CN112340071B - Large-scale heavy-load air floatation suspension expansion test device and test method - Google Patents
Large-scale heavy-load air floatation suspension expansion test device and test method Download PDFInfo
- Publication number
- CN112340071B CN112340071B CN202011272308.3A CN202011272308A CN112340071B CN 112340071 B CN112340071 B CN 112340071B CN 202011272308 A CN202011272308 A CN 202011272308A CN 112340071 B CN112340071 B CN 112340071B
- Authority
- CN
- China
- Prior art keywords
- air
- guide rail
- suspension
- floatation
- antenna
- 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
- 239000000725 suspension Substances 0.000 title claims abstract description 95
- 238000012360 testing method Methods 0.000 title claims abstract description 80
- 238000010998 test method Methods 0.000 title claims abstract description 16
- 238000000034 method Methods 0.000 claims abstract description 32
- 230000005484 gravity Effects 0.000 claims abstract description 26
- 238000005188 flotation Methods 0.000 claims abstract description 12
- 230000005486 microgravity Effects 0.000 claims abstract description 8
- 230000003068 static effect Effects 0.000 claims abstract description 8
- 230000000694 effects Effects 0.000 claims abstract description 7
- 238000007667 floating Methods 0.000 claims description 46
- 229910000831 Steel Inorganic materials 0.000 claims description 21
- 239000010959 steel Substances 0.000 claims description 21
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 7
- 210000001503 joint Anatomy 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims 1
- 230000002093 peripheral effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 8
- 230000007246 mechanism Effects 0.000 description 29
- 230000008569 process Effects 0.000 description 14
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000013102 re-test Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004579 marble Substances 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 210000003437 trachea Anatomy 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a large heavy-load air-flotation suspension unfolding test device and a test method, and the test device comprises the following steps: the air-float guide rail device, the air pipe follow-up device, the suspension bracket and the suspension device; the air pipe follow-up devices are distributed along the air floatation guide rails in the air floatation guide rail device and are connected with mounting plates at two ends of the air floatation guide rails, and each air floatation guide rail is provided with a set of air pipe follow-up device; the air floatation guide rail device is connected with the suspension bracket; the suspension device is connected with the air floatation guide rail device; the air-floatation guide rail device adopts a gas static pressure effect principle to simulate an on-orbit microgravity environment and provides an expansion test environment with near-zero friction force for a large-scale load antenna; the suspension device adopts a hanging balance type gravity compensation method to compensate the actual mass of the load antenna. The invention can meet the test tests of a plurality of types of load antennas, can adapt to the expansion tests under different design requirements of multiple working conditions, improves the working efficiency and meets the requirements of type tasks.
Description
Technical Field
The invention relates to a satellite unfolding test device, in particular to a large heavy-duty air suspension unfolding test device and a test method, more particularly to a large heavy-duty air suspension unfolding test principle and a test method, and is suitable for space unfolding mechanisms such as a large SXX antenna and a solar cell array.
Background
In order to ensure the reliability of in-orbit expansion of the satellite expansion mechanism, all the expansion mechanisms need to simulate the in-orbit expansion state on the ground to carry out an expansion test so as to check the compression and release functions of the compression and release device of the expansion mechanism and the expansion and locking functions of the expansion mechanism. The ground unfolding test of the large heavy-load space unfolding mechanism mainly aims to:
checking the structure and the coordination of the unfolding mechanism and the reliability and the stability of the unfolding function;
checking the conformity of the structure of the unfolding mechanism and the indexes of the mechanism part to the overall technical requirements;
the existing expansion test mode mainly comprises three modes of air floatation, suspension and air floatation and suspension. The air-flotation unfolding mode supplies air with certain air pressure to the air-flotation cushion assembly of the unfolding mechanism through a pipeline, an air film is formed between the air-flotation cushion assembly and the air-flotation platform, and stable acting force is generated to balance gravity so as to simulate an on-orbit gravity-free unfolding test and folding; the vertical suspension unfolding mode balances the gravity in the vertical direction through a suspension system, meanwhile, the suspension point horizontally moves along the guide rail, and the driving moment of the torsion spring is horizontally arranged in the unfolding process, so that the coupling with the gravity in the vertical direction is avoided.
The air flotation and suspension method is to adopt a mode of combining a bottom marble air flotation method and a top suspension method to unload the product by gravity aiming at some heavy-load mechanisms, so that the resistance in the unfolding process can be reduced to a certain degree, and the stability of the product is ensured.
However, for ground unfolding tests of some large heavy-load space unfolding mechanisms, the satellite structure layout is compact, the bottom supporting space is narrow, the traditional air floatation supporting mode cannot be adopted, the size of a novel SXX antenna or a solar cell array is large, the load is heavy, the friction resistance is unfolded by adopting the traditional pulley suspension mode, the unfolding locking performance of the mechanism is influenced, and the unfolding precision of the antenna is influenced.
Aiming at the problems, the invention relates to a large heavy-load air-flotation suspension unfolding test principle and a test method, which avoid the limitation of the traditional air-flotation support and the unfolding friction resistance brought by the traditional suspension, improve the unfolding precision of a mechanism, ensure the stability of repeated unfolding of a payload, and meet the requirements of a large heavy-load mechanism ground unfolding test.
The research on the ground expansion technology of the expansion mechanisms at home and abroad finds that the related content of the large-scale heavy-load air suspension expansion test principle and the test method is not searched at present.
Patent document CN103538733B (application number: 201310436356.5) discloses an air-floating suspension type three-dimensional unfolding test apparatus, including: four X direction air supporting motion mechanisms, six Y direction air supporting motion mechanisms, six Z direction counter weight mechanisms and braced frame, braced frame is last to be provided with two X direction guide rails and two Y direction guide rails, two X direction guide rail parallel arrangement, two a set of cup joints respectively to the X direction guide rail that corresponds of four X direction air supporting motion mechanisms, the both ends of Y direction guide rail are connected to the X direction air supporting motion mechanism who is located relative position on two X direction guide rails respectively, three a set of cup joints respectively to the Y direction guide rail that corresponds of six Y direction air supporting motion mechanisms, six Z direction counter weight mechanisms and six Y direction air supporting motion mechanisms one-to-one, be connected to corresponding Y direction air supporting motion mechanism's below respectively.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a large heavy-load air suspension unfolding test device and a test method.
The invention provides a large heavy-load air suspension unfolding test device, which comprises: the air-float guide rail device, the air pipe follow-up device, the suspension bracket and the suspension device;
the air pipe follow-up devices are distributed along the outer side and the upper side of the air floatation guide rail in the air floatation guide rail device and are connected with mounting blocks at two ends of the air floatation guide rail, and each air floatation guide rail is provided with a set of air pipe follow-up device;
the air floatation guide rail device is arranged on the suspension bracket; the suspension device is connected with the air-floating guide rail device;
the air-floatation guide rail device simulates an on-rail microgravity environment by adopting a gas static pressure effect principle and provides an expansion test environment with near-zero friction force for a large-scale load antenna;
the suspension device adopts a hanging balance type gravity compensation method to compensate the actual mass of the load antenna.
Preferably, the air rail device includes: the air-float long guide rail slide block, the air-float long guide rail, the air-float short guide rail and the air-float short guide rail slide block;
a preset air-floating long guide rail sliding block is arranged on the two parallel air-floating long guide rails in a mirror image manner; the air-floatation short guide rails are connected through the air-floatation long guide rail sliding blocks;
the middle point position on the air-floatation short guide rail is provided with the air-floatation short guide rail sliding block.
Preferably, the air-floating guide rail device realizes frictionless two-dimensional motion under heavy load through a mode of combining the air-floating guide rail and the air-floating slide block and a pressure-equalizing rigid air film formed after the top and the periphery of the air-floating slide block are ventilated by the air-floating cushions.
Preferably, the suspension device is in rigid-flexible coupling connection with the air rail device; and the real-time monitoring of the hanging force is carried out through the ground tension sensor, so that the actual gravity compensation of the load antenna is realized.
Preferably, the suspension device comprises: the device comprises a guide rail mounting plate, an adjusting assembly, a tension sensor, an upper cross beam, a high-rigidity spring, a mass center adjuster, a suspension cross beam and an antenna connecting rod;
the guide rail mounting plate is connected with the air-floatation short guide rail sliding block; the guide rail mounting plate is connected with the adjusting assembly; the adjusting assembly is connected with the tension sensor, and the tension sensor is connected with the upper cross beam; the upper cross beam is connected with the high-stiffness spring; the high-stiffness spring is connected with the mass center adjuster; the mass center adjuster is connected with the suspension cross beam; the suspension cross beam is connected with the plurality of antenna connecting rods.
Preferably, the suspension bracket comprises a preset number of splicing modules at the top and a preset number of supporting legs.
Preferably, the air pipe follow-up device comprises a steel wire rope connecting rod, a steel wire rope, an air pipe and an air pipe connecting ring; the steel wire rope connecting rod is arranged on the mounting blocks at two ends of the air floatation long guide rail and the air floatation short guide rail and is in a vertical state; the top of the steel wire rope connecting rod is provided with a ring buckle, and the steel wire rope is straightened and fixed through the ring buckle; the plurality of air pipe connecting rings are hung on the steel wire rope, and the air pipes penetrate into the air pipe connecting rings to ensure that the air pipes cannot sag.
According to the large heavy-load air suspension unfolding test method provided by the invention, the large heavy-load air suspension unfolding test device is used for executing the following steps:
step M1: carrying out butt joint installation on the suspension bracket and moving the suspension bracket to an expansion station;
step M2: hoisting the air floatation long guide rail to a suspension bracket, and adjusting the straightness, levelness, parallelism and guide rail spacing of the long guide rail;
step M3: hoisting the air floatation short guide rail to the air floatation long guide rail, and adjusting the levelness of the air floatation short guide rail;
step M4: after the installation is finished, carrying out a simulated counterweight test, carrying out a load test with preset weight for multiple times by a single point, and recording the running state of the air floatation guide rail and the friction force under different loads so as to enable the friction force to meet the preset requirement;
step M5: mounting a hanging device below each group of air floatation short guide rails;
step M6: moving the satellite to an unfolding station, adjusting the posture, and meeting the preset index requirement;
step M7: butting and adjusting the hanging device and the antenna plate, and carrying out mass center adjustment and gravity unloading;
step M8: retesting and adjusting the satellite attitude to enable the satellite attitude to meet the preset index requirement in a full-load state;
step M9: and (5) carrying out antenna test.
Preferably, the air-float guide rail adopts a laser tracker to measure levelness, straightness, parallelism and long guide rail distance.
Preferably, the step M9 includes: and testing an antenna test, including checking the unfolding locking performance of the antenna, the unfolding time of the antenna and various accurate tests after the antenna is unfolded.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention utilizes the principle of gas static pressure and the principle of balance hanging type gravity compensation, realizes the test requirements of high unloading precision and near zero friction force in the process of a large-scale heavy-load air-floatation hanging expansion test, breaks through the traditional expansion mode, avoids the limitation of the traditional air-floatation support and the expansion friction resistance brought by the traditional hanging, improves the mechanism expansion precision and ensures the stability of repeated expansion of the effective load.
2. The invention can meet the test tests of a plurality of types of load antennas, can adapt to the expansion tests under different design requirements of multiple working conditions, improves the working efficiency and meets the requirements of type tasks.
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 structural view of an air-floating guide rail device;
FIG. 2 is a schematic structural view of the trachea follow-up device;
FIG. 3 is a schematic structural view of a rigid-flexible coupling suspension device;
FIG. 4 is a schematic view of an air suspension system;
FIG. 5 is a diagram of an air suspension deployment test system;
FIG. 6 is a flow chart of an air suspension deployment test;
in the figure, 1 is an air-floating guide rail device, 2 is a suspension bracket, 3 is a mechanism console, 4 is an SXX antenna, 5 is an air distribution cabinet, 6 is a hanging device, and 7 is an air pipe follow-up device.
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.
Example 1
The invention provides a large heavy-load air floatation suspension expansion test principle and a test method aiming at the defects of the prior art, and the method is suitable for space expansion mechanisms such as a large SXX antenna, a solar cell array and the like.
The principle of the large-scale heavy-load air floatation suspension unfolding test adopts an air static pressure principle and a balance suspension type gravity compensation principle. In order to reduce the resistance of the large SXX antenna in the ground unfolding process and improve the unloading precision of the unfolding process, the ground near-zero friction test environment is constructed by adopting the aerostatic pressure principle, the in-orbit microgravity unfolding is simulated, the actual mass of the load antenna is compensated by adopting a balanced hanging gravity compensation method, and the unloading precision of the ground unfolding test is improved. The test method can preliminarily carry out simulation operation test on the air floatation guide rail by a simulation counterweight method, is finally combined with a product, and verifies the feasibility and application effect of the large-scale heavy-load air floatation suspension method by testing the unfolding and locking performance of the SXX antenna.
According to the present invention, as shown in fig. 1 to 6, the large heavy-duty air suspension deployment test apparatus includes: the air-float guide rail device, the air pipe follow-up device, the suspension bracket and the suspension device;
the air pipe follow-up devices are distributed along the outer side and the upper side of the air floatation guide rail in the air floatation guide rail device and are connected with mounting blocks at two ends of the air floatation guide rail, and each air floatation guide rail is provided with a set of air pipe follow-up device;
the air floatation guide rail device is arranged on the suspension bracket; the suspension device is connected with the air floatation guide rail device;
the air-floating guide rail device simulates an on-rail microgravity environment by adopting an aerostatic effect principle and a balance hanging type gravity compensation principle, provides an expansion test environment with near-zero friction for the large-scale load antenna, and performs ground microgravity expansion test verification on the large-scale load antenna;
the suspension device adopts a hanging balance type gravity compensation method to compensate the actual mass of the load antenna.
Specifically, the air rail device includes: the air-float long guide rail slide block, the air-float long guide rail, the air-float short guide rail and the air-float short guide rail slide block;
a preset air-floating long guide rail sliding block is arranged on the two parallel air-floating long guide rails in a mirror image manner; the air-floatation short guide rails are connected through the air-floatation long guide rail sliding blocks; the air-floating long guide rail sliding block is assembled on the air-floating long guide rail and can freely slide after being ventilated.
The middle point position on the air-floatation short guide rail is provided with the air-floatation short guide rail sliding block.
Specifically, the air-floating guide rail device realizes frictionless two-dimensional motion under heavy load through a mode of combining the air-floating guide rail and the air-floating slide block and a pressure-equalizing rigid air film formed after the top and the periphery of the air-floating slide block are ventilated by the air-floating cushions. The voltage-sharing rigid air film can load the actual mass (400 kg) of the loaded antenna, and the maximum load can reach 600kg; 5 surfaces of the top, two sides and the bottom of the long guide rail air-floating slide block are provided with air-floating cushions, and 3 surfaces of the top and two sides of the air-floating short guide rail slide block are provided with air-floating cushions.
Specifically, the principle of the balance hanging type gravity compensation is that the suspension device and the air floatation guide rail device are in rigid-flexible coupling connection through rigid-flexible coupling hanging; the high-precision tension sensor and the high-rigidity tension spring are matched, the unloading precision of the high-precision tension sensor is better than 1%, the fluctuation of the hanging force can be self-adapted in the unfolding process of the antenna, the hanging force can be monitored in real time through ground equipment, and the actual gravity compensation of the loaded antenna is realized;
and the real-time monitoring of the hanging force is carried out through the ground tension sensor, so that the actual gravity compensation of the load antenna is realized. The tension sensor at the hanging connection position is used for real-time hanging force adjustment and unloading, and the ground tension sensor display is combined for force display and accurate adjustment.
Specifically, the suspension device includes: the device comprises a guide rail mounting plate, an adjusting assembly, a tension sensor, an upper cross beam, a high-rigidity spring, a mass center adjuster, a suspension cross beam and an antenna connecting rod;
the guide rail mounting plate is connected with the bottom surface of the air-floatation short guide rail sliding block through a screw; the guide rail mounting plate is connected with the adjusting assembly; the adjusting assembly is connected with the tension sensor, and the tension sensor is connected with the upper cross beam; the upper cross beam is connected with the high-stiffness spring; the high-stiffness spring is connected with the mass center adjuster; the mass center adjuster is connected with the suspension cross beam; the suspension cross beam is connected with the plurality of antenna connecting rods.
Specifically, the hanger includes the concatenation module of the predetermined quantity in top and the supporting leg of predetermined quantity, as shown in fig. 5, indicates in the dotted line frame that 4 groups cuboid structures are 4 groups of concatenation modules, and the below is 8 groups of supporting legs.
Specifically, the air pipe follow-up device comprises a steel wire rope connecting rod, a steel wire rope, an air pipe and an air pipe connecting ring; the steel wire rope connecting rod is arranged on the mounting blocks at two ends of the air floatation long guide rail and the air floatation short guide rail and is in a vertical state; the top of the steel wire rope connecting rod is provided with a ring buckle, and the steel wire rope is straightened and fixed through the ring buckle; the plurality of air pipe connecting rings are hung on the steel wire rope, and the air pipes penetrate into the air pipe connecting rings to ensure that the air pipes cannot sag.
According to the large heavy-load air suspension unfolding test method provided by the invention, the large heavy-load air suspension unfolding test device is used for executing the following steps:
step M1: carrying out butt joint installation on the suspension bracket and moving the suspension bracket to an expansion station;
step M2: hoisting the air floatation long guide rail to a suspension bracket, and adjusting the straightness, levelness, parallelism and guide rail spacing of the long guide rail;
step M3: hoisting the air floatation short guide rail to the air floatation long guide rail, and adjusting the levelness of the air floatation short guide rail;
step M4: after the installation is finished, carrying out a simulated counterweight test, carrying out a load test with preset weight for multiple times by a single point, and recording the running state of the air floatation guide rail and the friction force under different loads so as to enable the friction force to meet the preset requirement;
step M5: mounting a hanging device below each group of air floatation short guide rails;
step M6: moving the satellite to an unfolding station, adjusting the posture, and meeting the preset index requirement;
step M7: butting and adjusting the hanging device and the antenna plate, and carrying out mass center adjustment and gravity unloading;
step M8: retesting and adjusting the satellite attitude to enable the satellite attitude to meet the preset index requirement in a full-load state;
step M9: and (5) carrying out antenna test.
Specifically, the air-float guide rail adopts a laser tracker to measure levelness, straightness, parallelism and long guide rail distance.
Specifically, the step M9 includes: and testing an antenna test, including checking the unfolding locking performance of the antenna, the unfolding time of the antenna and various accurate tests after the antenna is unfolded.
The testing method can adopt a simulated counterweight method preliminarily, namely 4 groups of weights are selected to be applied to 4 hanging point positions respectively, the air floatation running conditions and the corresponding friction force under various states are recorded by testing different masses (0-600 kg) of counterweights, and the test requirements can be met when the air floatation running friction force under 400kg is required to be less than 2N. And finally, combining an actual product to carry out SXX antenna ground expansion performance test, and judging the feasibility and the actual application effect of the large-scale heavy-load air suspension method by observing the operation state and the locking state after expansion of the SXX antenna in the expansion process.
Example 2
Example 2 is a modification of example 1
The invention adopts the principle of gas static pressure and the principle of balance hanging gravity compensation. As the array surface size of movable parts (SXX antenna and solar cell array) in a newly-researched satellite is obviously increased, the shape and surface precision of the SXX antenna is obviously improved, and the weight is increased. Therefore, when the ground is suspended and unfolded, in order to reduce resistance in the unfolding process and improve unloading precision in the unfolding process, the air static pressure effect principle is adopted to simulate an in-orbit microgravity environment, and an unfolding test environment with near-zero friction force is provided for a large-scale load antenna. The actual mass of the load antenna is compensated by adopting a hanging balanced gravity compensation method, and the unloading precision during the ground expansion test is improved.
The principle of gas static pressure is as follows: taking an SXX antenna as an example, the surface of the SXX antenna is vertically arranged, 1 hoisting point passing through the center of mass is arranged on each SXX antenna plate, a microgravity environment when the SXX antenna is unfolded is established through a top air-floating long guide rail, an air-floating short guide rail, an air-floating sliding block, an air pipe follow-up device and the like, the resistance of the unfolding process is not more than 2N under the load of 400kg, and the requirement of two-dimensional motion in the horizontal direction of the SXX antenna is met. The principle of hanging balance type gravity compensation is as follows: through the design of hanging of the rigid-flexible coupling, carry out rigid-flexible coupling with top air supporting device and bottom antenna and be connected, be equipped with high accuracy tension sensor and high rigidity extension spring, its uninstallation precision can be superior to 1% to can carry out hanging force real time monitoring through ground equipment, realize the actual gravity compensation to the load antenna, and to the adjustment control of the actual barycenter position of SXX antenna, verify better that product ground expandes and locking performance.
As shown in fig. 1 to 3, an SXX antenna air suspension expansion test is taken as an example, and the test apparatus includes: four major parts of a suspension bracket, an air floatation guide rail system, a hanging device and an air pipe follow-up device. The suspension bracket mainly comprises 4 groups of splicing modules at the top and 8 groups of supporting legs. The air-floating guide rail system mainly comprises an air-floating long guide rail, an air-floating short guide rail, an air-floating slide block, an air-floating cushion and corresponding accessory components. The hanging device mainly comprises a gravity adjusting device, a mass center adjuster, a high-precision tension sensor, a hanging force detection device, a high-rigidity tension spring, an antenna connecting rod and the like. The air pipe follow-up device is in butt joint with mounting plates at two ends of the long guide rail and the short guide rail and is positioned above the guide rails, each air floating guide rail is provided with one air pipe follow-up device, the air pipe follow-up device mainly comprises a steel wire rope connecting rod, a steel wire rope, air pipes, an air pipe connecting ring and the like, the air pipes are distributed and fixed on the steel wire rope connecting ring, and the trend of the air pipes can be controlled and the interference between the air pipes and the guide rail slide block can be prevented in the operation process of the air floating guide rails. The whole set of test device mainly adopts an air floatation suspension method to carry out the whole-star-level expansion test of the SXX antenna.
The steps of the whole test method are as follows: firstly, butt-joint installation is carried out on a suspension bracket and the suspension bracket is moved to an unfolding station, then an air-floatation long guide rail is hoisted to the suspension bracket, and the straightness, levelness, parallelism and guide rail interval of the long guide rail are adjusted; hoisting the air-floatation short guide rail to the air-floatation long guide rail, and adjusting the levelness of the air-floatation short guide rail; carrying out a simulated counterweight test, carrying out 100kg, 200kg, 300kg and 400kg load tests at a single point, and recording the running state of the air floatation guide rail and the friction force under different loads so as to meet the design requirement that the friction force is less than 2N; mounting a hanging device below each group of air floatation short guide rails in advance; moving the satellite to an unfolding station, and adjusting the posture to meet the index requirement; then, the hanging device and the antenna plate are in butt joint adjustment, and center of mass adjustment and gravity unloading are carried out; then, retest adjustment is carried out on the satellite attitude so that the satellite attitude meets the index requirement in a full-load state; and performing an SXX antenna expansion test, and checking the SXX antenna expansion locking performance, the SXX antenna expansion time, various precision tests after the expansion and the like.
Furthermore, the rigidity and the stability of the suspension bracket need to meet the requirements of concentrated force and distributed force load, and certain stability requirements are met.
Furthermore, the air-float guide rail adopts a laser tracker to measure levelness, straightness, parallelism and long guide rail distance, and the parallelism of the combined guide rail is less than or equal to 0.2mm/4500mm; the straightness of a single guide rail is less than or equal to 0.1mm/4500mm; the levelness of the combined guide rail is less than or equal to 0.1mm/4500mm; the levelness of a single guide rail is less than or equal to 0.1mm/2200mm; the distance between the long guide rails is 1800 +/-1 mm.
Furthermore, the friction test between the air-floating guide rail and the bearing test is an important factor influencing the repeatability of the unfolding process, and the friction resistance of the whole system in the unfolding process needs to be analyzed and tested. And (3) pulling the simulated balance weight by using an electronic dynamometer, wherein the indication number on the electronic dynamometer is the sliding friction force of the air-floatation guide rail, replacing 4 grades of balance weights, observing the running state of the air-floatation guide rail, and finally requiring that the full-stroke friction force of the air-floatation guide rail under the load of 400kg is less than 2N.
Further, the attitude of the satellite is adjusted in a no-load mode, and is tested and adjusted according to the no-load state, so that the requirement of the satellite meets the requirement of a design index.
Further, the SXX antenna quality and the mass center position are adjusted and tested, the actual quality of a product provided by a design file is added with the follow-up quality of the unfolding tool, the unloading quality of each plate is monitored and adjusted in real time by using the tension sensor, and the mass center position is adjusted and controlled within +/-0.2 mm of the actual mass center by adjusting the mass center adjuster of the hanging device.
Furthermore, retest adjustment is carried out on the attitude of the satellite, test adjustment is carried out according to the full load state, and the requirement meets the requirement of a design index.
Further, the SXX antenna confirms the state before expansion, and confirms the indexes of the air floatation suspension expansion tool, mechanism cable connection, existence of surplus objects, star bodies, factory air sources, air supply pressure and the like one by one.
Furthermore, the test of the expansion performance of the SXX antenna can evaluate the expansion performance of the SXX antenna to meet the design index requirement by observing the expansion telemetering signals of the antenna, judging whether the expansion process is stable or not through hooking or not and expanding the hinge locking performance after the expansion in place.
Furthermore, the antenna unfolding precision is measured, the flatness is fitted by adopting an antenna array target point through photogrammetry, and the pointing precision of the antenna can be measured by using a laser tracker.
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 those skilled in the art within the scope of the appended claims without departing from the spirit of the invention
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
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 (5)
1. The utility model provides a large-scale heavy load air supporting hangs expandes test device which characterized in that includes: the air-float guide rail device, the air pipe follow-up device, the suspension bracket and the suspension device;
the air pipe follow-up devices are distributed along the outer side or the upper part of the air floatation guide rail in the air floatation guide rail device and are connected with mounting blocks at two ends of the air floatation guide rail, and each air floatation guide rail is provided with a set of air pipe follow-up device;
the air floatation guide rail device is arranged on the suspension bracket; the suspension device is connected with the air floatation guide rail device;
the air-floatation guide rail device adopts a gas static pressure effect principle to simulate an on-orbit microgravity environment and provides an expansion test environment with near-zero friction force for a large-scale load antenna;
the suspension device compensates the actual mass of the load antenna by adopting a hanging balanced gravity compensation method;
the air-floating guide rail device comprises: the air-float long guide rail slide block, the air-float long guide rail, the air-float short guide rail and the air-float short guide rail slide block;
a preset air-floating long guide rail sliding block is arranged on the two parallel air-floating long guide rails in a mirror image manner; the air-floatation short guide rails are connected through the air-floatation long guide rail sliding blocks;
the air-floating short guide rail sliding block is arranged at the middle point of the air-floating short guide rail;
the air-floating guide rail device is formed by a pressure-equalizing rigid air film formed after air is ventilated by the top and the peripheral air-floating pads of the air-floating slide block through the combination of the air-floating guide rail and the air-floating slide block, so that friction-free two-dimensional motion under heavy load is realized;
the suspension device is in rigid-flexible coupling connection with the air-floatation guide rail device, and the suspension force is monitored in real time through a ground tension sensor, so that the actual gravity compensation of the load antenna is realized;
the suspension device includes: the device comprises a guide rail mounting plate, an adjusting assembly, a tension sensor, an upper cross beam, a high-rigidity spring, a mass center adjuster, a suspension cross beam and an antenna connecting rod;
the guide rail mounting plate is connected with the air-floatation short guide rail sliding block; the guide rail mounting plate is connected with the adjusting component; the adjusting assembly is connected with the tension sensor, and the tension sensor is connected with the upper cross beam; the upper cross beam is connected with the high-stiffness spring; the high-stiffness spring is connected with the mass center adjuster; the mass center adjuster is connected with the suspension cross beam; the suspension cross beam is connected with a plurality of antenna connecting rods;
the air pipe follow-up device comprises a steel wire rope connecting rod, a steel wire rope, an air pipe and an air pipe connecting ring; the steel wire rope connecting rod is arranged on the mounting blocks at two ends of the air floatation long guide rail and the air floatation short guide rail and is in a vertical state; the top of the steel wire rope connecting rod is provided with a ring buckle, and the steel wire rope is straightened and fixed through the ring buckle; the plurality of air pipe connecting rings are hung on the steel wire rope, and the air pipes penetrate into the air pipe connecting rings to ensure that the air pipes cannot sag.
2. The large heavy-duty air suspension deployment test device according to claim 1, wherein said suspension frame comprises a predetermined number of top splicing modules and a predetermined number of support legs.
3. A large heavy-duty air-suspension deployment test method, characterized in that the large heavy-duty air-suspension deployment test device according to any one of claims 1-2 is used to perform the following steps:
step M1: carrying out butt joint installation on the suspension bracket and moving the suspension bracket to an expansion station;
step M2: hoisting the air floatation long guide rail to a suspension bracket, and adjusting the straightness, levelness, parallelism and guide rail spacing of the long guide rail;
step M3: hoisting the air-flotation short guide rail to the air-flotation long guide rail, and adjusting the levelness of the air-flotation short guide rail;
step M4: after the installation is finished, carrying out a simulated counterweight test, carrying out a load test with preset weight for multiple times by a single point, and recording the running state of the air floatation guide rail and the friction force under different loads so as to enable the friction force to meet the preset requirement;
step M5: mounting a hanging device below each group of air floatation short guide rails;
step M6: moving the satellite to an unfolding station, adjusting the posture, and meeting the preset index requirement;
step M7: butting and adjusting the hanging device and the antenna plate, and carrying out mass center adjustment and gravity unloading;
step M8: retesting and adjusting the satellite attitude to enable the satellite attitude to meet the preset index requirement in a full-load state;
step M9: and (5) performing an antenna test.
4. The large heavy-duty air suspension deployment test method according to claim 3, wherein said air rail uses a laser tracker for levelness, straightness, parallelism, and long rail spacing measurements.
5. The large heavy-duty air suspension deployment test method of claim 3, wherein said step M9 comprises: and testing an antenna test, including checking the unfolding locking performance of the antenna, the unfolding time of the antenna and various accurate tests after the antenna is unfolded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011272308.3A CN112340071B (en) | 2020-11-13 | 2020-11-13 | Large-scale heavy-load air floatation suspension expansion test device and test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011272308.3A CN112340071B (en) | 2020-11-13 | 2020-11-13 | Large-scale heavy-load air floatation suspension expansion test device and test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112340071A CN112340071A (en) | 2021-02-09 |
| CN112340071B true CN112340071B (en) | 2023-03-17 |
Family
ID=74363775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011272308.3A Active CN112340071B (en) | 2020-11-13 | 2020-11-13 | Large-scale heavy-load air floatation suspension expansion test device and test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112340071B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114955022A (en) * | 2021-02-19 | 2022-08-30 | 北京九天微星科技发展有限公司 | Zero-gravity unfolding device and unfolding method |
| CN114955012A (en) * | 2021-02-19 | 2022-08-30 | 北京九天微星科技发展有限公司 | Solar cell array unfolding device |
| CN113358849B (en) * | 2021-05-20 | 2022-09-20 | 广东工业大学 | Simulation dynamic rock breaking sampling non-vertical installation system and vertical installation system |
| CN113619818B (en) * | 2021-08-16 | 2023-02-03 | 哈尔滨工业大学 | Six-degree-of-freedom microgravity test system based on air floatation pulley |
| CN114056608A (en) * | 2021-11-30 | 2022-02-18 | 北京卫星制造厂有限公司 | Counter weight mechanism and zero-gravity unfolding experimental device |
| CN114408230B (en) * | 2022-01-20 | 2023-03-31 | 浙江工商大学 | Gravity unloading system of multiple following movable air-floating trolleys |
| CN114922935B (en) * | 2022-05-18 | 2023-12-08 | 佛山市华道超精科技有限公司 | Rigid-flexible coupling position force composite actuating mechanism and constant force control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1321455A (en) * | 1970-03-17 | 1973-06-27 | Dunlop Holdings Ltd | Boarding arrangements for inflatable craft |
| JP2004331008A (en) * | 2003-05-12 | 2004-11-25 | Fuji Heavy Ind Ltd | Inflatable structure |
| CN106114914A (en) * | 2016-08-12 | 2016-11-16 | 浙江工业大学 | A kind of flexible hanging device for the hanging of sun wing plate |
| CN109625344A (en) * | 2018-12-12 | 2019-04-16 | 上海卫星装备研究所 | Microgravity compensation control system is unfolded in flexible extensions arm integration |
| CN110901966A (en) * | 2019-11-29 | 2020-03-24 | 北京卫星制造厂有限公司 | Air floatation suspension type gravity unloading device for space deployable mechanism |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060270290A1 (en) * | 2005-05-25 | 2006-11-30 | TELLEW John | Lightweight personal rescue tube flotation device |
| CN101905748B (en) * | 2010-07-09 | 2013-03-06 | 哈尔滨工业大学 | Gas-filled unfolded article storing cabin |
| CN203178051U (en) * | 2012-12-31 | 2013-09-04 | 浙江工业大学 | Ultralow-frequency modal test gravitational equilibrium system |
| CN103466109B (en) * | 2013-09-05 | 2016-12-07 | 哈尔滨工业大学 | A kind of space microgravity environment ground simulation experiment device |
| CN104318828B (en) * | 2014-10-10 | 2016-08-24 | 北京卫星制造厂 | A kind of zero gravity experimental system for Spatial Multi-Dimensional development mechanism |
| CN109515770B (en) * | 2018-12-13 | 2021-09-28 | 上海宇航系统工程研究所 | High-bearing low-friction suspension type antenna unloading device |
-
2020
- 2020-11-13 CN CN202011272308.3A patent/CN112340071B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1321455A (en) * | 1970-03-17 | 1973-06-27 | Dunlop Holdings Ltd | Boarding arrangements for inflatable craft |
| JP2004331008A (en) * | 2003-05-12 | 2004-11-25 | Fuji Heavy Ind Ltd | Inflatable structure |
| CN106114914A (en) * | 2016-08-12 | 2016-11-16 | 浙江工业大学 | A kind of flexible hanging device for the hanging of sun wing plate |
| CN109625344A (en) * | 2018-12-12 | 2019-04-16 | 上海卫星装备研究所 | Microgravity compensation control system is unfolded in flexible extensions arm integration |
| CN110901966A (en) * | 2019-11-29 | 2020-03-24 | 北京卫星制造厂有限公司 | Air floatation suspension type gravity unloading device for space deployable mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112340071A (en) | 2021-02-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112340071B (en) | Large-scale heavy-load air floatation suspension expansion test device and test method | |
| CN110895186B (en) | Vibration system comprising a plurality of vibration tables and vibration test method | |
| CN108001713B (en) | On-orbit separation ground test device and detection method for double-star combined spacecraft | |
| US10746627B2 (en) | Multiple configuration wind tunnel balance and method for converting the wind tunnel balance | |
| CN102853978B (en) | Testing device and method for three-dimensional static stiffness loading of machine tool | |
| EP2613134B1 (en) | System and method for aligning a test article with a load | |
| CN109515770B (en) | High-bearing low-friction suspension type antenna unloading device | |
| CN109115510B (en) | Six-component force test bed and error determination method thereof | |
| CN113525733B (en) | Six-degree-of-freedom microgravity test system with double-layer structure | |
| CN113619818A (en) | Six-degree-of-freedom microgravity test system based on air floatation pulley | |
| CN117091800B (en) | Full-automatic six-degree-of-freedom balance calibration system for low-temperature balance calibration | |
| CN113029415A (en) | Non-interference multi-component solid rocket engine thrust measurement system and installation measurement method | |
| CN109551521A (en) | Six-degree-of-freedom parallel robot rigidity weak link apparatus for quantitatively and method | |
| CN112985694A (en) | Method and system for balancing mass center of triaxial air bearing table | |
| CN113291489B (en) | Loading device and method suitable for large-deformation undercarriage structure static test | |
| CN107246862B (en) | Gravity balance method for ground test of heavy satellite-borne deployable antenna | |
| CN114988280B (en) | Satellite ground test flexible support zero-stress suspension device and suspension method | |
| CN112461259B (en) | Gravity balancing device for large-caliber space camera | |
| Tao et al. | Research on automatic leveling device of suspension and elevation Type | |
| CN116062198B (en) | Virtual-real fusion ground test system and method for ultra-large aerospace structure | |
| CN118089644A (en) | Level measurement method and device suitable for large-scale aircraft | |
| RU2797387C1 (en) | Stand for measuring the mass, coordinates of the centers of mass and moments of inertia of products | |
| CN111735597B (en) | Drop interaction test stand suitable for nuclear power equipment anti-seismic safety inspection | |
| CN115077878A (en) | Antenna horizontal unfolding test device and method | |
| CN118457951A (en) | Ground lunar vehicle gravity balancing device based on multi-rotor unmanned aerial vehicle suspension |
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 |