CN211123776U

CN211123776U - Device for simulating three-axis attitude stability of satellite

Info

Publication number: CN211123776U
Application number: CN202020063685.5U
Authority: CN
Inventors: 耿赛猛
Original assignee: Beijing Geekyc Education Technology Co ltd
Current assignee: Beijing Geekyc Education Technology Co ltd
Priority date: 2020-01-13
Filing date: 2020-01-13
Publication date: 2020-07-28
Anticipated expiration: 2030-01-13

Abstract

The utility model discloses a device that simulation satellite triaxial gesture is stable, including main rotary mechanism, vice rotary mechanism and gear drive part group, main rotary mechanism includes "U" type main rotating frame, circular base, fixed mounting circuit part group, fixed mounting in the main rotating frame the one-way bearing and the fixed mounting on main rotating frame left side top are in the spherical outside bearing fixing base two on main rotating frame right side top, evenly install a plurality of adjustable stabilizer blades around its circumferencial direction on the base bottom face, base central point puts the one end of rotating connection optical axis one, the fixed cover of an optical axis outer wall has plane thrust ball bearing, fixed mounting is on the plane thrust ball bearing top face main rotating frame. The utility model relates to a novelty has characteristics such as mechanism compactness, angle are accurate, focus are in the middle of and the maintenance is convenient, is applicable to the revolving stage field.

Description

Device for simulating three-axis attitude stability of satellite

Technical Field

The utility model relates to a device field of simulation satellite specifically is a device that simulation satellite triaxial gesture is stable.

Background

The simulation satellite attitude cloud platform simulates the operation attitude of a satellite in space by adjusting each attitude angle of the cloud platform, most cloud platforms on the market are used for adapting to an antenna, a camera, a radar and a large aircraft at present, and the cloud platforms for simulating the satellite attitude for small aircraft and teaching are too few and have too complex structures, so that the exploration of the relationship among the attitude angles is not facilitated.

SUMMERY OF THE UTILITY MODEL

In order to solve the problem, the utility model provides a device field of simulation satellite, wherein rotate the optical axis system and all adopt independent drive unit to place power take off part group in the position that does not influence whole focus, reduce the influence of focus to simulation satellite triaxial angle, have that mechanism is compact, the angle is accurate, focus is in the middle and maintain characteristics such as convenient, be applicable to the revolving stage field.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a device that simulation satellite triaxial gesture is stable, includes main rotary mechanism, vice rotary mechanism and gear drive part group, its characterized in that: the main rotating mechanism comprises a U-shaped main rotating frame, a circular base, a circuit component group fixedly mounted on the main rotating frame, an one-way bearing fixedly mounted at the top end of the left side of the main rotating frame and an outer spherical surface bearing fixing seat II fixedly mounted at the top end of the right side of the main rotating frame, a plurality of adjustable supporting legs are uniformly mounted on the bottom end face of the base around the circumferential direction of the base, the central position of the base is rotatably connected with one end of a first optical axis, a plane thrust ball bearing is fixedly sleeved on the outer wall of the first optical axis, the main rotating frame is fixedly mounted on the top end face of the plane thrust ball bearing, a second stepping motor is fixedly mounted on one side of the middle part of the inner surface of the main rotating frame, the driving end of the second stepping motor is connected with one end of a third belt transmission set, and the other end of the, the inner sides of two ends of the main rotating frame are fixedly provided with a first stepping motor and a second stepping motor respectively, the driving ends of the first stepping motor are respectively in driving connection with the lower ends of a second belt transmission set outside the two ends of the main rotating frame, one of the lower ends of the second belt transmission set is fixedly connected with one end of a second optical shaft, the other end of the second optical shaft is connected with the second optical shaft fixing seat on the left side of the auxiliary rotating mechanism through a one-way bearing, the other end of the second optical shaft is fixedly connected with the second optical shaft fixing seat on the left side of the auxiliary rotating mechanism through a second outer spherical bearing fixing seat and a first outer spherical bearing fixing seat fixedly connected with the.

Preferably, the auxiliary rotating mechanism comprises an auxiliary rotating frame, a micro-nano satellite fixing component group and a micro-nano satellite fixedly installed in the micro-nano satellite fixing component group, the two sides of the auxiliary rotating frame are respectively provided with an optical axis fixing seat II and an outer spherical bearing fixing seat I, the central positions of the upper end and the lower end of the auxiliary rotating frame are respectively fixedly provided with an outer spherical bearing fixing seat IV and an outer spherical bearing fixing seat II, a longitudinal insertion is installed between the outer spherical bearing fixing seats IV, the top end of the optical axis III extends out to correspond to the outer spherical bearing fixing seat IV and the optical axis III and is fixedly connected with one end of the belt transmission group I, and the other end of the belt transmission group I is in driving connection with the driving end of the gear transmission component group.

Preferably, the gear transmission component group comprises a fifth outer spherical bearing fixing seat, a sixth outer spherical bearing fixing seat, a fourth optical axis, a bearing support seat, a fifth optical axis, a fifth bevel gear, a fifth main body frame and a second bevel gear at the left end of the fifth optical axis, the fifth outer spherical bearing fixing seat is fixedly mounted at the outer side of the top end of the main body frame, the sixth outer spherical bearing fixing seat is fixedly mounted at the inner side of the top end of the main body frame, the bearing support seat is fixedly mounted at the inner side of the bottom end of the main body frame, the bottom end of the fifth optical axis penetrates through the fifth outer spherical bearing fixing seat, the sixth outer spherical bearing fixing seat and the main body frame in sequence, the bottom end of the fifth optical axis extends into the inner cavity of the main body frame, the left end of the fourth optical axis penetrates through and extends into the inner cavity of the main body frame, and the second, and the optical axis four and the optical axis five are vertically arranged.

Preferably, the belt transmission group II, the belt transmission group I and the belt transmission group III have the same structure, the belt transmission group II consists of a belt and two synchronizing wheels, the two synchronizing wheels are connected through belt transmission, and the two synchronizing wheels respectively adopt a 1-die 20-tooth synchronizing wheel structure and a 1-die 10-tooth synchronizing wheel structure.

Preferably, main rotatory frame both ends are all through a plurality of copper post fixed connection ya keli backplate two, vice rotatory frame top is through a plurality of copper post fixed connection ya keli backplate one.

Preferably, a transmission end of the gear transmission component group is set as a right end of the optical axis four, and a driving end of the gear transmission component group is set as a top end of the optical axis five.

The utility model adopts the above technique, compare with current technique and have following beneficial effect: the rotating optical shafting adopts independent driving units, the power output component group is placed at the position without influencing the integral gravity center, the influence of the gravity center on the three-axis angle of the simulated satellite is reduced, and the mechanism has the characteristics of compact structure, accurate angle, centering of the gravity center, convenience in maintenance and the like, and is suitable for the field of rotary tables.

Drawings

Fig. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the installation and use of the present invention;

fig. 3 is a schematic diagram of the explosion structure of the present invention;

FIG. 4 is a schematic structural view of a gear assembly of the present invention;

fig. 5 is a schematic structural view of the middle belt transmission set of the present invention.

In the figure: 1. an acrylic guard plate I; 2. a belt transmission set I; 3. a gear transmission component group; 301. a fifth bearing fixing seat with an outer spherical surface; 302. a sixth outer spherical bearing fixing seat; 303. an optical axis four; 304. a bearing support seat; 305. an optical axis five; 306. a first bevel gear; 307. a main body frame; 308. a second bevel gear; 4. fixing a component group by a micro-nano satellite; 401. an optical axis fixing seat I; 5. a first outer spherical bearing fixing seat; 6. a second outer spherical bearing fixing seat; 7. a belt transmission set II; 701. a synchronizing wheel 702, a belt; 8. a first stepping motor; 9. a second acrylic guard plate; 10. a base; 11. adjustable support legs; 12. an optical axis I; 13. a planar thrust ball bearing; 14. a main rotating frame; 15. a second stepping motor; 16. a circuit component group; 17. a second optical axis; 18. a one-way bearing; 19. a sub-rotating frame; 20. an optical axis fixing seat II; 22. micro/nano satellite; 24. an optical axis three; 25. a bearing fixing seat IV with an outer spherical surface; 26. a support plate; 27. and a third belt transmission set.

Detailed Description

In combination with the drawings of the embodiments of the present invention, the following will clearly and completely describe the technical solutions of the embodiments of the present invention.

Referring to fig. 1-5, in an embodiment of the present invention, a device for simulating three-axis attitude stabilization of a satellite includes a main rotating mechanism, an auxiliary rotating mechanism and a gear transmission component assembly 3, the main rotating mechanism includes a U-shaped main rotating frame 14, a circular base 10, a circuit component assembly 16 fixedly mounted on the main rotating frame 14, a one-way bearing 18 fixedly mounted on the top end of the left side of the main rotating frame 14, and a spherical bearing fixing base two 6 fixedly mounted on the top end of the right side of the main rotating frame 14, a plurality of adjustable supporting legs 11 are uniformly mounted on the bottom end surface of the base 10 around the circumferential direction thereof, the center position of the base 10 is rotatably connected to one end of an optical axis one 12, a planar thrust ball bearing 13 is fixedly sleeved on the outer wall of the optical axis one 12, the main rotating frame 14 is fixedly mounted on the top end surface of the planar thrust ball bearing 13, a stepping, the driving end of the second stepping motor 15 is in driving connection with one end of a third belt transmission set 27, the other end of the third belt transmission set 27 is fixedly connected with one end, far away from the base 10, of a first optical axis 12, the inner sides of the two ends of the main rotating rack 14 are fixedly provided with a first stepping motor 8, the driving ends of the two first stepping motors 8 are respectively in driving connection with the lower end of a second belt transmission set 7 positioned on the outer sides of the two ends of the main rotating rack 14, the upper end of one second belt transmission set 7 is fixedly connected with one end of a second optical axis 17, the other end of the second optical axis 17 is fixedly connected with a second optical axis fixing seat 20 positioned on the left side of the auxiliary rotating mechanism through a one-way bearing 18, and the upper end of the other second belt transmission set 7 is fixedly connected with the driving end of. Specifically, a light axis seat is arranged at the bottom end in the middle of the base 10 and used for fixing the bottom end of the first light axis 12; the circuit component group 16 is internally provided with electronic components and batteries and is used for supplying power to the first stepping motor 8 and the stepping motor 15; the third belt transmission set 27 is used for driving the main rotating mechanism to rotate, and the second belt transmission set 7 is used for driving the auxiliary rotating mechanism to rotate.

In this embodiment, the auxiliary rotating mechanism includes an auxiliary rotating frame 19, a micro-nano satellite fixing part group 4 and a micro-nano satellite 22 fixedly installed in the micro-nano satellite fixing part group 4, two sides of the auxiliary rotating frame 19 are respectively provided with a second optical axis fixing seat 20 and a first external spherical bearing fixing seat 5, the central positions of the upper end and the lower end of the auxiliary rotating frame 19 are both fixedly provided with a fourth external spherical bearing fixing seat 25, a third optical axis 24 longitudinally penetrating the micro-nano satellite fixing part group 4 is installed between the fourth external spherical bearing fixing seats 25, the top end of the third optical axis 24 extends out of the fourth external spherical bearing fixing seat 25 and the third optical axis 24 is fixedly connected with one end of a first belt transmission group 2, and the other end of the first belt transmission group 2 is connected with. Specifically, the upper end and the lower end of the micro-nano satellite fixing part group 4 are both provided with a first optical axis fixing seat 401, and the first optical axis fixing seat 401 is used for fixedly connecting the micro-nano satellite fixing part group 4 with a third optical axis 24 so that the third optical axis 24 drives the micro-nano satellite fixing part group 4 to rotate; the top end of the micro-nano satellite fixing part group 4 is combined into an opening and closing mechanism by using a spring hinge and a lock catch.

In this embodiment, the gear transmission component group 3 includes an outer spherical bearing fixing seat five 301, an outer spherical bearing fixing seat six 302, an optical axis four 303, a bearing support seat 304, an optical axis five 305, a bevel gear one 306, a main body frame 307 and a bevel gear two 308 at the left end of the optical axis four 303, the outer spherical bearing fixing seat five 301 is fixedly installed at the outer side of the top end of the main body frame 307, the outer spherical bearing fixing seat six 302 is fixedly installed at the inner side of the top end of the main body frame 307, the bearing support seat 304 is fixedly installed at the inner side of the bottom end of the main body frame 307, the bottom end of the optical axis five 305 penetrates through the outer spherical bearing fixing seat five 301, the outer spherical bearing fixing seat six 302 and the main body frame 303 in sequence, the bottom end of the optical axis five 305 extends into the inner cavity of the main body frame 303, the left end of the optical axis four 303 penetrates through and extends into the, and optical axis four 303 and optical axis five 305 are disposed perpendicularly. Specifically, the top end of the optical axis five 305 extends out and is connected with the right end of the belt transmission group one 2; the right end of the optical axis four 303 extends out and is connected with the top end of the belt transmission group two 7.

In this embodiment, the second belt transmission set 7, the first belt transmission set 2 and the third belt transmission set 27 have the same structure, the second belt transmission set 7 is composed of a belt 7 and two synchronizing wheels 701, the two synchronizing wheels 701 are in transmission connection through the belt 7, and the two synchronizing wheels 701 respectively adopt 1-die 20-tooth synchronizing wheel structures and 1-die 10-tooth synchronizing wheel structures.

In this embodiment, the two ends of the main rotating frame 14 are both fixedly connected to the acrylic protection plate two 9 through a plurality of copper cylinders, and the top end of the auxiliary rotating frame 19 is fixedly connected to the acrylic protection plate one 1 through a plurality of copper cylinders. Specifically, the belt transmission group two 7 is located between the outer side walls of the acrylic guard plate two 9 and the main rotating frame 14, the belt transmission group one 2 is located between the acrylic guard plate one 1 and the outer wall of the top end of the auxiliary rotating frame 19, and the acrylic guard plate one 1 and the acrylic guard plate two 9 have a protection effect.

In this embodiment, the transmission end of the gear transmission component group 3 is set as the right end of the optical axis four 303, and the driving end of the gear transmission component group 3 is set as the top end of the optical axis five 305 to cooperate with transmission.

In specific implementation, the circuit component group 16 supplies power to the first stepping motor 8 and the second stepping motor 15, the driving end of the second stepping motor 15 drives the third belt transmission group 27 to drive the main rotating mechanism to rotate, the driving end of the first stepping motor 8 drives the second belt transmission group 7 to drive the auxiliary rotating mechanism to rotate, meanwhile, the first belt transmission group 7 is in transmission connection with the first belt transmission group 2 through the gear transmission component group 3, and the first belt transmission group 2 is driven to drive the micro-nano satellite fixing component group 4 to rotate.

The above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.

Claims

1. The utility model provides a device that simulation satellite triaxial gesture is stable, includes main rotary mechanism, vice rotary mechanism and gear drive part group (3), its characterized in that: the main rotating mechanism comprises a U-shaped main rotating frame (14), a circular base (10), a circuit component group (16) fixedly installed on the main rotating frame (14), a one-way bearing (18) fixedly installed at the top end of the left side of the main rotating frame (14) and a second outer spherical bearing fixing seat (6) fixedly installed at the top end of the right side of the main rotating frame (14), a plurality of adjustable supporting legs (11) are evenly installed on the bottom end face of the base (10) in the circumferential direction, the center of the base (10) is rotatably connected with one end of a first optical axis (12), a first plane thrust ball bearing (13) is fixedly sleeved on the outer wall of the first optical axis (12), the main rotating frame (14) is fixedly installed on the top end face of the first plane thrust ball bearing (13), and a second stepping motor (15) is fixedly installed on one side of the middle of the inner surface of the main rotating, the drive end drive of step motor two (15) connects the one end of belt drive group three (27), the other end fixed connection of belt drive group three (27) the one end of base (10) is kept away from in optical axis one (12), the equal fixed mounting in main rotating frame (14) both ends inboard has step motor one (8), two the drive end of step motor one (8) drives respectively to be connected and is located the lower extreme of belt drive group two (7) in main rotating frame (14) both ends outside, one of them the one end of the upper end fixed connection optical axis two (17) of belt drive group two (7), the other end of optical axis two (17) passes through one-way bearing (18) fixed connection is located left optical axis fixing base two (20) of vice rotary mechanism, another the upper end of belt drive group two (7) is passed through outer spherical surface bearing fixing base two (6) and is located outer spherical surface bearing fixing base one (5) fixed connection on vice rotary mechanism right side A transmission end of the gear transmission component group (3).

2. The device for simulating the three-axis attitude stabilization of the satellite according to claim 1, wherein: the auxiliary rotating mechanism comprises an auxiliary rotating rack (19), a micro-nano satellite fixing component group (4) and a micro-nano satellite (22) fixedly arranged in the micro-nano satellite fixing component group (4), the two sides of the auxiliary rotating frame (19) are respectively provided with the second optical axis fixing seat (20) and the first outer spherical surface bearing fixing seat (5), the center positions of the upper end and the lower end of the auxiliary rotating frame (19) are respectively fixedly provided with an outer spherical bearing fixing seat four (25), an optical axis three (24) longitudinally penetrating through the micro-nano satellite fixing component group (4) is arranged between the two outer spherical bearing fixing seats four (25), the top end of the optical axis III (24) extends out of the corresponding outer spherical surface bearing fixing seat IV (25) and the optical axis III (24) is fixedly connected with one end of the belt transmission group I (2), the other end of the belt transmission set I (2) is connected with the driving end of the gear transmission component set (3) in a driving mode.

3. The device for simulating the three-axis attitude stabilization of the satellite according to claim 2, wherein: the gear transmission component group (3) comprises an outer spherical bearing fixing seat five (301), an outer spherical bearing fixing seat six (302), an optical axis four (303), a bearing supporting seat (304), an optical axis five (305), a bevel gear one (306), a main body frame (307) and a bevel gear two (308) at the left end of the optical axis four (303), the outer spherical bearing fixing seat five (301) is fixedly installed at the outer side of the top end of the main body frame (307), the outer spherical bearing fixing seat six (302) is fixedly installed at the inner side of the top end of the main body frame (307), the bearing supporting seat (304) is fixedly installed at the inner side of the bottom end of the main body frame (307), the bottom end of the optical axis five (305) penetrates through the outer spherical bearing fixing seat five (301), the outer spherical bearing fixing seat six (302) and the main body frame (307) in sequence, and the bottom end of the optical axis five (305), the left end of the optical axis four (303) penetrates through and extends into the inner cavity of the main body frame (307), a bevel gear two (308) positioned at the left end of the optical axis four (303) and a bevel gear one (306) positioned at the bottom end of the optical axis five (305) are in meshing transmission, and the optical axis four (303) and the optical axis five (305) are vertically arranged.

4. The device for simulating the three-axis attitude stabilization of the satellite according to claim 2, wherein: the belt transmission group II (7), the belt transmission group I (2) and the belt transmission group III (27) are identical in structure, the belt transmission group II (7) is composed of a belt (702) and two synchronizing wheels (701), the two synchronizing wheels (701) are in transmission connection through the belt (702), and the two synchronizing wheels (701) respectively adopt 1-die 20-tooth synchronizing wheel structure and 1-die 10-tooth synchronizing wheel structure.

5. The device for simulating the three-axis attitude stabilization of the satellite according to claim 2, wherein: main rotatory frame (14) both ends all are through a plurality of copper post fixed connection ya keli backplate two (9), vice rotatory frame (19) top is through a plurality of copper post fixed connection ya keli backplate (1).

6. The device for simulating the three-axis attitude stabilization of the satellite according to claim 3, wherein: the transmission end of the gear transmission component group (3) is set as the right end of the optical axis four (303), and the driving end of the gear transmission component group (3) is set as the top end of the optical axis five (305).