CN114750941A - Self-adaptive gap-eliminating tilting mechanism and tilting rotorcraft - Google Patents
Self-adaptive gap-eliminating tilting mechanism and tilting rotorcraft Download PDFInfo
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- CN114750941A CN114750941A CN202210552615.XA CN202210552615A CN114750941A CN 114750941 A CN114750941 A CN 114750941A CN 202210552615 A CN202210552615 A CN 202210552615A CN 114750941 A CN114750941 A CN 114750941A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 37
- 230000005540 biological transmission Effects 0.000 claims abstract description 12
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 7
- 244000309464 bull Species 0.000 claims description 17
- 230000003044 adaptive effect Effects 0.000 claims description 5
- 230000008901 benefit Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000008030 elimination Effects 0.000 description 3
- 238000003379 elimination reaction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
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- 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
- B64C27/12—Rotor drives
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- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
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- General Details Of Gearings (AREA)
Abstract
The invention discloses a self-adaptive clearance-eliminating tilting mechanism and a tilting rotorcraft, wherein the tilting mechanism comprises a supporting plate, a rotating box and a clearance eliminating device, a rotor wing is installed on the rotating box, and power transmitted by a main speed reducer of the tilting rotorcraft is transmitted to the rotor wing through the rotating box; two sides of the rotating box are respectively provided with a supporting plate, the outer side of the rotating box is rotatably connected with the supporting plates, and the inner side of the rotating box is connected with the supporting plates through the gap eliminating device; the tilting rotor aircraft comprises an airframe, wings, the self-adaptive anti-backlash tilting mechanism and the rotors, wherein the wings are arranged on two sides of the airframe, the tilting mechanism is installed at the tail ends of the wings, and the rotors are installed on the tilting mechanism; according to the self-adaptive anti-backlash tilting mechanism and the tilting rotorcraft, the gear structure with the most stable transmission is utilized, and the gap eliminating device is arranged, so that the transmission precision is improved again, the working safety is ensured, and the high-precision tilting function is realized.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a self-adaptive anti-backlash tilting mechanism and a tilting rotorcraft.
Background
At present, tiltrotors are novel aircrafts that combine fixed-wing aircraft and helicopters into one, both having the capability of normal helicopter take-off and landing and hovering in the air, and also having the capability of turboprop aircraft of cruising flight at high speed.
The tilting angle of the rotor wing of the tilt rotor aircraft ranges from-5 degrees to 105 degrees. When the tilt rotor aircraft takes off, the rotor shaft faces upwards to provide lift force; after the rotorcraft that verts takes off and reaches the uniform velocity, vert forward under the drive of the mechanism that verts, be the horizontality, use the rotor as the pulling force screw, make it can possess the ability that the fixed wing aircraft is long-range flight with higher speed.
The current internationally mature tiltrotors are of the V-22 and V280 type. The V-22 type tilt rotor aircraft is jointly developed by Boeing company and Bell helicopter company in America, and enters the service of the United states air force in 2006 after long-time testing, modification and verification work. The machine has the advantages of good overall maneuverability, vertical take-off and landing, high speed, long range, low oil consumption and the like. However, this model also has the obvious disadvantage that the moment of inertia of the two rotors is too small, resulting in very poor autorotation characteristics of the V-22 model. And the motor also needs to rotate in the process of verting, and the accident rate is higher.
The V280 model is greatly upgraded and improved on the basis of the V-22 model, and the first time in 2017. The aircraft type has the characteristics of vertical take-off and landing, high-speed cruising and the like of an aircraft with the tilt wings. The reason for this feature is that a tilting mechanism is provided therein to tilt the rotor, and the V280 tilting mechanism is implemented by a multi-stage ball screw. The advantage of this mechanism is that the in-process motor irrotational that verts, and the security obtains promoting to the structure is compacter, practices thrift the space. The defects are that the self-locking performance is poor and the clearance is larger because of line contact. The large clearance results in the possibility of back-and-forth collisions, greater vibration and noise, and higher manufacturing requirements and therefore higher costs.
Vert among the gyroplane mainstream scheme mechanism that verts and construct and not find a most suitable configuration yet to in case live time overlength, can have the clearance between the mechanism part, lead to the speed of rotor and axle to mismatch, can cause the part collision back and forth or even the card die, cause great potential safety hazard.
Disclosure of Invention
The invention aims to provide a self-adaptive anti-backlash tilting mechanism and a tilting rotorcraft, which solve the problems in the prior art, utilize a gear structure with the most stable transmission and are provided with a clearance eliminating device, improve the transmission precision again, ensure the working safety and realize the high-precision tilting function.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a self-adaptive anti-backlash tilting mechanism which comprises a supporting plate, a rotating box and a backlash eliminating device, wherein a rotor wing is installed on the rotating box, and power transmitted by a main speed reducer of a tilting rotorcraft is transmitted to the rotor wing by the rotating box; two sides of the rotating box are respectively provided with a supporting plate, the outer side of the rotating box is rotatably connected with the supporting plates, and the inner side of the rotating box is connected with the supporting plates through the gap eliminating device;
the clearance eliminating device comprises a connecting plate, a pinion, a bull gear, an idler wheel and a spring; the inner side of the rotating box is provided with the bull gear, the periphery of the bull gear is connected with the pinion gear and the idler gear in a meshing manner, the pinion gear and the idler gear are respectively arranged on the corresponding connecting plates, the connecting plates are connected through springs, and the power of the pinion gear is transmitted by the gear shaft.
Preferably, power transmitted from the main speed reducer is transmitted into the rotating box through a transmission shaft and a coupling, output power is turned through a bevel gear in the rotating box and is finally transmitted to the rotor shaft to drive the rotor to rotate.
Preferably, the tilting motor is connected to the one end of gear shaft, the other pot head of gear shaft has deep groove ball bearing and connects the pinion, deep groove ball bearing installs on the bearing frame, the bearing frame is installed by the pin on the fagging.
Preferably, the number of the idler wheels is two, two groups of the connecting plates are arranged, each group of the connecting plates comprises three connecting plates, the two groups of the connecting plates are symmetrically arranged on the inner side and the outer side of the bull gear, each connecting plate in the two groups of the connecting plates is circumferentially and uniformly distributed by taking the axis of the bull gear as the center, and the pinion and the two idler wheels are circumferentially meshed with the periphery of the bull gear and are connected between the opposite connecting plates of the two groups of the connecting plates through pin shafts; and three of the two groups of connecting plates are sequentially connected through three springs.
Preferably, two ends of each connecting plate are provided with spring pins, and the springs are connected with the connecting plates through the spring pins.
The invention also provides a tilt rotor aircraft which comprises an airframe, wings, the self-adaptive anti-backlash tilt mechanism and the rotors, wherein the wings are arranged on two sides of the airframe, the tilt mechanism is installed at the tail ends of the wings, and the rotors are installed on the tilt mechanism.
Compared with the prior art, the invention has the following beneficial technical effects:
the self-adaptive anti-backlash tilting mechanism and the tilting rotorcraft provided by the invention utilize a gear structure with the most stable transmission, have the advantages of simple structure, convenience in processing, lower cost, fixed transmission ratio, high stability and the like. And a clearance eliminating device is arranged, so that the transmission precision is improved again, the working safety is ensured, and the high-precision tilting function is realized.
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 diagram of an adaptive backlash eliminating tilting mechanism according to a first embodiment;
FIG. 2 is a schematic front view of a backlash elimination apparatus according to an embodiment;
FIG. 3 is a schematic diagram of a backside structure of a backlash elimination device according to an embodiment;
fig. 4 is a schematic structural view of a tiltrotor aircraft according to a second embodiment;
fig. 5 is a schematic structural diagram of a helicopter mode of a tiltrotor aircraft according to a second embodiment;
FIG. 6 is a schematic view of a cruise mode configuration of a tiltrotor aircraft according to a second embodiment;
in the figure: the device comprises a fuselage 1, wings 2, rotors 3, a tilting mechanism 4, a gear shaft 5, a clearance eliminating device 6, a rotating box 7, an end cover 8, a rotor shaft 9, a supporting plate 10, a coupler 11, a transmission shaft 12, a connecting plate 13, a pinion 14, a bearing seat 15, a pin 16, a gearwheel 17, a spring pin 18, an idler wheel 19, a deep groove ball bearing 20 and a spring 21.
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.
The invention aims to provide a self-adaptive anti-backlash tilting mechanism and a tilting rotorcraft, which aim to solve the problems in the prior art.
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.
The first embodiment is as follows:
the embodiment provides a self-adaptive anti-backlash tilting mechanism, which comprises a supporting plate 10, a rotating box 7 and a backlash eliminating device 6, wherein a rotor 3 is installed on the rotating box 7, and power transmitted by a main reducer of a tilting rotor aircraft is transmitted to the rotor 3 through the rotating box 7; two sides of the rotating box 7 are respectively provided with a supporting plate 10, the outer side of the rotating box 7 is rotatably connected with the supporting plate 10, and the inner side of the rotating box 7 is connected with the supporting plate 10 through a clearance eliminating device 6;
as shown in fig. 2-3, the backlash elimination device 6 includes a connecting plate 13, a pinion 14, a bull gear 17, an idler gear 19, and a spring 21; a large gear 17 is arranged on the inner side of the rotating box 7, a small gear 14 and an idle gear 19 are meshed and connected to the periphery of the large gear 17, the small gear 14 and the idle gear 19 are respectively arranged on corresponding connecting plates 13, the connecting plates 13 are connected through springs 21, and the power of the small gear 14 is transmitted by the gear shaft 5.
In this embodiment, the power transmitted from the main reducer is transmitted to the rotating box 7 through the transmission shaft 12 and the coupling 11, and the output power is turned by the bevel gear in the rotating box 7 and finally transmitted to the rotor shaft 9 to drive the rotor 3 to rotate.
In this embodiment, one end of the gear shaft 5 is connected to a tilt motor (not shown), the tilt motor is mounted on the body 1 of the rotor 3, the other end of the gear shaft 5 is sleeved with a deep groove ball bearing 20 and connected to the pinion 14, the deep groove ball bearing 20 is mounted on a bearing block 15, and the bearing block 15 is mounted on the supporting plate 10 by a pin 16.
In the embodiment, two idler wheels 19 are provided, two groups of connecting plates 13 are provided, each group of connecting plates comprises three connecting plates 13, the two groups of connecting plates are symmetrically arranged on the inner side and the outer side of the bull gear 17, each connecting plate 13 in the two groups of connecting plates is circumferentially and uniformly distributed by taking the axis of the bull gear 17 as the center, and the pinion 14 and the two idler wheels 19 are circumferentially meshed with the periphery of the bull gear 17 and are connected between the opposite connecting plates 13 of the two groups of connecting plates through pin shafts; three connecting plates 13 in two groups of connecting plates are sequentially connected through three springs 21, two ends of each connecting plate 13 are respectively provided with a spring pin 18, and the springs 21 are connected with the connecting plates 13 through the spring pins 18 to form a regular triangle structure with the three springs 21 connecting the three connecting plates 13.
After a long time of operation, the pinion gears 14 on the gear shafts 5 and the bull gears 17 on the outside of the rotating box 7 are not tightly meshed. At this time, the three extension springs 21 have a tendency of recovering the original length, and the elastic potential energy of the extension of the springs 21 enables the connecting plates 13 to approach each other, so as to provide a pulling force for the connecting plates 13, and enable the whole regular triangle structure to contract inwards. The connecting plate 13 drives the small gear 14 and the idle gear 19 to be tightly meshed with the large gear 17, so that the purpose of eliminating the clearance between the large gear and the small gear 14 is achieved, and the precision of gear transmission is improved; because two sets of connecting plates are symmetrically arranged on the inner side and the outer side of the large gear, the device can be prevented from overturning to one side, and therefore the self-adaptive gap eliminating function is met.
Example two:
the embodiment provides a tilt rotorcraft, as shown in fig. 4, including fuselage 1, wing 2, self-adaptation that embodiment one disappears the crack mechanism 4 and rotor 3 that verts, fuselage 1 both sides set up wing 2, and the terminal installation of wing 2 is verted the mechanism 4, and rotor 3 installs on tilting the mechanism 4.
The tilt rotor aircraft in this embodiment is tilt rotor aircraft that can VTOL and hover in the air, and tilt rotor aircraft has 2 kinds of working modes in total, is helicopter mode and cruise mode respectively. The helicopter mode rotor 3 is directed upwards as shown in fig. 5, providing the aircraft with a lifting power for the aircraft to take off and hover in the air; cruise mode rotor 3 is forward, as shown in fig. 6, providing forward power to the aircraft for high speed flight.
The principle and the implementation mode of the invention are explained by applying a specific embodiment, and the description of the embodiment is only used for helping to understand the method and the core idea of the 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 summary, this summary should not be construed to limit the present invention.
Claims (6)
1. The utility model provides a self-adaptation anti-backlash mechanism of verting which characterized in that: the tilting rotorcraft comprises a supporting plate, a rotating box and a clearance eliminating device, wherein a rotor wing is installed on the rotating box, and power transmitted by a main speed reducer of the tilting rotorcraft is transmitted to the rotor wing by the rotating box; two sides of the rotating box are respectively provided with a supporting plate, the outer side of the rotating box is rotatably connected with the supporting plates, and the inner side of the rotating box is connected with the supporting plates through the gap eliminating device;
the clearance eliminating device comprises a connecting plate, a pinion, a bull gear, an idler wheel and a spring; the inner side of the rotating box is provided with the bull gear, the periphery of the bull gear is connected with the pinion gear and the idler gear in a meshing manner, the pinion gear and the idler gear are respectively arranged on the corresponding connecting plates, the connecting plates are connected through springs, and the power of the pinion gear is transmitted by the gear shaft.
2. The adaptive backlash eliminating tilting mechanism according to claim 1, wherein: the power transmitted by the main speed reducer is transmitted into the rotating box through a transmission shaft and a coupler, the output power is turned through a bevel gear in the rotating box and finally transmitted to a rotor shaft to drive the rotor to rotate.
3. The adaptive backlash eliminating tilting mechanism according to claim 1, wherein: the tilting motor is connected to the one end of gear shaft, the other pot head of gear shaft has deep groove ball bearing and connects the pinion, deep groove ball bearing installs on the bearing frame, the bearing frame is installed by the pin on the fagging.
4. The adaptive backlash eliminating tilting mechanism according to claim 1, wherein: the two idler wheels are arranged, two groups of connecting plates are arranged, each group of connecting plates comprises three connecting plates, the two groups of connecting plates are symmetrically arranged on the inner side and the outer side of the bull gear, each connecting plate in the two groups of connecting plates is circumferentially and uniformly distributed by taking the axis of the bull gear as the center, and the pinion and the two idler wheels are circumferentially meshed with the periphery of the bull gear and are connected between the opposite connecting plates of the two groups of connecting plates through pin shafts; and three of the two groups of connecting plates are sequentially connected through three springs.
5. The adaptive backlash eliminating tilting mechanism according to claim 4, wherein: and two ends of each connecting plate are provided with spring pins, and the springs are connected with the connecting plates through the spring pins.
6. A tiltrotor aircraft, characterized in that: the self-adaptive anti-backlash tilting mechanism comprises a fuselage, wings, the self-adaptive anti-backlash tilting mechanism according to any one of claims 1 to 5 and rotors, wherein the wings are arranged on two sides of the fuselage, the tilting mechanism is installed at the tail ends of the wings, and the rotors are installed on the tilting mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210552615.XA CN114750941B (en) | 2022-05-19 | 2022-05-19 | Self-adaptive gap-eliminating tilting mechanism and tilting gyroplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210552615.XA CN114750941B (en) | 2022-05-19 | 2022-05-19 | Self-adaptive gap-eliminating tilting mechanism and tilting gyroplane |
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| CN114750941A true CN114750941A (en) | 2022-07-15 |
| CN114750941B CN114750941B (en) | 2024-04-12 |
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| CN114750941B (en) | 2024-04-12 |
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