CN112720391A - Attitude adjustment three-axis turntable for large-scale space satellite product test - Google Patents
Attitude adjustment three-axis turntable for large-scale space satellite product test Download PDFInfo
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- CN112720391A CN112720391A CN202011522050.8A CN202011522050A CN112720391A CN 112720391 A CN112720391 A CN 112720391A CN 202011522050 A CN202011522050 A CN 202011522050A CN 112720391 A CN112720391 A CN 112720391A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H1/00—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
- B25H1/14—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby with provision for adjusting the bench top
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H5/00—Tool, instrument or work supports or storage means used in association with vehicles; Workers' supports, e.g. mechanics' creepers
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Abstract
The utility model provides an attitude adjustment triaxial revolving stage for test of large-scale space satellite product, belongs to space device technical field, includes: a table body; the device is mainly used for supporting, leveling and moving equipment; a pitch mechanism; the device is used for realizing the adjustment of the 0-90-degree pitching attitude of a large space satellite product; a lifting mechanism; the lifting posture adjusting device is used for realizing the lifting posture adjustment of a large-scale space satellite product; an orientation mechanism; the device is used for realizing the azimuth angle adjustment of a large space satellite product at 0-360 degrees; the invention adopts the pitching frame with the arc-shaped structure, so that the whole structure of the equipment has better rigidity and safety; the pitching angle adjustment is realized by adopting a mode that the motor drives the gear and the arc-shaped rack through the speed reduction system, compared with the prior art, the adjusting mode effectively reduces the overall length of the table body, lightens the overall weight of the equipment, and meanwhile, the driving mode has better rigidity and requires smaller driving moment of the motor during starting.
Description
Technical Field
The invention belongs to the technical field of space equipment, and particularly relates to an attitude adjustment three-axis rotary table for testing a large-scale space satellite product.
Background
The satellite attitude adjusting rotary table is mainly applied to assembly, test and experiment of space satellite products. In recent years, with the emergence of large-scale space satellite products, some satellite test attitude adjusting rotary tables which can be suitable for high loads and large volumes are urgently needed to meet the research, development and use of the satellite products.
The two-axis rotary table or the three-axis rotary table for adjusting the satellite attitude commonly used at present mainly adopts a crank slide block and a lead screw transmission mechanism to adjust the angle attitude of a pitching axis. For some satellite products with light weight and compact structure, the turntable can better meet the functional test requirement. However, for the test of a large-mass satellite product, the rigidity of the turntable pitching structure, the crank slide block and the screw mechanism is poor, so that adverse effects are generated on the aspects of test precision and safety; and the driving torque required by the crank-slider mechanism in the starting process is larger. Meanwhile, the size of a general large-scale space satellite product is larger in the aspect of structure, so that a test turntable is generally required to provide a larger installation and test space and is limited by the pitching frame structure of the turntable and the length of a turntable body, and the turntable is difficult to realize the functional requirement.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides an attitude adjustment three-axis turntable for testing a large-scale space satellite product, and the problems of testing precision, driving moment and the size of the turntable are solved under the synergistic action of a turntable body, a pitching mechanism, a lifting mechanism and a direction mechanism.
(2) Technical scheme
The embodiment of the invention provides an attitude adjustment three-axis turntable for testing a large-scale space satellite product, which comprises:
a table body; the device is mainly used for supporting, leveling and moving equipment;
a pitch mechanism; the device is used for realizing the adjustment of the 0-90-degree pitching attitude of a large space satellite product;
a lifting mechanism; the lifting posture adjusting device is used for realizing the lifting posture adjustment of a large-scale space satellite product;
an orientation mechanism; the device is used for realizing the azimuth angle adjustment of a large space satellite product at 0-360 degrees; the pitching mechanism comprises a pitching frame, a pitching arc-shaped guide rail, a pitching motor, a pitching speed reducer, a pitching driving gear and a pitching arc-shaped rack; every single move frame left and right sides all sets firmly every single move arc guide rail, every single move arc rack has set firmly every single move arc rack on one side of the cambered surface of every single move frame, every single move arc rack meshing is provided with every single move drive gear, every single move drive gear power connect in on the every single move motor.
Furthermore, the stage body is including running through the arrangement chamber of terminal surface about the stage body, just it all rotates to be provided with every single move slider to settle intracavity surface and stage body both sides.
Furthermore, the pitching slide blocks positioned on two sides of the table body are matched with the arc-shaped guide rails positioned on two sides of the pitching frame to realize the support and the motion guidance of the pitching attitude adjusting mechanism. Further, elevating system including set firmly in elevating motor and the lift linear guide on the every single move frame, elevating motor's drive end has set firmly T type commutator, T type commutator's output power is connected with the lifting reducer, the drive end power of lifting reducer is connected with lift ball, ball last screw nut bolted connection has the position platform, position platform bolted connection has the lifting slide, the lifting slide slides and locates on the lift linear guide.
Furthermore, one end, far away from the lifting speed reducer, of the lifting ball screw is connected with an encoder.
Furthermore, the azimuth mechanism comprises an azimuth table, the azimuth table is connected with the lifting slide block through bolts, and an adapter is fixedly arranged on the front end face of the azimuth table.
Furthermore, driving wheels are arranged on the periphery of the outer side of the table body.
Furthermore, auxiliary supports are fixedly arranged on the periphery of the outer side of the table body.
(3) Advantageous effects
In conclusion, the pitching frame with the arc-shaped structure is adopted, so that the whole structure of the equipment is good in rigidity and safety; in addition, the invention drives the rack arranged on the pitching frame to adjust by driving the pitching driving gear. Compared with a pitch shaft which adopts a crank-slider mechanism, the motor starting driving torque is reduced by adopting a gear transmission mode; when the device is applied to the test of satellite products with larger volume, the pitch axis adopts a gear transmission mode, thereby effectively reducing the overall length of the table body and lightening the overall weight of the device.
Drawings
FIG. 1 is an isometric view of the present invention at 90 pitch;
FIG. 2 is a schematic view of the driving structure of the pitch part according to the present invention;
FIG. 3 is a schematic view of the construction of the lifting member of the present invention;
fig. 4 is a front view of the present invention at 0 pitch.
In the figure: 1-a table body; 2-driving wheels; 3-auxiliary supporting; 4-a lifting motor; a 5-T type commutator; 6-lifting speed reducer; 7-lifting ball screw; 8-pitch frame; 9-an azimuth stage; 10-an adapter; 11-pitching arc-shaped guide rails; 12-a lifting linear guide rail; 13-pitch slider; 14-pitch reducer; 15-a pitch motor; 16-pitch drive gear; 17-pitch arc rack; 18-lifting slide block.
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 an isometric view of an attitude-adjusting three-axis turntable for testing a large space satellite product, which includes a table body 1, as shown in fig. 1, when the attitude-adjusting three-axis turntable is tilted by 90 degrees; the device is mainly used for supporting, leveling and moving equipment; the table body 1 comprises a placing cavity penetrating through the upper end surface and the lower end surface of the table body 1, a pitching sliding block 13 is rotatably arranged on the inner surface of the placing cavity and two sides of the table body 1, and then a pitching mechanism is arranged; the device is used for adjusting and fixedly arranging a 0-90-degree pitching attitude of a large space satellite product on the platform body 1; a lifting mechanism; the lifting posture adjusting device is used for realizing the lifting posture adjustment of a large-scale space satellite product; an orientation mechanism; the device is used for realizing the azimuth angle adjustment of a large space satellite product at 0-360 degrees; as can be seen in fig. 2, the pitch mechanism includes a pitch frame 8, a pitch arc-shaped guide rail 11, a pitch motor 15, a pitch reducer 14, a pitch drive gear 16, and a pitch arc-shaped rack 17; every single move frame 8 left and right sides all sets firmly every single move arc guide rail 11, every single move arc rack has been set firmly to the cambered surface one side of every single move frame, every single move arc rack 17 meshes and is provided with every single move drive gear 16, every single move drive gear 16 power connect in on the every single move motor 15, be located 1 both sides of stage body every single move slider slip with be located every single move frame both sides arc guide rail mutually supports realization every single move gesture guiding mechanism's support and motion direction.
It is worth mentioning that the pitch mechanism as taught above; the adjusting device is used for adjusting and fixing a 0-90-degree pitching attitude of a large space satellite product on the table body 1, namely the pitching frame 8 takes a hinged point hinged to the table body 1 as a rotating circle center.
According to the invention, the pitching motor 15 drives the pitching driving gear 16 to drive the pitching arc-shaped rack 17 arranged on the pitching frame 8 to adjust, and compared with the pitching shaft adopting a crank-slider mechanism, the pitching shaft adopting a gear transmission mode has better structural rigidity and better safety; the driving torque is reduced by starting the motor in a gear transmission mode; when the device is applied to the test of satellite products with larger volume, the pitch axis adopts a gear transmission mode, thereby effectively reducing the overall length of the table body and lightening the overall weight of the device.
Referring to fig. 3, the lifting mechanism includes a lifting motor 4 and a lifting linear guide rail 12 fixedly arranged on the pitching frame 8, a T-type commutator 5 is fixedly arranged at a driving end of the lifting motor 4, an output end of the T-type commutator 5 is connected with a lifting speed reducer 6, the driving end of the lifting speed reducer 6 is connected with a lifting ball screw 7, a screw nut is connected with a position platform 9 on the ball screw 7 through a screw thread, the position platform 9 is connected with a lifting slide block 18 through a screw thread, the lifting slide block 18 is slidably arranged on the lifting linear guide rail 12, and it is worth noting that one end of the lifting ball screw 7, which is far away from the lifting speed reducer 6, is connected with an encoder.
The azimuth mechanism comprises an azimuth table 9, the azimuth table 9 is connected with the lifting slide block 18 through bolts, and an adapter 10 is fixedly arranged on the front end face of the azimuth table;
in this embodiment, a worm and gear transmission structure is dynamically arranged inside the azimuth stage 9, and a driving end of the worm and gear transmission structure is connected with the turntable bearing and is used for driving the turntable bearing to rotate.
In another embodiment, a pressure bearing mechanism and an angle measuring mechanism are further arranged in the azimuth table 9, so as to further accurately realize 0-360 ° azimuth angle adjustment, at this time, the large-scale space satellite product is fixedly arranged on the azimuth table 9, and 0-360 ° angle adjustment of the large-scale space satellite product is to be realized, that is, the rotation of 0-360 ° is performed by using the axis of the azimuth table 9 as a rotation axis.
Referring to fig. 4, the driving wheels 2 are installed around the outer side of the table body 1, the auxiliary supports 3 are fixed around the outer side of the table body 1, in this embodiment, each auxiliary support 3 includes a lifting shaft, a spring buffer is fixedly arranged at the bottom end of the lifting shaft, a hydraulic cylinder is fixedly arranged at the top end of the lifting shaft, the hydraulic cylinder is fixedly arranged on the outer side of the table body 1, and the hydraulic cylinder is used for supporting the table body 1 and adjusting the level of the table body 1 or the small-amplitude lifting table body 1 through the auxiliary supports 3.
It should be noted that, when the satellite attitude adjustment three-axis rotary table is in the initial state, as shown in fig. 4, the space occupied by storage is small in this state. In the using process, the steps of adjusting the attitude of the large-scale space satellite product test sequentially comprise pitching motion of the pitching mechanism, lifting motion of the lifting mechanism and azimuth rotation of the azimuth mechanism, and finally, triaxial arbitrary attitude adjustment of the test product is realized.
In the description of the present invention, it is to be understood that the terms "center", "lateral", "upper", "lower", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified. Furthermore, the term "comprises" and any variations thereof is intended to cover non-exclusive inclusions.
The present invention has been described in terms of embodiments, and several variations and modifications can be made to the device without departing from the principles of the present invention. It should be noted that all the technical solutions obtained by means of equivalent substitution or equivalent transformation, etc., fall within the protection scope of the present invention.
Claims (8)
1. The utility model provides an attitude adjustment triaxial revolving stage for test of large-scale space satellite product which characterized in that: the method comprises the following steps:
a table body (1); the device is mainly used for supporting, leveling and moving equipment;
a pitch mechanism; the device is used for realizing the adjustment of the 0-90-degree pitching attitude of a large space satellite product; (ii) a
A lifting mechanism; the lifting posture adjusting device is used for realizing the lifting posture adjustment of a large-scale space satellite product;
an orientation mechanism; the device is used for realizing the azimuth angle adjustment of a large space satellite product at 0-360 degrees; the pitching mechanism comprises a pitching frame (8), a pitching arc-shaped guide rail (11), a pitching motor (15), a pitching speed reducer (14), a pitching driving gear (16) and a pitching arc-shaped rack (17); every single move frame (8) left and right sides all has set firmly every single move arc guide rail (11), the cambered surface one side of every single move frame (8) has set firmly every single move arc rack (17), every single move arc rack (17) meshing is provided with every single move drive gear (16), every single move drive gear (16) power connect in on every single move motor (15).
2. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 1, wherein: the table body (1) comprises a placement cavity penetrating through the upper end face and the lower end face of the table body (1), and pitching sliding blocks (13) are arranged on the inner surface of the placement cavity and on the two sides of the table body (1) in a rotating mode.
3. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 2, wherein: the pitching sliding blocks (13) positioned on the two sides of the table body (1) and the arc-shaped guide rails (11) positioned on the two sides of the pitching frame (8) are mutually matched to realize the support and the motion guidance of the pitching attitude adjusting mechanism.
4. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 3, wherein: elevating system is including setting firmly in elevator motor (4) and lift linear guide (12) on every single move frame (8), the drive end of elevator motor (4) has set firmly T type commutator (5), the output power of T type commutator (5) is connected with lift speed reducer (6), the drive end power of lift speed reducer (6) is connected with lift ball (7), screw nut bolted connection has position platform (9) on ball (7), position platform (9) bolted connection has elevator slide (18), elevator slide (18) slide and locate on lift linear guide (12).
5. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 4, wherein: and one end of the lifting ball screw (7) far away from the lifting speed reducer (6) is connected with an encoder.
6. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 5, wherein: the azimuth mechanism comprises an azimuth table (9), the azimuth table (9) is in bolted connection with the lifting slide block (18), and an adapter (10) is fixedly arranged on the front end face of the azimuth table (9).
7. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 1, wherein: and driving wheels (2) are arranged on the periphery of the outer side of the table body (1).
8. The attitude adjustment three-axis rotary table for testing the large space satellite product according to claim 1, wherein: and auxiliary supports (3) are fixedly arranged on the periphery of the outer side of the table body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011522050.8A CN112720391A (en) | 2020-12-21 | 2020-12-21 | Attitude adjustment three-axis turntable for large-scale space satellite product test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011522050.8A CN112720391A (en) | 2020-12-21 | 2020-12-21 | Attitude adjustment three-axis turntable for large-scale space satellite product test |
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| CN112720391A true CN112720391A (en) | 2021-04-30 |
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| CN202011522050.8A Pending CN112720391A (en) | 2020-12-21 | 2020-12-21 | Attitude adjustment three-axis turntable for large-scale space satellite product test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113580083A (en) * | 2021-07-30 | 2021-11-02 | 博众精工科技股份有限公司 | Test fixture |
| CN114111778A (en) * | 2021-11-25 | 2022-03-01 | 江苏科技大学 | Photoelectric detection device's stable platform |
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| CN110712770A (en) * | 2019-08-15 | 2020-01-21 | 燕山大学 | 9-freedom hybrid attitude adjusting platform for horizontal butt joint assembly of solar wings in low space |
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| US20120274520A1 (en) * | 2010-10-25 | 2012-11-01 | Acc Ingenierie Et Maintenance | Triaxial Positioner for an Antenna |
| CN104015171A (en) * | 2014-05-27 | 2014-09-03 | 北京卫星环境工程研究所 | Multifunctional rotary table used for posture adjustment of spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114111778A (en) * | 2021-11-25 | 2022-03-01 | 江苏科技大学 | Photoelectric detection device's stable platform |
| CN114111778B (en) * | 2021-11-25 | 2024-03-26 | 江苏科技大学 | Stable platform of photoelectric detection device |
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Application publication date: 20210430 |