CN113247243A - Seesaw type unmanned helicopter rotor wing structure and chord direction dynamic balance balancing method - Google Patents
Seesaw type unmanned helicopter rotor wing structure and chord direction dynamic balance balancing method Download PDFInfo
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- CN113247243A CN113247243A CN202110722992.9A CN202110722992A CN113247243A CN 113247243 A CN113247243 A CN 113247243A CN 202110722992 A CN202110722992 A CN 202110722992A CN 113247243 A CN113247243 A CN 113247243A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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Abstract
The invention relates to the technical field of unmanned helicopters, and particularly discloses a seesaw type unmanned helicopter rotor wing structure and a chordwise dynamic balance balancing method. By the method disclosed by the invention, the chord dynamic balance of the rotor wing can be quickly and conveniently adjusted, no additional counter weight is needed, and no structure for installing the counter weight is needed. The weight of the counterweight can be effectively reduced; the dynamic balance adjusting time is reduced; reducing the complexity of the aircraft structure; reduce unmanned aerial vehicle's maintenance time. The economy and the safety of the unmanned helicopter are improved.
Description
Technical Field
The invention relates to the technical field of unmanned helicopters, and particularly discloses a seesaw type unmanned helicopter rotor wing structure and a chord-direction dynamic balance balancing method.
Background
In the use process of the unmanned helicopter, alternating loads generated by rotating components such as a rotor wing, a tail rotor, an engine, a transmission mechanism and the like cause vibration of a helicopter body structure. The vibration of the body can have serious consequences for the use of the helicopter: the main stress parts of the helicopter, the instrument equipment and the like generate vibration fatigue, so that the service life is reduced. Among the rotating parts of unmanned helicopters, the alternating loads generated by the rotor are the largest and are the main vibration sources of helicopters. Rotor dynamic balance is therefore particularly important for helicopters.
The dynamic balance of the seesaw type unmanned helicopter rotor wing can be divided into chord-direction dynamic balance and span-direction dynamic balance. The traditional dynamic balance adjustment is realized by increasing or decreasing the balance weight. When the dynamic balance in the chord direction is adjusted, if the balance weight is arranged on the rotor wing, the rotor wing has a large aspect ratio, so the size in the chord direction is small, and the mass of the balance weight needs to be large to meet the adjustment requirement; if the balance weight is installed at other positions, other structures need to be designed to meet the function.
The two chord-direction dynamic balance adjusting methods can increase the weight of the unmanned helicopter, increase the structural complexity, and finally cause the economic efficiency and the safety of the unmanned helicopter to be poor.
Disclosure of Invention
In order to solve the defects of the prior art mentioned in the above, the invention provides a seesaw type unmanned helicopter rotor chord direction dynamic balance balancing method, which is used for optimally adjusting the rotor chord direction balancing method of the unmanned helicopter, so that the rotor chord direction dynamic balance adjustment of the unmanned helicopter is simpler and faster, and the reliability is higher.
In order to achieve the purpose, the invention specifically adopts the technical scheme that:
a seesaw type unmanned helicopter rotor wing structure comprises a rotor wing shaft, wherein a rotor wing hub is arranged on the rotor wing shaft, and a drum-shaped hanging piece is arranged on the rotor wing shaft and is connected and matched with the rotor wing hub through the drum-shaped hanging piece; the drum-shaped hanging piece is symmetrically provided with straight arms, the rotor hub is sleeved with the straight arms, a sleeved inner bushing and an outer bushing are arranged between the rotor hub and the straight arms, the inner bushing is sleeved on the straight arms, and the outer bushing is sleeved on the inner bushing and is connected and fastened with the rotor hub; the inner side of the inner bushing is tightly abutted to the straight arm, the front end of the straight arm is provided with an orifice, a positioning pin is arranged in the support, the front end of the positioning pin extends out of the orifice of the support, an adjusting gasket tightly abutted to the outer side of the straight arm is arranged at the front end of the positioning pin, an end cover is further arranged on the outer side of the adjusting gasket, and the end cover presses the adjusting gasket to the inner bushing.
Above-mentioned disclosed rotor structure connects rotor propeller hub through the epaxial cydariform pendant of rotor, optimizes the improvement to the connection structure of cydariform pendant and rotor propeller hub for the axial distance between rotor propeller hub and the cydariform pendant is adjustable, allows to select suitable adjustment shim according to the dynamic balance demand, thereby satisfies the dynamic balance of rotor.
Further, the drum-shaped hanging piece is simple in structure, particularly used for connection and transmission, reliable in structure, optimized and provided with one of the following feasible options: the drum-shaped hanging piece comprises an annular sleeving part, a pin hole is formed in the sleeving part, and the positioning pin is fixed at the pin hole. When adopting such scheme, thereby the cydariform pendant passes through the pinhole and is connected with the locating pin cooperation and realize the location on the rotor shaft and connect, and the general rotor shaft sets for cylindricly, and the cydariform pendant cup joints on the rotor shaft, with the rotor shaft cooperation and bear transmission axial and radial load.
Further, the rotor hub is used to transmit the rotation of the rotor shaft to the rotor, and the rotor hub may be configured to accommodate the dynamic balance balancing described above, where it is optimized and one of the possible options is: the rotor hub comprises two hub clamping plates, the two hub clamping plates are respectively connected and matched with a straight arm, connecting holes are formed in the hub clamping plates, and the outer bushing is sleeved with the connecting holes. When the scheme is adopted, the two propeller hub clamping plates are symmetrically arranged at the straight arm, the propeller hub clamping plates are sleeved on the straight arm and can adjust the position along the axial direction of the straight arm, and the end cover is arranged on the propeller hub clamping plates and then plays a role in blocking and limiting, so that the propeller hub clamping plates are axially fixed relative to the straight arm.
Further, when the end cover is connected to the hub clamping plate, the end cover is kept to be abutted and abutted, so that the axial stability of the hub clamping plate can be improved, and particularly, the structure of the end cover can be optimized to adopt various feasible options, which are not limited only, and one of the feasible options is as follows: the end cover comprises an inner ring attaching portion and an outer ring attaching portion, the inner ring attaching portion is attached to and abutted against the adjusting gasket, and the outer ring attaching portion is attached to and abutted against the propeller hub clamping plate. When the scheme is adopted, the inner ring attaching portion tightly supports the adjusting gasket to the outer side of the straight arm, and the outer ring attaching portion and the propeller hub clamping plate are fixedly connected and mutually tightly fixed.
Further, in the present invention, in order to arrange the rotor, the structure of the hub clamp plate is optimized and one possible option is given as follows: and a hub support arm is arranged between the two hub clamping plates, and one end of the hub support arm is connected with the two hub clamping plates in a fastening fit. When adopting such scheme, the flabelling hinge structure is constituteed with the propeller hub splint to the propeller hub support arm, and the propeller hub support arm realizes through many connecting bolts that the cooperation is connected with the propeller hub splint, and the propeller hub support arm is used for setting up subsequent rotor correlation structure, and the propeller hub support arm drives the rotor and rotates and produce lift along with the propeller hub splint pivoted simultaneously.
Further, the structure of the hub arm in the present invention is optimized, and one possible option is as follows: the propeller hub support arm is provided with a variable pitch hinge structure, and the variable pitch hinge structure comprises a rotor wing variable pitch hinge arranged on the propeller hub support arm and a variable pitch rocker arm arranged on the rotor wing variable pitch hinge. When adopting such scheme, the rotor displacement hinge rotates in the circumferencial direction and realizes the inclination of rotor and adjust, thereby the displacement rocking arm can drive the displacement hinge and rotate and realize the inclination of rotor and adjust.
Further, the hub clamp plate structure of the present invention is optimized, and one possible option is as follows: and an oil injection nozzle is arranged on the propeller hub clamping plate, penetrates through the propeller hub clamping plate and extends to the side surface of the outer bushing. Grease and other substances can be added to the inner lining and the outer lining through the oil injection nozzle.
Further, in order to enhance the connection stability of the end cap, the following feasible options are optimized and presented here: the end cover is detachably fixed on the surface of the rotor hub clamping plate through a fastener.
The above disclosure discloses a rotor structure of an unmanned helicopter, and the invention further describes a balancing method for chord-wise dynamic balance of the rotor of the unmanned helicopter, which is described here:
a seesaw type unmanned helicopter rotor chord direction dynamic balance balancing method is applied to the helicopter spiral wing structure and comprises the following steps:
weighing rotor hubs and bladesm 1Selecting an adjusting shim according to a preset thickness value, and installing the adjusting shim on a rotor hub;
measuring dynamic unbalance weight after installationm 2Distance from the dynamic unbalance to the axis of the rotor shaftrCalculating the adjustment amount of dynamic balanced；
According to the dynamic balance adjustment quantity obtained by calculationdFor adjusting shim with increased thicknessdFor adjusting shim thickness reductiond。
According to the balancing method, the dynamic balance adjustment amount can be calculated by combining the actual weight of the rotor hub and the actual weight of the blades according to the dynamic unbalance weight and the dynamic unbalance axis distance at the rotor hub as the calculation reference, so that the thickness of the adjusting shim is adjusted, and the dynamic balance adjustment of the rotor is realized.
Still further, the adjustment amount of the dynamic balance is calculated according to the following method:m 1 d=m 2 r。
compared with the prior art, the invention has the beneficial effects that:
the rotor wing structure disclosed by the invention is simple in integral structure and convenient to operate, and can realize the chordwise dynamic balance balancing of the rotor wing under the condition of not increasing independent counter weights, so that the dynamic balance balancing efficiency of the rotor wing of the unmanned aerial vehicle is greatly improved, and the balancing operation of the dynamic balance of the rotor wing of the unmanned aerial vehicle is simplified. By the method disclosed by the invention, the chord dynamic balance of the rotor wing can be quickly and conveniently adjusted, no additional counter weight is needed, and no structure for installing the counter weight is needed. The weight of the counterweight can be effectively reduced; the dynamic balance adjusting time is reduced; reducing the complexity of the aircraft structure; reduce unmanned aerial vehicle's maintenance time. The economy and the safety of the unmanned helicopter are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Figure 1 is an overall schematic view at the hub of a see-saw rotor configuration.
Fig. 2 is a schematic view of the overall structure of the drum pendant.
Fig. 3 is a schematic view of the overall structure of the flapping hinge.
Fig. 4 is a schematic front view of a flapping hinge.
FIG. 5 is a schematic cross-sectional view of a flapping hinge.
Fig. 6 is a schematic cross-sectional view of the connection of the hub clamp plate and the straight arm at a in fig. 5.
In the above drawings, the meaning of each symbol is: 1. a rotor shaft; 2. a hub clamp plate; 3. an end cap; 301. an inner ring attaching part; 302. a spacer ring; 303. an outer ring attaching part; 4. a pitch-variable rocker arm; 5. a rotor wing variable pitch hinge; 6. a drum-shaped pendant; 7. a straight arm; 8. a pin hole; 9. installing a positioning hole; 10. a mounting member; 11. a hub arm; 12. positioning pins; 13. adjusting the cushion layer; 14. an oil injection nozzle; 15. an inner liner; 16. an outer liner.
Detailed Description
The invention is further explained below with reference to the drawings and the specific embodiments.
It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. This invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
Example 1
There is the characteristics that balancing structure is complicated, inefficiency and the counter weight is big to current unmanned aerial vehicle rotor dynamic balance balancing, and the problem among the prior art is solved in the scheme that wherein improves is optimized and is lifted to this embodiment.
As shown in fig. 1 and 2, a seesaw type unmanned helicopter rotor structure comprises a rotor shaft 1, wherein a rotor hub is arranged on the rotor shaft 1, and a drum-shaped hanging piece 6 is arranged on the rotor shaft 1 and is connected and matched with the rotor hub through the drum-shaped hanging piece 6; the drum-shaped hanging piece 6 is symmetrically provided with straight arms 7, a rotor wing hub is sleeved with the straight arms 7, an inner bushing 15 and an outer bushing 16 which are sleeved are arranged between the rotor wing hub and the straight arms 7, the inner bushing 15 is sleeved on the straight arms 7, and the outer bushing 16 is sleeved on the inner bushing 15 and is connected and fastened with the rotor wing hub; the inner side of the inner bushing 15 is tightly abutted to the straight arm 7, the front end of the straight arm 7 is provided with an orifice, the support is internally provided with a positioning pin 12, the front end of the positioning pin 12 extends out of the orifice of the support, the front end of the positioning pin 12 is provided with an adjusting gasket tightly abutted to the outer side of the straight arm 7, the outer side of the adjusting gasket is further provided with an end cover 3, and the end cover 3 presses the adjusting gasket to the inner bushing 15.
According to the rotor wing structure, the drum-shaped hanging pieces 6 on the rotor wing shaft 1 are connected with the rotor wing hub, the connection structure of the drum-shaped hanging pieces 6 and the rotor wing hub is optimized and improved, the axial distance between the rotor wing hub and the drum-shaped hanging pieces 6 can be adjusted, a proper adjusting gasket is allowed to be selected according to the dynamic balance requirement, and therefore the dynamic balance of the rotor wing is met.
In this embodiment, the drum-shaped suspension member 6 has a simple structure, is specifically used for connection and transmission, and has a reliable structure, and is optimized and one of the following feasible options is provided: the drum-shaped hanging piece 6 comprises an annular sleeving part, a pin hole 8 is formed in the sleeving part, and the positioning pin 12 is fixed at the pin hole 8. When the scheme is adopted, the drum-shaped hanging piece 6 is connected with the positioning pin 12 in a matched mode through the pin hole 8, so that the positioning connection is achieved on the rotor shaft 1, the rotor shaft 1 is generally set to be cylindrical, and the drum-shaped hanging piece 6 is sleeved on the rotor shaft 1 and matched with the rotor shaft 1 to bear and transfer axial and radial loads.
Preferably, in this embodiment, the outer side surface of the drum-shaped suspension member 6 is an arc surface protruding outward, the whole drum-shaped suspension member is drum-shaped, and the drum-shaped suspension member 6 is connected with the rotor shaft 1 by interference fit. The drum-shaped hanger 6 is provided with two straight arms 7, the straight arms are symmetrically arranged at two sides of the drum-shaped hanger 6 relative to the straight arms 7 at 180 degrees, mounting positioning holes 9 are arranged at intervals of 90 degrees from the straight arms 7, the mounting positioning holes 9 are two and are also symmetrically arranged at 180 degrees, the mounting positioning holes 9 are used for fixedly mounting the drum-shaped hanger 6 on the rotor shaft 1, and in the embodiment, mounting pieces 10 are arranged at the mounting positioning holes 9.
As shown in fig. 5 and 6, in the present embodiment, the rotor hub is used for transmitting the rotation of the rotor shaft 1 to the rotor, and the structure of the rotor hub can adopt various structures capable of adapting to the dynamic balance balancing, and the present embodiment is optimized and adopts one of the feasible options: the rotor wing hub comprises two hub clamping plates 2, the two hub clamping plates 2 are respectively connected and matched with a straight arm 7, connecting holes are formed in the hub clamping plates 2, and the outer lining 16 is sleeved with the connecting holes. When adopting such scheme, two propeller hub splint 2 symmetries set up in straight arm 7 department, and propeller hub splint 2 cover is established on straight arm 7 and can be followed straight arm 7 axial adjusting position, and end cover 3 sets up plays the spacing effect of blockking behind the propeller hub splint 2, makes propeller hub splint 2 for straight arm 7 axial fixity.
When the end cover 3 is connected to the hub clamping plate 2, the end cover 3 is kept to be abutted and abutted, so that the axial stability of the hub clamping plate 2 can be improved, specifically, the structure of the end cover 3 can be optimized to adopt various feasible options, which are not only limited, but also one of the feasible options is adopted in the embodiment: the end cover 3 comprises an inner ring attaching portion 301 and an outer ring attaching portion 303, the inner ring attaching portion 301 is attached and abutted to the adjusting gasket, and the outer ring attaching portion 303 is attached and abutted to the hub clamping plate 2; a separating ring 302 is further arranged between the outer ring attaching portion 303 and the inner ring attaching portion 301, the separating ring 302 is continuously arranged on the inner surface of the end cover in an extending mode and forms an end-to-end annular structure, a gap between the separating ring 302 and the outer bushing 16 is small, and the outer bushing 16 can be prevented from falling off. When the scheme is adopted, the inner ring attaching portion 301 tightly abuts against the adjusting gasket to the inner bushing 15, and the outer ring attaching portion 303 is fixedly connected with the hub clamping plate 2 and tightly fixed with the hub clamping plate.
As shown in fig. 3 and 4, in the present embodiment, in order to arrange the rotor, the structure of the hub clamp plate 2 is optimized and one possible option is shown as follows: a hub support arm 11 is arranged between the two hub clamping plates 2, and one end of the hub support arm 11 is connected and tightly matched with the two hub clamping plates 2. When adopting such scheme, the flabelling hinge structure is constituteed with hub splint 2 to hub support arm 11, and hub support arm 11 realizes through many connecting bolts with hub splint 2 that the cooperation is connected, and hub support arm 11 is used for setting up subsequent rotor correlation structure, and hub support arm 11 drives the rotor and rotates and produce lift along with hub splint 2 rotates simultaneously.
Preferably, the connecting block is arranged at the end of the hub arm 11 connected with the hub clamping plates 2, and the connecting block is arranged between the two hub clamping plates 2 and is fastened through a bolt connection.
The structure at the hub arms 11 in this embodiment is optimized using one of the following possible options: the propeller hub support arm 11 is provided with a variable pitch hinge structure, and the variable pitch hinge structure comprises a rotor wing variable pitch hinge 5 arranged on the propeller hub support arm 11 and a variable pitch rocker arm 4 arranged on the rotor wing variable pitch hinge 5. When adopting such scheme, rotor displacement hinge 5 rotates in the circumferencial direction and realizes the inclination of rotor and adjust, thereby displacement rocking arm 4 can drive the displacement hinge and rotate the inclination that realizes the rotor and adjust.
In this embodiment, the rotor pitch hinge 5 and pitch horn 4 are of conventional construction.
Preferably, the structure of the hub clamping plate 2 in the embodiment is optimized, and the following feasible options are adopted: the hub clamping plate 2 is provided with an oil injection nozzle 14, and the oil injection nozzle 14 penetrates through the hub clamping plate 2 and extends to the side surface of the outer bushing 16. In this arrangement, a grease or the like can be added to the inner and outer liners through the oil nozzle.
In order to enhance the connection stability of the end cap 3, the present embodiment is optimized and adopts one of the following possible options: the end cover 3 is detachably fixed on the surface of the hub clamping plate 2 through a fastener.
Preferably, the fastener is a bolt.
Example 2
The content of the above embodiments discloses a rotor structure of an unmanned helicopter, and the present embodiment describes a balancing method for the chord-wise dynamic balance of a rotor of an unmanned helicopter, where:
a seesaw type unmanned helicopter rotor chord direction dynamic balance balancing method is applied to the helicopter spiral wing structure and comprises the following steps:
s01: weighing rotor hubs and bladesm 1Selecting an adjusting shim according to a preset thickness value, and installing the adjusting shim on a rotor hub;
s02: measuring dynamic unbalance weight after installationm 2Distance from the dynamic unbalance to the axis of the rotor shaftrCalculating the adjustment amount of dynamic balanced；
S03: according to the dynamic balance adjustment quantity obtained by calculationdFor adjusting shim with increased thicknessdFor adjusting shim thickness reductiond。
According to the balancing method, the dynamic balance adjustment amount can be calculated by combining the actual weight of the rotor hub and the actual weight of the blades according to the dynamic unbalance weight and the dynamic unbalance axis distance at the rotor hub as the calculation reference, so that the thickness of the adjusting shim is adjusted, and the dynamic balance adjustment of the rotor is realized.
Preferably, the adjustment amount of the dynamic balance is calculated as follows:m 1 d=m 2 r. In the formula (I), the compound is shown in the specification,m 1representing the total weight of the rotor hub and rotor.
When the method in the embodiment is used for adjusting, after the thickness of the adjusting cushion layer is adjusted, particularly after the thickness of the adjusting cushion layer at one end is increased, the inner ring attaching part of the end cover is tightly attached to the adjusting cushion layer and is pushed outwards along the axial direction of the straight arm, so that a gap is generated between the end cover and the hub clamping plate, at the moment, the hub clamping plate is moved along the axial direction of the straight arm, the hub clamping plate can enable the inner bushing and the outer bushing to move relatively under the action of external force, the purpose that the whole hub moves axially along the drum-shaped hanging point straight arm is achieved, the hub clamping plate is in contact and abutting contact with the outer ring attaching part of the end cover, and the dynamic balance is adjusted and leveled.
The above embodiments are just exemplified in the present embodiment, but the present embodiment is not limited to the above alternative embodiments, and those skilled in the art can obtain other various embodiments by arbitrarily combining with each other according to the above embodiments, and any other various embodiments can be obtained by anyone in light of the present embodiment. The above detailed description should not be construed as limiting the scope of the present embodiments, which should be defined in the claims, and the description should be used for interpreting the claims.
Claims (10)
1. The utility model provides a seesaw formula unmanned helicopter rotor structure which characterized in that: the rotor comprises a rotor shaft (1), wherein a rotor hub is arranged on the rotor shaft (1), and a drum-shaped pendant (6) is arranged on the rotor shaft (1) and is connected and matched with the rotor hub through the drum-shaped pendant (6); straight arms (7) are symmetrically arranged on the drum-shaped hanging piece (6), a rotor wing hub is sleeved with the straight arms (7), a sleeved inner bushing (15) and an outer bushing (16) are arranged between the rotor wing hub and the straight arms (7), the inner bushing (15) is sleeved on the straight arms (7), and the outer bushing (16) is sleeved on the inner bushing (15) and is connected and fastened with the rotor wing hub; the inner side of the inner bushing (15) is tightly abutted to the straight arm (7), the front end of the straight arm (7) is provided with a hole, the support is internally provided with a positioning pin (12), the front end of the positioning pin (12) extends out of the hole of the support, the front end of the positioning pin (12) is provided with an adjusting gasket tightly abutted to the outer side of the inner bushing (15), the outer side of the adjusting gasket is further provided with an end cover (3), and the end cover (3) presses the adjusting gasket to the straight arm (7).
2. The see-saw unmanned helicopter rotor structure of claim 1, wherein: the drum-shaped hanging piece (6) comprises an annular sleeving part, a pin hole (8) is formed in the sleeving part, and the positioning pin (12) is fixed at the pin hole (8).
3. The see-saw unmanned helicopter rotor structure of claim 1, wherein: the rotor wing hub comprises two hub clamping plates (2), the two hub clamping plates (2) are respectively connected and matched with a straight arm (7), connecting holes are formed in the hub clamping plates (2), and the connecting holes are sleeved on an outer lining (16).
4. A see-saw unmanned helicopter rotor structure according to claim 3, wherein: the end cover (3) comprises an inner ring attaching portion (301) and an outer ring attaching portion (303), the inner ring attaching portion (301) is attached to and abutted against the adjusting gasket, and the outer ring attaching portion (303) is attached to and abutted against the hub clamping plate (2).
5. A see-saw unmanned helicopter rotor structure according to claim 3, wherein: a hub support arm (11) is arranged between the two hub clamp plates (2), and one end of the hub support arm (11) is connected with the two hub clamp plates (2) in a fastening and matching manner.
6. A seesaw-type unmanned helicopter rotor structure, according to claim 5, characterized in that: the propeller hub support arm (11) is provided with a variable pitch hinge structure, and the variable pitch hinge structure comprises a rotor wing variable pitch hinge (5) arranged on the propeller hub support arm (11) and a variable pitch rocker arm (4) arranged on the rotor wing variable pitch hinge (5).
7. A see-saw unmanned helicopter rotor structure according to claim 3, wherein: an oil injection nozzle (14) is arranged on the propeller hub clamping plate (2), and the oil injection nozzle (14) penetrates through the propeller hub clamping plate (2) and extends to the side surface of the outer bushing (16).
8. A see-saw unmanned helicopter rotor structure according to claim 3, wherein: the end cover (3) is detachably fixed on the surface of the hub clamping plate (2) through a fastener.
9. A seesaw type unmanned helicopter rotor chord-direction dynamic balance balancing method is applied to the seesaw type unmanned helicopter rotor structure of any one of claims 1-8, and is characterized by comprising the following steps:
weighing rotor hubs and bladesm 1Selecting an adjusting shim according to a preset thickness value, and installing the adjusting shim on a rotor hub;
measuring dynamic unbalance weight after installationm 2Distance from the dynamic unbalance to the axis of the rotor shaftrCalculating the adjustment amount of dynamic balanced；
According to the dynamic balance adjustment quantity obtained by calculationdIncreasing the thickness of the adjusting shimdFor adjusting shim thickness reductiond。
10. The chord wise dynamic balance balancing method according to claim 9, wherein the amount of adjustment of the dynamic balance is calculated as follows:m 1 d=m 2 r。
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115123533A (en) * | 2022-09-01 | 2022-09-30 | 北京赛沃摩申科技有限公司 | Mixed rotor configuration coaxial unmanned aerial vehicle |
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