CN214456418U - Transmission mechanism of lifting machine for aircraft missile hanging - Google Patents
Transmission mechanism of lifting machine for aircraft missile hanging Download PDFInfo
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- CN214456418U CN214456418U CN202120348799.9U CN202120348799U CN214456418U CN 214456418 U CN214456418 U CN 214456418U CN 202120348799 U CN202120348799 U CN 202120348799U CN 214456418 U CN214456418 U CN 214456418U
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Abstract
The utility model discloses an aircraft hangs transmission of bullet with lifting machine, include wire rope reel, the wire rope of winding on the wire rope reel, and set up and be in just drive in the wire rope reel the electric actuator of wire rope reel action, electric actuator is including the servo motor, first order NGW planetary gear train, second level NW planetary gear train and the middle NGW planetary gear train that the transmission is connected in proper order, middle NGW planetary gear train is located between first order NGW planetary gear train and the second level NW planetary gear train. The utility model relates to a rationally, small, reasonable in design to make whole lifting machine structure compacter, the fly mounting is realized promoting and is hung the bullet.
Description
Technical Field
The utility model belongs to the technical field of the bullet promotes is hung to the aircraft, especially, relate to a transmission of aircraft string bullet lifting machine.
Background
At present, the aircraft is generally hung by manual hanging ammunition or a hanging ammunition vehicle, and the manual hanging ammunition is not only low in efficiency but also low in precision rate; when the ammunition hanging vehicle carries out ammunition hanging, the ammunition hanging vehicle needs to be moved to the bottom of the aircraft, so that the ammunition hanging vehicle is not easy to enter and exit due to the space limitation below the aircraft in the ammunition hanging process; in addition, the position of the missile hanging vehicle needs to be adjusted for multiple times in the process of hanging the missile, so that the connection interface between the missile hanging frame and the missile hanging position of the aircraft is aligned, the operation difficulty is high, the utilization rate of human resources is insufficient, the missile hanging efficiency is greatly reduced, and the safety is poor. At present, however, an aircraft missile lifting machine does not exist in the market, and the aircraft missile lifting machine is installed at the bottom of an aircraft to lift a missile, so that the missile lifting difficulty is greatly reduced, the efficiency is improved, and the missile lifting time is saved. Therefore, a transmission mechanism of the aircraft missile hanging elevator needs to be designed, and the design is reasonable, so that the whole elevator is more compact in structure, convenient to install on the aircraft, and capable of realizing hoisting missile hanging.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that not enough among the above-mentioned prior art is directed against, provide a transmission of lifting machine for bullet is hung to aircraft, its reasonable in design, it is small, reasonable in design to make whole lifting machine structure compacter, the person of facilitating the installation is on the aircraft, realizes promoting to hang the bullet.
In order to solve the technical problem, the utility model discloses a technical scheme is: the utility model provides an aircraft hangs drive mechanism of bullet with lifting machine which characterized in that: the electric mechanism comprises a servo motor, a first-stage NGW planetary gear train, a second-stage NW planetary gear train and an intermediate NGW planetary gear train, wherein the servo motor, the first-stage NGW planetary gear train, the second-stage NW planetary gear train and the intermediate NGW planetary gear train are sequentially in transmission connection, and the intermediate NGW planetary gear train is positioned between the first-stage NGW planetary gear train and the second-stage NW planetary gear train.
Foretell aircraft hangs drive mechanism of bullet lifting machine, its characterized in that: the first-stage NGW planetary gear train comprises a right support and a first planetary transmission mechanism arranged in the right support, wherein the first planetary transmission mechanism comprises a first sun gear in transmission connection with a servo motor, a plurality of first planetary gears which are uniformly distributed along the circumferential direction of the first sun gear and engaged with the first sun gear, a first gear ring which is arranged outside the first planetary gears and engaged with the first planetary gears, and a first planetary gear frame for mounting the first planetary gear shafts in the first planetary gears, a first sun gear shaft is arranged in the first sun gear in a penetrating mode, the first sun gear shaft is in transmission connection with an output shaft of the servo motor, and the first planetary gear frame is in transmission connection with a second-stage NW planetary gear train.
Foretell aircraft hangs drive mechanism of bullet lifting machine, its characterized in that: the second-stage NW planetary gear train comprises a left support and a second planetary transmission mechanism arranged in the left support, the second planetary transmission mechanism comprises a second sun gear in transmission connection with the first-stage NGW planetary gear train, a plurality of second planetary gears which are uniformly distributed along the circumferential direction of the second sun gear and meshed with the second sun gear, a second gear ring which is arranged outside the second planetary gears in an enclosing mode and meshed with the second planetary gears, and a second planetary gear carrier for mounting second planetary gears in the second planetary gears, a second sun gear shaft penetrates through the second sun gear, the second sun gear shaft is in transmission connection with a first planetary gear carrier in the first-stage NGW planetary gear train, and the second sun gear penetrates through the second planetary gear carrier.
Foretell aircraft hangs drive mechanism of bullet lifting machine, its characterized in that: the second gear ring comprises a first gear ring part and a second gear ring part which is integrally formed with the first gear ring part, the outer diameter of the first gear ring part is larger than that of the second gear ring part, and the inner diameter of the first gear ring part is larger than that of the second gear ring part;
the transmission piece is arranged on the plurality of second planet wheel shafts and comprises a connecting plate connected with the plurality of second planet wheel shafts and a transmission shaft integrally formed with the connecting plate, the connecting plate is located in the first gear ring portion, and the transmission shaft penetrates through the second gear ring portion.
Foretell aircraft hangs drive mechanism of bullet lifting machine, its characterized in that: the middle NGW planetary gear train comprises a middle sun gear in transmission connection with the second-stage NW planetary gear train, a plurality of middle planet gears which are uniformly distributed along the circumferential direction of the middle sun gear and meshed with the middle sun gear, and a middle inner gear ring which is arranged on the inner side wall of the steel wire rope reel and meshed with the middle planet gears, wherein a middle planet gear shaft penetrates through the middle planet gears, the middle planet gear shaft is installed on the right support, the middle inner gear ring drives the steel wire rope reel to rotate, and the axis of the middle inner gear ring is overlapped with the axis of the steel wire rope reel.
Foretell aircraft hangs drive mechanism of bullet lifting machine, its characterized in that: the wire rope reel lateral wall circumferencial direction is provided with a plurality of hold-down mechanism that compress tightly wire rope on the wire rope reel, and is a plurality of hold-down mechanism's structure is the same, and each hold-down mechanism all includes that support connecting axle and two symmetries wear to establish the wire rope compression roller on the support connecting axle, is provided with the clearance between two wire rope compression rollers, the surface laminating wire rope of wire rope compression roller.
Compared with the prior art, the utility model has the following advantage:
1. the utility model has the advantages of simple structure and reasonable design, volume weight is little, and easy to assemble, the input cost is lower.
2. The utility model discloses an electric mechanism that adopts includes servo motor, first order NGW planetary gear train, second level NW planetary gear train and middle NGW planetary gear train, middle NGW planetary gear train is located between first order NGW planetary gear train and the second level NW planetary gear train, so that servo motor's power passes through first order NGW planetary gear train and second level NW planetary gear train transmission to middle NGW planetary gear train, thereby realize the transmission mode who turns back, make whole lifting machine structure compacter, make the intermediate position that the intermediate ring gear in the wire rope reel laid and is located wire rope reel length direction in addition, wire rope reel atress is more reasonable.
To sum up, the utility model relates to a rationally, small, reasonable in design to make whole lifting machine structure compacter, the facilitate mounting realizes that electronic promotion hangs the bullet on the aircraft.
The technical solution of the present invention is further described in detail by the accompanying drawings and examples.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Description of reference numerals:
1-a servo motor; 1-output shaft; 2-first stage NGW planetary gear train;
2-1-right support; 2-1-oilless bearing; 2-2 — a first planet carrier;
2-2-1-a second pin; 2-3 — a first planet; 2-3-1 — a first planet axle;
2-4 — a first sun gear; 2-4-1-a first sun gear shaft; 2-4-2-a first pin;
2-5 — a first ring gear; 3-second stage NW planetary gear train; 3-1-left support;
3-2-a second planet carrier; 3-2-1-the ring planet carrier portion; 3-2-straight rod planet carrier part;
3-3 — a second planet wheel; 3-3-1-a second planet wheel shaft; 3-3-2 — a first planetary wheel section;
3-3-3-a second planetary wheel section; 3-4 — a second sun gear; 3-4-1-a second sun gear shaft;
3-4-2-shaft end retainer ring; 3-5-second gear ring; 3-5-1-a first rim portion;
3-5-2-second ring gear portion; 3-6-transmission parts; 3-6-1-connecting plate;
3-6-2-transmission shaft; 3-7-support sleeve; 7-wire rope drum;
8-intermediate NGW planetary gear train; 8-3-intermediate planet wheel; 8-3-1-middle planet wheel shaft;
8-4-intermediate sun gear; 8-5-middle inner gear ring; 8-7-a positioning sleeve;
9-1-support connecting shaft; 9-2-steel wire rope pressing roller; 10-steel wire rope;
15-1-left cover plate; 15-2-right cover plate.
Detailed Description
As shown in fig. 1, the transmission mechanism of the hoisting machine for aircraft missile hanging comprises a wire rope reel 7, a wire rope 10 wound on the wire rope reel 7, and an electric mechanism arranged in the wire rope reel 7 and driving the wire rope reel 7 to move, wherein the electric mechanism comprises a servo motor 1, a first NGW planetary gear train 2, a second NGW planetary gear train 3 and an intermediate NGW planetary gear train 8 which are in transmission connection in sequence, and the intermediate NGW planetary gear train 8 is located between the first NGW planetary gear train 2 and the second NGW planetary gear train 3.
In the embodiment, the first-stage NGW planetary gear train 2 comprises a right support 2-1 and a first planetary transmission mechanism arranged in the right support 2-1, the first planetary transmission mechanism comprises a first sun gear 2-4 in transmission connection with the servo motor 1, a plurality of first planetary gears 2-3 which are uniformly distributed along the circumferential direction of the first sun gear 2-4 and are meshed with the first sun gear 2-4, a first gear ring 2-5 which surrounds the outside of the plurality of first planetary gears 2-3 and is meshed with the first planetary gears 2-3, and a first planetary gear carrier 2-2 for mounting a first planetary gear shaft 2-3-1 in the plurality of first planetary gears 2-3, a first sun gear shaft 2-4-1 penetrates through the first sun gear 2-4-1, the first sun gear shaft 2-4-1 is in transmission connection with an output shaft 1-1 of the servo motor 1, the first planet carrier 2-2 is in driving connection with the second stage NW planetary gear train 3.
In this embodiment, the second stage NW planetary gear train 3 comprises a left support 3-1, a second planetary transmission mechanism arranged in the left support 3-1, and the second planetary transmission mechanism comprises a second sun gear 3-4 in transmission connection with the first stage NGW planetary gear train 2, a plurality of second planet gears 3-3 uniformly distributed along the circumference of the second sun gear 3-4 and engaged with the second sun gear 3-4, a second ring gear 3-5 surrounding the plurality of second planet gears 3-3 and engaged with the second planet gears 3-3, and a second planet carrier 3-2 for mounting a second planet gear shaft 3-3-1 in the plurality of second planet gears 3-3, wherein a second sun gear shaft 3-4-1 penetrates through the second sun gear 3-4, and the second sun gear shaft 3-4-1 and the first planet carrier 2-2 in the first stage NGW planetary gear train 2 are in transmission connection And in dynamic connection, the second sun gear 3-4 penetrates through the second planet carrier 3-2.
In this embodiment, the second ring gear 3-5 includes a first ring gear portion 3-5-1 and a second ring gear portion 3-5-2 integrally formed with the first ring gear portion 3-5-1, the first ring gear portion 3-5-1 has an outer diameter larger than an outer diameter of the second ring gear portion 3-5-2, and the first ring gear portion 3-5-1 has an inner diameter larger than an inner diameter of the second ring gear portion 3-5-2;
a transmission piece 3-6 is arranged on the plurality of second planetary gear shafts 3-3-1, the transmission piece 3-6 comprises a connecting plate 3-6-1 connected with the plurality of second planetary gear shafts 3-3-1 and a transmission shaft 3-6-2 integrally formed with the connecting plate 3-6-1, the connecting plate 3-6-1 is positioned in the first gear ring part 3-5-1, and the transmission shaft 3-6-2 penetrates through the second gear ring part 3-5-2.
In this embodiment, the intermediate NGW planetary gear train 8 includes an intermediate sun gear 8-4 in transmission connection with the second-stage NW planetary gear train 3, a plurality of intermediate planetary gears 8-3 evenly distributed along the circumference of the intermediate sun gear 8-4 and engaged with the intermediate sun gear 8-4, and an intermediate ring gear 8-5 arranged on the inner side wall of the wire rope reel 7 and engaged with the plurality of intermediate planetary gears 8-3, the intermediate planetary gear 8-3 is provided with an intermediate planetary gear shaft 8-3-1 in a penetrating manner, the intermediate planetary gear shaft 8-3-1 is mounted on the right support 2-1, the intermediate ring gear 8-5 drives the wire rope reel 7 to rotate, and the axis of the intermediate ring gear 8-5 coincides with the axis of the wire rope reel 7.
In this embodiment, a plurality of pressing mechanisms for pressing the steel wire rope 10 on the steel wire rope reel 7 are arranged in the circumferential direction of the outer side wall of the steel wire rope reel 7, the structures of the plurality of pressing mechanisms are the same, each pressing mechanism comprises a support connecting shaft 9-1 and two steel wire rope pressing rollers 9-2 symmetrically arranged on the support connecting shaft 9-1 in a penetrating mode, a gap is arranged between the two steel wire rope pressing rollers 9-2, and the outer surface of each steel wire rope pressing roller 9-2 is attached to the steel wire rope 10.
In this embodiment, the servo motor 1 is installed on the outer end face of the right cover plate 15-2, the output shaft 1-1 of the servo motor 1 penetrates through the right cover plate 15-2, an installation hole for installing the first sun gear shaft 2-4-1 is formed in the output shaft 1-1, and the first sun gear shaft 2-4-1 and the output shaft 1-1 are in transmission connection, so that power transmission of the servo motor 1 is achieved.
In this embodiment, the first sun gear shaft 2-4-1 and the output shaft 1-1 are connected by a first pin 2-4-2, and the first planetary gear shaft 2-3-1 is mounted on the first planetary gear carrier 2-2 by a second pin 2-2-1.
In this embodiment, the outer side wall of the first gear ring 2-5 is attached to the inner side wall of the right support 2-1, the outer end surface of the right support 2-1 is attached to the inner end surface of the right cover plate 15-2, and the inner side wall of the right support 2-1 is provided with a first bearing for mounting the first planet carrier 2-2, so that the first planet wheel 2-3 drives the first planet carrier 2-2 to rotate.
In the embodiment, a second sun gear shaft 3-4-1 in the second sun gear 3-4 passes through a second planet carrier 3-2 and extends into a first planet carrier 2-2, the second sun gear shaft 3-4-1 is in transmission connection with the first planet carrier 2-2 through a double bond,
in the embodiment, the first planet carrier 2-2 is provided with a through hole for mounting the second sun gear shaft 3-4-1, the extending end of the second sun gear shaft 3-4-1 is provided with a shaft end check ring 3-4-2, the shaft end check ring 3-4-2 is arranged to prevent the second sun gear shaft 3-4-1 from moving on one hand and prevent double keys from falling off on the other hand, and the transmission stability between the first planet carrier 2-2 and the second sun gear shaft 3-4-1 is improved.
In this embodiment, a second bearing for mounting the second planet wheel shaft 3-3-1 is arranged in the second planet wheel 3-3, and a third bearing is arranged in the second planet wheel carrier 3-2, so that the second planet wheel 3-3 drives the second planet wheel carrier 3-2 to rotate.
In this embodiment, a fourth bearing for rotatably mounting the second ring gear 3-5 is disposed in the left support 3-1, the fourth bearing is located between the inner side wall of the left support 3-1 and the outer side wall of the first ring gear 3-5-1, and the second ring gear 3-5-2 is attached to the left cover plate 15-1.
In this embodiment, the second planetary gear 3-3 includes a first planetary gear portion 3-3-2 and a second planetary gear portion 3-3-3 integrally formed with the first planetary gear portion 3-3-2, the first planetary gear portion 3-3-2 is engaged with the second sun gear 3-4, the second planetary gear portion 3-3-3 is engaged with an inner sidewall of the first ring gear portion 3-5-1, an outer diameter of the first planetary gear portion 3-3-2 is larger than an outer diameter of the second planetary gear portion 3-3-3, and the second planetary gear shaft 3-3-1 passes through the first planetary gear portion 3-3-2 and the second planetary gear portion 3-3-3.
In the embodiment, the second planet wheel shaft 3-3-1 is mounted on the second planet wheel carrier 3-2 through a first bolt.
In the embodiment, the connecting plate 3-6-1 is provided with a stepped hole corresponding to the second planet wheel shaft 3-3-1, the second planet wheel shaft 3-3-1 is provided with a threaded hole, a second bolt penetrates through the stepped hole and extends into the second planet wheel shaft 3-3-1, and the connecting plate 3-6-1 and the second planet wheel shaft 3-3-1 are connected through the second bolt.
In this embodiment, in practical use, the left cover plate 15-1 is provided with a first flanging oilless bearing for rotatably mounting the transmission shaft 3-6-2.
In this embodiment, the second planet carrier 3-2 includes a circular ring planet carrier portion 3-2-1 and a straight rod planet carrier portion 3-2-2 integrally formed with the circular ring planet carrier portion 3-2-1, a through hole is formed in the straight rod planet carrier portion 3-2-2, the second sun gear shaft 3-4-1 penetrates through the circular ring planet carrier portion 3-2-1 and the straight rod planet carrier portion 3-2 and then extends into the first planet carrier portion 2-2, and the intermediate sun gear 8-4 is mounted on the straight rod planet carrier portion 3-2-2.
In the embodiment, an intermediate planetary wheel shaft 8-3-1 penetrates through the intermediate planetary wheel 8-3, and the intermediate planetary wheel shaft 8-3-1 is connected and mounted with the right support 2-1 through a fourth bolt.
In the embodiment, the straight rod planet carrier part 3-2-2 is externally sleeved with an oilless bearing 2-1-1 for rotatably mounting the right support 2-1, and the oilless bearing 2-1-1 is positioned between the outer side wall of the straight rod planet carrier part 3-2-2 and the inner side wall of the right support 2-1.
In the embodiment, a second flanging oilless bearing for rotatably mounting the middle planet wheel 8-3 is sleeved on the middle planet wheel shaft 8-3-1, a support sleeve 3-7 is arranged in the steel wire rope winding drum 7, the support sleeve 3-7 is positioned between the circular ring planet carrier part 3-2-1 and the middle planet wheel 8-3, the support sleeve 3-7 is sleeved on the straight rod planet carrier part 3-2-2 to limit the second planet wheel carrier 3-2 and the middle planet wheel 8-3, and the straight rod planet carrier part 3-2-2 is prevented from being bent by torque; in addition, a sixth bearing for rotatably mounting the middle planet wheel shaft 8-3-1 is arranged in the support sleeve 3-7.
In this embodiment, the middle planet wheel shaft 8-3-1 is sleeved with a positioning sleeve 8-7, and the positioning sleeve 8-7 is located between the second flanging oilless bearing and the sixth bearing, so that the axial positioning of the middle planet wheel 8-3 is realized, and the positioning of the third flanging oilless bearing and the sixth bearing can also be realized.
In this embodiment, the left support 3-1 is provided with a left engaging lug for mounting one end of the support connecting shaft 9-1, the right support 2-1 is provided with a right engaging lug for mounting the other end of the support connecting shaft 9-1, and the left engaging lug and the right engaging lug are symmetrically arranged.
In the embodiment, the outer diameter of the middle of the support connecting shaft 9-1 is smaller than the outer diameter of the support connecting shaft 9-1 where the steel wire rope pressing roller 9-2 is located, a convex edge is arranged in the middle of the support connecting shaft 9-1 to limit the end of the steel wire rope pressing roller 9-2, one end of one steel wire rope pressing roller 9-2 is attached to the left support 3-1, and one end of the other steel wire rope pressing roller 9-2 is attached to the right support 2-1.
In this embodiment, during actual use, still the transmission is provided with the encoder on servo motor 1's the output shaft 1-1, realizes the detection of the number of turns of the output shaft of servo motor 1 through the encoder to obtain the lifting distance of lifting machine according to the number of turns of the output shaft of servo motor 1, be convenient for judge the installation of hanging the bullet frame and target in place.
In this embodiment, it should be noted that the utility model discloses the whole weight of lifting machine is no longer than 7kg, and the diameter of wire rope reel 7 is not more than 78 mm.
In this embodiment, it should be noted that, in actual use, the hoisting machine may also be installed or lowered by hoisting or lowering other loads.
In this embodiment, it should be noted that, the utility model discloses mainly be applicable to the miniwatt motor promote and transfer the heavy load and guarantee to park midway and can not slide the car, wire rope load and unloaded state under promote and transfer when wire rope not lax and jump the groove on the reel, in addition, the utility model discloses promote under electronic and transfer the load.
The utility model discloses during the specific use, through the rotation of electric mechanism operation wire rope reel 7, wire rope reel 7 rotates wire rope 10 that makes on the wire rope reel 7 and twines, twines at wire rope 10 and drives and hang the bullet frame and promote.
The wire rope reel 7 is operated to rotate through an electric mechanism, the servo motor 1 is operated to rotate, and the servo motor 1 rotates to drive the first planet wheel 2-3 and the first planet wheel carrier 2-2 to rotate through the rotation of the first sun wheel 2-4; the first planet wheel carrier 2-2 rotates to drive the second sun wheel 3-4 to rotate through the second sun wheel shaft 3-4-1, and the second sun wheel 3-4 rotates to drive the second planet wheel 3-3 and the second planet wheel carrier 3-2 to rotate; the second planet carrier 3-2 rotates to drive the middle sun gear 8-4 on the straight rod planet carrier part 3-2-2 in the second planet carrier 3-2 to rotate; the middle sun gear 8-4 rotates to drive the middle planet gear 8-3 to rotate, and the middle planet gear 8-3 rotates to drive the steel wire rope reel 7 to rotate through the middle inner gear ring 8-5.
To sum up, the utility model relates to a rationally, small, reasonable in design to make whole lifting machine structure compacter, the fly-ash can be installed to the convenience on the aircraft, realize promoting to hang the bullet.
The above, only be the utility model discloses a preferred embodiment, it is not right the utility model discloses do any restriction, all according to the utility model discloses the technical entity all still belongs to any simple modification, change and the equivalent structure change of doing above embodiment the utility model discloses technical scheme's within the scope of protection.
Claims (6)
1. The utility model provides an aircraft hangs drive mechanism of bullet with lifting machine which characterized in that: the novel electric control device comprises a steel wire rope winding drum (7), a steel wire rope (10) wound on the steel wire rope winding drum (7), and an electric mechanism which is arranged in the steel wire rope winding drum (7) and drives the steel wire rope winding drum (7) to act, wherein the electric mechanism comprises a servo motor (1), a first-stage NGW planetary gear train (2), a second-stage NW planetary gear train (3) and an intermediate NGW planetary gear train (8) which are sequentially in transmission connection, and the intermediate NGW planetary gear train (8) is located between the first-stage NGW planetary gear train (2) and the second-stage NW planetary gear train (3).
2. The transmission mechanism of the hoisting machine for the aircraft missile according to claim 1, characterized in that: the first-stage NGW planetary gear train (2) comprises a right support (2-1) and a first planetary transmission mechanism arranged in the right support (2-1), wherein the first planetary transmission mechanism comprises a first sun gear (2-4) in transmission connection with a servo motor (1), a plurality of first planetary gears (2-3) which are uniformly distributed along the circumferential direction of the first sun gear (2-4) and are meshed with the first sun gear (2-4), a first gear ring (2-5) which is arranged outside the first planetary gears (2-3) and is meshed with the first planetary gears (2-3), and a first planetary gear carrier (2-2) which is used for installing a first planetary gear shaft (2-3-1) in the first planetary gears (2-3), a first sun gear shaft (2-4-1) penetrates through the first sun gear (2-4), the first sun gear shaft (2-4-1) is in transmission connection with an output shaft (1-1) of the servo motor (1), and the first planetary gear carrier (2-2) is in transmission connection with the second-stage NW planetary gear train (3).
3. The transmission mechanism of the hoisting machine for the aircraft missile according to claim 1, characterized in that: the second-stage NW planetary gear train (3) comprises a left support (3-1) and a second planetary transmission mechanism arranged in the left support (3-1), the second planetary transmission mechanism comprises a second sun gear (3-4) in transmission connection with the first-stage NGW planetary gear train (2), a plurality of second planetary gears (3-3) which are uniformly distributed along the circumferential direction of the second sun gear (3-4) and are meshed with the second sun gear (3-4), a second gear ring (3-5) which is arranged outside the second planetary gears (3-3) and is meshed with the second planetary gears (3-3), and a second planetary gear carrier (3-2) for mounting a second planetary gear shaft (3-3-1) in the second planetary gears (3-3), a second sun gear shaft (3-4-1) penetrates through the second sun gear (3-4), the second sun gear shaft (3-4-1) is in transmission connection with a first planet carrier (2-2) in the first-stage NGW planetary gear train (2), and the second sun gear (3-4) penetrates through the second planet carrier (3-2).
4. The transmission mechanism of the hoisting machine for the aircraft missile according to claim 3, characterized in that: the second gear ring (3-5) comprises a first gear ring part (3-5-1) and a second gear ring part (3-5-2) which is integrally formed with the first gear ring part (3-5-1), the outer diameter of the first gear ring part (3-5-1) is larger than that of the second gear ring part (3-5-2), and the inner diameter of the first gear ring part (3-5-1) is larger than that of the second gear ring part (3-5-2);
a transmission piece (3-6) is arranged on the plurality of second planet wheel shafts (3-3-1), the transmission piece (3-6) comprises a connecting plate (3-6-1) connected with the plurality of second planet wheel shafts (3-3-1) and a transmission shaft (3-6-2) integrally formed with the connecting plate (3-6-1), the connecting plate (3-6-1) is located in the first gear ring portion (3-5-1), and the transmission shaft (3-6-2) penetrates through the second gear ring portion (3-5-2).
5. The transmission mechanism of the hoisting machine for the aircraft missile according to claim 1, characterized in that: the middle NGW planetary gear train (8) comprises a middle sun gear (8-4) in transmission connection with the second-stage NW planetary gear train (3), a plurality of middle planetary gears (8-3) which are uniformly distributed along the circumferential direction of the middle sun gear (8-4) and engaged with the middle sun gear (8-4), and a middle inner gear ring (8-5) which is arranged on the inner side wall of the steel wire rope reel (7) and engaged with the plurality of middle planetary gears (8-3), the middle planet wheel (8-3) is provided with a middle planet wheel shaft (8-3-1) in a penetrating way, the middle planet wheel shaft (8-3-1) is arranged on the right support (2-1), the middle inner gear ring (8-5) drives the steel wire rope reel (7) to rotate, and the axis of the middle inner gear ring (8-5) is superposed with the axis of the steel wire rope reel (7).
6. The transmission mechanism of the hoisting machine for the aircraft missile according to claim 1, characterized in that: the steel wire rope pressing mechanism is characterized in that a plurality of pressing mechanisms for pressing steel wire ropes (10) on the steel wire rope winding drum (7) are arranged in the circumferential direction of the outer side wall of the steel wire rope winding drum (7), the pressing mechanisms are identical in structure and each comprises a support connecting shaft (9-1) and two steel wire rope pressing rollers (9-2) symmetrically arranged on the support connecting shaft (9-1), a gap is formed between the two steel wire rope pressing rollers (9-2), and the outer surfaces of the steel wire rope pressing rollers (9-2) are attached to the steel wire ropes (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120348799.9U CN214456418U (en) | 2021-02-07 | 2021-02-07 | Transmission mechanism of lifting machine for aircraft missile hanging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120348799.9U CN214456418U (en) | 2021-02-07 | 2021-02-07 | Transmission mechanism of lifting machine for aircraft missile hanging |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214456418U true CN214456418U (en) | 2021-10-22 |
Family
ID=78136981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120348799.9U Active CN214456418U (en) | 2021-02-07 | 2021-02-07 | Transmission mechanism of lifting machine for aircraft missile hanging |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214456418U (en) |
-
2021
- 2021-02-07 CN CN202120348799.9U patent/CN214456418U/en active Active
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