CN113460338B - Multifunctional antenna gravity unloading device - Google Patents
Multifunctional antenna gravity unloading device Download PDFInfo
- Publication number
- CN113460338B CN113460338B CN202110754661.3A CN202110754661A CN113460338B CN 113460338 B CN113460338 B CN 113460338B CN 202110754661 A CN202110754661 A CN 202110754661A CN 113460338 B CN113460338 B CN 113460338B
- Authority
- CN
- China
- Prior art keywords
- antenna
- balance assembly
- gravity
- balance
- unloading device
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Abstract
The invention provides a multifunctional antenna gravity unloading device, which relates to the technical field of satellite antenna ground test and comprises the following components: the device comprises a ball bar truss, a two-dimensional plane translation mechanism, a gravity balancing device, an antenna hanging device and control equipment; the gravity balance device includes: the rotating shaft is fixedly connected with the rotating seat, and the first balance assembly, the second balance assembly and the third balance assembly are sequentially sleeved with the rotating shaft from top to bottom; the antenna cable suspension device comprises: the first suspender, the second suspender and the third suspender. The invention can simulate the space weightlessness state of the large-caliber antenna, realizes that the large-caliber antenna is arranged on the special-shaped surface of the satellite body in the unfolding state, and has the functions of carrying out tests such as unfolding motion on the satellite.
Description
Technical Field
The invention relates to the technical field of satellite antenna ground test, in particular to a gravity unloading device for a multifunctional antenna.
Background
In certain type satellite engineering, a large-caliber reflector antenna with a pointing mechanism is matched. Because the antenna and the whole satellite adopt a conformal design idea, the main mounting surface is concave in the satellite structure, the satellite mounting operation cannot be finished under the state that the emitting surface is folded, and the antenna cannot be directly mounted on the satellite mounting surface. In addition, because the antenna is big in self-mass, under the influence of ground gravity, the motor driving force can not satisfy the direct test demand on ground.
At present, the known similar large-caliber reflector antenna with a pointing mechanism for the satellite mostly adopts an integral direct assembly scheme, the installation positions are all on the same plane, and the whole antenna is installed on the surface of the satellite; or directly in the development stage of a stand-alone product, the antenna is arranged on a single cabin plate corresponding to the satellite, and then the antenna and the cabin plate are delivered to a satellite system together, and the cabin plate is connected with a satellite main structure. By adopting the conventional star mounting scheme, the star mounting operation of the large-aperture reflector antenna with the pointing structure developed by the model cannot be completed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a multifunctional antenna gravity unloading device, which realizes the horizontal expansion and two-dimensional pointing test of a large antenna and the star loading of the antenna.
The invention provides a multifunctional antenna gravity unloading device, which comprises: the device comprises a ball bar truss, a two-dimensional plane translation mechanism, a gravity balancing device, an antenna hanging device and control equipment; the gravity balance device includes: the rotating shaft is fixedly connected with the rotating seat, and the first balance assembly, the second balance assembly and the third balance assembly are sequentially sleeved with the rotating shaft from top to bottom; the antenna cable suspension device comprises: a first boom, a second boom, a third boom; the top of the two-dimensional plane translation mechanism is fixed to the upper portion of the ball bar truss, the bottom of the two-dimensional plane translation mechanism is connected with the rotary seat, the first balance assembly, the second balance assembly and the third balance assembly are respectively connected with the tops of the first hanging rod, the second hanging rod and the third hanging rod, the bottoms of the first hanging rod, the second hanging rod and the third hanging rod are respectively connected with an antenna reflecting surface, a pointing mechanism and a unfolding arm, and the control device is connected with the gravity balance device through cables.
Further, the two-dimensional plane translation mechanism includes: motor, lead screw, guide rail.
Further, the first balancing component, the second balancing component, the third balancing component comprise: the first balance assembly, the second balance assembly and the third balance assembly are respectively sleeved with the rotating shaft through the swing rod, and the guide rail sliding block is fixed at the bottom of the swing rod.
Further, the bottom of the guide rail sliding block of the first balance assembly is sequentially connected with a force sensor, an electric cylinder and a lifting rope, and the bottom of the guide rail sliding block of the second balance assembly and the bottom of the guide rail sliding block of the third balance assembly are sequentially connected with a force balancer and a lifting rope.
Further, the axis of the rotating shaft is perpendicular to the ground.
Further, the first boom includes: and the hanging frame is formed by assembling pipe fittings connected to the antenna hanging points.
Further, the suspension point of the suspension frame passes through the center of mass of the antenna and the suspension frame.
Further, the second hanger rod and the third hanger rod are of C-shaped structures.
Compared with the prior art, the invention has the following beneficial effects:
the multifunctional antenna gravity unloading device provided by the invention realizes the gravity balance of the large-aperture antenna through the balance force control on each lifting point, and simulates the space weightlessness motion state of the antenna; the functional tests of horizontal unfolding of the root part of the antenna and two-dimensional movement of the pointing mechanism are completed through high-precision control of hanging balance force and the design of passive following of multiple hanging points in space, and the large-caliber antenna is mounted on a special-shaped surface of a satellite body in an unfolded state and has the capability of performing functional tests such as unfolding movement on the satellite; the two-dimensional plane translation mechanism provided by the invention can realize translation of the antenna in two directions on the horizontal plane so as to meet the requirement of satellite mounting.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a multifunctional antenna gravity unloading device provided by the present invention;
FIG. 2 is a schematic view of a two-dimensional planar translation mechanism provided by the present invention;
FIG. 3 is a schematic view of a gravity balancing apparatus according to the present invention;
fig. 4 is a schematic view of an antenna suspension device according to the present invention.
In the figure:
1-a club truss;
2-a two-dimensional plane translation mechanism;
3-a gravity balancing device;
4-an antenna hanging device;
5-control equipment;
21-a motor;
22-a lead screw;
31-transposition;
32-a rotating shaft;
33-a first balancing component;
34-a second balancing component;
35-a third balancing assembly;
361-first balance assembly pendulum rod;
362-first balance assembly rail slide;
363-a force sensor;
364-electric cylinder;
365-a first counterbalance assembly hoist line;
366-a force balancer;
41-a first boom;
42-a second boom;
43-a third boom;
411-a hanging frame;
412-longitudinal adjustment block;
413-vertical adjustment block.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Fig. 1 is a schematic view of a multifunctional antenna gravity unloading device provided in the present invention, and as shown in fig. 1, the gravity unloading device of the present invention includes: the device comprises a ball bar truss 1, a two-dimensional plane translation mechanism 2, a gravity balance device 3, an antenna hanging device 4 and a control device 5. The club truss 1 is the mounting base of the gravity unloading device and provides a mounting interface and support for the gravity unloading device. The ball rod truss 1 is connected with the ball head and the ball rod through threads, and the truss formed by connecting a plurality of groups of the ball rod truss has high rigidity and stability.
As shown in fig. 2, the two-dimensional plane translation mechanism 2 includes two sets of motors 21, a lead screw 22, and a guide rail moving in two directions, so as to implement translation of the antenna on a horizontal plane. The lead screw 22 is used as a transmission element, the motor 21 is used as a driving source, when the star is installed, the antenna can be moved to the position near the star body, and then the fine adjustment function of the guide rails in two directions is used for accurately installing the antenna on the star body. The top of the two-dimensional plane translation structure 2 is fixed on the upper cross bar of the ball bar truss 1.
As shown in fig. 3, the gravity balance device 3 includes a rotation base 31, a rotation shaft 32, a first balance assembly 33, a second balance assembly 34, and a third balance assembly 35. The rotary seat 31 is connected with the bottom of the two-dimensional plane translation mechanism 2, the rotating shaft 32 is fixed on the rotary seat 31, and the axis is vertical to the ground. The first balance assembly 33, the second balance assembly 34 and the third balance assembly 35 respectively comprise a swing rod and a guide rail sliding block, the swing rods of the first balance assembly 33, the second balance assembly 34 and the third balance assembly 35 are sequentially sleeved with the rotating shaft 32 from top to bottom, so that the first balance assembly 33, the second balance assembly 34 and the third balance assembly 35 can freely rotate around the rotating shaft 32, and passive following rotation in the antenna unfolding process is realized. The guide rail sliding blocks of the first balance assembly 33, the second balance assembly 34 and the third balance assembly 35 are fixedly connected with the swing rod. The lower end of the guide rail sliding block 363 of the first balancing assembly 33 is further connected with a force sensor 363, an electric cylinder 364 and a lifting rope 365 in sequence, the force sensor 363 is used for measuring the value of the gravity of the balancing antenna in real time, and forms closed loop feedback with the electric cylinder 364 to control the contraction or push-out of a push rod of the electric cylinder 364, so that the balanced gravity is adjusted in real time. The lower ends of the guide rail sliding blocks of the second balance assembly 34 and the third balance assembly 35 are also sequentially connected with a force balancer and a lifting rope, and the force balancer realizes constant gravity balance of the pointing mechanism and the lifting point of the unfolding arm.
The gravity balancing device 3 can move in a plane in a two-dimensional orthogonal direction along with the two-dimensional plane translation mechanism 2 so as to meet the requirement of star loading.
As shown in fig. 4, the antenna hanger 4 includes a first boom 41, a second boom 42, and a third boom 43. The first boom 41, the second boom 42 and the third boom 43 are connected at the top with the first counterbalance assembly 33, the second counterbalance assembly 34 and the third counterbalance assembly 35, respectively, and at the bottom with the antenna, the pointing mechanism and the deployment arm, respectively. The first hanger rod 41 comprises a hanging frame 411, wherein the hanging frame 411 is designed as an enclosing frame, is formed by splicing aluminum alloy pipes and is connected to an antenna hanging point interface; the hanging frame 411 is provided with a longitudinal adjusting block 412 and a vertical adjusting block 413 to adjust the center of the hanging frame 411, so that the hanging point of the hanging frame 411 always passes through the center of mass of the antenna. The second suspender 42 and the third suspender 43 are C-shaped adjustable suspenders, which can avoid the interference of stars when loading stars.
As shown in fig. 1, the control device 5 is connected to the gravity balance device 3 through a cable, and the control device 5 includes a data acquisition and processing system and a gravity balance device control system. The measurement and control signals of the gravity unloading device 3 are transmitted to the control equipment 5 through a cable, and the driving control of the motor 21 and the gravity balancing device 3 is realized.
The multifunctional antenna gravity unloading device of the invention connects the unfolding mechanism, the pointing mechanism and the antenna with the gravity unloading device 3 through the antenna hanging device 4 in the antenna contraction state. The movement of the gravity unloading device 3 is passive following movement, and the front and back displacement is adjusted while the movement follows the rotation of the antenna, so that the purpose that the gravity unloading point of the antenna always passes through the mass center of each component is achieved. During the unfolding process, the motion parameters such as the position, the speed, the acceleration and the like of the unfolding mechanism are measured in real time, the load resisting moment is detected in real time, and the magnitude of the unloading force is adjusted in real time according to detection data so as to automatically balance the gravity.
In the embodiment, the force sensor is used for measuring the gravity value of the balance antenna in real time and feeding the gravity value back to the electric cylinder to control the action of the electric cylinder, so that the real-time adjustment of the balance gravity is realized, the constant gravity balance of the pointing mechanism and the unfolding arm is realized through the force balancer, and the balance force control of multiple suspension points realizes the simulation of the spatial weightlessness motion state of the antenna. Through the movement of the guide rail sliding block on the swing rod, the rotation of the swing rod and the two-dimensional motion of the two-dimensional plane translation mechanism, the passive following of a hanging point in space is realized, the functional tests of the horizontal unfolding of the root part of the antenna and the two-dimensional motion of the pointing mechanism are completed, and the functional tests of the installation, the unfolding motion and the like of a special-shaped surface of the large-aperture antenna on a star body are realized.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (8)
1. A multifunctional antenna gravity unloading device, characterized by comprising: the device comprises a ball bar truss, a two-dimensional plane translation mechanism, a gravity balancing device, an antenna hanging device and control equipment; the gravity balance device includes: the rotating shaft is fixedly connected with the rotating seat, and the first balance assembly, the second balance assembly and the third balance assembly are sequentially sleeved with the rotating shaft from top to bottom; the first balance assembly comprises a swing rod and a guide rail sliding block, the first balance assembly is sleeved with the rotating shaft through the swing rod, the guide rail sliding block of the first balance assembly is fixed at the bottom of the swing rod, and the bottom of the guide rail sliding block of the first balance assembly is sequentially connected with a force sensor, an electric cylinder and a lifting rope; the antenna cable suspension device comprises: a first boom, a second boom, a third boom; the top of the two-dimensional plane translation mechanism is fixed to the upper part of the ball-bar truss, the bottom of the two-dimensional plane translation mechanism is connected with the rotary seat, the first balance assembly, the second balance assembly and the third balance assembly are respectively connected with the tops of the first suspension rod, the second suspension rod and the third suspension rod, the bottoms of the first suspension rod, the second suspension rod and the third suspension rod are respectively connected with an antenna reflecting surface, a pointing mechanism and a unfolding arm, the first suspension rod comprises a suspension frame, and a longitudinal adjusting block and a vertical adjusting block are arranged on the suspension frame; the control equipment is connected with the gravity balancing device through a cable.
2. The multifunctional antenna gravity unloading device according to claim 1, wherein the two-dimensional plane translation mechanism comprises: motor, lead screw, guide rail.
3. The multifunctional antenna gravity unloading device of claim 1, wherein the second and third balancing assemblies comprise: the second balance assembly and the third balance assembly are respectively sleeved with the rotating shaft through the swing rod, and the guide rail sliding block is fixed at the bottom of the swing rod.
4. The multifunctional antenna gravity unloading device of claim 3, wherein the bottom of the rail slider of the second balance assembly and the bottom of the rail slider of the third balance assembly are further connected with a force balancer and a lifting rope in sequence.
5. The multifunctional antenna gravity unloading device of claim 1, wherein the axis of the rotating shaft is perpendicular to the ground.
6. The multifunctional antenna gravity unloading device of claim 1, wherein the hanging frame is assembled from pipe fittings connected to the antenna hanging points.
7. The multifunctional antenna gravity unloading device of claim 6, wherein the hanging frame has a hanging point that passes through the center of mass of the antenna and the hanging frame.
8. The multifunctional antenna gravity unloading device of claim 1, wherein the second boom and the third boom are of a C-shaped structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110754661.3A CN113460338B (en) | 2021-07-02 | 2021-07-02 | Multifunctional antenna gravity unloading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110754661.3A CN113460338B (en) | 2021-07-02 | 2021-07-02 | Multifunctional antenna gravity unloading device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113460338A CN113460338A (en) | 2021-10-01 |
| CN113460338B true CN113460338B (en) | 2023-03-31 |
Family
ID=77877854
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110754661.3A Active CN113460338B (en) | 2021-07-02 | 2021-07-02 | Multifunctional antenna gravity unloading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113460338B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113859592B (en) * | 2021-10-14 | 2024-02-09 | 上海航天设备制造总厂有限公司 | Zero-gravity balance unfolding and folding test device for cabin door of spacecraft and application 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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205973442U (en) * | 2016-08-04 | 2017-02-22 | 威海银河永磁发电机有限公司 | Balanced handling frock |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2950691B2 (en) * | 1992-10-13 | 1999-09-20 | 株式会社日立製作所 | Weightless drop test equipment |
| JP4277128B2 (en) * | 1999-06-25 | 2009-06-10 | 株式会社Ｉｈｉエアロスペース | Power shut-off device |
| JP3864195B2 (en) * | 2001-06-12 | 2006-12-27 | 三菱重工業株式会社 | Space structure and its deployment system, and solar power generation satellite |
| CN102564784B (en) * | 2011-12-20 | 2015-04-08 | 北京卫星环境工程研究所 | Ground walking test system of lunar surface inspection device |
| CN102589917B (en) * | 2012-02-23 | 2014-09-24 | 华中科技大学 | Free-falling body verification device for drag-free spacecraft |
| US11268789B2 (en) * | 2012-09-13 | 2022-03-08 | Christopher V. Beckman | Device controlling shooting based on firearm movement |
| CN104177120B (en) * | 2014-08-14 | 2015-12-02 | 合肥科斯孚安全科技有限公司 | A kind of preparation method of low cost light flyash porous insulation material |
| CN104691793B (en) * | 2015-03-11 | 2016-08-17 | 哈尔滨工业大学 | Position sensing type intelligent gas foot |
| CN110637511B (en) * | 2015-08-27 | 2018-12-28 | 上海宇航系统工程研究所 | Follow-up mechanism for balancing influence of space expansion and gravity of multidimensional movement mechanism |
| CN105510891B (en) * | 2015-11-30 | 2018-05-18 | 上海卫星工程研究所 | For the in-orbit modal identification method of satellites with synthetic aperture radar |
| US20170225320A1 (en) * | 2016-02-10 | 2017-08-10 | Other Lab, Llc | Gravity balanced monopod system and method |
| CN105883010B (en) * | 2016-04-21 | 2018-10-26 | 北京空间飞行器总体设计部 | A kind of c-type structure connecting tooling |
| CN212965089U (en) * | 2020-06-17 | 2021-04-13 | 上海泰肯射频技术有限公司 | A shielded cell antenna boom structure for cell-phone complete machine shielding test |
| CN212667708U (en) * | 2020-06-30 | 2021-03-09 | 中国人民解放军61096部队 | Satellite antenna gravity unloading device |
-
2021
- 2021-07-02 CN CN202110754661.3A patent/CN113460338B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205973442U (en) * | 2016-08-04 | 2017-02-22 | 威海银河永磁发电机有限公司 | Balanced handling frock |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113460338A (en) | 2021-10-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113460338B (en) | Multifunctional antenna gravity unloading device | |
| CN101907893B (en) | Aircraft component attitude adjusting assembly system based on parallel mechanism with six degrees of freedom and debugging method | |
| US11052533B2 (en) | Engine assembly stand | |
| CN103552697B (en) | Active suspension type satellite antenna three-dimensional developing test device | |
| CN104326368A (en) | Gravity compensation device for solar wing low temperature unfolding experiment | |
| CN105599922B (en) | A kind of 1/6g low gravitations balance erecting by overhang | |
| CN105459086B (en) | A kind of freedom degree parallel connection posture adjustment platform of horizontal direction and yaw steering | |
| CN112340071B (en) | Large-scale heavy-load air floatation suspension expansion test device and test method | |
| CN110146274B (en) | Cabin door mechanism unfolding test device and implementation method thereof | |
| CN105589062B (en) | A kind of photoelectric detection equipment dynamic target tracking accuracy test device | |
| CN109540198B (en) | Parabolic cylinder antenna unfolding reflecting surface ground test equipment | |
| CN109540452B (en) | Rotary rocket three-degree-of-freedom angular motion simulation test device | |
| CN212667708U (en) | Satellite antenna gravity unloading device | |
| CN204964218U (en) | Multidimension framework formula satellite antenna deployment mechanism gravity balance arm | |
| CN110637511B (en) | Follow-up mechanism for balancing influence of space expansion and gravity of multidimensional movement mechanism | |
| CN109110163B (en) | Follow-up gravity compensation device of three-degree-of-freedom space station cloud table lamp | |
| CN106275525B (en) | A kind of sun wing plate air supporting support ground simulation hanging expanding unit | |
| CN110395415B (en) | Universal zero-gravity unloading device | |
| CN207649808U (en) | A kind of test device of quiet dynamic flexible rope tension and space configuration | |
| CN114527008B (en) | Device and method for simulating loading of folding gravity load of aircraft wing | |
| CN106184835B (en) | A kind of 90 degree of hanging expanding units of sun wing plate cantilevered | |
| CN106921026A (en) | A kind of orthogonal satellite antenna drive mechanism ground air supporting gravity unloading mechanism of two axles | |
| RU2721448C1 (en) | Rotary device with a block and tackle system for weighlessing open structures of a spacecraft | |
| CN114166496A (en) | Tilt rotor wing test device | |
| CN110001328B (en) | Spacecraft simulation device |
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 |