CN112078787A - Self-adaptive positioning device of helicopter main reducing gear - Google Patents
Self-adaptive positioning device of helicopter main reducing gear Download PDFInfo
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- CN112078787A CN112078787A CN202010981907.6A CN202010981907A CN112078787A CN 112078787 A CN112078787 A CN 112078787A CN 202010981907 A CN202010981907 A CN 202010981907A CN 112078787 A CN112078787 A CN 112078787A
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
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Abstract
The invention relates to a self-adaptive positioning device of a helicopter main reducer, which comprises an adapter, a swinging layer, a translation layer and a fixing layer, wherein the adapter is arranged on the swinging layer; the adapter is arranged on the upper end face of the swinging layer and is used for connecting the main speed reducer, the translation layer is arranged on the lower end face of the swinging layer, and the fixing layer is arranged on the lower end face of the translation layer; the fixed upright post is arranged on the upper end face of the swinging layer main body, the ball socket is arranged at the center of the lower end face of the swinging layer main body, and the limiting groove is arranged on the periphery of the swinging layer main body; the upper end face center department of translation layer main part is equipped with first heavy universal ball that carries, and the lower terminal surface of translation layer main part is equipped with second heavy universal ball along circumference, and swing buffer gear, swing canceling release mechanical system all set up along the peripheral circumference of first heavy universal ball, and limit stop and spacing groove looks adaptation, ball socket and the cooperation of first heavy universal ball that carries. The self-adaptive positioning device of the helicopter main reducer aims to solve the problem that the traditional special tool cannot meet the positioning requirements of different types of machines.
Description
Technical Field
The invention relates to the technical field of speed reducer assembling tools, in particular to a self-adaptive positioning device of a helicopter main speed reducer.
Background
In the ground assembly process of the helicopter lift system, the most critical procedure is the assembly of a main propeller hub and a main reducer shaft output shaft. The two are matched through a high-precision spline, the gap between the teeth is not more than 0.05mm, and the positioning precision of the digital positioning system is far higher than that of a common digital positioning system. Traditionally, a host factory is hoisted by adopting a flexible hanger, manual monitoring is carried out, the spline is aligned by manual control, and natural nesting is realized by means of gravity. When the flexible assembly system is adopted for automatic assembly, the internal spline and the external spline are difficult to avoid contact due to the limitation of the manufacturing precision and the system control precision of the existing equipment. Automatic equipment usually has higher rigidity, and after the internal and external splines contact, surface load can not be released, leads to key part surface fish tail or crushing.
At present, a helicopter lift system assembling process does not have a special main reducer positioning tool, the assembling process is generally finished on a ground fixed platform or a small-sized cart, the manufacturing accuracy of a main hub and a main reducer output shaft and the position deviation of the main hub and the main reducer nesting process cause that the surface of a spline matched with a main hub and a main reducer shaft output shaft bears contact stress. In order to ensure that the main speed reducer with the self weight exceeding 1 ton is reliably supported, the fixed platform or the trolley is of a rigid structure and cannot release the surface contact stress of key parts. The traditional fixed platform or the trolley is a special tool, can not meet the requirements of adapting to the positioning of different machine types, and can not adapt to the requirements of a future digital assembly system of a lift system.
Therefore, the inventor provides an adaptive positioning device of a helicopter main reducing gear.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a self-adaptive positioning device of a helicopter main reducer, which is characterized in that a converter is connected with the main reducer, a swing layer is used for bearing the weight of the main reducer and an adapter, the swing layer is matched with a translation layer to realize free swing with multiple degrees of freedom, the translation layer is used for limiting the stroke and the position of the main reducer, and a fixed layer is fixedly connected with a Y-direction moving platform of a digital assembly system of a lift system, so that the technical problem that the traditional special tool cannot meet the positioning requirements of different types is solved.
(2) Technical scheme
The embodiment of the invention provides a self-adaptive positioning device of a helicopter main reducing gear, which comprises an adapter, a swinging layer, a translation layer and a fixing layer, wherein the adapter is arranged on the swinging layer; the adapter is arranged on the upper end face of the swinging layer and is used for connecting a main speed reducer, the translation layer is arranged on the lower end face of the swinging layer, and the fixing layer is arranged on the lower end face of the translation layer;
the swing layer comprises a swing layer main body, fixed stand columns, ball sockets and limiting grooves, the fixed stand columns are arranged on the upper end face of the swing layer main body, the ball sockets are arranged at the center of the lower end face of the swing layer main body, and the limiting grooves are arranged on the periphery of the swing layer main body;
the translation layer includes translation layer main part, first heavy load universal ball, the heavy load universal ball of second, swing buffer gear, swing canceling release mechanical system, translation canceling release mechanical system and limit stop, the up end center department of translation layer main part is equipped with first heavy load universal ball, the lower terminal surface of translation layer main part is equipped with a plurality ofly along circumference the heavy load universal ball of second, and is a plurality of swing buffer gear, a plurality of swing canceling release mechanical system all follows the peripheral circumference of first heavy load universal ball sets up, translation canceling release mechanical system limit stop all locates the up end edge of translation layer main part, limit stop with spacing groove looks adaptation, the ball socket with the cooperation of first heavy load universal ball is used for realizing the free swing on swing layer.
Further, swing buffer gear includes buffer spring, spring guide post and the spacing fulcrum of swing stroke, the spring guide post cover is located the spacing fulcrum of swing stroke, the buffer spring cover is located the spring guide post, the spring guide post is used for the restriction buffer spring's swing direction, the spacing fulcrum of swing stroke is used for the restriction buffer spring's amplitude of oscillation just the peak of the spacing fulcrum of swing stroke is higher than the upper surface of spring guide post.
Further, the swing reset mechanism comprises a first linear cylinder and a supporting block which are connected with each other, the first linear cylinder is used for driving the supporting block to ascend or descend, the first linear cylinder is arranged on the lower end face of the translation layer, and the supporting block is arranged on the upper end face of the translation layer.
Further, translation canceling release mechanical system includes second sharp cylinder, the round pin that resets and first bush, second sharp cylinder is connected the round pin that resets, second sharp cylinder is used for the drive the round pin that resets reciprocates, the round pin that resets includes interconnect's locking section and the spacing section of toper, the spacing section of toper is located the lower extreme of locking section, first bush cover is located the round pin that resets.
Further, when the second linear cylinder is used for driving the reset pin to be in a first set position, the locking section completely enters the inner hole of the first bushing; and the second linear cylinder is used for driving the reset pin to be in a second set position, the conical limiting section is positioned in the inner hole of the first bushing, and the locking section is separated from the first bushing.
Further, the fixed layer includes fixed layer main part, second bush and universal ball backup pad, the second bush universal ball backup pad all locates the up end of fixed layer main part, the second bush with reset round pin looks adaptation is a plurality of universal ball backup pad is with a plurality of the universal ball one-to-one of second heavy-duty just is used for supporting the universal ball of second heavy-duty.
Furthermore, a plurality of swing reset mechanisms are arranged on the periphery of the swing buffer mechanisms, and the swing reset mechanisms and the translation reset mechanisms are arranged on the translation layer main body in a penetrating mode.
Furthermore, the lower end face of the adapter is provided with pin holes, and the pin holes correspond to the fixed stand columns one to one and are matched with the fixed stand columns.
Furthermore, the translation reset mechanism and the limit stop are symmetrically arranged on the translation layer main body.
Further, the swing layer body, the translation layer body and the fixed layer body are all rigid flat plates.
(3) Advantageous effects
In summary, the invention is connected with the main reducer through the converter, the swing layer is used for bearing the weight of the main reducer and the adapter, the swing layer is matched with the translation layer to realize free swing with multiple degrees of freedom, the translation layer is used for limiting the stroke and the position of the main reducer, and the fixed layer is fixedly connected with the Y-direction moving platform of the digital assembly system of the lift system. Applicable in multiple helicopter main reducer location demand, realize that one set of equipment satisfies the assembly demand of different models, improve equipment flexibility degree. The device has good rigidity in the locking state and high positioning precision; the release state eliminates the contact stress of the helicopter main reducer output shaft and the key matching area of the main propeller hub, avoids product damage risks, greatly reduces the requirements of manufacturing and control precision of a digital assembly system, reduces equipment manufacturing cost and technical risks, and has higher economic benefit.
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 of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of an overall structure of an adaptive positioning device for a helicopter main reducer according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of an upper surface of an adapter in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a lower surface of an adapter in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a swing layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of an upper surface of a translation layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a lower surface of a translation layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a swing damping mechanism in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 8 is a schematic structural diagram of a swing reset mechanism in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 9 is a schematic structural diagram of a translational reset mechanism in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 10 is a schematic structural diagram of a fixing layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention;
FIG. 11 is a schematic diagram of an assembly of an adaptive positioning device of a helicopter main reducer and the main reducer according to an embodiment of the present invention.
In the figure:
1-an adapter; 101-pin holes; 2-a wobble layer; 201-a wobble layer body; 202-fixed upright post; 203-a ball and socket; 204-a limiting groove; 3-a translation layer; 301-a translation layer body; 302-a first heavy-duty universal ball; 303-a second heavy-duty universal ball; 304-a swing damping mechanism; 3041-a cushion spring; 3042-spring guide post; 3043-swing travel limit fulcrum; 305-a swing reset mechanism; 3051-a first linear cylinder; 3052-a support block; 306-a translational reset mechanism; 3061-a second linear cylinder; 3062-a reset pin; 30621-locking section; 30622-a conical spacing section; 3063 — a first bushing; 307-limit stop; 4-a fixing layer; 401-fixed layer body; 402-a second bushing; 403-universal ball support plate; 5-a main reducer; 501-main reducer output shaft.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic general structural diagram of an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, fig. 2 is a schematic structural diagram of an upper surface of an adapter in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, fig. 3 is a schematic structural diagram of a lower surface of an adapter in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, fig. 4 is a schematic structural diagram of a swing layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, fig. 5 is a schematic structural diagram of an upper surface of a translation layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, fig. 6 is a schematic structural diagram of a lower surface of a translation layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, as shown in fig. 1 to 6, the embodiment of the invention provides a self-adaptive positioning device of a helicopter main reducing gear, which comprises an adapter 1, a swinging layer 2, a translation layer 3 and a fixing layer 4; the adapter 1 is arranged on the upper end face of the swing layer 2 and is used for being connected with a main speed reducer 5, the translation layer 3 is arranged on the lower end face of the swing layer 2, and the fixing layer 4 is arranged on the lower end face of the translation layer 3; the swing layer 2 comprises a swing layer main body 201, fixed columns 202, ball sockets 203 and limiting grooves 204, the fixed columns 202 are arranged on the upper end face of the swing layer main body 201, the ball sockets 203 are arranged in the center of the lower end face of the swing layer main body 201, and the limiting grooves 204 are arranged on the periphery of the swing layer main body 201; translation layer 3 includes translation layer main part 301, first heavily loaded universal ball 302, second heavily loaded universal ball 303, swing buffer gear 304, swing canceling release mechanical system 305, translation canceling release mechanical system 306 and limit stop 307, translation layer main part 301's up end center department is equipped with first heavily loaded universal ball 302, translation layer main part 301's lower terminal surface is equipped with a plurality of second heavily loaded universal balls 303 along circumference, a plurality of swing buffer gear 304, a plurality of swing canceling release mechanical system 305 all set up along the peripheral circumference of first heavily loaded universal ball 302, translation canceling release mechanical system 306, limit stop 307 all locates translation layer main part 301's up end edge, limit stop 307 and limit groove 204 looks adaptation, ball socket 203 is used for realizing the free swing of swing layer 2 with the cooperation of first heavily loaded universal ball 302.
In this embodiment, fig. 11 is a schematic assembly diagram of an adaptive positioning device of a helicopter main reducer and a main reducer provided by an embodiment of the present invention, as shown in fig. 11, specifically, the adapter 1 is a sheet-shaped circular ring, the main reducer 5 is inserted into the adapter 1, the adapter 1 is pin-fitted with the top of the fixed upright 202 of the swing layer 2 through a pin hole at the bottom, and is mounted on the fixed upright 202 of the swing layer 2, the upper surface of the adapter 1 is specially designed according to the bottom of the main reducer 5 of each model, by adjusting the supporting position and angle, the center of gravity of the whole body formed by connecting the main reducer 5 of any model with the adapter 1 is positioned in the center of the fixed upright column 202 of the swing layer 2, and the output shaft 501 of the main reducer is in a vertical state, and the lower surface of the output shaft is a uniform interface matched with the swing layer 2, so that the main reducer 5 of any model can be matched with the swing layer 2 after being connected with the adapter 1.
Swing layer main part 201 is the steel flat board, and six fixed standing pillar 202 are installed to upper portion for bear the weight of main reducer 5 and adapter 1, be equipped with ball socket 203 in the middle of the bottom, with the first heavy universal ball 302 cooperation of carrying on in translation layer 3 middle part, the part of swing layer 2 top can be wholly with first heavy universal ball 302 centre of sphere as the center carry on A, B, C three degree of freedom free swing, the periphery is equipped with the spacing groove 204 of dropproof.
The below on swing layer 2 is translation layer 3, translation layer main part 301 is the steel flat board, the middle part is equipped with first heavy-duty universal ball 302, first heavy-duty universal ball 302 periphery is equipped with the swing buffer gear 304 that circumference was arranged, more the periphery is equipped with the swing canceling release mechanical system 305 that circumference was arranged, the edge is equipped with symmetrical arrangement's dropproof limit stop 307, be equipped with symmetrical arrangement's translation canceling release mechanical system 306, there is the second heavy-duty universal ball 303 of circumference arrangement in the bottom, support all loads more than translation layer 3.
The limit stopper 307 and the swing layer main body 201 are provided with a falling-proof limit groove 204, a gap is reserved between the limit stopper 307 and the swing layer main body in a normal state, and when the ball socket 203 in the middle of the swing layer 2 is horizontally separated from the first heavy-load universal ball 302 on the translation layer 3, the limit stopper 307 can prevent the falling-proof limit groove from overturning within a certain range.
As a preferred implementation manner, fig. 7 is a schematic structural diagram of a swing buffer mechanism in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, and as shown in fig. 7, the swing buffer mechanism 303 includes a buffer spring 3031, a spring guide post 3032, and a swing stroke limit fulcrum 3033, the spring guide post 3032 is sleeved on the swing stroke limit fulcrum 3033, the buffer spring 3031 is sleeved on the spring guide post 3032, the spring guide post 3032 is used for limiting a swing direction of the buffer spring 3031, the swing stroke limit fulcrum 3033 is used for limiting a swing amplitude of the buffer spring 3031, and a highest point of the swing stroke limit fulcrum 3033 is higher than an upper surface of the spring guide post 3032.
In this embodiment, the swing damper mechanism 303 is composed of six sets of mechanisms having the same structure and distributed circumferentially, and includes a damper spring 3031, a spring guide post 3032, and a swing stroke limit fulcrum 3033. When the swing layer 2 swings under the action of load, the load of the supporting position is carried by the buffer spring 3031, the direction of the buffer spring 3031 is limited by the spring guide post 3032, when the swing amplitude reaches a limited stroke, the rigid swing stroke limit fulcrum 3033 limits the continuous movement of the buffer spring 3031, and the highest point of the swing stroke limit fulcrum 3033 is higher than the upper surface of the spring guide post 3032.
As a preferred embodiment, fig. 8 is a schematic structural diagram of a swing resetting mechanism in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, and as shown in fig. 8, the swing resetting mechanism 304 includes a first linear cylinder 3041 and a supporting block 3042 that are connected to each other, the first linear cylinder 3041 is used to drive the supporting block 3042 to ascend or descend, the first linear cylinder 3041 is disposed on a lower end surface of the translation layer 3, and the supporting block 3042 is disposed on an upper end surface of the translation layer 3.
In this embodiment, the swing reset mechanism 305 is composed of six sets of identical mechanisms arranged in the circumferential direction, and includes the first linear cylinder 3051, the support block 3052, and necessary electric components, and the six sets of first linear cylinders 3051 move synchronously.
The swing reset mechanism 305 has two states: resetting the locked state and the released state. The reset locking state refers to that the first linear cylinder 3051 drives the supporting block 3052 to be located at a relatively high position, the upper supporting surfaces of the six supporting blocks 3052 are located on the same plane which is calibrated in advance and is a neutral position plane of the swing layer 2, the release state refers to a state that the first linear cylinder 3051 drives the supporting block 3052 to fall and then leaves the plane, and the switching of the states is controlled by an instruction sent by integrated control software of a lift system digital assembly system.
As a preferred embodiment, fig. 9 is a schematic structural diagram of a translational resetting mechanism in an adaptive positioning device of a main speed reducer of a helicopter according to an embodiment of the present invention, as shown in fig. 9, the translational resetting mechanism 306 includes a second linear cylinder 3061, a resetting pin 3062 and a first bushing 3063, the second linear cylinder 3061 is connected to the resetting pin 3062, the second linear cylinder 3061 is used for driving the resetting pin 3062 to move up and down, the resetting pin 3062 includes a locking section 30621 and a tapered limiting section 30622, the tapered limiting section 30622 is located at a lower end of the locking section 30621, and the first bushing 3063 is sleeved on the resetting pin 3062.
In this embodiment, the translational reset mechanism 306 is comprised of two identical sets of mechanisms that are symmetrically arranged. The device comprises second linear cylinders 3061 arranged on a translation layer main body 301, a reset pin 3062, a first bush 3063 arranged on a fixed layer 4 and necessary electrical components, and the two groups of second linear cylinders 3061 move synchronously; the resetting pin 3062 is provided with a locking section 30621 and a conical limiting section 30622, the locking section 30621 is in small clearance fit with the first bushing 3063, and the conical limiting section 30622 is in larger clearance with the first bushing 3063.
The translational reset mechanism 306 has two states: and resetting a locking state and a limiting state. The reset locking state means that the second linear cylinder 3061 drives the reset pin 3062 to be located at a relatively lower position, the locking section 30621 completely enters the inner hole of the first bushing 3063, and the translation freedom degrees of the translation layer 3 and all the structures above in the XY direction are limited; the limiting state is that the second linear cylinder 3061 drives the resetting pin 3062 to be located at a relatively high position, only the conical limiting section 30622 is located in the inner hole of the first bushing 3063, and the translation layer 3 and all the structures above can move freely in the XY direction within the range allowed by limiting.
In a preferred embodiment, the second linear cylinder 3051 is used to drive the reset pin 3052 to the first setting position, and the locking section 30521 is completely inserted into the inner hole of the first bushing 3053; when the second linear cylinder 3051 is used for driving the reset pin 3052 to be located at the second setting position, the conical limiting section 30522 is located in the inner hole of the first bushing 3053, and the locking section 30521 is separated from the first bushing 3053.
Fig. 10 is a schematic structural diagram of a fixing layer in an adaptive positioning device of a helicopter main reducer according to an embodiment of the present invention, and as shown in fig. 10, the fixing layer 4 includes a fixing layer main body 401, a second bushing 402, and a universal ball support plate 403, the second bushing 402 and the universal ball support plate 403 are both disposed on an upper end surface of the fixing layer main body 401, the second bushing 402 is adapted to a reset pin 3052, and the plurality of universal ball support plates 403 correspond to the plurality of second heavy-load universal balls 303 one to one and are used for supporting the second heavy-load universal balls 303.
In a preferred embodiment, the plurality of swing resetting mechanisms 304 are provided on the outer periphery of the plurality of swing buffer mechanisms 303, and the swing resetting mechanisms 304 and the translation resetting mechanisms 305 are both inserted into the translation layer main body 301.
In a preferred embodiment, the lower end surface of the adapter 1 is provided with pin holes 101, and the pin holes 101 are in one-to-one correspondence with and fit with the fixing posts 202.
In a preferred embodiment, the translational reset mechanism 305 and the limit stop 306 are symmetrically disposed on the translational layer main body 301. The purpose of the symmetrical arrangement is to force the forces evenly.
As a preferred embodiment, the oscillating layer body 201, the translating layer body 301 and the fixed layer body 401 are all rigid flat plates. The rigid plate is selected to improve the rigidity of the positioning device.
The embodiment of the invention provides a working process of a self-adaptive positioning device of a helicopter main reducer, which comprises the following specific steps:
(1) preparing a digital assembly system;
(2) connecting the adapter 1 with the main reducer 5;
(3) hoisting the main reducer 5 and the adapter 1 to the upper part of the device body integrally, and directly positioning and locking;
(4) the digital assembly system operates to adjust the position of the main hub to contact the main reducer output shaft 501;
(5) when the contact force detected by the sensor reaches a preset threshold value, the integrated control system issues a release instruction;
(6) the translational reset mechanism 306 and the swing reset mechanism 305 are switched to the release state simultaneously;
(7) the digital assembly system continues to operate until the main propeller hub is assembled;
(8) withdrawing the main propeller hub clamping tool, issuing a reset locking instruction by the integrated control system, and simultaneously switching the translational reset mechanism 306 and the swinging reset mechanism 305 to a reset locking state;
(9) and the lifting system products are put off the shelf and are withdrawn from the digital assembly system.
It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.
The above are merely examples of the present application and are not intended to limit the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (10)
1. A self-adaptive positioning device of a helicopter main reducer is characterized by comprising an adapter (1), a swinging layer (2), a translation layer (3) and a fixing layer (4); the adapter (1) is arranged on the upper end face of the swinging layer (2) and is used for being connected with a main speed reducer (5), the translation layer (3) is arranged on the lower end face of the swinging layer (2), and the fixing layer (4) is arranged on the lower end face of the translation layer (3);
the swing layer (2) comprises a swing layer main body (201), fixed stand columns (202), ball sockets (203) and limiting grooves (204), the fixed stand columns (202) are arranged on the upper end face of the swing layer main body (201), the ball sockets (203) are arranged in the center of the lower end face of the swing layer main body (201), and the limiting grooves (204) are arranged on the periphery of the swing layer main body (201);
the translation layer (3) comprises a translation layer main body (301), a first heavy-load universal ball (302), a second heavy-load universal ball (303), a swing buffer mechanism (304), a swing reset mechanism (305), a translation reset mechanism (306) and a limit stop (307), the first heavy-load universal ball (302) is arranged at the center of the upper end face of the translation layer main body (301), the second heavy-load universal ball (303) is circumferentially arranged on the lower end face of the translation layer main body (301), the swing buffer mechanism (304) and the swing reset mechanism (305) are circumferentially arranged on the periphery of the first heavy-load universal ball (302), the translation reset mechanism (306) and the limit stop (307) are arranged on the edge of the upper end face of the translation layer main body (301), and the limit stop (307) is matched with the limit groove (204), the ball socket (203) is matched with the first heavy-load universal ball (302) to realize free swing of the swing layer (2).
2. The self-adaptive positioning device of the helicopter main reducer according to claim 1, wherein the swing buffering mechanism (304) comprises a buffering spring (3041), a spring guide post (3042) and a swing stroke limit fulcrum (3043), the spring guide post (3042) is sleeved on the swing stroke limit fulcrum (3043), the buffering spring (3041) is sleeved on the spring guide post (3042), the spring guide post (3042) is used for limiting the swing direction of the buffering spring (3041), the swing stroke limit fulcrum (3043) is used for limiting the swing amplitude of the buffering spring (3041), and the highest point of the swing stroke limit fulcrum (3043) is higher than the upper surface of the spring guide post (3042).
3. The adaptive positioning device of the helicopter main reducer according to claim 1, characterized in that the swing reset mechanism (305) comprises a first linear cylinder (3051) and a support block (3052) which are connected with each other, the first linear cylinder (3051) is used for driving the support block (3052) to ascend or descend, the first linear cylinder (3051) is arranged on the lower end face of the translation layer (3), and the support block (3052) is arranged on the upper end face of the translation layer (3).
4. The self-adaptive positioning device of the helicopter main speed reducer according to claim 1, characterized in that the translational reset mechanism (306) comprises a second linear cylinder (3061), a reset pin (3062) and a first bushing (3063), the second linear cylinder (3061) is connected with the reset pin (3062), the second linear cylinder (3061) is used for driving the reset pin (3062) to move up and down, the reset pin (3062) comprises a locking section (30621) and a conical limit section (30622) which are connected with each other, the conical limit section (30622) is located at the lower end of the locking section (30621), and the first bushing (3063) is sleeved on the reset pin (3062).
5. The adaptive positioning device of a helicopter main reducer according to claim 4 characterized in that said second linear cylinder (3061) is used to drive said reset pin (3062) in a first set position, said locking section (30621) fully entering said first bushing (3063) inner bore; when the second linear cylinder (3061) is used for driving the resetting pin (3062) to be in the second setting position, the conical limiting section (30622) is located in the inner hole of the first lining (3063) and the locking section (30621) is separated from the first lining (3063).
6. The adaptive positioning device of the helicopter main speed reducer according to claim 5, characterized in that the fixed layer (4) comprises a fixed layer main body (401), a second bushing (402) and a universal ball support plate (403), the second bushing (402) and the universal ball support plate (403) are both arranged on the upper end face of the fixed layer main body (401), the second bushing (402) is adapted to the reset pin (3062), and the plurality of universal ball support plates (403) are in one-to-one correspondence with the plurality of second heavy-load universal balls (303) and are used for supporting the second heavy-load universal balls (303).
7. The adaptive positioning device of the helicopter main reducer according to claim 1, characterized in that a plurality of swing reset mechanisms (305) are provided at the periphery of a plurality of swing buffer mechanisms (304), and the swing reset mechanisms (305) and the translation reset mechanisms (306) are both disposed through the translation layer main body (301).
8. The adaptive positioning device of the helicopter main reducer according to claim 1, characterized in that the lower end face of the adapter (1) is provided with a pin hole (101), and the pin hole (101) is in one-to-one correspondence and is matched with the fixed upright post (202).
9. The adaptive positioning device of the helicopter main reducer according to claim 1, characterized in that the translational reset mechanism (306) and the limit stop (307) are symmetrically arranged on the translational layer main body (301).
10. The adaptive positioning device of a helicopter main reducer according to claim 1, characterized in that said oscillating layer body (201), said translating layer body (301) and said fixed layer body (401) are all rigid flat plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN102581794A (en) * | 2012-03-21 | 2012-07-18 | 南京航空航天大学 | Driven big swing angle flexible positioning and holding device |
| US20140302938A1 (en) * | 2011-10-27 | 2014-10-09 | K4A S.R.L. | Constant velocity universal joint for helicopter rotor |
| CN205524967U (en) * | 2016-01-13 | 2016-08-31 | 中国航空动力机械研究所 | Rotor shaft device and have its helicopter |
| CN111114765A (en) * | 2020-01-20 | 2020-05-08 | 中国人民解放军总参谋部第六十研究所 | Main rotor driving system of unmanned helicopter |
| CN111421486A (en) * | 2020-05-19 | 2020-07-17 | 江门市大长江集团有限公司 | Universal positioning tool |
| CN111498098A (en) * | 2020-05-09 | 2020-08-07 | 天峋创新（北京）科技有限公司 | Unmanned helicopter starting mechanism combining synchronous belt and wet type speed reducer |
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|---|---|---|---|---|
| US20140302938A1 (en) * | 2011-10-27 | 2014-10-09 | K4A S.R.L. | Constant velocity universal joint for helicopter rotor |
| CN102581794A (en) * | 2012-03-21 | 2012-07-18 | 南京航空航天大学 | Driven big swing angle flexible positioning and holding device |
| CN205524967U (en) * | 2016-01-13 | 2016-08-31 | 中国航空动力机械研究所 | Rotor shaft device and have its helicopter |
| CN111114765A (en) * | 2020-01-20 | 2020-05-08 | 中国人民解放军总参谋部第六十研究所 | Main rotor driving system of unmanned helicopter |
| CN111498098A (en) * | 2020-05-09 | 2020-08-07 | 天峋创新（北京）科技有限公司 | Unmanned helicopter starting mechanism combining synchronous belt and wet type speed reducer |
| CN111421486A (en) * | 2020-05-19 | 2020-07-17 | 江门市大长江集团有限公司 | Universal positioning tool |
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