CN219750126U - Transmission structure in wing of single-shot unmanned tilt rotorcraft - Google Patents
Transmission structure in wing of single-shot unmanned tilt rotorcraft Download PDFInfo
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- CN219750126U CN219750126U CN202223353349.2U CN202223353349U CN219750126U CN 219750126 U CN219750126 U CN 219750126U CN 202223353349 U CN202223353349 U CN 202223353349U CN 219750126 U CN219750126 U CN 219750126U
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- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
Abstract
The utility model provides an inner transmission structure of a wing of a single-shot unmanned tilt rotorcraft, which relates to the technical field of transmission, and comprises the following components: the first transmission piece is used for being rotationally connected to the middle position of the wing structure of the tiltrotor, and can be connected with the output end of the engine of the tiltrotor; one end of the two second transmission parts are respectively and flexibly connected with two ends of the first transmission part, the two second transmission parts are respectively and rotatably connected with two side positions of the wing structure, and two ends of the two second transmission parts are respectively and flexibly connected with the input ends of two wing tip reducers of the tiltrotor; the second transmission piece comprises a plurality of wing section transmission shafts, and two adjacent wing section transmission shafts are flexibly connected; compared with an integral transmission shaft, the split type multiple wing section transmission shafts have the advantages that the slenderness ratio of the split type multiple wing section transmission shafts is greatly reduced, the dynamic problem of the transmission shafts is reduced, the design difficulty and the processing cost of the transmission shafts are reduced, and the possibility is provided for the low-cost application of the unmanned tiltrotor aircraft.
Description
Technical Field
The utility model belongs to the technical field of transmission, and particularly relates to an internal transmission structure of a wing of a single-shot unmanned tilt rotorcraft.
Background
Two unmanned tiltrotors, which have been put into use today worldwide, each employ the general layout of a single-engine built-in engine, including the TR series unmanned tiltrotor for the U.S. eagle eye and korean KARI. The two unmanned tilt rotorcraft transmit the power of a single engine arranged in the fuselage to the transmission shaft system in the wing through the transmission system, and further transmit the power to the left wing tip reducer and the right wing tip reducer, and finally drive the rotor. Due to the low use cost of a single engine, the single engine is widely used on unmanned tiltrotors. The transmission system scheme that the single-engine unmanned tilt rotorcraft must adopt is also realized by transmitting the power of the engine in the fuselage to the wing tip speed reducer through the transmission shafting in the wing.
At present, the united states hawk eye and korean TR series unmanned tilt rotorcraft transmission shafting uses an integral transmission shaft 17, but has unavoidable disadvantages, firstly, when the wing structure is subjected to bending deformation, the swept area of the integral transmission shaft is larger, and an airfoil with larger thickness is required to accommodate the swing of the transmission shaft, so that the plane flight resistance of the airfoil is increased; secondly, only one group of diaphragm coupling components are arranged between the integrated transmission shaft and the central speed reducer, and the allowable bending angle is small, so that higher requirements are put forward on the bending rigidity of the wing, and the weight of the wing structure is increased; finally, the integral transmission shaft has large slenderness ratio, and higher requirements on dynamic design, processing technology and manufacturing cost are put forward, so that low-cost mass production is not facilitated.
Disclosure of Invention
The utility model aims to provide an internal transmission structure of a wing of a single-shot unmanned tiltrotor aircraft, which aims to solve the problems that the thick wing type structure proposed in the background art can improve the bending rigidity of the wing, but can cause the increase of the flat flight resistance of the tiltrotor aircraft in a fixed wing mode, and is not beneficial to increasing the flight speed; the problems that the integral transmission shaft is used, the length of the shaft section is almost the same as that of a single-side wing, the compensation angle of a single diaphragm coupler is about 1-1.5 degrees, the bending deformation of the wing can be compensated only to a limited extent, and if the design rigidity of the wing needs to be increased, the structural weight of the wing needs to be further increased are solved; and solve the high-speed operation of transmission shaft, the slenderness ratio of integral type transmission shaft is big, and the dynamics problem is outstanding, brings the difficulty to design and processing, has increased manufacturing cost's problem.
In order to achieve the above object, the present utility model provides a transmission structure in a wing of a single-shot unmanned tiltrotor aircraft, the transmission structure comprising:
the first transmission piece is used for being rotatably connected to the middle position of the wing structure of the tiltrotor, and can be connected with the output end of the engine of the tiltrotor;
one end of each second transmission piece is flexibly connected with two ends of each first transmission piece, each second transmission piece is rotatably connected with two side positions of the wing structure, and the other end of each second transmission piece is flexibly connected with the input ends of two wing tip reducers of the tiltrotor;
the second transmission piece comprises a plurality of wing section transmission shafts, the wing section transmission shafts are sequentially arranged, and two adjacent wing section transmission shafts are flexibly connected.
Preferably, the first transmission member includes:
the device comprises a machine body inner transmission shaft and a synchronous pulley shaft, wherein one end of the machine body inner transmission shaft is flexibly connected with one end of the synchronous pulley shaft;
and the synchronous pulley is sleeved on the synchronous pulley shaft.
Preferably, the two ends of the wing section transmission shaft, the two ends of the transmission shaft in the machine body and the two ends of the synchronous pulley shaft are fixedly connected with transmission shaft flanges, the opposite flange hole installation angles of the two transmission shaft flanges are mutually perpendicular, a diaphragm coupler is connected between the opposite transmission shaft flanges, and the independent transmission shaft flanges and the output flange are also connected with the diaphragm coupler.
Preferably, the output flange is internally provided with sliding internal splines for sliding connection with the opposite external splines of the input end of the wing tip reducer.
Preferably, the diaphragm coupler comprises a plurality of stainless steel sheets, the plurality of stainless steel sheets are sequentially overlapped and riveted to form the diaphragm coupler, and the diaphragm coupler is square.
Preferably, the number of the wing section transmission shafts is two, the two wing section transmission shafts respectively comprise an inner section transmission shaft and an outer section transmission shaft, the inner section transmission shaft is arranged between the first transmission piece and the outer section transmission shaft, and flexible bearing assemblies connected with the wing structure are arranged on the outer section transmission shaft and the inner transmission shaft of the fuselage.
Preferably, the flexible bearing assembly comprises a rubber bearing seat and a first deep groove ball bearing, wherein the first deep groove ball bearing is in interference fit with an inner hole of the rubber bearing seat, and an outer adhesive layer of the rubber bearing seat is connected to the wing structure.
Preferably, rigid bearing assemblies used for being connected with the wing structure are arranged on the synchronous pulley shaft and located on two sides of the synchronous pulley.
Preferably, the rigid bearing assembly comprises a metal bearing seat and a second deep groove ball bearing, wherein the second deep groove ball bearing is in interference fit with an inner hole of the metal bearing seat, and an outer metal layer of the metal bearing seat is connected to the wing structure.
The utility model provides an inner transmission structure of a wing of a single-engine unmanned tilt rotorcraft, which has the beneficial effects that: the transmission structure changes the traditional integral transmission shaft which is longer into the split type multiple wing section transmission shafts which are shorter, and the adjacent two wing section transmission shafts are flexibly connected, so that the requirement of a second transmission part on the bending rigidity of the wing is reduced, thinner wing sections can be selected when the wing is designed, the problem of large flat flight resistance caused by thicker wing types of the traditional single-shot unmanned tilt rotorcraft is solved, the flat flight speed of the whole helicopter is further improved, the effects of reducing the weight of the wing structure and saving the processing and manufacturing cost can be achieved, meanwhile, the slenderness ratio of the split type multiple wing section transmission shafts is greatly reduced compared with that of the integral transmission shafts, the dynamics problem of the transmission shafts is reduced, the design difficulty and the processing cost of the transmission shafts are reduced, and the possibility is provided for low-cost application of the unmanned tilt rotorcraft.
Additional features and advantages of the utility model will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the utility model will be apparent from the following more particular descriptions of exemplary embodiments of the utility model as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the utility model.
FIG. 1 illustrates a schematic perspective view of a transmission structure within a wing of a single-shot unmanned tiltrotor aircraft according to one embodiment of the present utility model;
FIG. 2 illustrates a structural schematic diagram of an in-wing drive structure of a single-shot unmanned tiltrotor aircraft assembled with a wing structure of the rotorcraft, in accordance with one embodiment of the present utility model;
FIG. 3 illustrates a schematic view, partially in section, of a transmission structure within a wing of a single-shot unmanned tiltrotor aircraft, in accordance with one embodiment of the present utility model;
FIG. 4 illustrates a schematic diagram of a diaphragm coupling of a single-shot unmanned tiltrotor aircraft wing internal drive structure, according to one embodiment of the present utility model;
FIG. 5 illustrates a schematic view of the inside cross-sectional configuration of a transmission within a wing of a single-shot unmanned tiltrotor aircraft, according to one embodiment of the present utility model;
figure 6 shows a schematic view of the internal structure of a transmission in a wing of a single-shot unmanned tiltrotor aircraft according to one embodiment of the present utility model.
Reference numerals illustrate:
1. an output flange; 2. a diaphragm coupling; 3. a drive shaft flange; 4. an outer section transmission shaft; 5. rubber bearing seat; 6. a first deep groove ball bearing; 7. an inner section transmission shaft; 8. a transmission shaft in the machine body; 9. a metal bearing seat; 10. a second deep groove ball bearing; 11. a synchronous pulley; 12. a timing belt axle; 13. a wing structure; 14. a first rib clip; 15. a second rib clip; 16; and a third rib splint.
Detailed Description
Preferred embodiments of the present utility model will be described in more detail below. While the preferred embodiments of the present utility model are described below, it should be understood that the present utility model may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the utility model to those skilled in the art.
As shown in fig. 1-3, the present utility model provides a transmission structure in a wing of a single-shot unmanned tiltrotor aircraft, the transmission structure comprising:
the first transmission piece is used for being rotationally connected to the middle position of the wing structure of the tiltrotor, and can be connected with the output end of the engine of the tiltrotor;
one end of the two second transmission parts are respectively and flexibly connected with two ends of the first transmission part, the two second transmission parts are respectively and rotatably connected with two side positions of the wing structure, and the other ends of the two second transmission parts are respectively and flexibly connected with the input ends of two wing tip reducers of the tiltrotor;
the second transmission piece comprises a plurality of wing section transmission shafts, the plurality of wing section transmission shafts are sequentially arranged, and two adjacent wing section transmission shafts are flexibly connected.
Specifically, in order to solve the problems that although the thick wing profile can improve the bending rigidity of the wing, the flat flight resistance of the tiltrotor aircraft in the fixed wing mode is increased, and the increase of the flight speed is not facilitated; in order to solve the problems that the integral transmission shaft is used, the length of the shaft section is almost the same as that of a single-side wing, the compensation angle of a single diaphragm coupler is about 1-1.5 degrees, the bending deformation of the wing can be compensated only to a limited extent, and if the design rigidity of the wing needs to be increased, the structural weight of the wing needs to be further increased; the utility model provides an internal transmission structure of a wing of a single-shot unmanned tilt-rotor aircraft, which is characterized in that a traditional integral transmission shaft with a longer length is changed into a split type transmission shaft with a plurality of wing segments with shorter length, and the transmission shafts of two adjacent wing segments are flexibly connected, so that the requirement of a second transmission part on the bending rigidity of the wing is reduced, thinner wing sections can be selected when the wing is designed, the problem of large flat flight resistance caused by thicker wing type of the traditional single-shot unmanned tilt-rotor aircraft is solved, the flat flight speed of the whole aircraft is improved, the effects of reducing the weight of the wing structure 13 and saving the processing and manufacturing cost are further achieved, meanwhile, the long and thin ratio of the split type transmission shafts is greatly reduced compared with the transmission shafts, the dynamic problem of the transmission shafts is reduced, the design difficulty and the processing cost of the transmission shafts are reduced, and the possibility is provided for the low-cost application of the integral type unmanned tilt-rotor aircraft.
As shown in fig. 1 and 3, preferably, the first transmission member includes:
the device comprises a machine body inner transmission shaft and a synchronous pulley shaft, wherein one end of the machine body inner transmission shaft is flexibly connected with one end of the synchronous pulley shaft;
and the synchronous pulley is sleeved on the synchronous pulley shaft.
Preferably, the output end of the engine is also sleeved with a synchronous pulley, and the two synchronous pulleys are connected through a synchronous belt.
Specifically, under the transmission action of the timing belt, the driving power from the engine is received, and the engine can drive the timing belt shaft 12 to rotate.
As shown in fig. 4 and 6, preferably, two ends of the wing section transmission shaft, two ends of the transmission shaft in the machine body and two ends of the synchronous pulley shaft are fixedly connected with transmission shaft flanges, the flange hole mounting angles of the two opposite transmission shaft flanges are mutually perpendicular, a diaphragm coupler is connected between the two opposite transmission shaft flanges, and a diaphragm coupler is also connected between the independent transmission shaft flange and the output flange;
the diaphragm coupler comprises a plurality of stainless steel sheets, the plurality of stainless steel sheets are sequentially overlapped and riveted to form the diaphragm coupler in a square shape.
Specifically, the diaphragm coupler 2 is formed by riveting a plurality of stainless steel sheets, and has certain elastic deformation capability, when the transmission shaft flange 3 on one side of the two opposite transmission shaft flanges is bent relative to the transmission shaft flange 3 on the other side, as the flange hole installation angles of the two transmission shaft flanges 3 are mutually perpendicular, the bending moment of the transmission shaft flange 3 on one side can be transmitted to the diaphragm coupler 2, and the diaphragm coupler 2 generates elastic deformation, so that the bending moment received by the transmission shaft flange 3 on the other side is very small and even zero, and the diaphragm coupler 2 can still stably transmit torque at constant speed without transmitting the bending moment when the relative bending is generated between the transmission shaft flanges 3.
Preferably, bolt holes are formed in the riveting positions of the diaphragm coupler, and as shown in fig. 4, the number of the bolt holes can be 4, 6 or 8, and the bolt holes are connected with corresponding flange holes through bolts.
Preferably, the output flange is internally provided with sliding internal splines for sliding connection with external splines of the input end of the opposite wing tip reducer.
Specifically, when the wing structure 13 is bent and deformed, the transmission structure 13 can only bend the wing segment transmission shafts around the diaphragm coupler 2, but cannot bend synchronously with the wing structure 13 at all positions, so that when the wing structure 13 is bent and deformed, the transmission structure and the wing structure 13 displace in the wingspan direction, in order to prevent the displacement from generating wingspan direction stress on the transmission structure, one ends of the two second transmission parts, which are far away from each other, are provided with the output flange 1, sliding internal splines are arranged in the output flange 1, the displacement of the transmission structure in the wingspan direction can be converted into relative sliding in the sliding internal splines, the transmission structure is prevented from generating wingspan direction stress, and the transmission structure can still stably transmit power in the bending and deforming process of the wing structure 13.
Preferably, the number of the wing section transmission shafts is two, the two wing section transmission shafts respectively comprise an inner section transmission shaft and an outer section transmission shaft, the inner section transmission shaft is arranged between the first transmission piece and the outer section transmission shaft, and flexible bearing assemblies connected with the wing structures are arranged on the outer section transmission shaft and the inner transmission shaft of the machine body.
As shown in fig. 5, the compliant bearing assembly preferably includes a rubber bearing block and a first deep groove ball bearing that is interference fit within an inner bore of the rubber bearing block, with an outer layer of rubber bearing block being attached to the wing structure.
Preferably, the wing structure 13 comprises two wing beams, the two wing beams are oppositely arranged, and an outer adhesive layer of a rubber bearing seat on the outer end transmission shaft 4 is connected between the two wing beams through a first wing rib clamping plate 14; the outer adhesive layer of the rubber bearing seat on the transmission shaft in the machine body is connected between the two wing beams through a second wing rib clamping plate 15.
Specifically, the rubber bearing seat of the flexible bearing assembly on the inner section transmission shaft 8 is made of flexible rubber material, and can compensate the bending deformation of the spar through swinging deformation, so that the bending moment cannot be born between the inner ring and the outer ring of the first deep groove ball bearing 6 under the working condition of bending the spar.
Since the diaphragm coupler 2 can realize elastic deformation, when the wing structure 13 is bent and deformed, the relative positions of the diaphragm coupler 2 and the wing structure 13 must be ensured to be unchanged, otherwise, severe bending vibration is caused to occur to the transmission shafts on two sides of the diaphragm coupler 2, as shown in fig. 5, a left wing transmission shaft system is taken as an example, a flexible bearing assembly is used for supporting the outer section transmission shaft 4 near the diaphragm coupler 2, when the wing structure 13 is bent and deformed, the first deep groove ball bearing 6 and the outer section transmission shaft 4 synchronously relatively bend and deform, the bending deformation between the first deep groove ball bearing 6 and the first wing rib clamping plate 14 is compensated by the rubber bearing seat 5, the rubber bearing seat 5 can also provide certain supporting rigidity while the elastic deformation is ensured, the relative positions of the diaphragm coupler 2 and the wing structure 13 are almost unchanged, and the power between the inner section transmission shaft 7 and the outer section transmission shaft 4 is stably transmitted at the same speed.
Preferably, rigid bearing assemblies for connection with the wing structure are provided on the timing pulley shaft on both sides of the timing pulley.
Preferably, the rigid bearing assembly comprises a metal bearing seat and a second deep groove ball bearing, wherein the second deep groove ball bearing is in interference fit in an inner hole of the metal bearing seat, and an outer metal layer of the metal bearing seat is connected to the wing structure.
As shown in fig. 6, the outer metal layer of the metal bearing housing is preferably connected between the two wing beams by a third wing rib clip 16.
Specifically, the synchronous pulley 11 transmits engine power to the synchronous pulley shaft 12, the second deep groove ball bearings 10 at two sides of the synchronous pulley shaft 12 are fixed in the inner holes of the metal bearing seat 9, the metal bearing seat 9 is fixed on the wing structure 13 through the third wing rib clamping plate 16, rigid connection with the wing structure 13 is achieved, stability of power transmission is guaranteed, and bending deformation between the second deep groove ball bearings 10 at the left side and the right side of the synchronous pulley 11 is negligible because the length of the synchronous pulley shaft 12 is short compared with that of the whole transmission structure 13.
In summary, when the transmission structure in the wing of the single-engine unmanned tilt rotorcraft is implemented, the transmission structure changes the traditional longer integral transmission shaft into the shorter split type multiple wing section transmission shafts, the diaphragm coupling 2 is arranged between the two adjacent wing section transmission shafts, the diaphragm coupling 2 is formed by riveting multiple stainless steel sheets, certain elastic deformation capacity is achieved, when the transmission shaft flange 3 on one side of the two opposite transmission shaft flanges is bent relative to the transmission shaft flange 3 on the other side, as the flange hole installation angles of the two transmission shaft flanges 3 are mutually perpendicular, the bending moment of the transmission shaft flange 3 on one side can be transmitted to the diaphragm coupling 2, the diaphragm coupling 2 generates elastic deformation, so that the bending moment received by the transmission shaft flange 3 on the other side is very small or even zero, the requirement of the second transmission part on bending rigidity is reduced, the wing can be selected to use thinner wing profiles, the problem of large lifting resistance caused by the traditional single-engine unmanned tilt rotorcraft when the wing is designed, the manufacturing cost of the integral transmission shaft flange 3 is reduced, the split transmission shaft has the advantages of being further reduced, the manufacturing cost of the integral transmission shaft is reduced, the split transmission shaft cost is reduced, the manufacturing cost is reduced, the integral transmission shaft is reduced, the manufacturing cost is reduced, and the integral transmission shaft is reduced, and the cost is reduced, and the integral transmission shaft is manufactured simultaneously, and the cost is reduced.
The foregoing description of embodiments of the utility model has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (9)
1. The utility model provides a transmission structure in unmanned rotor craft wing that verts of single shot which characterized in that, this transmission structure includes:
the first transmission piece is used for being rotatably connected to the middle position of the wing structure of the tiltrotor, and can be connected with the output end of the engine of the tiltrotor;
one end of each second transmission piece is flexibly connected with two ends of each first transmission piece, each second transmission piece is rotatably connected with two side positions of the wing structure, and the other end of each second transmission piece is flexibly connected with the input ends of two wing tip reducers of the tiltrotor;
the second transmission piece comprises a plurality of wing section transmission shafts, the wing section transmission shafts are sequentially arranged, and two adjacent wing section transmission shafts are flexibly connected.
2. The wing internal transmission structure of a single-shot unmanned tiltrotor aircraft according to claim 1, wherein the first transmission member comprises:
the device comprises a machine body inner transmission shaft and a synchronous pulley shaft, wherein one end of the machine body inner transmission shaft is flexibly connected with one end of the synchronous pulley shaft;
and the synchronous pulley is sleeved on the synchronous pulley shaft.
3. The wing inner transmission structure of the single-engine unmanned tilt rotorcraft according to claim 2, wherein transmission shaft flanges are fixedly connected at two ends of the wing section transmission shaft, two ends of the inner transmission shaft of the fuselage and two ends of the synchronous pulley shaft, flange hole installation angles of two opposite transmission shaft flanges are mutually perpendicular, a diaphragm coupler is connected between the two opposite transmission shaft flanges, and a diaphragm coupler is also connected between the independent transmission shaft flanges and the output flange.
4. A single-shot unmanned tiltrotor aircraft wing internal transmission structure according to claim 3, wherein the output flange is internally provided with sliding internal splines for sliding connection with opposing external splines of the input end of the wing tip reducer.
5. The internal transmission structure of the wing of the single-shot unmanned tiltrotor aircraft according to claim 3, wherein the diaphragm coupler comprises a plurality of stainless steel sheets, the plurality of stainless steel sheets are sequentially overlapped and riveted, and the diaphragm coupler is square.
6. The wing inner transmission structure of the single-emission unmanned tiltrotor aircraft according to claim 2, wherein the number of the wing section transmission shafts is two, the two wing section transmission shafts respectively comprise an inner section transmission shaft and an outer section transmission shaft, the inner section transmission shaft is arranged between the first transmission piece and the outer section transmission shaft, and flexible bearing assemblies connected with the wing structure are arranged on the outer section transmission shaft and the fuselage inner transmission shaft.
7. The wing inner drive structure of the single-shot unmanned tiltrotor aircraft according to claim 6, wherein the flexible bearing assembly comprises a rubber bearing block and a first deep groove ball bearing, the first deep groove ball bearing is in interference fit with an inner hole of the rubber bearing block, and an outer adhesive layer of the rubber bearing block is connected to the wing structure.
8. The wing inner transmission structure of the single-shot unmanned tiltrotor aircraft according to claim 2, wherein rigid bearing assemblies for connection with the wing structure are arranged on the synchronous pulley shafts and on both sides of the synchronous pulleys.
9. The wing inner drive structure of a single-shot unmanned tiltrotor aircraft according to claim 8, wherein the rigid bearing assembly comprises a metal bearing housing and a second deep groove ball bearing, the second deep groove ball bearing being interference fit within an inner bore of the metal bearing housing, an outer metal layer of the metal bearing housing being attached to the wing structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223353349.2U CN219750126U (en) | 2022-12-14 | 2022-12-14 | Transmission structure in wing of single-shot unmanned tilt rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223353349.2U CN219750126U (en) | 2022-12-14 | 2022-12-14 | Transmission structure in wing of single-shot unmanned tilt rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219750126U true CN219750126U (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223353349.2U Active CN219750126U (en) | 2022-12-14 | 2022-12-14 | Transmission structure in wing of single-shot unmanned tilt rotorcraft |
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| Country | Link |
|---|---|
| CN (1) | CN219750126U (en) |
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- 2022-12-14 CN CN202223353349.2U patent/CN219750126U/en active Active
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