CN215182706U - Earth synchronous orbit satellite display system - Google Patents

Abstract

The utility model provides a geosynchronous orbit satellite display system, include: the earth simulator is arranged on the rack and comprises a globe and a rotation driving device for driving the globe to horizontally rotate; the satellite models of the at least two satellite simulation devices use the globe as a revolution center, and the at least two satellite simulation devices are located on different planes; the controller is used for controlling the revolution period of the satellite models of the at least two satellite simulation devices to be consistent with the rotation period of the globe. The utility model provides a geosynchronous orbit satellite display system for solve at least that difference and satellite and earth's relative motion between the different satellite orbit of unable visual display are concerned technical problem.

Description

Earth synchronous orbit satellite display system

Technical Field

The utility model relates to an aerospace knowledge teaching field especially relates to a geosynchronous orbit satellite display system.

Background

The aerospace science popularization industry is a very important part in the aerospace industry in China, and is helpful for stimulating the learning interest of the public on the aerospace technology. With the development of the aerospace industry, the aerospace industry of China is continuously broken through, China launches many artificial satellites, the number of orbits of the artificial satellites is large, and the orbits of the artificial satellites of different types and applications can be selected according to observation tasks.

At present, as for the mode of satellite science popularization display, the traditional mode adopts the mode of propaganda picture and text and video explanation for display, the display mode is tedious, some static display models appear in recent years, but the models can only be seen on the surface and can be deeply understood by the public with abundant imagination, the science popularization content is difficult to visually present to the public, and the difference between different satellite orbits cannot be clearly displayed. In addition, most exhibits focus on the functions of communication, navigation, climate monitoring and the like of the display satellite, and no display system capable of visually displaying the operation mode of the orbit satellite and the relative motion relationship between the orbit satellite and the earth exists, so that the scientific popularization of the aerospace knowledge is influenced.

Therefore, how to visually display the difference between different satellite orbits and the relative motion relationship with the earth is particularly important and urgent in the development of aerospace science popularization exhibit industry.

SUMMERY OF THE UTILITY MODEL

The utility model provides a geosynchronous orbit satellite display system for solve at least that difference and satellite and earth's relative motion between the different satellite orbit of unable visual display are concerned technical problem.

In order to achieve the above object, the present invention provides a geosynchronous orbit satellite display system, comprising:

a frame;

the earth simulator is arranged on the rack and comprises a globe and a rotation driving device for driving the globe to horizontally rotate;

the satellite models of the at least two satellite simulation devices use the globe as a revolution center;

and the controller is used for controlling the revolution period of the satellite models of the at least two satellite simulation devices to be consistent with the rotation period of the globe.

The utility model provides a pair of geosynchronous orbit satellite display system, through the revolution motion of simulation satellite and the rotation motion of earth, with the audio-visual presentation of difference between the different satellite orbit to the motion process of the different satellite of dynamic demonstration and the relative motion relation between the earth can leave dark impression for masses, increase the interest of show, can play fine science popularization bandwagon effect.

In one possible embodiment, one of the at least two satellite simulation devices is a first satellite simulation device, and the other of the at least two satellite simulation devices is a second satellite simulation device;

the first satellite simulation device comprises a first orbit and a first satellite model, the first orbit is arranged on the rack, the first satellite model moves along the first orbit, and the first satellite model takes the globe as a revolution center;

the second satellite simulation device comprises a second orbit and a second satellite model, the second orbit is arranged on the rack, the second satellite model moves along the second orbit, the second satellite model takes the globe as a revolution center, and the second orbit and the first orbit are positioned on the same plane or different planes;

the controller is used for controlling the revolution period of the first satellite model and the revolution period of the second satellite model to be consistent with the rotation period of the globe.

In a possible implementation manner, an outer gear ring is arranged on the periphery of each of the first orbit and the second orbit, each of the first satellite model and the second satellite model comprises a gear, and the gear of the first satellite model is meshed with the outer gear ring arranged on the periphery of the first orbit; the gear of the second satellite model is meshed with an outer gear ring arranged on the periphery of the second orbit.

In a possible implementation manner, each of the first satellite model and the second satellite model further includes a sliding seat, a second motor, and a second driver electrically connected to the second motor, the second motor is disposed on the sliding seat, an output shaft of the second motor is connected to the gear through a second speed reducer, and the second driver is disposed on the sliding seat.

In a possible implementation manner, the rotation driving device is disposed in the rack, the rotation driving device includes a first motor, a first driver and a vertically disposed spindle, an output shaft of the first motor is connected with a lower end of the spindle, an upper end of the spindle is provided with a tray, the globe is disposed in the tray, and the first driver is electrically connected with the first motor.

In one possible implementation, the controller includes a first controller, a second controller, and a third controller, the first controller is disposed on the rack, the second controller is disposed on the first satellite simulation device, and the third controller is disposed on the second satellite model;

the first controller is electrically connected with the first driver, and the first controller controls the rotating speed of the first motor through the first driver;

the second controller is electrically connected with the second driver of the first satellite model, and the second controller controls the rotating speed of the second motor of the first satellite model through the second driver of the first satellite model;

the third controller is electrically connected with the second driver of the second satellite model, and the third controller controls the rotating speed of the second motor of the second satellite model through the second driver of the second satellite model.

In a possible implementation manner, each of the first satellite model and the second satellite model further includes an adjustment limiting mechanism, the adjustment limiting mechanism includes a concentric axle, an eccentric axle, a first limiting wheel sleeved on the concentric axle, and a second limiting wheel sleeved on the eccentric axle, the concentric axle and the eccentric axle are both disposed on the sliding seat, and the first limiting wheel of the first satellite model and the second limiting wheel of the first satellite model respectively abut against an inner ring surface and an outer ring surface of the first track; and the first limiting wheel of the second satellite model and the second limiting wheel of the second satellite model respectively abut against the inner ring surface and the outer ring surface of the second orbit.

In a possible implementation manner, a first limiting groove is formed along each of the inner ring surface of the first rail and the inner ring surface of the second rail, and the first limiting wheel rolls along the first limiting groove;

second limiting grooves are formed in the outer ring surface of the first rail and the outer ring surface of the second rail, and the second limiting wheels roll along the second limiting grooves.

In a possible implementation mode, the first satellite model and the second satellite model further include a power taking device, the power taking device includes a current collector and a sliding contact line, the current collector is arranged on the lower side of the sliding seat, the first track and the lower surface of the second track are connected with a track switching frame, the sliding contact line is arranged on the inner wall of the track switching frame, and the current collector abuts against the sliding contact line.

In a possible implementation manner, a plurality of support frames are arranged on the inner wall of the rail transit frame, a clamping groove is formed in the inner side of each support frame, and the sliding contact line is clamped in the clamping groove.

In a possible implementation manner, the globe further comprises a laser transmitter, the laser transmitter is arranged on the sliding seat, and laser emitted by the laser transmitter faces the globe.

In one possible embodiment, the laser emitter is a laser pointer.

In a possible embodiment, the device further comprises a camera, and the camera is arranged on the sliding seat.

In a possible implementation manner, the rack comprises an inner rack and an outer rack, the outer rack is connected to the outer side of the inner rack, the self-rotation driving device is arranged inside the inner rack, the first rail is obliquely arranged at the top end of the inner rack, and the second rail is horizontally arranged at the top end of the outer rack; or the first rail is horizontally arranged at the top end of the inner frame, and the second rail is obliquely arranged at the top end of the outer frame.

In a possible embodiment, the bottom of the inner frame and the outer frame are provided with a plurality of foot cups and a plurality of foot wheels.

The utility model provides a geosynchronous orbit satellite display system, because the frame bottom has set up a plurality of foot cup and a plurality of truckle, therefore can easily remove on needs remove, when needs are static, can remain stable placing effect again.

The utility model provides a geosynchronous orbit satellite display system, owing to set up laser emitter, laser emitter sends is right the globe carries out the part and shines, therefore first satellite model with when second satellite model simulation satellite carried out revolution motion, can draw and demonstrate the orbit audio-visual of star lower point, the difference of the horizontal orbit of the popular contrast of being convenient for and the synchronous satellite motion of slope track, think the effect and the meaning of different orbit satellites, consequently the utility model discloses can play fine science popularization effect.

The utility model discloses still include the camera, shoot in real time first satellite model with picture when second satellite model simulation satellite carries out revolution motion shows satellite system's full appearance comprehensively.

The utility model provides a first satellite model with among the second satellite model, through setting adjust stop gear, adjust stop gear and realized limiting displacement during the slide motion has ensured first satellite model with circular motion's stationarity is to the second satellite model to reduce frictional force.

In addition to the technical problems, technical features constituting technical solutions, and advantageous effects brought by the technical features of the technical solutions described above, other technical problems that can be solved by the geosynchronous orbit satellite display system provided by the embodiments of the present invention, other technical features included in the technical solutions, and advantageous effects brought by the technical features will be further described in detail in specific embodiments.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.

Fig. 1 is a front view of a geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 2 is a schematic control structure diagram of a geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 3 is a cross-sectional view of a first satellite simulation device or a second satellite simulation device of a geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 4 is a cross-sectional view of an adjusting and limiting mechanism of a geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 5 is a front view of an earth simulator of a display system for geosynchronous orbit satellites according to an embodiment of the present invention;

fig. 6 is an enlarged view of a lower half structure of the earth simulator of the geosynchronous orbit satellite display system according to the embodiment of the present invention;

fig. 7 is an enlarged view of the upper half structure of the earth simulator of the display system of geosynchronous orbit satellites according to the embodiment of the present invention;

fig. 8 is an assembly state diagram of a second satellite model of the first satellite model of the geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 9 is a schematic perspective view of a rack of a geosynchronous orbit satellite display system according to an embodiment of the present invention;

fig. 10 is a schematic partial structural view of an inner frame of a geosynchronous orbit satellite display system according to an embodiment of the present invention.

Description of reference numerals:

10-a frame;

11-an internal frame;

12-an external frame;

13-a foot cup;

131-cushion blocks;

14-a caster wheel;

15-a first track strut;

16-a second track strut;

20-earth simulating means;

21-table body;

211-a desktop;

212-a first strut;

213-a second strut;

214-lower plate of support;

215-pedestal upper plate;

216-a bearing seat;

217-a first bearing;

218-mounting holes;

219-a base plate;

22-a bracket;

23-a globe;

24-rotation driving means;

241-a first motor;

242 — a first reducer;

243-main shaft;

244-a first flange;

245-a coupling;

246-locating sleeve;

247-positioning pads;

248 — a first driver;

25-a tray;

26-table legs;

261-table leg;

30-a first satellite simulation device;

31-a first track;

311-outer gear ring;

312-a first retaining groove;

313-a second limit groove;

32-a first satellite model;

331-a second motor;

332-a gear;

333-a second reducer;

334-a second driver;

34-a slide seat;

341-connecting plate;

342-a housing;

343-windsurfing boards;

35-motor flange;

36-adjusting a limit mechanism;

361-concentric wheel axis;

362-eccentric axle;

363-a first spacing wheel;

364-a second limit wheel;

365-needle roller bearings;

37-a second satellite simulation device;

371 — a second track;

372-a second satellite model;

40-satellite simulation means;

50-a controller;

51-a first controller;

52-a second controller;

53-a third controller;

60-a laser emitter;

70-a camera;

71-a mobile terminal;

90-electricity taking device;

91-a current collector;

92-trolley line;

93-a track adapter rack;

931-a support frame;

932-card slot.

Detailed Description

To make the objects, technical solutions and advantages of the present invention clearer, the drawings of the present invention are combined to clearly and completely describe the technical solutions of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Geosynchronous satellite orbits can be divided into geostationary orbits, the motion trail of which is a circular orbit coincident with the equator and inclined geosynchronous orbits, the motion trail of which is not coincident with the equator, and no geosynchronous orbit satellite display system can visually display the difference between different satellite orbits and the relative motion relation with the earth and can not vividly draw the track of the intersatellite point of the geosynchronous satellite, wherein the intersatellite point refers to the projection point of the geosynchronous satellite on the ground or the intersection point of the connecting line of the satellite and the geocentric and the ground. The existing static aerospace popular exhibit model or image-text version has not ideal display effect, lacks interest and cannot catch the eyeball of the public.

In view of the above-mentioned background, the utility model provides a geosynchronous orbit satellite display system through the rotation motion of simulation earth and the revolution motion of satellite, presents a dynamic bandwagon effect to masses, and masses can directly see the difference between the different satellite orbit and with the relative motion relation of earth, can leave deep impression by masses, promote the rapid development of space science popularization cause.

The geosynchronous orbit satellite display system provided by the embodiments of the present invention is described below with reference to the accompanying drawings.

Referring to fig. 1 and 2, the present invention provides a geosynchronous orbit satellite display system, which includes: the earth simulator comprises a frame 10, an earth simulator 20, at least two satellite simulators 40 and a controller 50, wherein the earth simulator 20 is arranged on the frame 10, and the earth simulator 20 comprises a globe 23 and a rotation driving device 24 for driving the globe 23 to rotate horizontally; the satellite models of the at least two satellite simulation devices 40 all use the globe 23 as a revolution center, and the at least two satellite simulation devices 40 are located on the same plane or different planes; the controller 50 is configured to control the revolution period of the satellite models of the at least two satellite simulation devices to coincide with the rotation period of the globe 23.

The utility model provides a pair of geosynchronous orbit satellite display system, through the revolution of the rotation of simulation earth and satellite, dynamic display system, can show the interrelation of satellite and earth motion on the different orbits directly perceivedly, two kinds of orbit satellite operation modes of entity show geostationary orbit and slope synchronous orbit, the convenient basic knowledge to masses science popularization satellite system, the motion characteristics of satellite on the geostationary orbit and the synchronous slope orbit have been shown vividly, have fine science popularization and educational meaning, interest and appeal have been increased for the functional principle of show satellite system.

It is to be understood that the present embodiment provides a geosynchronous orbit satellite display system including at least two satellite simulation apparatuses 40.

In one possible embodiment, one of the at least two satellite simulation devices 40 is the first satellite simulation device 30 and the other one is the second satellite simulation device 37.

Of course, in another possible implementation, the geosynchronous orbit satellite display system may also include three or more satellite simulation devices 40, each of the plurality of satellite simulation devices 40 uses the globe 23 as a revolution center, and the plurality of satellite simulation devices 40 display different characteristics of the geosynchronous orbit satellite motion through orbits with different inclination angles. The number of the satellite simulation apparatuses 40 is not further limited here.

The first satellite simulation device 30 includes a first orbit 31 and a first satellite model 32, the first orbit 31 is set on the frame 10, the first satellite model 32 moves along the first orbit 31, and the first satellite model 32 uses the globe 23 as the revolution center; the second satellite simulation device 37 includes a second orbit 371 and a second satellite model 372, the second orbit 371 is arranged on the frame 10, the second satellite model 372 moves along the second orbit 371, and the second satellite model 372 uses the globe 23 as a revolution center, and the second orbit 371 is located on the same plane or different plane with the first orbit 31.

It is easy to understand that the second rail 371 is located on the same plane as the first rail 31, for example, the second rail 371 is located on the same horizontal plane or the same inclined plane as the first rail 31; the second rail 371 is located on a different plane from the first rail 31, and one of the second rail 371 and the first rail 31 may be located on a horizontal plane and the other may be located on an inclined plane, or the second rail 371 and the first rail 31 may be located on two different inclined planes, respectively.

The controller 50 is configured to control the revolution period of the first satellite model 32 and the second satellite model 372 to coincide with the rotation period of the globe 23.

The spinning cycle of the globe 23 is the time it takes for the globe 23 to rotate one turn. The revolution of the first satellite model 32 refers to the circular motion of the first satellite model 32 along the first orbit 31 with the globe 23 as the revolution center. The revolution period of the first satellite model 32 is the time taken for the first satellite model 32 to rotate one circle along the first orbit 31.

The revolution of the second satellite model 372 refers to the cyclic motion of the second satellite model 372 along the second orbit 371 with the globe 23 as the revolution center, and the revolution period of the second satellite model 372 is the time taken by the second satellite model 372 to rotate once along the second orbit 371.

Referring to fig. 1 and 3, the first orbit 31 and the second orbit 371 are each provided with an outer ring gear 311 on the outer periphery thereof, the first satellite model 32 and the second satellite model 372 each include a gear 332, and the gear 332 of the first satellite model 32 is engaged with the outer ring gear 311 provided on the outer periphery of the first orbit 31; the gear 332 of the second satellite model 372 is engaged with the outer ring gear 311 provided on the outer periphery of the second orbit 371.

Referring to fig. 1 and 3, each of the first satellite model 32 and the second satellite model 372 further includes a sliding base 34, a second motor 331, and a second driver 334 electrically connected to the second motor 331, the second motor 331 is disposed on the sliding base 34, an output shaft of the second motor 331 is connected to the gear 332 through a second reducer 333, and the second driver 334 is disposed on the sliding base 34. The second motor 331 is employed as a power source of the gear 332.

Referring to fig. 1 and 5, the rotation driving device 24 is disposed in the housing 10, the rotation driving device 24 includes a first motor 241 and a vertically disposed spindle 243, an output shaft of the first motor 241 is connected to a lower end of the spindle 243 through a first reducer 242, an upper end of the spindle 243 is provided with a tray 25, and the globe 23 is disposed in the tray 25.

The tray 25 can be welded at the upper end of the main shaft 243, the tray 25 can be of an arc-shaped structure and is matched with the globe 23, the globe 23 can be fixed in the tray 25 in a riveting mode, and the first speed reducer 242 is connected with the lower end of the main shaft 243 through the coupling 245.

Referring to fig. 2 and 5, the rotation driving device 24 further includes a first driver 248, and the first motor 241 is electrically connected to the first driver 248.

Referring to fig. 2 and 5, the controller 50 includes a first controller 51, a second controller 52, and a third controller 53, the first controller 51 being disposed on the rack 10, the second controller 52 being disposed on the first satellite simulation device 30, and the third controller 53 being disposed on the second satellite model 372; the first controller 51 is electrically connected to the first driver 248, and the first controller 51 controls the rotation speed of the first motor 241 through the first driver 248. The first controller 51 outputs Pulse Width Modulation (PWM) to the first driver 248, so that the first driver 248 controls the rotation speed of the first motor 241, thereby controlling the rotation period of the globe 23. The first controller 51 may be a single chip microcomputer.

Referring to fig. 2 and 3, the second controller 52 is electrically connected to the second driver 334 of the first satellite model 32, and the second controller 52 controls the rotation speed of the second motor 331 of the first satellite model 32 through the second driver 334 of the first satellite model 32. The second controller 52 outputs a PWM rotation speed command to the second driver 334 of the first satellite model 32, so that the second driver 334 controls the rotation speed of the corresponding second motor 331, thereby controlling the revolution period of the first satellite model 32.

The third controller 53 is electrically connected to the second driver 334 of the second satellite model 372, and the third controller 53 controls the rotation speed of the second motor 331 of the second satellite model 372 through the second driver 334 of the second satellite model 372. The third controller 53 outputs a PWM rotation speed command to the second driver 334 of the second satellite model 372, so that the second driver 334 controls the rotation speed of the corresponding second motor 331, thereby controlling the revolution period of the second satellite model 372.

The second controller 52 may be a single chip microcomputer, a program is preset on the single chip microcomputer, the second controller 52 performs Proportional-Integral-Derivative (PID) control on the rotation speed of the second motor 331 of the first satellite model 32, and when the rotation speed of the second motor 331 of the first satellite model 32 deviates from a target value, the second controller 52 may shift the rotation speed of the second motor 331 of the first satellite model 32 towards the target value until the target value is reached by adjusting a duty ratio output by PWM, so as to adjust the revolution period of the first satellite model 32.

The third controller 53 may be a single chip microcomputer, a program is preset on the single chip microcomputer, and the third controller 53 performs PID control on the rotation speed of the second motor 331 of the second satellite model 372.

When the rotation speed of the second motor 331 of the second satellite model 372 deviates from the target value, the third controller 53 may shift the rotation speed of the second motor 331 of the second satellite model 372 toward the target value by adjusting the duty ratio of the PWM output until the target value is reached, thereby adjusting the revolution period of the second satellite model 372. And controls the revolution periods of the first and second satellite models 32 and 372 to coincide with the rotation period of the globe 23.

The first orbit 31 and the second orbit 371 can be circular or elliptical, so as to visually represent the orbit of the actual motion of the satellite, thereby improving the display effect.

An output shaft of the second motor 331 is fixedly connected with the second speed reducer 333 through a bolt and a key slot, so that the second motor 331 and the second speed reducer 333 are connected into a whole, the second speed reducer 333 is connected with the motor flange 35 at the lower end of the sliding seat 34 through a bolt, the second motor 331 is connected above the second speed reducer 333, the output shaft of the second motor 331 is connected with an input shaft of the second speed reducer 333, the output shaft of the second speed reducer 333 extends downwards, and the gear 332 is connected with the lower end of the output shaft of the second speed reducer 333. The second driver 334 controls the corresponding second motor 331 to rotate at a set rotation speed, and transmits power to the gear 332 through the second reducer 333.

Referring to fig. 1 and 3, in the geosynchronous orbit satellite display system provided by this embodiment, the first satellite model 32 and the second satellite model 372 both realize smooth and accurate movement of the first satellite simulation device 30 and the second satellite simulation device 37 by adopting a manner that the gear 332 and the external gear ring 311 are engaged with each other, so as to simulate the revolving movement of the satellite around the earth. By processing the toothed ring 311 on the outer peripheries of the first rail 31 and the second rail 371, the volumes of the first rail 31 and the second rail 371 do not need to be increased, so that the overall structure is compact, and the cross-sectional areas of the first rail 31 and the second rail 371 are small.

Referring to fig. 4, each of the first satellite model 32 and the second satellite model 372 further includes an adjustment limiting mechanism 36, each of the adjustment limiting mechanisms 36 includes a concentric wheel shaft 361, an eccentric wheel shaft 362, a first limiting wheel 363 sleeved on the concentric wheel shaft 361, and a second limiting wheel 364 sleeved on the eccentric wheel shaft 362, each of the concentric wheel shaft 361 and the eccentric wheel shaft 362 is disposed on the sliding seat 34, and the first limiting wheel 363 of the first satellite model 32 and the second limiting wheel 364 of the first satellite model 32 respectively abut against an inner ring surface and an outer ring surface of the first orbit 31; and the first limiting wheel 363 of the second satellite model 372 and the second limiting wheel 364 of the second satellite model 372 abut against the inner circle surface and the outer circle surface of the second orbit 371 respectively. The structure realizes the limiting effect when the sliding seat 34 moves, ensures the smoothness of the movement of the first satellite model 32 and the second satellite model 372 and reduces the friction force.

The concentric wheel shaft 361 and the eccentric wheel shaft 362 are arranged through the upper surface and the lower surface of the sliding seat 34, the upper half sections of the concentric wheel shaft 361 and the eccentric wheel shaft 362 are connected in the sliding seat 34, nuts are connected to the upper ends of the concentric wheel shaft 361 and the eccentric wheel shaft 362 through threads, the concentric wheel shaft 361 and the eccentric wheel shaft 362 are fixed on the sliding seat 34, the lower half sections of the concentric wheel shaft 361 and the eccentric wheel shaft 362 extend downwards to the lower side of the sliding seat 34, and the distance between the first limiting wheel 363 and the second limiting wheel 364 can be adjusted and changed by adjusting the position of the eccentric wheel shaft 362.

Referring to fig. 1 and 4, when the first satellite model 32 is mounted on the first track 31, the distance between the first limiting wheel 363 and the second limiting wheel 364 is adjusted to be larger, the sliding seat 34 is mounted on the first track 31, and then the distance between the first limiting wheel 363 and the second limiting wheel 364 is adjusted to be smaller, so that the first limiting wheel 363 and the second limiting wheel 364 are respectively clamped on the inner side surface and the outer side surface of the first track 31, and the first satellite model 32 is ensured to make planar circular motion along the first track 31; similarly, when the second satellite model 372 is mounted on the second track 371, the distance between the first limiting wheel 363 and the second limiting wheel 364 is adjusted to be larger, the sliding base 34 is mounted on the second track 371, and then the distance between the first limiting wheel 363 and the second limiting wheel 364 is adjusted to be smaller, so that the first limiting wheel 363 and the second limiting wheel 364 are respectively clamped on the inner side surface and the outer side surface of the second track 371, and the second satellite model 372 is ensured to do planar circular motion along the second track 371.

Referring to fig. 4, the first limiting wheel 363 is sleeved on the lower half section of the concentric wheel shaft 361, a needle bearing 365 is disposed between the first limiting wheel 363 and the concentric wheel shaft 361, an inner ring of the needle bearing 365 is engaged with the lower half section of the concentric wheel shaft 361, and an outer ring of the needle bearing 365 is engaged with the first limiting wheel 363, so that the first limiting wheel 363 smoothly rotates relative to the concentric wheel shaft 361; the second limiting wheel 364 is sleeved on the lower half section of the eccentric shaft 362, a needle bearing 365 is also arranged between the second limiting wheel 364 and the eccentric shaft 362, the inner ring of the needle bearing 365 is matched with the lower half section of the eccentric shaft 362, and the outer ring of the needle bearing 365 is matched with the second limiting wheel 364, so that the second limiting wheel 364 smoothly rotates relative to the eccentric shaft 362. The structure can reduce the rolling friction resistance of the first limiting wheel 363 and the second limiting wheel 364, and is beneficial to the compact structure of the first limiting wheel 363 and the second limiting wheel 364.

It is easily understood that the upper half of the eccentric shaft 362 and the lower half of the eccentric shaft 362 are integrally connected and the axes are offset and misaligned from each other.

It will be readily appreciated that the axial positioning of the needle bearing 365 on the concentric axle 361 may employ a circlip as well as a shoulder on the concentric axle 361 and a step inside the first retainer 363. The axial positioning of the needle bearing 365 on the cam shaft 362 may employ a spring collar and a shoulder on the cam shaft 362, a step inside the second spacing wheel 364.

Referring to fig. 3 and 4, the inner ring surface of the first rail 31 and the inner ring surface of the second rail 371 are both provided with a first limiting groove 312, and the first limiting wheel 363 rolls along the first limiting groove 312; the outer ring surface of the first rail 31 and the outer ring surface of the second rail 371 are both provided with a second limiting groove 313, and the second limiting wheel 364 rolls along the second limiting groove 313. The first position-limiting groove 312 is matched with the structure of the first position-limiting wheel 363, and the second position-limiting groove 313 is matched with the structure of the second position-limiting wheel 364. By the first limiting wheel 363 rolling along the first limiting groove 312 and the second limiting wheel 364 rolling along the second limiting groove 313, when the first satellite model 32 and the second satellite model 372 realize revolution, the influence of the sliding seat 34 on the movement stability of the first satellite model 32 and the second satellite model 372 is avoided.

The adjustment limiting mechanisms 36 of the first satellite model 32 and the second satellite model 372 both adopt a concentric wheel shaft 361 and an eccentric wheel shaft 362, and the distance between the first limiting wheel 363 and the second limiting wheel 364 can be adjusted, so that the sliding base 34 can smoothly move on the first track 31 and the second track 371, and the resistance of the sliding base 34 in the movement process is reduced.

Referring to fig. 5 and 6, a table body 21 is arranged in the frame 10, the table body 21 includes a table top 211, table legs 26 and a bracket 22 connected below the table top 211, the table legs 26 are connected to the lower side of the table top 211 to support the table top 211, the bottom ends of the bracket 22 and the table legs 26 are both connected to a table foot 261, the table foot 261 connected to the bottom end of the bracket 22 and the lower end of the table foot 261 connected to the bottom end of the table legs 26 are in the same horizontal plane, and the table legs 26 are fixed inside the frame 10.

The legs 26 may be attached to the underside of the table top 211 by welding, and the feet 261 may be attached to the bottom end of the bracket 22 and the bottom ends of the legs 26 by welding.

The controller 50 is disposed on the frame 10, and the controller 50 may be disposed on a table top 211 of the table body 21, which is not shown in the figure.

Referring to fig. 5 and 6, the table top 211 is provided with three first struts 212 and three second struts 213, the three first struts 212 are uniformly distributed in a circle, the three second struts 213 are uniformly distributed in a circle, the three first struts 212 are located inside the three second struts 213, tops of the three first struts 212 are connected and fixed to the lower support plate 214 through bolts, tops of the three second struts 213 are connected and fixed to the upper support plate 215 through bolts, heights of the three second struts 213 are greater than those of the three first struts 212, so that the lower support plate 214 is located below the upper support plate 215, and the main shaft 243 extends upwards through a mounting hole 218 formed in the lower support plate 214 and a mounting hole 218 formed in the upper support plate 215.

In one possible embodiment, the table top 211 is connected to a bottom plate 219 by a plurality of screws, and the three first struts 212 and the three second struts 213 are all welded to the bottom plate 219 in an upright manner, and the bottom plate 219 has a circular ring shape.

Referring to fig. 6 and 7, a bearing seat 216 is fixed on the upper support plate 215 through a bolt and a nut, a bearing seat 216 is also fixed on the lower support plate 214 through a bolt and a nut, and a first bearing 217 sleeved on the main shaft 243 is arranged in the bearing seat 216, so that the main shaft 243 is supported for rotation through the two first bearings 217. The first bearing 217 may be a rolling bearing, an inner ring of the first bearing 217 and the main shaft 243 are sleeved on an outer circumference of the main shaft 243, and an outer ring of the first bearing 217 is arranged in the bearing seat 216.

The center of the table top 211 is fixed with a first flange 244 through a screw, the first reducer 242 is connected below the table top 211 through the first flange 244, the output shaft of the first motor 241 is connected with the input shaft of the first reducer 242, the output shaft of the first reducer 242 is connected to the lower end of the main shaft 243 through a coupling 245, the coupling 245 is located above the table top 211, a positioning pad 247 is arranged between the coupling 245 and the first flange 244, a positioning sleeve 246 is arranged between the coupling 245 and the lower support plate 214, and the coupling 245 is positioned through the positioning sleeve 246 and the positioning pad 247.

In a possible embodiment, the lower end of the main shaft 243 is keyed to the upper half of the coupling 245 by a key, and the output shaft of the first reducer 242 is keyed to the lower half of the coupling 245 by a key. The first reducer 242 is coupled to the first flange 244 by a plurality of screws.

Referring to fig. 2 and 6, the first driver 248 is electrically connected to the first motor 241, the first driver 248 is fixed to the frame 10, and the first controller 51 sends a command to the first driver 248, so that the first driver 248 controls the rotation speed of the corresponding first motor 241, thereby controlling the rotation period of the globe 23.

A PWM output pin of the first controller 51 is electrically connected to the first driver 248, and the PWM output function of the first controller 51 controls the rotation speed of the first motor 241. The first controller 51 performs PID control on the rotation speed of the first motor 241 through a preset program on the single chip microcomputer, and drives the main shaft 243 and the globe 23 to rotate, thereby realizing the simulation of the autorotation motion of the earth.

The bracket 22 is fixed below the tabletop 211 through bolt connection, the bracket 22 is supported at the bottom of the first motor 241, the first motor 241 drives the main shaft 243 to rotate, and the main shaft 243 drives the tray 25 arranged at the upper end of the main shaft 243 and the globe 23 arranged on the tray 25 to rotate, so that the rotation motion of the earth is simulated.

Referring to fig. 1 and 8, each of the first satellite model 32 and the second satellite model 372 further includes a power taking device 90, the power taking device 90 includes a current collector 91 and a trolley line 92, the current collector 91 is disposed on the lower side of the sliding seat 34, the lower surfaces of the first rail 31 and the second rail 371 are connected to a rail adapter 93, the trolley line 92 is disposed on the inner wall of the rail adapter 93, and the current collector 91 abuts against the trolley line 92. The electricity taking device 90 is small in occupied volume due to the structure.

In the present embodiment, the current collector 91 and the trolley line 92 are used for supplying power in a sliding contact manner, so that mobile power supply of the geosynchronous orbit satellite display system is realized, and compared with a form of supplying power by using a cable, the present embodiment can avoid the winding problem of the cable in the process of continuously performing revolution motion of the first satellite model 32 and the second satellite model 372.

The track adapter rack 93 is of an annular structure, the shape of the track adapter rack 93 is matched with the shapes of the corresponding first track 31 and the second track 371, the track adapter rack 93 can be connected to the lower surfaces of the first track 31 and the second track 371 through screws, the mounting position of the track adapter rack 93 can be adjusted, the pressing force of the current collector 91 against the sliding contact line 92 can be adjusted by adjusting the mounting position of the track adapter rack 93, and the electricity taking stability is kept. The rail adapter 93 serves to restrain and fix the trolley wire 92.

The underside of the carriage 34 has a connection plate 341 and the current collector 91 is disposed on the underside of the connection plate 341 of the carriage 34. The connection plate 341 is connected to the lower surface of the slider 34 by screws.

In order to stably arrange the trolley line 92 on the inner wall of the rail adapter frame 93, a plurality of support frames 931 are arranged on the inner ring surface of the rail adapter frame 93 at intervals through screws, the trolley line 92 is located in the support frames 931, the current collector 91 and the trolley line 92 are kept pressed tightly, and continuous and stable electricity taking is guaranteed.

In a possible embodiment, the inside of the supporting frame 931 is provided with a slot 932, and the sliding contact line 92 is clamped in the slot 932 on the inside surface of the supporting frame 931.

The first satellite model 32 and the second satellite model 372 each have an outer shell 342 on the outer side, the outer shell 342 is mounted on the outer side of the slide carriage 34, a sail 343 is connected to the upper and lower ends of the outer shell 342 by screws, and one end of the connecting plate 341 extends to the outer side of the outer shell 342. The housing 342 may be a rectangular structure formed by splicing several plates.

Referring to fig. 1 and 8, in one possible implementation manner, in order to show the motion state of the satellites relative to the earth and the characteristics of the track of the subsatellite point of the geostationary satellite to the public, so that the audience can visually know the characteristics of the geostationary satellite, the geostationary orbit satellite display system provided by the embodiment further comprises a laser transmitter 60, wherein the laser transmitter 60 is arranged on the slide base 34, and the laser emitted by the laser transmitter 60 faces the globe 23 to locally irradiate the globe 23.

In one possible embodiment, the laser emitter 60 is arranged on the connection plate 341 of the carriage 34, and the laser emitter 60 is a laser pointer.

In this embodiment, since the first orbit 31 of the first satellite simulation apparatus 30 is obliquely disposed, when the first satellite model 32 moves along the first orbit 31, the laser pen carried on the first satellite model 32 can draw the shape of the arabic numeral "8" on the surface of the globe 23; since the second orbit 371 of the second satellite simulation apparatus 37 is a horizontal orbit, when the second satellite model 372 moves along the second orbit 371, a light spot irradiated on the surface of the globe 23 by the laser pen mounted on the second satellite model 372 is stationary with respect to the globe 23.

In a possible implementation manner, the geosynchronous orbit satellite display system further comprises a camera 70, the camera 70 is arranged on the sliding seat 34, the camera 70 is connected with the mobile terminal 71 through Wireless Fidelity (Wi-Fi), the shot video pictures are transmitted to the mobile terminal 71, and the video pictures are played on a display of the mobile terminal 71 for comprehensive display.

The mobile terminal 71 may be a computer, a mobile phone or a tablet computer.

The mobile terminal 71 is connected with the first controller 51, the second controller 52 and the third controller 53 through bluetooth wireless communication, and the mobile terminal 71 is used for sending a rotating speed control instruction to the first controller 51, the second controller 52 and the third controller 53 and adjusting the duty ratio of the PWM output by each of the first controller 51, the second controller 52 and the third controller 53.

The mobile terminal 71 sends a rotation speed control command to the second controller 52 and the third controller 53 to ensure that the revolution periods of the first satellite model 32 and the second satellite model 372 are consistent with the rotation period of the globe 23. In one possible implementation, the difference between the revolution of the first satellite model 32 and the second satellite model 372 and the rotation angle of the globe 23 is identified by using an image recognition technology through the picture returned by the camera 70 on the first satellite model 32 and the picture returned by the camera 70 on the second satellite model 372, and then the feedback control is performed. By comparing the picture returned by the camera 70 when the first satellite model 32 rotates at the initial position and the picture returned by the camera 70 when the first satellite model rotates at the end position of the whole period, the difference between the pictures returned by the camera 70 is analyzed to know whether the first satellite model 32 advances or lags in the rotation, and then the mobile terminal 71 sends a rotating speed control command to the second controller 52. The second controller 52 controls the rotation speed of the second motor 331 of the first satellite model 32 to control the revolution period of the first satellite model 32 to be consistent with the rotation period of the globe 23.

Similarly, by comparing the frame returned by the camera 70 when the second satellite model 372 is at the initial position of rotation with the frame returned by the camera 70 when the second satellite model 372 is at the final position of the whole rotation period, the difference between the frames returned by the camera 70 is analyzed to determine whether the second satellite model 372 is leading or lagging during rotation, and then the mobile terminal 71 sends a rotation speed control command to the third controller 53. The third controller 53 controls the rotation speed of the second motor 331 of the second satellite model 372 to control the revolution period of the second satellite model 372 to be consistent with the rotation period of the globe 23.

Meanwhile, as shown in fig. 1 and 2, the computer calculates and feeds back the motion errors of the first satellite model 32 and the second satellite model 372 in real time through an image recognition function, and feeds back the velocity adjustment command to the controller 50, thereby controlling the motion velocities of the first satellite model 32 and the second satellite model 372.

Referring to fig. 1 and 8, the camera 70 is disposed on an end surface of the connecting plate 341 of the slide base 34 near the globe 23, so that the camera 70 can take a picture.

Get electric installation 90 for the power supply of second motor 331, laser emitter 60, and camera 70 power supply, realized that the motion of object on closed arc orbit and getting the electricity, realized that first satellite model 32 moves steadily and lasts the power supply along curved first orbit 31, also realized that second satellite model 372 moves steadily and lasts the power supply along curved second orbit 371, avoided adopting external power supply to supply power, prevent the electric wire winding problem that takes place of external power supply's electric wire when first satellite model 32 and the continuous circular motion of second satellite model 372.

The geosynchronous orbit satellite display system provided by the embodiment is assisted with a multimedia technology to display the movement mode of the geosynchronous orbit satellite, so that the overall appearance of the satellite system is comprehensively displayed.

Referring to fig. 1 and 9, in one possible embodiment, the housing 10 includes an inner frame 11 and an outer frame 12, the outer frame 12 is connected to the outside of the inner frame 11, a first rail 31 is obliquely disposed at the top end of the inner frame 11, a second rail 371 is horizontally disposed at the top end of the outer frame 12, a rotation driving device 24 is disposed inside the inner frame 11, and the table body 21 is located inside the inner frame 11. The interconnected structure of the inner frame 11 and the outer frame 12 not only enriches the display diversity, but also makes the structure more stable.

In this example, the first rail 31 is obliquely disposed at the top end of the inner frame 11, and the second rail 371 is horizontally disposed at the top end of the outer frame 12. Of course, in other examples, the first rail 31 may be horizontally disposed at the top end of the inner frame 11, and the second rail 371 may be obliquely disposed at the top end of the outer frame 12.

In a possible embodiment, the frame 10 is made of steel sections, the outer frame 12 is polygonal and the inner frame 11 is rectangular. The outer frame 12 is connected to the outer side of the inner frame 11 through a plurality of section steels, so that the frame 10 is of an integral structure and can play a role in stable support.

Of course, the outer frame 12 may have a circular or rectangular shape, and the inner frame 11 may have a polygonal or circular shape.

The upper end of the inner frame 11 is provided with a plurality of first track supporting rods 15 extending upwards, the plurality of first track supporting rods 15 are distributed at the corner positions of the upper end of the inner frame 11, the upper ends of the plurality of first track supporting rods 15 are positioned in the same inclined plane, and the first track 31 is arranged at the upper end of the first track supporting rods 15; the upper end of the outer frame 12 is provided with a plurality of second track supporting rods 16 extending upwards, the plurality of second track supporting rods 16 are distributed at the corner positions of the upper end of the outer frame 12, the upper ends of the plurality of second track supporting rods 16 are positioned on the same horizontal plane, the second track 371 is arranged at the upper ends of the plurality of second track supporting rods 16, the first track 31 is obliquely arranged, and the second track 371 is horizontally arranged.

Referring to fig. 9 and 10, in one possible embodiment, a plurality of first rail support bars 15 are obliquely disposed at the upper end of the inner frame 11, and a plurality of second rail support bars 16 are vertically disposed at the upper end of the outer frame 12.

In another possible implementation manner, the plurality of first rail support rods 15 may be vertically disposed at the upper end of the inner frame 11, and the heights of the plurality of first rail support rods 15 are different, so that the upper ends of the plurality of first rail support rods 15 are located in the same inclined plane, the plurality of second rail support rods 16 are vertically disposed at the upper end of the outer frame 12, and the heights of the plurality of second rail support rods 16 are the same, so that the upper ends of the plurality of second rail support rods 16 are located in the same horizontal plane.

It is easily understood that in another possible implementation manner, the upper ends of the plurality of first track supporting rods 15 may also be in the same horizontal plane, so that the first track 31 is horizontally arranged at the upper ends of the plurality of first track supporting rods 15; the upper ends of the plurality of second rail support rods 16 are located in the same inclined plane, so that the second rail 371 is obliquely arranged at the upper ends of the plurality of second rail support rods 16.

Referring to fig. 1 and 9, threaded holes are formed at the upper ends of the inner frame 11 and the outer frame 12 to facilitate the installation of the second rail brace 16 and the first rail brace 15 by means of a threaded connection.

The bottoms of the inner frame 11 and the outer frame 12 are provided with a plurality of foot cups 13 and a plurality of foot wheels 14. The casters 14 can be steered in any direction, so that the geostationary orbit satellite display system provided by the present embodiment not only can move freely, but also can provide stable support through a plurality of foot cups 13 when stationary.

In a possible implementation mode, a plurality of cushion blocks 131 are connected to the bottoms of the inner frame 11 and the outer frame 12, a plurality of foot cups 13 and a plurality of foot wheels 14 are arranged at the lower ends of the cushion blocks 131 at the bottom of the inner frame 11, and a plurality of foot cups 13 and a plurality of foot wheels 14 are arranged at the lower ends of the cushion blocks 131 at the bottom of the outer frame 12. The table leg 261 is fixed to the pad 131 connected to the bottom of the inner frame 11.

The bottoms of the inner frame 11 and the outer frame 12 can be connected with a plurality of cushion blocks 131 in a screw connection mode, the caster 14 is connected to the lower ends of the cushion blocks 131 through bolts, the foot cup 13 is connected to the lower ends of the cushion blocks 131 through threads, and the foot cup 13 can move up and down; when the geosynchronous orbit satellite display system provided by the embodiment is static, the foot cup 13 moves downwards and is supported on the ground, so that the placing stability is ensured.

The frame 10 is formed by welding standard section steel, which greatly reduces the number of parts to be machined. And the frame 10 has various reinforcing measures to improve the supporting rigidity.

In a possible embodiment, not shown, when the geostationary orbit satellite display system includes three or more satellite simulation devices 40, the frame 10 further includes one or more auxiliary frames connected to the outer side of the outer frame 12, and the auxiliary frames may have the same structure as the outer frame 12 or the inner frame 11 when supporting a third or more satellite simulation devices 40, respectively, but the size of the auxiliary frames is required to be larger than that of the outer frame 12 or the inner frame 11.

Referring to fig. 1 and 9, the present invention adopts the frame 10 as a whole, the frame 10 supports the earth simulator 20, the first satellite simulator 30 and the second satellite simulator 37 at the same time, and the structure of the frame 10 designed as an integrated structure makes the movement of the geosynchronous orbit satellite display system provided by the present embodiment more convenient.

The utility model discloses a compact structure, the cross sectional dimension of first track 31 and second track 371 is less, when showing first satellite model 32 and second satellite model 372 movement track and for first satellite model 32 and the power supply of second satellite model 372, has reduced sheltering from of first track 31 and second track 371 to globe 23, and the outward appearance is pleasing to the eye.

The utility model discloses a simulated earth rotation and satellite revolution, the special simulation has demonstrated satellite geostationary orbit and synchronous inclined orbit to the revolution cycle through guaranteeing first satellite model 32 and second satellite model 372 is unanimous with the rotation cycle of globe 23, and then the simulation shows the earth-surrounding motion state of geostationary orbit satellite, and the motion characteristics of satellite on the earth geostationary orbit and the synchronous inclined orbit have been demonstrated vividly, have fine science popularization and educational significance.

The utility model discloses a set up laser emitter 60, demonstrate the intersatellite point orbit of geostationary orbit satellite, pass back the video picture through setting up camera 70, demonstrate the motion characteristics of the relative earth of geostationary orbit satellite, the difference of the masses' contrast horizontal orbit of being convenient for and the geostationary orbit motion of slope, think the effect and the meaning of different orbit satellites, consequently the utility model discloses can play fine science popularization effect.

It should be noted that the numerical values and numerical ranges referred to in this application are approximate values, and there may be some error due to the manufacturing process, and the error may be considered to be negligible by those skilled in the art.

In the description of the present invention, it is to be understood that the terms "center", "length", "width", "thickness", "top", "bottom", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "inner", "outer", "axial", "circumferential", and the like, which are used to indicate the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of the description, and do not indicate or imply that the position or element referred to must have a particular orientation, be of particular construction and operation, and therefore should not 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 at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; either directly or indirectly through intervening media, such as through internal communication or through an interaction between two elements. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

Finally, it should be noted that: 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 or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.

Claims (14)

1. A geosynchronous orbit satellite display system, comprising:

a frame (10);

the earth simulator (20), the earth simulator (20) is arranged on the frame (10), the earth simulator (20) comprises a globe (23) and a rotation driving device (24) for driving the globe (23) to rotate horizontally;

at least two satellite simulation devices (40), wherein the satellite models of the at least two satellite simulation devices (40) take the globe (23) as a revolution center;

a controller (50), wherein the controller (50) is used for controlling the revolution period of the satellite models of the at least two satellite simulation devices to be consistent with the rotation period of the globe (23).

2. A geosynchronous orbit satellite display system according to claim 1, wherein one of the at least two satellite simulation devices (40) is a first satellite simulation device (30) and the other is a second satellite simulation device (37);

the first satellite simulation device (30) comprises a first orbit (31) and a first satellite model (32), the first orbit (31) is arranged on the frame (10), the first satellite model (32) moves along the first orbit (31), and the first satellite model (32) takes the globe (23) as a revolution center;

the second satellite simulation device (37) comprises a second orbit (371) and a second satellite model (372), the second orbit (371) is arranged on the frame (10), the second satellite model (372) moves along the second orbit (371), the second satellite model (372) takes the globe (23) as a revolution center, and the second orbit (371) and the first orbit (31) are positioned on the same plane or different planes;

the controller (50) is used for controlling the revolution period of the first satellite model (32) and the second satellite model (372) to be consistent with the rotation period of the globe (23).

3. The geosynchronous orbit satellite display system of claim 2, wherein the first orbit (31) and the second orbit (371) each have an outer gear ring (311) disposed on their outer periphery, the first satellite model (32) and the second satellite model (372) each comprise a gear (332), the gear (332) of the first satellite model (32) intermeshes with the outer gear ring (311) disposed on the outer periphery of the first orbit (31); the gear (332) of the second satellite model (372) is engaged with an outer ring gear (311) provided on the outer periphery of the second orbit (371).

4. The geosynchronous orbit satellite display system of claim 3, wherein the first satellite model (32) and the second satellite model (372) each further comprise a slide (34), a second motor (331), and a second driver (334) electrically connected to the second motor (331), the second motor (331) being disposed on the slide (34), an output shaft of the second motor (331) being connected to the gear (332) through a second reducer (333), the second driver (334) being disposed on the slide (34).

5. The geosynchronous orbit satellite display system of claim 4, wherein the autorotation drive mechanism (24) is disposed within the frame (10), the autorotation drive mechanism (24) comprises a first motor (241), a first driver (248) and a vertically disposed spindle (243), an output shaft of the first motor (241) is connected to a lower end of the spindle (243), a tray (25) is disposed at an upper end of the spindle (243), the globe (23) is disposed within the tray (25), and the first driver (248) is electrically connected to the first motor (241).

6. The geosynchronous orbit satellite presentation system of claim 5, wherein the controller (50) comprises a first controller (51), a second controller (52) and a third controller (53), the first controller (51) being disposed on the gantry (10), the second controller (52) being disposed on the first satellite simulation apparatus (30), the third controller (53) being disposed on the second satellite model (372);

the first controller (51) is electrically connected with the first driver (248), and the first controller (51) controls the rotating speed of the first motor (241) through the first driver (248);

the second controller (52) is electrically connected with the second driver (334) of the first satellite model (32), and the second controller (52) controls the rotating speed of the second motor (331) of the first satellite model (32) through the second driver (334) of the first satellite model (32);

the third controller (53) is electrically connected with the second driver (334) of the second satellite model (372), and the third controller (53) controls the rotating speed of the second motor (331) of the second satellite model (372) through the second driver (334) of the second satellite model (372).

7. The geosynchronous orbit satellite display system of any of claims 4-6, wherein the first satellite model (32) and the second satellite model (372) further each comprise an adjustment limiting mechanism (36), the adjustment limiting mechanism (36) comprises a concentric axle (361), an eccentric axle (362), a first limiting wheel (363) sleeved on the concentric axle (361), and a second limiting wheel (364) sleeved on the eccentric axle (362), the concentric axle (361) and the eccentric axle (362) are both disposed on the slide base (34), the first limiting wheel (363) of the first satellite model (32) and the second limiting wheel (364) of the first satellite model (32) respectively abut against an inner circle surface and an outer circle surface of the first orbit (31); and

the first limiting wheel (363) of the second satellite model (372) and the second limiting wheel (364) of the second satellite model (372) respectively abut against the inner ring surface and the outer ring surface of the second orbit (371).

8. The geosynchronous orbit satellite display system of claim 7, wherein the inner race of the first orbit (31) and the inner race of the second orbit (371) are each provided with a first limiting groove (312) along their edges, and the first limiting wheel (363) rolls along the first limiting groove (312);

and second limiting grooves (313) are formed in the outer ring surface of the first rail (31) and the outer ring surface of the second rail (371), and the second limiting wheels (364) roll along the second limiting grooves (313).

9. The geosynchronous orbit satellite display system of claim 7, wherein the first satellite model (32) and the second satellite model (372) further each comprise a power taking device (90), the power taking device (90) comprises a current collector (91) and a trolley line (92), the current collector (91) is disposed at the lower side of the slide carriage (34), the lower surfaces of the first orbit (31) and the second orbit (371) are both connected with an orbit adapter frame (93), the trolley line (92) is disposed on the inner wall of the orbit adapter frame (93), and the current collector (91) abuts against the trolley line (92).

10. The geosynchronous orbit satellite display system of claim 9, wherein the inner wall of the orbit adapter rack (93) is provided with a plurality of supporting racks (931), the inner side of each supporting rack (931) is provided with a clamping groove (932), and the trolley line (92) is clamped in the clamping groove (932).

11. A geosynchronous orbit satellite display system according to any of claims 4-6, further comprising a laser transmitter (60), wherein the laser transmitter (60) is disposed on the slide (34) and wherein the laser emitted by the laser transmitter (60) is directed towards the globe (23).

12. A geosynchronous orbit satellite display system according to any of claims 4-6, further comprising a camera (70), wherein the camera (70) is disposed on the carriage (34).

13. The geostationary orbit satellite display system of any one of claims 2 to 6, wherein the frame (10) comprises an inner frame (11) and an outer frame (12), the outer frame (12) is connected to the outside of the inner frame (11), the rotation driving means (24) is provided inside the inner frame (11), the first orbit (31) is provided obliquely at the top end of the inner frame (11), and the second orbit (371) is provided horizontally at the top end of the outer frame (12); or

The first rail (31) is horizontally arranged at the top end of the inner frame (11), and the second rail (371) is obliquely arranged at the top end of the outer frame (12).

14. Geostationary orbit satellite display system according to claim 13, characterised in that the bottom of the inner frame (11) and the outer frame (12) are each provided with a number of foot cups (13) and a number of foot wheels (14).

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