CN215417120U

CN215417120U - Power input mechanism for manned attitude flight simulator

Info

Publication number: CN215417120U
Application number: CN202121862669.3U
Authority: CN
Inventors: 任军洲; 杨易; 赵培宇; 张祖国; 苟皓
Original assignee: Sichuan Yikong Robot Technology Co ltd
Current assignee: Sichuan Yikong Robot Technology Co ltd
Priority date: 2021-08-10
Filing date: 2021-08-10
Publication date: 2022-01-04
Anticipated expiration: 2031-08-10

Abstract

The utility model discloses a power input mechanism for a manned attitude flight simulator, which comprises a servo motor, a right-angle planetary reducer, a reducer cover, a reducer box body, a pinion, a gearwheel, an output flange, an X-frame main body connecting plate, a coder seat, a coder, a U-shaped square tube clamping plate and a plane clamping plate, wherein the servo motor is connected with the right-angle planetary reducer, the right-angle planetary reducer is connected with the reducer cover, the reducer cover is connected with the reducer box body, and the reducer box body is connected with the X-frame main body connecting plate. The output flange is fixedly connected with a U-shaped square tube clamping plate, and the U-shaped square tube clamping plate is fixedly connected with a plane clamping plate. The shell of the encoder is connected with the reducer cover through the encoder seat, and the rotating shaft of the encoder is fixedly connected with the end part of the large gear. The servo motor drives the small gear to rotate through the right-angle planetary reducer, the small gear is meshed with the large gear, and the large gear drives the output flange to synchronously move so as to drive the U-shaped square pipe clamping plate and the plane clamping plate to move.

Description

Power input mechanism for manned attitude flight simulator

Technical Field

The utility model belongs to the technical field of flight simulator manufacturing, and particularly relates to a power input mechanism for a manned attitude flight simulator.

Background

At present, the traditional manned three-axis angular attitude simulation rotating platform needs to directly collect the rotation angle of the equipment, and an appropriate transmission input chain is designed to meet the requirements of angular acceleration and angular velocity of simulated flight in a manned state.

The existing motor and transmission reducer are usually single-shaft or double-shaft rotating platforms, and can not finish data acquisition on angular acceleration and angular velocity. Meanwhile, the existing attitude simulator has the disadvantages of complex structure, complex operation and poor stability in the operation process.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the problems and provides a power input mechanism for a manned attitude flight simulator, which has the advantages of simple structure, convenient use, capability of finishing real-time data acquisition of angular acceleration and angular velocity and lower manufacturing cost.

In order to solve the technical problems, the technical scheme of the utility model is as follows: a power input mechanism for a manned attitude flight simulator comprises a servo motor, a right-angle planetary reducer, a reducer cover, a reducer box body, a pinion, a gearwheel, an output flange, an X-frame main body connecting plate, a coder seat, a coder, a U-shaped square tube clamp plate and a plane clamp plate, wherein the servo motor is connected with the right-angle planetary reducer, the right-angle planetary reducer is connected with the reducer cover, the reducer cover is connected with the reducer box body, and the reducer box body is connected with the X-frame main body connecting plate; the output flange cover is established on the gear wheel, and the output flange links firmly with U type side pipe splint, and U type side pipe splint and plane splint link firmly, and the shell of encoder passes through encoder seat and links to each other with the speed reducer lid, and the rotation axis of encoder links firmly with the tip of gear wheel, and servo motor passes through right angle planetary reducer and drives the pinion rotation, pinion and gear engagement, and the gear wheel drives output flange synchronous motion then drives U type side pipe splint and plane splint motion when rotating.

Preferably, a bull gear shaft penetrates through the middle of the bull gear, an involute spline is further arranged at the bottom of the bull gear shaft and connected with the output flange, and the top of the bull gear shaft is connected with a rotating shaft of the encoder.

Preferably, the output flange is of a hollow rotary body structure, the bottom of the output flange is connected with the U-shaped square pipe clamping plate, the inside of the output flange is of an involute spline structure, and the inside of the output flange is meshed with an involute spline at the bottom of the large gear shaft.

Preferably, the bottom of the output flange is sleeved with a slewing bearing.

Preferably, U type side's pipe splint are the structure of falling the U style of calligraphy, and U type side's pipe splint pass through the bolt and link to each other with the plane splint.

Preferably, an X frame main body connecting plate through hole is formed in the X frame main body connecting plate.

The utility model has the beneficial effects that:

the power input mechanism for the manned attitude flight simulator provided by the utility model can provide larger rotary inertia for manned rotating equipment, and meanwhile, the control is correspondingly stable, quick and accurate. In the utility model, except for the existing servo motor and the right-angle planetary reducer, the tail end of the transmission output is in meshing transmission by the bevel gear, so that the utility model has the characteristics of stable transmission, small volume and large bearing torque, and can meet the requirement for controlling the corresponding stable and quick use environment. In addition, the angle data collecting sensor adopts a mode that an output shaft is coaxial and directly connected to collect direct angle data, so that the control effect is stable, the transmission error in front of the large gear is small, and the purpose of accurately controlling rotation can be achieved. When the design of U type side pipe splint had guaranteed that big moment of torsion is exported, the moment of torsion is dispersed to the rocking arm department farther from the pivot for can adopt the less material of wall thickness and width by the transmission component, with reduce whole weight, satisfy some equipment that have the limit to weight.

Drawings

FIG. 1 is a schematic structural diagram of a power input mechanism for a manned attitude flight simulator in accordance with the present invention;

description of reference numerals: 1. a servo motor; 2. a right-angle planetary reducer; 3. a reducer cover; 4. a reducer case; 5. a pinion gear; 6. a bull gear; 7. an output flange; 8. a slew bearing; 9. an X frame main body connecting plate; 10. an encoder seat; 11. an encoder; 12. u-shaped square tube splints; 13. a plane splint.

Detailed Description

The utility model is further described with reference to the following figures and specific embodiments:

as shown in fig. 1, the power input mechanism for manned attitude flight simulator provided by the utility model comprises a servo motor 1, a right-angle planetary reducer 2, a reducer cover 3, a reducer box body 4, a pinion 5, a gearwheel 6, an output flange 7, an X-frame main body connecting plate 9, a coder seat 10, a coder 11, a U-shaped square tube clamp plate 12 and a plane clamp plate 13, wherein the servo motor 1 is connected with the right-angle planetary reducer 2, the right-angle planetary reducer 2 is connected with the reducer cover 3, the reducer cover 3 is connected with the reducer box body 4, and the reducer box body 4 is connected with the X-frame main body connecting plate 9. The output flange 7 is sleeved on the large gear 6, the output flange 7 is fixedly connected with the U-shaped square pipe clamping plate 12, and the U-shaped square pipe clamping plate 12 is fixedly connected with the plane clamping plate 13. The shell of the encoder 11 is connected with the reducer cover 3 through the encoder seat 10, and the rotating shaft of the encoder 11 is fixedly connected with the end part of the large gear 6. The servo motor 1 drives the pinion 5 to rotate through the right-angle planetary reducer 2, the pinion 5 is meshed with the large gear 6, and the large gear 6 drives the output flange 7 to synchronously move so as to drive the U-shaped square pipe clamp plate 12 and the plane clamp plate 13 to move.

In the present embodiment, the encoder 11 is a prior art device, and the encoder 11 is used for collecting rotation data.

A large gear shaft penetrates through the middle of the large gear 6, an involute spline is further arranged at the bottom of the large gear shaft and connected with the output flange 7, and the top of the large gear shaft is connected with a rotating shaft of the encoder 11.

The reducer cover 3 is located at the upper portion of the reducer case 4, and the pinion gear 5 and the bull gear 6 are located inside the reducer case 4.

The output flange 7 is a hollow revolving body structure, the bottom of the output flange 7 is connected with the U-shaped square tube clamp plate 12, the inside of the output flange 7 is of an involute spline structure, and the inside of the output flange 7 is meshed with an involute spline at the bottom of a large gear shaft. The output flange 7 is connected with the U-shaped square pipe clamp plate 12 through bolts.

The bottom cover of output flange 7 is equipped with slew bearing 8, and slew bearing 8 includes slew bearing inner race and slew bearing outer race, and the slew bearing outer race cover is established and is circled and can rotate relatively in the slew bearing inner race, and the slew bearing outer race passes through the bolt and links to each other with X frame main part connecting plate 9, and the slew bearing inner race passes through the bolt with output flange 7 and links to each other.

The U-shaped square tube clamp plate 12 is of an inverted U-shaped structure, and the U-shaped square tube clamp plate 12 is connected with the plane clamp plate 13 through bolts.

An X frame main body connecting plate through hole is formed in the X frame main body connecting plate 9, and a bolt penetrates through the X frame main body connecting plate through hole to be connected with external equipment.

In the use process of the utility model, a servo motor 1 drives a pinion gear 5 to rotate through a right-angle planetary reducer 2, the pinion gear 5 drives a bull gear 6 to rotate when rotating, an involute spline on the bull gear 6 simultaneously drives an output flange 7 to rotate, and the output flange 7 drives a rotary bearing inner ring and a U-shaped square tube clamping plate 12 and a plane clamping plate 13 to move when rotating. The U-shaped square pipe clamp plate 12 and the X-frame main body connecting plate 9 keep a relative rotating positional relationship, namely, when the U-shaped square pipe clamp plate 12 rotates, the X-frame main body connecting plate 9 keeps unchanged. The rotary shaft of the encoder 11 rotates in synchronism with the large gear 6, while the housing of the encoder 11 keeps moving in synchronism with the reducer cover 3. Therefore, the encoder 11 can directly collect the data of the relative angle between the X-frame body connecting plate 9 and the U-shaped square tube clamp plate 12. Therefore, the utility model can operate more stably, quickly and accurately.

It will be appreciated by those of ordinary skill in the art that the embodiments described herein are intended to assist the reader in understanding the principles of the utility model and are to be construed as being without limitation to such specifically recited embodiments and examples. Those skilled in the art can make various other specific changes and combinations based on the teachings of the present invention without departing from the spirit of the utility model, and these changes and combinations are within the scope of the utility model.

Claims

1. A power input mechanism for a manned attitude flight simulator, comprising: comprises a servo motor (1), a right-angle planetary reducer (2), a reducer cover (3), a reducer box body (4), a pinion (5), a gearwheel (6), an output flange (7), an X-frame main body connecting plate (9), a coder seat (10), a coder (11), a U-shaped square tube clamping plate (12) and a plane clamping plate (13), wherein the servo motor (1) is connected with the right-angle planetary reducer (2), the right-angle planetary reducer (2) is connected with the reducer cover (3), the reducer cover (3) is connected with the reducer box body (4), the reducer box body (4) is connected with the X-frame main body connecting plate (9), the output flange (7) is sleeved on the gearwheel (6), the output flange (7) is fixedly connected with the U-shaped square tube clamping plate (12), the U-shaped square tube clamping plate (12) and the plane clamping plate (13), the shell of the coder (11) is connected with the reducer cover (3) through the coder seat (10), the rotary shaft of encoder (11) links firmly with the tip of gear wheel (6), and servo motor (1) drives pinion (5) through right angle planetary reducer (2) and rotates, and pinion (5) and gear wheel (6) mesh, and gear wheel (6) drive output flange (7) synchronous motion then drive U type square pipe splint (12) and plane splint (13) motion when rotating.

2. A power input mechanism for a manned attitude flight simulator according to claim 1, wherein: a large gear shaft penetrates through the middle of the large gear (6), a third gear is further sleeved at the bottom of the large gear shaft and connected with the output flange (7), and the top of the large gear shaft is connected with a rotating shaft of the encoder.

3. A power input mechanism for a manned attitude flight simulator according to claim 1, wherein: the output flange (7) is of a hollow rotary body structure, the bottom of the output flange (7) is connected with the U-shaped square pipe clamping plate (12), the inside of the output flange (7) is of a gear structure, and the inside of the output flange (7) is meshed with a third gear.

4. A power input mechanism for a manned attitude flight simulator according to claim 1, wherein: the bottom of the output flange (7) is sleeved with a rotary bearing (8).

5. A power input mechanism for a manned attitude flight simulator according to claim 1, wherein: u type side pipe splint (12) are the structure of falling the U style of calligraphy, and U type side pipe splint (12) link to each other with plane splint (13) through the bolt.

6. A power input mechanism for a manned attitude flight simulator according to claim 1, wherein: and an X frame main body connecting plate through hole is formed in the X frame main body connecting plate (9).