CN107741334B - Microgravity large-scale folding and unfolding antenna test device - Google Patents
Microgravity large-scale folding and unfolding antenna test device Download PDFInfo
- Publication number
- CN107741334B CN107741334B CN201710991108.5A CN201710991108A CN107741334B CN 107741334 B CN107741334 B CN 107741334B CN 201710991108 A CN201710991108 A CN 201710991108A CN 107741334 B CN107741334 B CN 107741334B
- Authority
- CN
- China
- Prior art keywords
- guide rail
- pulley
- steel wire
- driving
- wire rope
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 31
- 230000005486 microgravity Effects 0.000 title claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims abstract description 62
- 230000001360 synchronised effect Effects 0.000 claims abstract description 22
- 229910000831 Steel Inorganic materials 0.000 claims description 72
- 239000010959 steel Substances 0.000 claims description 72
- 238000004804 winding Methods 0.000 claims description 36
- 238000009434 installation Methods 0.000 claims description 9
- 238000013461 design Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 14
- 230000005484 gravity Effects 0.000 description 3
- 238000011981 development test Methods 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Transmission Devices (AREA)
Abstract
The invention provides a microgravity large-scale folding and unfolding antenna test device, wherein a round guide rail is fixedly arranged under a cross beam by utilizing an adjusting bolt and an adjusting sleeve, a linear guide rail is fixed under the round guide rail through the adjusting bolt, one end of the linear guide rail is provided with a limiting block, the other end of the linear guide rail is provided with a counterweight pulley, two linear sliders are arranged on the linear guide rail in a front-back mode, and an encoder assembly, a driving pulley bracket, a pressure sensor assembly and a driving mechanism are arranged on a mounting plane at the lower part of a driving mechanism mounting plate. A coder swing arm is arranged on the coder assembly mounting shaft; the driving pulley is arranged below the driving pulley support, two groups of driving mechanism pull rods are fixedly arranged on the synchronous belt through one section of bolt connection from two groups of movable synchronous pulley components and two groups of synchronous belt mounting mechanisms, and the other ends of the driving mechanism pull rods are connected with the height adjusting block. The invention has reasonable structural design and good operation quality, and the operation is reliable, thereby meeting the requirement of the microgravity folding and unfolding test of the large-scale antenna.
Description
Technical Field
The invention relates to the field of space machinery, in particular to a microgravity large-scale folding and unfolding antenna test device.
Background
In the research and development process of aerospace products in China, the folding and unfolding test process of a large antenna is a basic indispensable test content. Because the spacecraft in the space is in a weightless state during orbital operation, whether the developed large antenna can be smoothly developed in space is an important factor for researching the reliability of the antenna structure, so that a certain development test needs to be carried out on the large antenna on the ground, and the microgravity state of the antenna in the space orbital environment is better simulated and called as a test. Meanwhile, the unfolding motion track of the satellite antenna is also an important factor considered by the experimental ground support equipment. At present, large-scale antenna unfolding test equipment with a complex structure is scarce, and an air-floating type unfolding test device is usually selected to carry out microgravity test on the unfolding of some small-sized antennas. Meanwhile, the air-floating type unfolding test device has certain limitations, is inconvenient to move and low in precision, and is not suitable for being applied to a large-scale antenna unfolding test process. Therefore, no description or report of the large-scale antenna folding technology similar to that of the present invention is found, and no similar domestic data is collected.
Disclosure of Invention
The invention provides a microgravity large-scale folding and unfolding antenna test device for solving the problems in the prior art, which is used for solving the defect that the prior art lacks a corresponding large-scale folding and unfolding antenna test device and solving the problem that a large-scale satellite antenna simulates the microgravity state of an environmental orbit in a ground gravity environment. The device has reasonable structural design, good operation quality and reliable operation, and meets the requirement of a microgravity folding and unfolding test of a large antenna.
The device comprises a cross beam, a round guide rail, a linear guide rail, an adjusting bolt, an adjusting sleeve, a height adjusting block, a linear sliding block, a driven synchronous pulley component, a fixing bolt, a driven synchronous pulley, a limiting block, an encoder component, a driving pulley bracket, a driving pulley, an encoder swing arm, a pressure sensor component, a driving steel wire winding wheel, a driving mechanism, an antenna, a driven movable pulley, a driven sliding block, a sliding bearing, a driving mechanism mounting plate, a driving mechanism pull rod, a synchronous belt driving mechanism, a counterweight pulley, a counterweight block, a synchronous belt mounting mechanism, a synchronous belt and a steel wire rope.
The circular guide rail is fixedly arranged right below the cross beam by utilizing a plurality of groups of adjusting bolts and adjusting sleeves, the linear guide rail is fixed below the circular guide rail through the adjusting bolts, an arc structure matched with the circular guide rail is designed on the upper surface of the linear guide rail so as to better ensure the stability of the structure, one end of the linear guide rail is provided with a limiting block, and the other end of the linear guide rail is provided with a counterweight pulley so as to better play a role in limiting and guiding a steel wire rope; the front and back parts of the two linear sliding blocks are arranged on the linear guide rail, the height adjusting block is arranged below the linear sliding blocks, the driving mechanism mounting plate is arranged below the height adjusting block, and the encoder assembly, the driving pulley support, the pressure sensor assembly and the driving mechanism are arranged on the mounting plane on the lower part of the driving mechanism mounting plate. A coder swing arm is arranged on the coder assembly mounting shaft, a round hole with the diameter of 2 mm is formed in the coder swing arm, and the first steel wire rope penetrates through the round hole; a driving pulley is arranged below the driving pulley support, a driving steel wire winding wheel is arranged at the front end of the driving mechanism, a corresponding U-shaped steel wire rope groove with the width of 1.5 mm is formed in the driving steel wire winding wheel, the structural design with the width of 1.5 mm is mainly used for reducing the vibration impact of the steel wire rope in the winding process, one end of a first steel wire rope is fixed on the driving steel wire winding wheel and is wound for a required length, then the first steel wire rope winds a pulley below the pressure sensor assembly, winds the driving pulley, penetrates through the swing arm of the encoder again, and is connected to a mounting hole in the antenna at the end part; 4 sliding bearings are fixedly arranged on the driven sliding block, in order to better reduce the friction force of horizontal movement, the outer surfaces of the 4 sliding bearings are tangent to the outer surface of the round guide rail, in order to avoid the influence of the gravity of the antenna and the movement process of the driven sliding block caused by the counterweight block, two groups of pulleys are arranged on the driven sliding block, a driven movable pulley is arranged under the driven sliding block in a hoisting mode through a second steel wire rope, a third steel wire rope is arranged under the driven movable pulley, the other end of the third steel wire rope is fixed with the installation position of the antenna, one end of the second steel wire rope is connected to the counterweight block, the driven sliding block and the driven movable pulley are bypassed after bypassing the counterweight pulley, and the other end of the second steel wire rope; two sets of driven hold-in range wheel subassemblies and two sets of hold-in range installation mechanisms pass through fixing bolt to be fixed on the crossbeam upper surface, and two sets of hold-in range actuating mechanism respectively with hold-in range installation mechanism fixed connection together, two sets of actuating mechanism pull rods pass through bolted connection, one end fixed mounting on the hold-in range, the other end links together with the height adjustment piece, and then drives hold-in range work through hold-in range actuating mechanism.
Preferably, the mounting distance between the two pulley blocks mounted on the driven sliding block is equal to the diameter of the U-shaped groove structure on the driven movable pulley, so that the third steel wire rope wound by the driven movable pulley is ensured to be parallel, and the motion stability of the mechanism is better ensured.
Preferably, the driving steel wire winding wheel is provided with a U-shaped groove with the width of 1.5 mm, so that the driving steel wire winding wheel can keep each circle of steel wires overlapped continuously in the process of winding the first steel wire rope with the diameter of 1 mm without staggering, the vibration of the structure is reduced better, and the unfolding stability of the antenna is improved.
Preferably, the counterweight block is fixed on the limiting block by passing through the second steel wire rope, passing through the two-stage pulley, passing through the passive movable pulley, and passing through the pulley on the passive sliding block again.
Preferably, the multiple groups of adjusting bolts are in threaded connection with the adjusting sleeve, and the structures are designed to better ensure that the circular guide rail and the linear guide rail can be kept in a horizontal position, so that the normal movement of the whole device is not influenced.
Preferably, the pressure sensor assembly needs to maintain a certain pre-pressure, so that the change of the pressure value in the working process can more accurately control the forward and reverse rotation of the driving mechanism, so as to realize the winding and releasing of the first steel wire rope, and better assist the antenna folding and unfolding test.
The invention has the beneficial effects that:
1. the folding and unfolding test of the large antenna is realized, and the purpose of the microgravity folding and unfolding test of the large antenna is realized.
2. The invention meets the requirement of simulating the microgravity state of the orbit environment required by the development test of the large-scale antenna on the ground, and has great significance for the microgravity test of important space equipment such as spacecrafts, space manipulators, antennas and the like.
3. The structure has reasonable design, good operation quality, reliable operation and high generalization degree, and completely meets the requirement of the microgravity folding and unfolding test of the large-scale antenna.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is an isometric view of the present invention;
fig. 3 is a schematic diagram of the active suspension point structure of the present invention.
The reference numbers in the figures: 1-beam, 2-round guide rail, 3-linear guide rail, 4-adjusting bolt, 5-adjusting sleeve, 6-height adjusting block, 7-linear slide block, 8-driven synchronous pulley component, 9-fixing bolt, 10-driven synchronous pulley, 11-limiting block, 12-encoder component, 13-driving pulley bracket, 14-driving pulley, 15-encoder swing arm, 16-pressure sensor component, 17-driving steel wire winding wheel, 18-driving mechanism, 19-antenna, 20-driven movable pulley, 21-driven slide block, 22-sliding bearing, 23-driving mechanism mounting plate, 24-driving mechanism pull rod, 25-synchronous belt driving mechanism, 26-counterweight pulley, 27-counterweight block, 27-height adjusting block, 28-synchronous belt mounting mechanism, 29-synchronous belt and 30-steel wire rope.
Detailed Description
The invention will be further explained with reference to the drawings.
The invention provides a micro-gravity large-scale folded and unfolded antenna test device which is structurally shown in figures 1, 2 and 3 and comprises a cross beam 1, a round guide rail 2, a linear guide rail 3, an adjusting bolt 4, an adjusting sleeve 5, a height adjusting block 6, a linear sliding block 7, a driven synchronous pulley component 8, a fixing bolt 9, a driven synchronous pulley 10, a limiting block 11, an encoder component 12, a driving pulley support 13, a driving pulley 14, an encoder swing arm 15, a pressure sensor component 16, a driving steel wire winding wheel 17, a driving mechanism 18, an antenna 19, a driven movable pulley 20, a driven sliding block 21, a sliding bearing 22, a driving mechanism mounting plate 23, a driving mechanism pull rod 24, a synchronous belt driving mechanism 25, a counterweight pulley 26, a counterweight block 27, a synchronous belt mounting mechanism 28, a synchronous belt 29 and a steel wire rope 30.
The circular guide rail 2 is fixedly arranged right below the cross beam 1 by utilizing a plurality of groups of adjusting bolts 4 and adjusting sleeves 5, the linear guide rail 3 is fixed below the circular guide rail 2 through the adjusting bolts 4, one end of the linear guide rail 3 is provided with a limiting block 11, and the other end of the linear guide rail 3 is provided with a counterweight pulley 26, so that the effects of limiting and guiding a steel wire rope are better achieved; the two linear sliders 7 are arranged on the linear guide rail 3 in a front-back mode, the height adjusting block 6 is arranged below the linear sliders 7, the driving mechanism mounting plate 23 is arranged below the height adjusting block 6, and the encoder assembly 12, the driving pulley support 13, the pressure sensor assembly 16 and the driving mechanism 18 are arranged on the mounting plane below the driving mechanism mounting plate 23. An encoder swing arm 15 is arranged on the mounting shaft of the encoder component 12, a round hole with the diameter of 2 mm is formed in the encoder swing arm 15, and a first steel wire rope penetrates through the round hole; a driving pulley 14 is mounted below the driving pulley bracket 13, a driving steel wire winding wheel 17 is mounted at the front end of the driving mechanism 18, a corresponding U-shaped steel wire rope groove with the width of 1.5 mm is formed in the driving steel wire winding wheel 17, the structural design with the width of 1.5 mm is mainly used for reducing the vibration impact of the steel wire rope in the winding process, one end of a first steel wire rope is fixed on the driving steel wire winding wheel 17 and is wound for a required length, then the first steel wire rope winds a pulley below the pressure sensor assembly 16, then winds the driving pulley 14, passes through the encoder swing arm 15 again, and is connected to a mounting hole in the antenna 19 at the end part; the sliding bearing 22 is fixedly installed on the passive sliding block 21, and in order to avoid the influence of the gravity of the antenna and the movement process of the passive sliding block 21 caused by the counterweight block 27, two groups of pulleys are installed on the passive sliding block 21, the passive movable pulley 20 is hung under the passive movable pulley through a second steel wire rope, a third steel wire rope is installed under the passive movable pulley 20, the other end of the third steel wire rope is fixed with the installation position of the antenna 19, meanwhile, one end of the second steel wire rope is connected to the counterweight block 27, bypasses the passive sliding block 21 and the passive movable pulley 20 after bypassing the counterweight pulley 26, and the other end of the third steel wire rope is fixed on the limiting block 11, so as to better; two sets of driven synchronous pulley subassemblies 8 and two sets of hold-in range installation mechanisms 28 pass through fixing bolt 9 to be fixed at crossbeam 1 upper surface, and two sets of hold-in range actuating mechanism 25 respectively with hold-in range installation mechanism 28 fixed connection together, two sets of actuating mechanism pull rods 24 pass through bolted connection, one end fixed mounting on hold-in range 29, the other end links together with height adjusting block 6, and then drives hold-in range 29 work through hold-in range actuating mechanism 25.
On the basis, the invention has the following specific embodiments:
example 1
The mounting distance of the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so that the third steel wire rope wound by the passive movable pulley 20 is ensured to be parallel, and the motion stability of the mechanism is better ensured.
Example 2
Preferably, the mounting distance between the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so as to ensure that the third steel wire rope wound around the passive movable pulley 20 is parallel, and better ensure the motion stability of the mechanism.
Preferably, the driving wire winding wheel 17 is provided with a U-shaped groove with a width of 1.5 mm, so that it is better ensured that the driving wire winding wheel 17 can continuously keep each circle of steel wires overlapped without staggering during the process of winding the first steel wire rope with a diameter of 1 mm, thereby better reducing the vibration of the structure and improving the stability of the antenna deployment.
Example 3
Preferably, the mounting distance between the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so as to ensure that the third steel wire rope wound around the passive movable pulley 20 is parallel, and better ensure the motion stability of the mechanism.
Preferably, the driving wire winding wheel 17 is provided with a U-shaped groove with a width of 1.5 mm, so that it is better ensured that the driving wire winding wheel 17 can continuously keep each circle of steel wires overlapped without staggering during the process of winding the first steel wire rope with a diameter of 1 mm, thereby better reducing the vibration of the structure and improving the stability of the antenna deployment.
Preferably, the upper surface of the linear guide rail 3 is designed with an arc structure matched with the circular guide rail 2.
Example 4
Preferably, the mounting distance between the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so as to ensure that the third steel wire rope wound around the passive movable pulley 20 is parallel, and better ensure the motion stability of the mechanism.
Preferably, the driving wire winding wheel 17 is provided with a U-shaped groove with a width of 1.5 mm, so that it is better ensured that the driving wire winding wheel 17 can continuously keep each circle of steel wires overlapped without staggering during the process of winding the first steel wire rope with a diameter of 1 mm, thereby better reducing the vibration of the structure and improving the stability of the antenna deployment.
Preferably, the upper surface of the linear guide rail 3 is designed with an arc structure matched with the circular guide rail 2.
Preferably, the multiple sets of adjusting bolts 4 are in screw connection with the adjusting sleeve 5, and the structure is to better ensure that the circular guide rail 2 and the linear guide rail 3 can be kept in a horizontal position, so that the normal movement of the whole device is not affected.
Example 5
Preferably, the mounting distance between the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so as to ensure that the third steel wire rope wound around the passive movable pulley 20 is parallel, and better ensure the motion stability of the mechanism.
Preferably, the driving wire winding wheel 17 is provided with a U-shaped groove with a width of 1.5 mm, so that it is better ensured that the driving wire winding wheel 17 can continuously keep each circle of steel wires overlapped without staggering during the process of winding the first steel wire rope with a diameter of 1 mm, thereby better reducing the vibration of the structure and improving the stability of the antenna deployment.
Preferably, the upper surface of the linear guide rail 3 is designed with an arc structure matched with the circular guide rail 2.
Preferably, the multiple sets of adjusting bolts 4 are in screw connection with the adjusting sleeve 5, and the structure is to better ensure that the circular guide rail 2 and the linear guide rail 3 can be kept in a horizontal position, so that the normal movement of the whole device is not affected.
Preferably, the pressure sensor assembly 16 needs to maintain a certain pre-pressure, so that the change of the pressure value during the operation can more accurately control the forward and reverse rotation of the driving mechanism 18, so as to realize the winding and releasing of the first steel wire rope, and better assist the performance of the folding and unfolding test of the antenna 19.
Example 6
Preferably, the mounting distance between the two pulley blocks mounted on the passive sliding block 21 is equal to the diameter of the U-shaped groove structure on the passive movable pulley 20, so as to ensure that the third steel wire rope wound around the passive movable pulley 20 is parallel, and better ensure the motion stability of the mechanism.
Preferably, the driving wire winding wheel 17 is provided with a U-shaped groove with a width of 1.5 mm, so that it is better ensured that the driving wire winding wheel 17 can continuously keep each circle of steel wires overlapped without staggering during the process of winding the first steel wire rope with a diameter of 1 mm, thereby better reducing the vibration of the structure and improving the stability of the antenna deployment.
Preferably, the upper surface of the linear guide rail 3 is designed with an arc structure matched with the circular guide rail 2.
Preferably, the multiple sets of adjusting bolts 4 are in screw connection with the adjusting sleeve 5, and the structure is to better ensure that the circular guide rail 2 and the linear guide rail 3 can be kept in a horizontal position, so that the normal movement of the whole device is not affected.
Preferably, the pressure sensor assembly 16 needs to maintain a certain pre-pressure, so that the change of the pressure value during the operation can more accurately control the forward and reverse rotation of the driving mechanism 18, so as to realize the winding and releasing of the first steel wire rope, and better assist the performance of the folding and unfolding test of the antenna 19.
Preferably, the outer surface of the sliding bearing 22 is tangent to the outer surface of the circular guide rail 2.
While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (7)
1. The utility model provides a large-scale exhibition antenna test device that rolls over of microgravity which characterized in that: comprises a beam (1), a round guide rail (2), a linear guide rail (3), an adjusting bolt (4), an adjusting sleeve (5), a height adjusting block (6), a linear slider (7), a driven synchronous pulley component (8), a fixing bolt (9), a driven synchronous pulley (10), a limiting block (11), an encoder component (12), a driving pulley bracket (13), a driving pulley (14) and an encoder swing arm (15), the device comprises a pressure sensor assembly (16), a driving steel wire winding wheel (17), a driving mechanism (18), an antenna (19), a driven movable pulley (20), a driven sliding block (21), a sliding bearing (22), a driving mechanism mounting plate (23), a driving mechanism pull rod (24), a synchronous belt driving mechanism (25), a counterweight pulley (26), a counterweight block (27), a synchronous belt mounting mechanism (28), a synchronous belt (29) and a steel wire rope; the circular guide rail (2) is fixedly arranged under the cross beam (1) by utilizing a plurality of groups of adjusting bolts (4) and adjusting sleeves (5), the linear guide rail (3) is fixed under the circular guide rail (2) through the adjusting bolts (4), one end of the linear guide rail (3) is provided with a limiting block (11), and the other end of the linear guide rail is provided with a counterweight pulley (26); the two linear sliding blocks (7) are arranged on the linear guide rail (3) in a front-back mode, a height adjusting block (6) is arranged below each linear sliding block (7), a driving mechanism mounting plate (23) is arranged below each height adjusting block (6), and an encoder assembly (12), a driving pulley bracket (13), a pressure sensor assembly (16) and a driving mechanism (18) are arranged on a mounting plane on the lower portion of each driving mechanism mounting plate (23); a mounting shaft of the encoder component (12) is provided with an encoder swing arm (15), the encoder swing arm (15) is provided with a round hole, and a first steel wire rope penetrates through the round hole; a driving pulley (14) is arranged below the driving pulley bracket (13), and a driving steel wire winding wheel (17) is arranged at the front end of the driving mechanism (18); one end of a first steel wire rope is fixed on the driving steel wire winding wheel (17), and the other end of the first steel wire rope passes by a pulley below the pressure sensor assembly (16), then passes by the driving pulley (14), passes through the encoder swing arm (15), and is connected to a mounting hole on an antenna (19) at the end part; a sliding bearing (22) is fixedly arranged on a driven sliding block (21), two groups of pulleys are arranged on the driven sliding block (21), a driven movable pulley (20) is hung under the pulleys through a second steel wire rope, a third steel wire rope is arranged under the driven movable pulley (20), and the other end of the third steel wire rope is fixed with the installation position of an antenna (19); one end of a second steel wire rope is connected to the counterweight block (27), bypasses the counterweight pulley (26), then bypasses the passive sliding block (21) and the passive movable pulley (20), and is fixed on the limiting block (11) at the other end; two sets of driven synchronous pulley subassemblies (8) and two sets of hold-in range installation mechanism (28) are fixed at crossbeam (1) upper surface through fixing bolt (9), two sets of hold-in range actuating mechanism (25) respectively with two sets of hold-in range installation mechanism (28) fixed connection together, two sets of actuating mechanism pull rods (24) pass through bolted connection, one end fixed mounting is on hold-in range (29), the other end links together with height adjustment piece (6), and then drive hold-in range (29) work through hold-in range actuating mechanism (25).
2. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the mounting distance of the two pulley blocks mounted on the driven sliding block (21) is equal to the diameter of a U-shaped groove structure on the driven movable pulley (20), and a third steel wire rope wound by the driven movable pulley (20) is ensured to be parallel.
3. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the driving steel wire winding wheel (17) is provided with a U-shaped groove with the width of 1.5 mm.
4. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the multiple groups of adjusting bolts (4) are in spiral connection with the adjusting sleeve (5).
5. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the pressure sensor assembly (16) is maintained at a pre-pressure.
6. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the upper surface of the linear guide rail (3) is provided with an arc structure matched with the circular guide rail (2).
7. The large-scale folded antenna test device of microgravity of claim 1, characterized in that: the outer surface of the sliding bearing (22) is tangent to the outer surface of the circular guide rail (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710991108.5A CN107741334B (en) | 2017-10-23 | 2017-10-23 | Microgravity large-scale folding and unfolding antenna test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710991108.5A CN107741334B (en) | 2017-10-23 | 2017-10-23 | Microgravity large-scale folding and unfolding antenna test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107741334A CN107741334A (en) | 2018-02-27 |
| CN107741334B true CN107741334B (en) | 2020-01-21 |
Family
ID=61238008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710991108.5A Active CN107741334B (en) | 2017-10-23 | 2017-10-23 | Microgravity large-scale folding and unfolding antenna test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107741334B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516113B (en) * | 2018-03-09 | 2021-05-14 | 中国科学院长春光学精密机械与物理研究所 | Gravity unloading method and device for ground debugging of eccentric rotation space load |
| CN109540198B (en) * | 2018-10-17 | 2022-02-22 | 南京航空航天大学 | Parabolic cylinder antenna unfolding reflecting surface ground test equipment |
| CN109638405B (en) * | 2018-12-03 | 2020-07-17 | 南京航空航天大学 | High-precision multi-butt-joint locking surface antenna auxiliary unfolding mechanism |
| CN109383852B (en) * | 2018-12-19 | 2020-10-09 | 北京航空航天大学 | Reel type stretch rod antenna zero gravity compensation device suitable for vacuum tank |
| CN109682622A (en) * | 2018-12-24 | 2019-04-26 | 天津航天瑞莱科技有限公司 | The fatigue life testing apparatus of space station sanitary district door |
| CN110271692B (en) * | 2019-05-29 | 2023-07-07 | 上海航天设备制造总厂有限公司 | Space stretching mechanism supports expansion device |
| CN110395415B (en) * | 2019-07-16 | 2021-03-26 | 西安空间无线电技术研究所 | Universal zero-gravity unloading device |
| CN110450993B (en) * | 2019-09-11 | 2021-03-19 | 北京邮电大学 | Zero-gravity self-adjusting air floatation platform and zero-gravity simulation system |
| CN110758782A (en) * | 2019-11-22 | 2020-02-07 | 北京理工大学 | Antenna microgravity simulation system |
| CN113161742B (en) * | 2021-04-28 | 2022-09-23 | 哈尔滨工业大学 | Active online adjusting mechanism for electric pole-holding rope-driven antenna |
| CN113371235B (en) * | 2021-05-31 | 2022-07-22 | 哈尔滨工业大学 | Active and passive combined suspension type double-layer motion platform and using method |
| CN114590422B (en) * | 2022-05-09 | 2022-07-29 | 天津航天机电设备研究所 | Three-rocker testing device for space mechanism compound motion microgravity unfolding |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102145755A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Zero-gravity suspension type deployment test device |
| CN103552697A (en) * | 2013-09-23 | 2014-02-05 | 上海卫星装备研究所 | Active suspension type satellite antenna three-dimensional extension testing device |
| CN105181373A (en) * | 2015-09-30 | 2015-12-23 | 中国科学院沈阳自动化研究所 | Gravity balancing mechanical arm of satellite antenna expanding mechanism of multi-dimensional structure |
| CN106450648A (en) * | 2016-12-07 | 2017-02-22 | 燕山大学 | Synchronous automatic antenna folding device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101077535B1 (en) * | 2009-12-07 | 2011-10-27 | 한국항공우주연구원 | Weightlessness offering apparatus for deployment test of satellite payload antenna |
| KR20140021740A (en) * | 2012-08-09 | 2014-02-20 | 한국전자통신연구원 | Apparatus for antenna weightlessness deployment test |
-
2017
- 2017-10-23 CN CN201710991108.5A patent/CN107741334B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102145755A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Zero-gravity suspension type deployment test device |
| CN103552697A (en) * | 2013-09-23 | 2014-02-05 | 上海卫星装备研究所 | Active suspension type satellite antenna three-dimensional extension testing device |
| CN105181373A (en) * | 2015-09-30 | 2015-12-23 | 中国科学院沈阳自动化研究所 | Gravity balancing mechanical arm of satellite antenna expanding mechanism of multi-dimensional structure |
| CN106450648A (en) * | 2016-12-07 | 2017-02-22 | 燕山大学 | Synchronous automatic antenna folding device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107741334A (en) | 2018-02-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107741334B (en) | Microgravity large-scale folding and unfolding antenna test device | |
| CN110366674B (en) | Collision simulation test device | |
| CN106932264B (en) | Can realize drawing compound testing arrangement that presses load in-process was twistd reverse | |
| CN109625344B (en) | Integrated unfolding microgravity compensation control system for flexible stretching arm | |
| CN102928220B (en) | Experimental device for comprehensively testing dynamic characteristics of linear feeding system | |
| CN109540198B (en) | Parabolic cylinder antenna unfolding reflecting surface ground test equipment | |
| CN201281653Y (en) | Four-freedom-degree movement device | |
| CN108037017A (en) | A kind of lead screw gear formula plate control with changed scale loading based on servomotor is double to draw pilot system | |
| CN103552697B (en) | Active suspension type satellite antenna three-dimensional developing test device | |
| CN108408088B (en) | Two-dimensional unfolding zero-gravity simulation device and method based on constant force spring | |
| CN103009391A (en) | Variable-structure rope-traction parallel robot for wind tunnel test | |
| CN103192999A (en) | Ground zero-gravity test device for small-space one-dimension extension mechanism | |
| CN108535035B (en) | Zero-gravity suspension test device for cylindrical surface unfolding mechanism | |
| CN114476148B (en) | Gravity unloading device and method for satellite-borne flat plate type antenna | |
| CN103846649A (en) | Two-stage parallel robot device applied to precision assembly | |
| CN102998074A (en) | Device and method for testing vibration performance of basic translation flexible beam | |
| CN108890625B (en) | Rigidity-adjustable cable driving parallel device | |
| CN205659995U (en) | Harmomegathus reel mechanism | |
| CN203310604U (en) | Tooling mechanism with three degrees of freedom | |
| CN113911408B (en) | Solar wing unfolding mechanism and system for simulating gravity unloading and use method | |
| CN102913553B (en) | Multi-layer air floatation hanging device capable of performing two-dimensional friction-free long-distance movement | |
| CN101957271B (en) | High-speed large-displacement servo loading test platform | |
| CN204359598U (en) | A kind of force push rod device and Multi-axis high-precision load add carrier aircraft | |
| CN117755519A (en) | Space coiling type stretching arm with pose active adjusting capability | |
| CN206353081U (en) | Damperparameters testing stand |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |