the ultrathin bearing b16 in an interference fit manner in a radial direction;
s3, respectively assembling the ultrathin bearing a15 and the ultrathin bearing b16 provided with the balance weight disc on the left side and the right side of the middle disc support, wherein the ultrathin bearing a15 and the ultrathin bearing b16 are in interference fit in the radial direction;
s4, side magnet a12, and side magnet plate b19 are respectively assembled to left support plate 1 and right support plate 30 by bolts, and side magnet plate c13 and side magnet plate d18 are similarly assembled to intermediate tray 29.
The static ring installation sequence is as follows:
s1, respectively winding a copper coil a10 and a copper coil b22 on a U-shaped coil frame a9 and a coil frame b23, and then installing a Hall sensor a5, a Hall sensor b4 and a Hall sensor c26 in pre-processed coil frames 9 and 23;
s2, an ultrathin bearing c7 and an ultrathin bearing d25 are assembled on the transition sleeve 8 and the transition sleeve end cover 24 respectively, the radial direction of the transition sleeve is in interference fit, and the transition sleeve is positioned by a shaft shoulder in the axial direction;
s3, sequentially mounting the coil rack a9 with the copper coil a10 and the copper coil b22, the magnetism isolating plate 21 and the coil rack b23 to the transition sleeve 8, and similarly, the radial direction is in interference fit.
The whole assembly sequence of the automatic balancing device is as follows:
s1, mounting the intermediate tray bracket 29 provided with the counterweight tray a14 and the counterweight tray b17 on the left support plate 1;
s2, connecting the transition sleeve 8 provided with the coil rack a9, the magnetism isolating plate 21 and the coil rack b23 with the left support plate 1 through a bearing c7, so as to form a local integral structure a together with the previous step;
s3, the right supporting plate 30 is connected with the transition sleeve end 21 through a bearing d25 to form a local integral structure b;
and (3) connecting the local integral structure a with the local integral structure b, connecting the left support plate 1 with the right support plate 30 through a bolt, and connecting the fastening sleeve 8 with the fastening sleeve end 24 through a bolt, so as to axially fix the local integral structure a and the local integral structure b.
So far, the integral installation of the automatic balancing device is realized. The assembled automatic balancing device is fixed on the hub through a bolt by utilizing the inner space of the hub bearing the propeller.
This embodiment, to specific screw rotor, make full use of screw wheel hub inner space, the mounting means is hidden, and is little to the structure influence of screw itself, and engineering application nature is reliable.
Example two:
as shown in fig. 4, the present embodiment is different from the first embodiment in that the assembled automatic balancing apparatus is fixed to the end of the propeller hub through the support plate, not installed inside the hub. In the embodiment, the dynamic balance can be performed on the propeller system with limited inner space of the hub.
The present invention has been described in detail with reference to the above examples, but it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (10)
1. An internal excitation automatic balancing device for a propeller is characterized in that: according to the structural characteristics of the propeller, an internal excitation automatic balancing device is arranged in a shaft penetrating shaft at the inner side of a blade close to the propeller or arranged at the outer side of the blade close to the propeller in an end part mode;
the automatic balancing device comprises a movable ring which can synchronously rotate along with the turboprop rotor and a static ring which is static relative to the casing; the movable ring consists of a left support plate (1), a right support plate (30), an intermediate disc support (29), a counterweight disc a (14) and a counterweight disc b (17); the static ring is composed of a coil rack a (9), a coil rack b (23), a magnetism isolating ring (21), a transition sleeve (8) and a transition sleeve end cover (24); the static ring is respectively assembled with an external ultrathin bearing c (7) and an ultrathin bearing d (25) through a left supporting plate (1) and a right supporting plate (30) and forms a follow-up structure with the movable ring, bosses are arranged on the left supporting plate (1) and the right supporting plate (30), the radial positioning of the assembly of the left supporting plate (1) and the right supporting plate (30) with the intermediate disc support (29) can be realized, and the left supporting plate (1) and the right supporting plate (30) are fixed through bolts so as to ensure the axial stability of the left supporting plate (1), the right supporting plate (30) and the intermediate disc support (29);
the installation ensures the integrated stable structure of the automatic balancer, and simultaneously, the distribution of the movable ring outside and the static ring inside is adopted on the whole structure, so that the distribution can increase the balancing capacity.
2. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the magnetic plate assembly is characterized in that a side magnetic plate a (12) is installed on the left supporting plate (1), a side magnetic plate b (19) is installed on the right supporting plate (30), and a side magnetic plate c (13) and a side magnetic plate d (18) are installed on the left side and the right side of the intermediate tray support (29) respectively.
3. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the movable ring comprises two rotatable balance weight disks a (14) and b (17), wherein balance weight blocks a (3) and b (27) are respectively arranged on the balance weight disks a (14) and b (17), and the balance weight disks a (14) and b (17) can independently rotate according to the specified size and direction and synthesize compensation masses with different sizes and directions; cylindrical permanent magnets are arranged on the counterweight disk a (14) and the counterweight disk b (17) in the circumferential direction corresponding to the through holes in the side magnetic plate a (12), the side magnetic plate c (13), the side magnetic plate d (18) and the side magnetic plate b (19), the number of the cylindrical permanent magnets is half of that of the through holes, the polarities of the adjacent magnets are opposite, and the cylindrical permanent magnets are installed in a crossed mode, so that the self-locking function of the counterweight disk is guaranteed, and the counterweight disk is stabilized at the position after dynamic balance.
4. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the balance weight disc a (14) and the balance weight disc b (17) are respectively matched with the intermediate disc support (29) through an ultrathin bearing a (15), an ultrathin bearing b (16) and a balance weight disc end cover a (2) and a balance weight disc end cover b (28) to realize the axial orientation of the balance weight disc a (14), the balance weight disc b (17), the ultrathin bearing a (15) and the ultrathin bearing b (16), the selection of the ultrathin bearing reduces the axial size of the automatic balancer, and meanwhile, as the radial thickness of the ultrathin bearing is reduced, the balance weight on the balance weight disc is arranged in a region with a larger radius, so that the balancing capacity is further increased.
5. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the static ring comprises a coil rack a (9), a coil rack b (23), a transition sleeve (8) and a transition sleeve end cover (24), wherein the coil rack a (9) and the coil rack b (23) are of a U-shaped groove structure, the materials are pure iron materials, a copper coil a (10) and a copper coil b (22) are respectively wound in the U-shaped groove, pulse direct current is conducted to the copper coil a (10) and the copper coil b (22), a permanent magnet (20) can generate driving force under the action of magnetic fields of a peripheral side magnetic plate a (12), a side magnetic plate c (13), a side magnetic plate d (18), a side magnetic plate b (19), the coil rack a (9) and the coil rack b (23), so that the balance weight disk a (14) and the balance weight disk b (17) can instantaneously generate stepping rotation, the pulse direct current disappears, the coil a (14) and the balance weight disk b (17) are self-locked at a certain stable position relative to the propeller rotor, i.e. maintain a rotational movement at the same rotational speed as the propeller.
6. The internally excited automatic balancing device for propellers of claim 1, characterized in that: coil former a (9), separate magnetic ring (21) and coil former b (23) and place in transition cover (8) in proper order, and transition cover end cover (24) realize through the bolt with the assembly of transition cover (8), make the assembly structure of inside coil former a (9) and coil former b (23) stable.
7. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the reference magnet (6) is arranged on the left supporting plate (1), and corresponds to the Hall sensor a (5) on the coil rack a (9), so that the Hall sensor a (5) obtains a pulse signal every time the movable ring rotates one circle; the counterweight plate a (14) and the counterweight plate b (17) are provided with positioning magnets which respectively correspond to the Hall sensor b (4) and the Hall sensor c (26), and the Hall sensor b (4) and the Hall sensor c (26) acquire a pulse signal every time the counterweight plate a (14) and the counterweight plate b (17) rotate for one circle; wire grooves (11) are formed in the coil frames a (9) and b (23) to ensure that the Hall sensors b (4), a Hall sensor a (5), a Hall sensor c (26) and a copper coil a (10) are connected with an external controller.
8. An internally excited automatic balancing device for propellers according to claim 2, characterized in that: each side magnetic plate is made of pure iron materials, and a certain number of through holes are formed in the circumferential direction of the side magnetic plate.
9. An internally excited automatic balancing device for propellers according to claim 6, characterized in that: the magnetism isolating ring (21) is made of hard aluminum materials.
10. The internally excited automatic balancing device for propellers of claim 1, characterized in that: the transition sleeve (8) is assembled with the left support plate (1) through an ultrathin bearing c (7), the end cover (24) of the transition sleeve is assembled with the right support plate (30) through an ultrathin bearing d (25), and meanwhile, the static ring is flexibly connected with the shell through an external cable connected with the wire passing groove (11), so that the static ring is static relative to the shell;
the two balancing weights are positioned through the three Hall sensors, the permanent magnet (20) generates driving force through impressed current, and the two balancing weights are accurately moved by combining reference signals provided by the three Hall sensors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811378231.0A CN109625246B (en) | 2018-11-19 | 2018-11-19 | Internal excitation automatic balancing device for propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811378231.0A CN109625246B (en) | 2018-11-19 | 2018-11-19 | Internal excitation automatic balancing device for propeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109625246A CN109625246A (en) | 2019-04-16 |
| CN109625246B true CN109625246B (en) | 2022-03-25 |
Family
ID=66068817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811378231.0A Active CN109625246B (en) | 2018-11-19 | 2018-11-19 | Internal excitation automatic balancing device for propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109625246B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2020167806A (en) * | 2019-03-28 | 2020-10-08 | 日本電産株式会社 | Motor, rotor blade device, and unmanned aerial vehicle |
| CN114537064A (en) * | 2022-03-28 | 2022-05-27 | 天津大学 | A rescue device for urban waterlogging |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000011322A1 (en) * | 1998-08-21 | 2000-03-02 | OMASI, Anstalt | Multipurpose propeller with vectored impulses |
| CN102761204A (en) * | 2012-07-11 | 2012-10-31 | 成都欧迅海洋工程装备科技有限公司 | Controller integrated deep sea motor |
| US9646597B1 (en) * | 2015-12-21 | 2017-05-09 | Amazon Technologies, Inc. | Delivery sound masking and sound emission |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US996728A (en) * | 1910-02-23 | 1911-07-04 | John A Renniee | Propelling and balancing apparatus for airships. |
| GB909004A (en) * | 1957-11-18 | 1962-10-24 | Kurt Axmann | Improvements in or relating to propeller blades |
| KR200268109Y1 (en) * | 2001-12-06 | 2002-03-15 | 김정훈 | Flat noncommutator vibration motor |
| US7815482B2 (en) * | 2006-01-19 | 2010-10-19 | Silverlit Toys Manufactory, Ltd. | Helicopter |
-
2018
- 2018-11-19 CN CN201811378231.0A patent/CN109625246B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000011322A1 (en) * | 1998-08-21 | 2000-03-02 | OMASI, Anstalt | Multipurpose propeller with vectored impulses |
| CN102761204A (en) * | 2012-07-11 | 2012-10-31 | 成都欧迅海洋工程装备科技有限公司 | Controller integrated deep sea motor |
| US9646597B1 (en) * | 2015-12-21 | 2017-05-09 | Amazon Technologies, Inc. | Delivery sound masking and sound emission |
Non-Patent Citations (2)
| Title |
|---|
| A study on electromagnetic driven bi-disc compensator for rotor auto-balancing and its movement control;Chen Li-fang, Cao Xi and Gao Jin-Ji;《WSEAS Transactions on Systems and Control》;20100531;333-342 * |
| 离心泵叶轮轴向力自动平衡新方法;陆伟刚,张金凤,袁寿其;《中国机械工程》;20170910;2037-2040 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109625246A (en) | 2019-04-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7042128B2 (en) | Brushless permanent magnet wheel motor with variable axial rotor/stator alignment | |
| US3997131A (en) | Rotor means for an aircraft | |
| CN106768642B (en) | A kind of dissection type automatic balancing arrangement for realizing rotating machinery on line auto balancing | |
| CN109625246B (en) | Internal excitation automatic balancing device for propeller | |
| RU2526331C1 (en) | Helicopter anti-torque rotor | |
| EP3683464B1 (en) | Active magnetic bearing apparatus | |
| AU2013349341B2 (en) | Machine with two co-axial rotors | |
| US6476534B1 (en) | Permanent magnet phase-control motor | |
| CN110435931B (en) | High-speed rotor device of magnetic suspension control moment gyroscope | |
| WO2020121671A1 (en) | Motor-integrated fluid machine and vertical take-off and landing aircraft | |
| CN107607099B (en) | Magnetic suspension control sensitive gyroscope with detection and control co-location | |
| CN105207431A (en) | Double-magnet double-rotor permanent magnet motor for flywheel | |
| CN102721510A (en) | Electromagnet-permanent magnet mixed type online active balance head structure for rotary machine and control method thereof | |
| CN110594294A (en) | Magnetic suspension bearing system with detachable thrust disc | |
| US3243621A (en) | Compact turbo-inductor alternator | |
| CN107947514B (en) | A kind of flat limited angle torque motor | |
| US3284651A (en) | Compact inductor alternator | |
| CN209593236U (en) | Linear rotating motor | |
| US11581782B2 (en) | Electric propulsion system | |
| CN114394243A (en) | Solar unmanned aerial vehicle magnetic suspension propulsion system | |
| CN106121731A (en) | A kind of dual-rotor structure and turbogenerator | |
| CN112065853A (en) | Outer winding controlled inner and outer double-rotor hybrid magnetic bearing | |
| RU220566U1 (en) | UNMANNED AIRCRAFT PROPELLER WITH AN INTEGRATED ELECTRIC MOTOR | |
| CN109905004A (en) | Linear rotating motor | |
| JP2020167903A (en) | Rotary electric machine and propulsion device using the same |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |