CN115123537A - Tiltrotor mechanism and rotorcraft - Google Patents
Tiltrotor mechanism and rotorcraft Download PDFInfo
- Publication number
- CN115123537A CN115123537A CN202210627805.3A CN202210627805A CN115123537A CN 115123537 A CN115123537 A CN 115123537A CN 202210627805 A CN202210627805 A CN 202210627805A CN 115123537 A CN115123537 A CN 115123537A
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- China
- Prior art keywords
- rotor
- rotating seat
- lead screw
- sliding block
- support
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- 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.)
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- 230000007246 mechanism Effects 0.000 title claims abstract description 70
- 230000005540 biological transmission Effects 0.000 claims abstract description 24
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Abstract
The invention relates to the technical field of aircrafts, and discloses a tiltable rotor wing mechanism and a rotor wing aircraft. The tiltable rotor mechanism includes: a support; the rotating seat is rotatably connected with the support; the rotor wing is rotatably connected with the rotating seat; the sliding block is connected with the support in a sliding way, and the running track of the sliding block is vertical to the rotating axis of the rotating seat; the two ends of the connecting rod are respectively and rotatably connected with the sliding block and the rotating seat; the lead screw is rotatably connected with the support, is in threaded fit with the sliding block and is parallel to the running track of the sliding block; and the rotation driving mechanism is in transmission connection with the lead screw and is used for driving the lead screw to rotate. The tiltable rotor wing mechanism provided by the invention has a simpler structure. The self-locking performance is realized between the screw rod and the sliding block, so that more stable support can be provided for the rotating seat, the rotating seat can stably keep the current angle, the condition that the meshing gear can generate vibration in high-frequency vibration can not occur, and the rotating seat is endowed with higher-precision tilting control.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a tiltable rotor wing mechanism and a rotor wing aircraft.
Background
Tilt rotor aircraft can enough hover, VTOL like traditional rotor aircraft, can again be like the high-speed flight that cruises of screw fixed wing aircraft. The rotation of the tiltable rotor mechanism in the prior art is usually realized by multi-stage gears, and the structure is complex. Therefore, how to solve the problem of complex structure of the tiltable rotor mechanism in the prior art is a technical problem that needs to be solved urgently by those skilled in the art.
Disclosure of Invention
In order to solve the technical problems, the invention provides a tiltable rotor wing mechanism and a rotor wing aircraft.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a tiltable rotor wing mechanism, comprising:
the support is used for being connected with the wing;
the rotating seat is rotatably connected with the support;
the rotor wing is rotatably connected with the rotating seat;
the sliding block is connected with the support in a sliding mode, and the running track of the sliding block is perpendicular to the rotating axis of the rotating seat;
the two ends of the connecting rod are respectively and rotatably connected with the sliding block and the rotating seat;
the lead screw is rotatably connected with the support and is in threaded fit with the sliding block, and the running track of the lead screw is parallel to that of the sliding block;
and the rotation driving mechanism is in transmission connection with the lead screw and is used for driving the lead screw to rotate.
Furthermore, still including set up in the drive mechanism who rotates the seat, drive mechanism's output with the rotor transmission is connected, drive mechanism's input is used for being connected with the drive shaft.
Further, the rotating seat comprises a box body structure, and the transmission mechanism comprises an input shaft and an output shaft;
the input shaft and the output shaft are both rotatably connected with the rotating seat, the input shaft and the output shaft are arranged at an angle, and the input shaft is in transmission connection with the output shaft;
the input shaft is connected with the drive shaft, and the output shaft is connected with the rotor.
Further, the input shaft is in transmission connection with the output shaft through a bevel gear.
Furthermore, the rotation driving mechanism comprises a motor, and a power shaft of the motor is in transmission connection with the connecting rod.
Furthermore, the rotation driving mechanism further comprises a gear box, a power shaft of the motor is connected with the input end of the gear box, and the lead screw is connected with the output end of the gear box.
Further, the motor and the lead screw are arranged on the same side of the gear box, and the motor and the lead screw are arranged in parallel.
The invention also provides a rotorcraft comprising a fuselage, wings and a tiltable rotor mechanism as described above;
at least one wing is arranged on each of two sides of the fuselage;
the rotor mechanism that can vert with the same and the one-to-one of quantity of wing, and the fuselage both sides the axis of rotation of rotating the seat respectively to the both sides of fuselage extend.
Compared with the prior art, the invention achieves the following technical effects:
according to the tiltable rotor wing mechanism, when the angle of the rotor wing needs to be adjusted, the rotary driving mechanism drives the lead screw to rotate, and the lead screw is in threaded fit with the sliding block so as to drive the sliding block to displace along the support. The slider drives the rotating seat to rotate relative to the support through the connecting rod while displacing, and the rotating seat drives the angle change of the rotor wing when rotating, thereby completing the adjustment of the angle of the rotor wing.
Compared with a mode of adopting multi-stage gear adjustment, the tiltable rotor wing mechanism provided by the invention has the advantages that the lead screw, the sliding block and the connecting rod drive the rotating seat to rotate, so that the effect of adjusting the angle of the rotor wing is achieved, and the structure is simpler. Meanwhile, the screw rod is matched with the sliding block through the thread pair, and the thread pair has self-locking performance, so that more stable support can be provided for the rotating seat, the rotating seat can stably keep the current angle, the condition that the meshing gear can generate vibration in high-frequency vibration can be avoided, and the rotating seat is endowed with higher-precision tilting control.
In addition, in the flight process, the tilting force received by the rotating seat is basically transmitted to the support through the connecting rod, the sliding block and the lead screw, and only a small part of the tilting force is transmitted to the rotating driving mechanism, so that the external force received by the rotating driving mechanism is smaller, the impact and the vibration received by the rotating driving mechanism can be reduced, and the service life of the rotating driving mechanism is prolonged.
Further, the present invention provides a rotorcraft that includes the tiltable rotor mechanism of the present invention, and therefore, includes all of the above advantages of the tiltable rotor mechanism.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural view of a tiltrotor rotor according to an embodiment of the present invention;
FIG. 2 is an isometric view of the view shown in FIG. 1;
FIG. 3 is a rotated view of section A-A of FIG. 1;
FIG. 4 is a schematic view of a connection structure of a connecting rod, a sliding block, a lead screw and a rotating base according to an embodiment of the present invention;
FIG. 5 is a schematic view showing a coupling structure of an input shaft and an output shaft according to an embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a support in an embodiment of the present invention;
figure 7 is a schematic view of a first operating condition of a rotary-wing aircraft in accordance with an embodiment of the present invention;
figure 8 is a schematic view of a second operating condition of a rotary-wing aircraft in accordance with an embodiment of the present invention.
Description of reference numerals:
1. a support; 101. a side plate; 102. a connecting plate;
2. a rotating seat; 3. a rotor; 4. a slider; 5. a connecting rod; 6. a lead screw; 7. an input shaft; 8. an output shaft; 9. a drive bevel gear; 10. a driven bevel gear; 11. a motor; 12. a gear case; 13. a body; 14. an airfoil.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Referring to fig. 1-8, a tiltable rotor mechanism provided in an embodiment of the present invention is described.
Specifically, the tiltable rotor mechanism includes a support 1, a rotating base 2, a rotor 3, a slider 4, a link 5, a lead screw 6, and a rotation drive mechanism.
Wherein the support 1 is intended to be connected to a wing 14.
The rotating base 2 is rotatably connected with the support 1.
The rotor 3 is rotatably connected to the rotary base 2.
The slider 4 is slidably connected to the holder 1. For example, the slider 4 may be slidably coupled with the cradle 1 via a guide rail provided on the cradle 1. And the running track of the slider 4 is perpendicular to the rotation axis of the rotating seat 2.
Two ends of the connecting rod 5 are respectively and rotatably connected with the sliding block 4 and the rotating seat 2. For example, the two ends of the connecting rod 5 are respectively hinged with the sliding block 4 and the rotating seat 2.
The lead screw 6 is rotatably connected with the support 1, the lead screw 6 is in threaded fit with the sliding block 4, and the running track of the lead screw 6 is parallel to that of the sliding block 4. For example, the lead screw 6 is provided as a trapezoidal lead screw.
The rotation driving mechanism is in transmission connection with the lead screw 6 and is used for driving the lead screw 6 to rotate.
According to the tiltable rotor wing mechanism provided by the embodiment of the invention, when the angle of the rotor wing 3 needs to be adjusted, the rotary driving mechanism drives the lead screw 6 to rotate, and the lead screw is in threaded fit with the sliding block 4 so as to drive the sliding block 4 to displace along the support 1. 4 drive when the displacement of slider through connecting rod 5 and rotate seat 2 and rotate for support 1, rotate the angle change that drives rotor 3 when seat 2 rotates to the completion is to the adjustment of 3 angles of rotor.
Compared with a mode of adopting multi-stage gear adjustment, the tiltable rotor wing mechanism provided by the invention has the advantages that the lead screw 6, the sliding block 4 and the connecting rod 5 drive the rotating seat to rotate so as to achieve the effect of adjusting the angle of the rotor wing 3, and the structure is simpler. Meanwhile, the screw rod 6 is matched with the sliding block 4 through the thread pair, and the thread pair has self-locking performance, so that more stable support can be provided for the rotating seat 2, the rotating seat 2 can stably keep the current angle, the condition that the meshing gear can generate vibration in high-frequency vibration can not occur, and the rotating seat 2 is endowed with higher-precision tilting control.
In addition, in the flight process, the tilting force received by the rotating seat 2 is basically transmitted to the support 1 through the connecting rod 5, the sliding block 4 and the lead screw, and only a small part of the tilting force is transmitted to the rotating driving mechanism, so that the external force received by the rotating driving mechanism is smaller, the impact and the vibration received by the rotating driving mechanism can be reduced, and the service life of the rotating driving mechanism is prolonged.
In some embodiments provided herein, the tiltrotor mechanism further comprises a transmission mechanism disposed at the swivel mount. The output end of the transmission mechanism is in transmission connection with the rotor wing 3, and the input end of the transmission mechanism is used for being connected with the driving shaft.
So set up, can be through drive shaft in the wing 14 with power transmission to drive mechanism, again by drive mechanism drive rotor 3 rotation to need not to set up power device on rotating seat 2, and then alleviate the volume and the weight of rotating seat 2, make to rotate seat 2 and be more convenient for the adjustment. For example, a power unit may be provided in the fuselage 13 of the rotorcraft, the power unit being connected to the transmission of the rotary seat 2 via a drive shaft provided in the wing 14, so as to indirectly drive the rotor 3 in rotation.
In some embodiments provided by the present invention, the transmission mechanism includes an input shaft 7 and an output shaft 8.
The input shaft 7 is connected to a drive shaft, for example, the input shaft 7 may be connected to the drive shaft by a coupling. Output shaft 8 is coupled to rotor 3, for example, output shaft 8 is coupled to rotor 3 including, but not limited to, via a keyed connection.
So set up, drive mechanism's simple structure.
Alternatively, the rotary base 2 is provided as a box structure, and the input shaft 7 and the output shaft 8 are both provided in the box structure. So set up, input shaft 7 and output shaft 8 all set up within the box structure for output shaft 8 and input shaft 7 can not receive external impurity's infringement, thereby extension drive mechanism's life.
Referring to fig. 6, in some embodiments provided by the present invention, the cradle 1 includes a side plate 101 and a connection plate 102. Wherein the number of the side plates 101 is set to two, the two side plates 101 are oppositely disposed, and the two side plates 101 are connected by the connecting plate 102. Referring to fig. 3, both ends of the case structure are rotatably connected to the two side plates 101, respectively. For example, circular bosses are provided at both ends of the case structure, and through holes for the circular bosses to extend into and rotate are provided in both side plates 101.
In some embodiments provided by the invention, the input shaft 7 and the output shaft 8 are arranged at 90 °, and the input shaft 7 and the output shaft 8 can be connected through a bevel gear transmission. Specifically, referring to fig. 3, the input shaft 7 is sleeved with a drive bevel gear 9, and the output shaft 8 is provided with a driven bevel gear 10 engaged with the drive bevel gear 9.
In some embodiments provided by the present invention, the rotation driving mechanism comprises a motor 11, and a power shaft of the motor 11 is in transmission connection with the connecting rod 5. Alternatively, the motor 11 is disposed in a space between the two side plates 101.
In some embodiments provided by the present invention, the rotation driving mechanism further comprises a gear box 12, the power shaft of the motor 11 is connected with the input end of the gear box 12, and the lead screw 6 is connected with the output end of the gear box 12. The torque can be increased and the torque requirement on the motor 11 can be reduced by providing the gear box 12 on the one hand. On the other hand, the gear box is arranged, so that the motor only needs to provide driving torque, and the acting force of external force on the rotating seat in the flight process does not need to be borne, and the service life of the motor can be prolonged. In another aspect, the power output direction can be adjusted, for example, as shown in fig. 2, in some embodiments of the present invention, the motor 11 and the lead screw 6 are disposed on the same side of the gear box 12, and the motor 11 and the lead screw 6 are disposed in parallel. So set up, can make motor 11 and lead screw 6 set up side by side between two curb plates 101 to improve space utilization, make the structure of tilting rotor mechanism more compact.
Referring to fig. 7-8, the present invention also provides a rotary wing aircraft.
In particular, the rotorcraft includes a fuselage 13, wings 14, and a tiltable rotor mechanism as described above.
At least one wing 14 is disposed on each side of the fuselage 13.
The tiltrotor mechanisms correspond to the wings 14 in the same number one by one, and the rotation axes of the rotation seats 2 on both sides of the fuselage 13 extend to both sides of the fuselage 13, respectively.
It should be noted that a rotorcraft includes a tiltrotor mechanism and all the advantages of a tiltrotor mechanism, which are not described in detail herein.
In the cruise mode, the attitude of the rotorcraft may be as shown in fig. 7, and in order to obtain a faster flight speed, the vertical attitude of the rotor 3 during takeoff is changed to the cruise attitude, the lift of the rotorcraft being provided by the wings 14, and the thrust generated by the rotor 3 causing the aircraft to fly at a faster speed.
In the vertical take-off and landing mode, the flight of the rotorcraft can be as shown in fig. 8, and the flight mode similar to the take-off and landing of a helicopter greatly reduces the requirements of the rotorcraft on the landing and landing sites, greatly widens the use scene of the rotorcraft, and at the moment, the lift force of the rotorcraft is provided by the rotor 3, and the wings 14 do not provide the lift force.
When the vertical take-off and landing mode is switched to the high-speed cruise mode, the connecting rod 5 drives the rotating seat 2 to rotate under the driving of the motor 11, when the rotating seat 2 rotates to incline from the vertical direction, a component of thrust of the rotor wing 3 starts to generate pushing force, and the generated airspeed above the wing 14 generates certain lift force to compensate part of the lift force lost when the rotor wing 3 tilts. This controlled process of increasing the forward speed of the rotorcraft and the airspeed above the wing 14 continues while lowering the vertical lift of the rotor 3 until all lift comes from the wing 14 and all thrust comes from the rotor 3.
The principle and the implementation mode of the present invention are explained by applying specific examples in the present specification, and the above descriptions of the examples are only used to help understanding the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (8)
1. A tiltrotor rotor mechanism, comprising:
the support is used for being connected with the wing;
the rotating seat is rotatably connected with the support;
the rotor wing is rotatably connected with the rotating seat;
the sliding block is connected with the support in a sliding mode, and the running track of the sliding block is perpendicular to the rotating axis of the rotating seat;
the two ends of the connecting rod are respectively and rotatably connected with the sliding block and the rotating seat;
the lead screw is rotatably connected with the support and in threaded fit with the sliding block, and the running track of the lead screw is parallel to that of the sliding block;
and the rotation driving mechanism is in transmission connection with the lead screw and is used for driving the lead screw to rotate.
2. A tiltable rotor mechanism according to claim 1, further comprising a transmission mechanism disposed on said rotatable base, an output end of said transmission mechanism being drivingly connected to said rotor, and an input end of said transmission mechanism being adapted to be connected to a drive shaft.
3. The tiltable rotor apparatus of claim 2, wherein said transmission comprises an input shaft and an output shaft;
the input shaft and the output shaft are both rotatably connected with the rotating seat, the input shaft and the output shaft are arranged at an angle, and the input shaft is in transmission connection with the output shaft;
the input shaft is connected with the drive shaft, and the output shaft is connected with the rotor.
4. A tiltrotor mechanism according to claim 3, wherein said input shaft is in bevel gear drive connection with said output shaft.
5. A tiltrotor rotor mechanism according to claim 1, wherein said rotary drive mechanism comprises a motor having a power shaft drivingly connected to said link.
6. A tiltrotor rotor mechanism according to claim 5, wherein said rotary drive mechanism further comprises a gear box, said motor power shaft being connected to an input of said gear box, said lead screw being connected to an output of said gear box.
7. A tiltrotor rotor mechanism according to claim 6, wherein said motor is disposed on the same side of said gearbox as said lead screw, and said motor is disposed parallel to said lead screw.
8. A rotary wing aircraft comprising a fuselage, wings and a tiltmg rotor mechanism as claimed in any one of claims 1 to 7;
at least one wing is arranged on each of two sides of the fuselage;
the rotor mechanism that can vert with the same and the one-to-one of quantity of wing, and the fuselage both sides the axis of rotation of rotating the seat respectively to the both sides of fuselage extend.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210627805.3A CN115123537A (en) | 2022-06-06 | 2022-06-06 | Tiltrotor mechanism and rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210627805.3A CN115123537A (en) | 2022-06-06 | 2022-06-06 | Tiltrotor mechanism and rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115123537A true CN115123537A (en) | 2022-09-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210627805.3A Pending CN115123537A (en) | 2022-06-06 | 2022-06-06 | Tiltrotor mechanism and rotorcraft |
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| CN (1) | CN115123537A (en) |
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| CN109018334A (en) * | 2018-09-28 | 2018-12-18 | 北京清航紫荆装备科技有限公司 | A kind of transmission device of tilt rotor helicopter |
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| CN208897318U (en) * | 2018-09-28 | 2019-05-24 | 北京清航紫荆装备科技有限公司 | A kind of reclining device and tilt rotor helicopter |
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| CN111516866A (en) * | 2020-04-29 | 2020-08-11 | 燕山大学 | Single-drive tilting dual-rotor aircraft |
| CN113232852A (en) * | 2021-05-11 | 2021-08-10 | 重庆大学 | Transmission mechanism for wings of tilt rotor aircraft |
| CN113320694A (en) * | 2021-07-13 | 2021-08-31 | 广东汇天航空航天科技有限公司 | Tilt rotor mechanism and aircraft with same |
| CN113371191A (en) * | 2021-07-22 | 2021-09-10 | 广东汇天航空航天科技有限公司 | Rotor wing tilting mechanism, tilting rotor wing aerocar and flying device |
-
2022
- 2022-06-06 CN CN202210627805.3A patent/CN115123537A/en active Pending
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