CN112326118A - Tool and method for testing rapid quality characteristics of satellites in batch production - Google Patents

Tool and method for testing rapid quality characteristics of satellites in batch production Download PDF

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Publication number
CN112326118A
CN112326118A CN202011155641.6A CN202011155641A CN112326118A CN 112326118 A CN112326118 A CN 112326118A CN 202011155641 A CN202011155641 A CN 202011155641A CN 112326118 A CN112326118 A CN 112326118A
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China
Prior art keywords
state
tool
positioning
satellite
support frame
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CN202011155641.6A
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Chinese (zh)
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CN112326118B (en
Inventor
杨立国
赵相禹
张雷
谷松
高飞
姚智
贾齐
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Chang Guang Satellite Technology Co Ltd
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Chang Guang Satellite Technology Co Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M1/00—Testing static or dynamic balance of machines or structures
    • G01M1/12—Static balancing; Determining position of centre of gravity
    • G01M1/122—Determining position of centre of gravity
    • G01M1/125—Determining position of centre of gravity of aircraft
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M1/00—Testing static or dynamic balance of machines or structures
    • G01M1/02—Details of balancing machines or devices
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M1/00—Testing static or dynamic balance of machines or structures
    • G01M1/10—Determining the moment of inertia

Abstract

The invention provides a tool and a testing method for rapid quality characteristic testing of satellites in batch production, wherein the tool comprises an outer supporting frame, an inner supporting frame, a first shafting, a second shafting, a third shafting, a transfer plate, a positioning block, a horizontal stop block and a vertical stop block, wherein the inner supporting frame is arranged in the outer supporting frame, rotates around the first shafting and the second shafting, and rotates around the third shafting; the included angle between the outer support frame and the inner support frame is 0 degree through the matching positioning of the horizontal stop block and the positioning block; the vertical stop block and the positioning block are matched and positioned to realize that the included angle between the inner support frame and the outer support frame is 90 degrees; the adapter plate is positioned by installing a positioning pin on the adapter plate. The invention has the advantages of high testing efficiency, simple structure, small size, high testing precision, strong universality and safe and reliable operation, can test the mass, the mass center and the rotational inertia parameters of the satellite after the satellite is installed once, greatly improves the testing efficiency, and is particularly suitable for the mass satellite quality characteristic testing requirements.

Description

Tool and method for testing rapid quality characteristics of satellites in batch production
Technical Field
The invention belongs to the technical field of spaceflight, and particularly relates to a tool and a testing method for testing the rapid quality characteristics of mass-produced satellites.
Background
Vertical frock and L type frock need be used to traditional quality characteristic test equipment, the satellite at first need be hung to vertical frock with the overhead traveling crane, carry out X, Y orientation barycenter and Z axle rotational inertia's measurement, then dismantle whole star and hang to install on L type frock, test Z is to barycenter and X, Y orientation inertia, the satellite needs to switch between two frocks, through hoist and mount many times, need many people to cooperate, a large amount of operating time consumes at the installation of L type support, upset and dismantlement in-process, be unfavorable for improving the test accuracy, work efficiency and assurance production safety. The test mode is more suitable for the current single-satellite or small-batch test, and when the number of the satellites reaches the batch scale, the mode is difficult to match the productivity.
Disclosure of Invention
In view of the above, the invention aims to provide a tool and a test method for rapid quality characteristic test of mass-produced satellites, which have the advantages of high test efficiency, simple structure, small size, high test precision, strong universality and safe and reliable operation, and can be used for measuring the quality, the mass center and the rotational inertia parameters of the satellites after the satellites are installed once, so that the test efficiency is greatly improved, and the tool and the test method are particularly suitable for mass quality characteristic test requirements of the satellites.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a tool for testing the rapid quality characteristics of satellites in batch production comprises an outer supporting frame, an inner supporting frame, a first shaft system, a second shaft system, a third shaft system, a transfer plate, a positioning block, a horizontal stop block and a vertical stop block, wherein the outer supporting frame comprises a horizontal supporting underframe and a vertical stand;
the top of an inner vertical frame on the left side of the inner supporting frame is connected with the top of a vertical frame on the left side of the outer supporting frame through a first shaft system, the top of the inner vertical frame on the right side of the inner supporting frame is connected with the top of a vertical frame on the right side of the outer supporting frame through a second shaft system, the first shaft system and the second shaft system are coaxially arranged, the inner supporting frame rotates around the first shaft system and the second shaft system, a third shaft system is arranged in the middle of an inner supporting underframe of the inner supporting frame, a transfer plate is arranged at the top of the third shaft system, and the transfer plate rotates;
the positioning blocks are respectively arranged at the same height positions of the front side and the rear side of the two vertical frames, the horizontal check blocks and the vertical check blocks are both arranged on the inner vertical frames, and the included angle between the outer support frame and the inner support frame is 0 degree through the matching positioning of the horizontal check blocks and the positioning blocks; the vertical stop block and the positioning block are matched and positioned to realize that the included angle between the inner support frame and the outer support frame is 90 degrees; the adapter plate is positioned by installing a positioning pin on the adapter plate.
Furthermore, the locating piece includes locating plate and location arch, the central point department at the locating plate is fixed to the location arch, the locating plate passes through the fix with screw on the grudging post.
Furthermore, horizontal dog includes the dog body, set up on the dog body with the protruding complex slotted hole in location of locating piece and with set screw complex screw hole, be equipped with the ladder in dog body and locating plate cooperation department, just realize the location of interior support frame in outer support frame through the cooperation of locating piece and horizontal dog and front and back both sides to the set screw who arranges.
Furthermore, a containing through groove for containing the vertical frame is formed in one side of the vertical stop block, a mounting hole matched with the positioning protrusion is formed in the vertical stop block, a threaded hole matched with the positioning screw is formed in the groove wall for containing the through groove, and the positioning of the inner support frame in the outer support frame is realized through the matching of the positioning block and the vertical stop block and the positioning screws arranged in pairs on the left side and the right side of the positioning block.
Furthermore, the adapter plate comprises six satellite mounting positioning holes corresponding to six positioning pins, the adapter plate is positioned with the positioning pins 2 through the positioning pins 1 in a 0-degree state, is positioned with the positioning pins 4 through the positioning pins 3 in a 90-degree state, and is positioned with the positioning pins 6 through the positioning pins 5 in a 180-degree state and is fixed on the inner support frame through screws.
Furthermore, the first shaft system and the second shaft system are identical in structure and respectively comprise a first positioning shaft, two angular contact ball bearings, an outer supporting seat, a first bearing end cover and an inner supporting seat, the two angular contact ball bearings are arranged in the outer supporting seat in a back-to-back mode, the first positioning shaft is arranged on an inner ring of the angular contact ball bearing, one side of the angular contact ball bearing is positioned through a shaft shoulder, the other side of the angular contact ball bearing is fixed through an adjusting first bearing end cover, and the inner supporting seat is positioned with the first positioning shaft through a positioning boss and locked through a.
Furthermore, the third shaft system comprises a third positioning shaft, a double-row angular contact ball bearing, a second bearing end cover and a third bearing end cover, wherein the double-row angular contact ball bearing is arranged in a middle disc of the inner support frame, one end of the double-row angular contact ball bearing is positioned through a three-shaft shoulder of the positioning shaft, and the inner ring and the outer ring at the other end of the double-row angular contact ball bearing respectively realize the adjustment of the bearing clearance through adjusting the second bearing end cover.
Furthermore, the outer support frame and the inner support frame are formed by welding aluminum alloy sections.
A test method for a tool for testing the rapid quality characteristics of satellites in batches comprises the following steps when testing the quality characteristics of sailboards of satellites in a folded state or an unfolded state:
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame, and connecting the tool with the test table through a screw;
(2) installing a positioning block and a horizontal stop block, and adjusting the included angle between the inner support frame and the outer support frame to be 0 degree by adjusting the position of a positioning screw; rotating the adapter plate, positioning the adapter plate through a positioning pin 5 and a positioning pin 6, and locking the adapter plate and the inner support frame through a screw, adjusting the tool to be in a state of 0 degrees and 180 degrees of the adapter plate, recording the state as state 2, and measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) detaching the positioning pin 5, the positioning pin 6 and the screw, rotating the adapter plate by 180 degrees, positioning the adapter plate by the positioning pin 1 and the positioning pin 2, locking the adapter plate with the inner support frame by the screw, adjusting the tool to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate, recording the state as a state 1, measuring and recording the quality characteristic parameters of the no-load tool in the state 1;
(4) dismantling the horizontal stop block, manually turning the inner support frame around the first shafting and the second shafting by 90 degrees, installing the vertical stop block, adjusting the included angle between the inner support frame and the outer support frame to 90 degrees by adjusting the position of the positioning screw, adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of the adapter plate', recording the state as state 3, and measuring and recording the quality characteristic parameters of the no-load tool in the state 3;
(5) the positioning pin 1, the positioning pin 2 and the screw are disassembled, the adapter plate rotates 90 degrees clockwise, is positioned by the positioning pin 3 and the positioning pin 4 and is locked with the inner support frame by the screw, the tool is adjusted to be in a state of '90 degrees of the inner support frame and 90 degrees of the adapter plate', the state is marked as state 4, and the quality characteristic parameter of the no-load tool in the state 4 is measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate, and locking the satellite supporting legs through screws; testing and recording parameters of the satellite-X mass center and the satellite-Y mass center in the state 2;
(8) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(9) adjusting the tool to a state 3, testing and recording the satellite + Z centroid parameters in the state 1;
(10) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(11) keeping the tool in the state 3 unchanged, testing and recording parameters of a satellite + Z mass center and a rotating inertia Ix around an X axis in the state 3;
(12) adjusting the tool to a state 4, testing and recording the parameters of the rotational inertia Iy of the satellite in the state 4 around the Y axis;
(13) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(14) adjusting the tool to a state 2, and testing and recording parameters of a satellite-X mass center, a satellite-Y mass center and a rotational inertia Iz around a Z axis in the state 2;
(15) after the test is finished, the satellite is lifted and separated from the tool, and the test bench is restored to the initial state.
A test method for a tool for testing the rapid quality characteristics of satellites in batch comprises the following steps of:
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame, and connecting the tool with the test table through a screw;
(2) installing a positioning block and a horizontal stop block, and adjusting the included angle between the inner support frame and the outer support frame 1 to 0 degree by adjusting the position of a positioning screw; rotating the adapter plate, positioning the adapter plate through a positioning pin 5 and a positioning pin 6, and locking the adapter plate and the inner support frame through a screw, adjusting the tool to be in a state of 0 degrees and 180 degrees of the adapter plate, recording the state as state 2, and measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) detaching the positioning pin 5, the positioning pin 6 and the screw, rotating the adapter plate by 180 degrees, positioning the adapter plate by the positioning pin 1 and the positioning pin 2, locking the adapter plate with the inner support frame by the screw, adjusting the tool to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate, recording the state as a state 1, measuring and recording the quality characteristic parameters of the no-load tool in the state 1;
(4) dismantling the horizontal stop block, manually turning the inner support frame around the first shafting and the second shafting by 90 degrees, installing the vertical stop block, adjusting the included angle between the inner support frame and the outer support frame to 90 degrees by adjusting the position of the positioning screw, adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of the adapter plate', recording the state as state 3, and measuring and recording the quality characteristic parameters of the no-load tool in the state 3;
(5) the positioning pin 1, the positioning pin 2 and the screw are disassembled, the adapter plate 3 is rotated by 90 degrees clockwise, the positioning pin 3 and the positioning pin 4 are positioned and locked with the inner support frame through the screw, the tool is adjusted to be in a state of 90 degrees of the inner support frame and 90 degrees of the adapter plate, the state is marked as a state 4, and the quality characteristic parameters of the no-load tool in the state 4 are measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate, and locking the satellite supporting legs through screws; satellite-X under test State 2Harvesting machineCenter of mass, -YHarvesting machineRecording the centroid parameters;
(8) adjusting the tool to the state 1, testing the satellite + X in the state 1Harvesting machineCenter of mass, + YHarvesting machineRecording the centroid parameters;
(9) adjusting the tool to state 3, testing the satellite + Z in state 3Harvesting machineRecording the centroid parameters;
(10) unfolding and locking the satellite sailboard, and testing the satellite + Z in the state 3Exhibition (or exhibition)Recording the centroid parameters;
(11) adjusting the tool to the state 1, testing the satellite + X in the state 1Exhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Recording the centroid parameters;
(12) adjusting the tool to the state 2, and testing the satellite-X in the state 2Exhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(13) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(14) keeping the tool unchanged in state 2 and testing the satellite-X in state 2Exhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(15) adjusting the tool to the state 1, testing the satellite + X in the state 1Exhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Center of mass and rotational inertia around Z axis Iz exhibitionParameters are recorded;
(16) adjusting the tool to 3 state and testing 3 stateSatellite + ZExhibition (or exhibition)Center of mass and rotational inertia around X axis IX exhibitionParameters are recorded;
(17) adjusting the tool to a state 4, and testing the rotational inertia I of the satellite in the state 4 around the Y axisY exhibitionParameters are recorded;
(18) folding and locking the satellite sailboard, and testing the rotational inertia I of the satellite around the Y axis in the state 4y receiveParameters are recorded;
(19) adjusting the tool to state 3, testing the satellite + Z in state 3Harvesting machineCenter of mass and rotational inertia around X axis Ix is receivedParameters are recorded;
(20) adjusting the tool to the state 1, testing the satellite + X in the state 1Harvesting machineCentroid sum + YHarvesting machineRecording the centroid parameters;
(21) adjusting the tool to the state 2, and testing the satellite-X in the state 2Harvesting machineCenter of mass, -YHarvesting machineCenter of mass and moment of inertia about Z axis Iz is receivedParameters are recorded;
(22) after the test is finished, the satellite is lifted and separated from the test equipment, and the test bench is restored to the initial state.
Compared with the prior art, the tool for the rapid quality characteristic test of the mass production satellites has the following advantages: the satellite mass and mass measuring device has the advantages of high testing efficiency, simple structure, small size, high testing precision, strong universality, safe and reliable operation and the like, the mass center and the rotational inertia parameters of the satellite can be measured after the satellite is installed for one time, the efficiency is improved by three times, the testing safety is greatly improved, and the satellite mass and mass measuring device is particularly suitable for the mass satellite quality characteristic testing requirements.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic perspective view of a tool for testing rapid quality characteristics of satellites in batch production in a certain state according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of a tool for testing rapid quality characteristics of satellites in batch production in another state according to an embodiment of the present invention;
FIG. 3 is a cross-sectional view of a tool for rapid quality characterization of a batch satellite according to an embodiment of the present invention;
FIG. 4 is an enlarged view taken at A of FIG. 1;
FIG. 5 is an enlarged view of FIG. 2 at B;
FIG. 6 is a cross-sectional view of a first shaft of the present invention;
FIG. 7 is a sectional view of a third shaft assembly according to the present invention;
FIG. 8 is a schematic structural view of the horizontal stopper of the present invention;
FIG. 9 is a schematic view of the vertical stopper according to the present invention;
FIG. 10 is a schematic view of the location of the locating pin of the present invention;
FIG. 11 is a schematic view of the operation of the testing apparatus of the present invention; wherein (a) state 1: 0 degree of the inner support frame and 0 degree of the adapter plate; (b) state 2: 0 degree of the inner support frame and 180 degrees of the adapter plate; (c) state 3: the inner support frame is 90 degrees, and the adapter plate is 0 degree; (d) and 4: the inner support frame is 90 degrees, and the adapter plate is 90 degrees;
FIG. 12 is a flow chart of the present invention for testing the quality characteristics of a model satellite.
Description of reference numerals:
1-an outer supporting frame, 2-a third shaft system, 3-an adapter plate, 4-an inner supporting frame, 5-a second shaft system, 7-a first shaft system, 8-a positioning block, 9-a positioning screw, 10-a horizontal stop block, 11-a vertical stop block, 12-an angular contact ball bearing, 13-a first bearing end cover, 14-an outer supporting seat, 15-a first positioning shaft, 16-an inner supporting seat, 17-a second bearing end cover, 18-a third bearing end cover, 19-a third positioning shaft, 20-a double-row angular contact ball bearing, 21-a stop block body, 22-a long circular hole, 23-an accommodating through groove and 24-a mounting hole, 25-positioning pins 1, 26-positioning pins 2, 27-positioning pins 3, 28-positioning pins 4, 29-positioning pins 5, 30-positioning pins 6.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-10, a tool for testing rapid mass characteristics of mass produced satellites includes an outer support frame 1, an inner support frame 4, a first shafting 7, a second shafting 5, a third shafting 2, an adapter plate 2, a positioning block 8, a horizontal stop block 10 and a vertical stop block 11, wherein the outer support frame 1 includes a horizontal support chassis and a vertical stand, the left end and the right end of the horizontal support chassis are respectively fixed with a vertical stand, the inner support frame 4 is arranged in an area surrounded by the horizontal support chassis and the two vertical stands, the inner support frame 4 includes an inner support chassis and two inner vertical stands, and the two inner vertical stands are vertically fixed at the left end and the right end of the inner support chassis;
the top of an inner vertical frame on the left side of the inner supporting frame 4 is connected with the top of a vertical frame on the left side of the outer supporting frame 1 through a first shafting 7, the top of the inner vertical frame on the right side of the inner supporting frame 4 is connected with the top of a vertical frame on the right side of the outer supporting frame 1 through a second shafting 5, the first shafting 7 and the second shafting 5 are coaxially arranged, the inner supporting frame 4 rotates around the first shafting 7 and the second shafting 5 (only 90-degree overturning is performed in actual measurement), a third shafting 2 is installed in the middle of an inner supporting underframe of the inner supporting frame 4, an adapter plate 3 is installed at the top of the third shafting 3, and the adapter plate;
the positioning blocks 8 are respectively arranged at the same height positions of the front side and the rear side of the two vertical frames, the horizontal check blocks 10 and the vertical check blocks 11 are both arranged on the inner vertical frames, and the included angle between the outer support frame 1 and the inner support frame 4 is 0 degree through the matching positioning of the horizontal check blocks 10 and the positioning blocks 8; the vertical stop block 11 and the positioning block 8 are matched for positioning to realize that the included angle between the inner support frame 4 and the outer support frame 1 is 90 degrees; the positioning of the adapter plate 3 is realized by mounting a positioning pin on the adapter plate 3.
The positioning block 8 comprises a positioning plate and a positioning bulge, the positioning bulge is fixed at the center of the positioning plate, and the positioning plate is fixed on the vertical frame through a screw.
The horizontal stop block 10 comprises a stop block body 21, a long round hole 22 matched with the positioning protrusion of the positioning block 8 and a threaded hole matched with the positioning screw 9 are formed in the stop block body 21, a step is arranged at the matching position of the stop block body 21 and the positioning plate, and the positioning of the inner support frame 4 in the outer support frame 1 is realized through the matching of the positioning block 8 and the horizontal stop block 10 and the positioning screws 9 which are arranged on the front side and the rear side.
Offer the logical groove 23 that holds the grudging post in one side of vertical dog 11, be equipped with on vertical dog 11 with the protruding complex mounting hole 24 of location, offer on the cell wall that holds logical groove 23 with set screw 9 complex screw hole, through the cooperation of locating piece 8 and vertical dog 11 and the set screw 9 that the left and right sides was arranged in pairs realize the location of interior support frame in outer braced frame.
The adapter plate 3 comprises six satellite installation positioning holes, the six satellite installation positioning holes correspond to six positioning pins, namely a positioning pin 125, a positioning pin 226, a positioning pin 327, a positioning pin 428, a positioning pin 529 and a positioning pin 630, the adapter plate 3 is positioned with the positioning pin 226 through the positioning pin 125 in a 0-degree state, is positioned with the positioning pin 428 through the positioning pin 327 in a 90-degree state, is positioned with the positioning pin 630 through the positioning pin 529 in a 180-degree state, and is fixed on the inner support frame through screws.
Two locating pins of the same state of location take diagonal distance to arrange, and three 6 locating pins of group, arrange along keysets 3's periphery, the pinhole adopts the mode of limit assembly limit processing, keysets 3 square board, and when keysets 3's location limit (four avris) were parallel with testboard location limit (four avris) under the 1.2.4 circumstances of adjustment state, including braced frame and keysets 3 relevant position configuration beat the cotter hole, realize accurate positioning.
The first shafting 7 and the second shafting 5 are identical in structure and respectively comprise a first positioning shaft 15, two angular contact ball bearings 12, an outer support seat 14, a first bearing end cover 13 and an inner support seat 16, the two angular contact ball bearings 12 are arranged in the outer support seat 14 in a back-to-back mode, the first positioning shaft 15 is arranged on the inner ring of the angular contact ball bearing 12, one side of the angular contact ball bearing 12 is positioned through a shaft shoulder, the other side of the angular contact ball bearing is fixed through the first adjusting bearing end cover 13, and the inner support seat 16 is positioned with the first positioning shaft 15 through a positioning boss and.
The third shaft system 2 comprises a third positioning shaft 19, a double-row angular contact ball bearing 20, a second bearing end cover 17 and a third bearing end cover 18, the double-row angular contact ball bearing 20 is installed in a middle disc of the inner support frame 4, one end of the double-row angular contact ball bearing is positioned through a third positioning shaft 19, and the inner ring and the outer ring at the other end of the double-row angular contact ball bearing respectively realize adjustment of bearing clearance through adjustment of the second bearing end cover 17 and the third bearing end.
The outer supporting frame 1 and the inner supporting frame 4 are both formed by welding aluminum alloy profiles, and sufficient specific strength is provided. A reinforced inclined frame is arranged between the vertical frame and the supporting underframe.
The center of mass of the tool in the Y direction is less than or equal to 20mm in no-load and full-load, and the inner support frame can turn around the first shafting and the second shafting under a small driving moment.
As shown in fig. 11, the tool includes four working states: state 1: the adapter plate is 0 degree, and the inner support frame is 0 degree; state 2: the adapter plate is 180 degrees, and the inner support frame is 0 degree; state 3: the adapter plate is 0 degree, and the inner support frame is 90 degrees; and 4: the adapter plate is 90 degrees, and the inner support frame is 90 degrees.
A test method for a tool for testing the rapid quality characteristics of satellites in batches comprises the following steps when testing the quality characteristics of sailboards of satellites in a folded state or an unfolded state:
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame, and connecting the tool with the test table through a screw;
(2) installing a positioning block and a horizontal stop block, and adjusting the included angle between the inner support frame and the outer support frame to be 0 degree by adjusting the position of a positioning screw; rotating the adapter plate, positioning the adapter plate through a positioning pin 5 and a positioning pin 6, and locking the adapter plate and the inner support frame through a screw, adjusting the tool to be in a state of 0 degrees and 180 degrees of the adapter plate, recording the state as state 2, and measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) detaching the positioning pin 5, the positioning pin 6 and the screw, rotating the adapter plate by 180 degrees, positioning the adapter plate by the positioning pin 1 and the positioning pin 2, locking the adapter plate with the inner support frame by the screw, adjusting the tool to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate, recording the state as a state 1, measuring and recording the quality characteristic parameters of the no-load tool in the state 1;
(4) dismantling the horizontal stop block, manually turning the inner support frame around the first shafting and the second shafting by 90 degrees, installing the vertical stop block, adjusting the included angle between the inner support frame and the outer support frame to 90 degrees by adjusting the position of the positioning screw, adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of the adapter plate', recording the state as state 3, and measuring and recording the quality characteristic parameters of the no-load tool in the state 3;
(5) the positioning pin 1, the positioning pin 2 and the screw are disassembled, the adapter plate rotates 90 degrees clockwise, is positioned by the positioning pin 3 and the positioning pin 4 and is locked with the inner support frame by the screw, the tool is adjusted to be in a state of '90 degrees of the inner support frame and 90 degrees of the adapter plate', the state is marked as state 4, and the quality characteristic parameter of the no-load tool in the state 4 is measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate, and locking the satellite supporting legs through screws; testing and recording parameters of the satellite-X mass center and the satellite-Y mass center in the state 2;
(8) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(9) adjusting the tool to a state 3, testing and recording the satellite + Z centroid parameters in the state 1;
(10) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(11) keeping the tool in the state 3 unchanged, testing and recording parameters of a satellite + Z mass center and a rotating inertia Ix around an X axis in the state 3;
(12) adjusting the tool to a state 4, testing and recording the parameters of the rotational inertia Iy of the satellite in the state 4 around the Y axis;
(13) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(14) adjusting the tool to a state 2, and testing and recording parameters of a satellite-X mass center, a satellite-Y mass center and a rotational inertia Iz around a Z axis in the state 2;
(15) for tests with other requirements (such as testing quality characteristic parameters of the sailboard in the unfolded state), a test link needs to be added in the corresponding step;
(16) after the test is finished, the satellite is lifted and separated from the tool, and the test bench is restored to the initial state.
The quality characteristic parameters of the sailboard in the folded and unfolded state can be tested by repeating the steps of the method.
The quality characteristic parameters of the sailboard in the folded and unfolded state can be tested by the following method, and the test method of the tool for the rapid quality characteristic test of the mass-produced satellites specifically comprises the following steps: as shown in figure 12 of the drawings,
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame 1, and connecting the tool with the test table through a screw;
(2) installing a positioning block 8 and a horizontal stop block 10, and adjusting the included angle between the inner support frame 4 and the outer support frame 1 to 0 degree by adjusting the position of a positioning screw 9; rotating the adapter plate 3, positioning the adapter plate by a positioning pin 5 and a positioning pin 6, and locking the adapter plate with the inner support frame 4 by a screw, adjusting the tool to be in a state of 0 degrees and 180 degrees of the adapter plate, recording the state as a state 2, and measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) detaching the positioning pin 5, the positioning pin 6 and the screw, rotating the adapter plate 3 by 180 degrees, positioning the adapter plate with the positioning pin 1 and the positioning pin 2, and locking the adapter plate with the inner support frame 4 through the screw, adjusting the tool to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate, recording the state as a state 1, and measuring and recording the quality characteristic parameters of the no-load tool in the state 1;
(4) removing the horizontal stop block 10, manually turning the inner support frame 4 by 90 degrees around the first shafting 7 and the second shafting 5, installing a vertical stop block 11, adjusting the included angle between the inner support frame 4 and the outer support frame 1 to 90 degrees by adjusting the position of a positioning screw 9, adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of an adapter plate', recording the state as state 3, measuring and recording the quality characteristic parameters of the no-load tool in the state 3;
(5) the positioning pin 1, the positioning pin 2 and the screw are disassembled, the adapter plate 3 is rotated by 90 degrees clockwise, the positioning pin 3 and the positioning pin 4 are positioned and locked with the inner support frame 4 through the screw, the tool is adjusted to be in a state of '90 degrees of the inner support frame and 90 degrees of the adapter plate', the state is marked as state 4, and the quality characteristic parameters of the no-load tool in the state 4 are measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate 3, and locking the satellite supporting legs through screws; satellite-X under test State 2Harvesting machineCenter of mass, -YHarvesting machineRecording the centroid parameters;
(8) adjusting the tool to a state 1, and testing the satellite + X in the stateHarvesting machineCenter of mass, + YHarvesting machineRecording the centroid parameters;
(9) adjusting the tool to a state 3, and testing the satellite + Z in the stateHarvesting machineRecording the centroid parameters;
(10) unfolding and locking the satellite sailboard, and testing the satellite + Z in the stateExhibition (or exhibition)Recording the centroid parameters;
(11) adjusting the tool to a state 1, and testing the satellite + X in the stateExhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Recording the centroid parameters;
(12) adjusting the tool to a state 2, and testing the satellite-X in the stateExhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(13) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(14) keeping the fixture unchanged in the state 2, and testing the satellite-X in the stateExhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(15) adjusting the tool to a state 1, and testing the satellite + X in the stateExhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Center of mass and rotational inertia around Z axis Iz exhibitionParameters are recorded;
(16) adjusting the tool to a state 3, and testing the satellite + Z in the stateExhibition (or exhibition)Center of mass and rotational inertia around X axis IX exhibitionParameters are recorded;
(17) adjusting the tool to a state 4, and testing the rotational inertia I of the satellite in the state around the Y axisY exhibitionParameters are recorded;
(18) the satellite sailboard is folded and locked, and the rotational inertia I of the satellite around the Y axis in the state is testedy receiveParameters are recorded;
(19) adjusting the tool to a state 3, and testing the satellite + Z in the stateHarvesting machineCenter of mass and rotational inertia around X axis Ix is receivedParameters are recorded;
(20) adjusting the tool to a state 1, and testing the satellite + X in the stateHarvesting machineCenter of mass, + YHarvesting machineRecording the centroid parameters;
(21) adjusting the tool to a state 2, and testing the satellite-X in the stateHarvesting machineCenter of mass, -YHarvesting machineCenter of mass and rotational inertia around Z axis Iz is receivedParameters are recorded;
(22) after the test is finished, the satellite is lifted and separated from the test equipment, and the test bench is restored to the initial state.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims (10)

1. The utility model provides a frock for batch production satellite rapid quality characteristic test which characterized in that: the novel bearing support device comprises an outer support frame (1), an inner support frame (4), a first shafting (7), a second shafting (5), a third shafting (2), a transfer plate (2), a positioning block (8), a horizontal stop block (10) and a vertical stop block (11), wherein the outer support frame (1) comprises a horizontal support chassis and a vertical stand, the left end and the right end of the horizontal support chassis are respectively fixed with the vertical stand, the inner support frame (4) is arranged in an area enclosed by the horizontal support chassis and the two vertical stands, the inner support frame (4) comprises an inner support chassis and two inner vertical stands, and the two inner vertical stands are vertically fixed at the left end and the right end of the inner support chassis;
the top of an inner vertical frame on the left side of an inner supporting frame (4) is connected with the top of a vertical frame on the left side of an outer supporting frame (1) through a first shafting (7), the top of the inner vertical frame on the right side of the inner supporting frame (4) is connected with the top of a vertical frame on the right side of the outer supporting frame (1) through a second shafting (5), the first shafting (7) and the second shafting (5) are coaxially arranged, the inner supporting frame (4) rotates around the first shafting (7) and the second shafting (5), a third shafting (2) is arranged in the middle of an inner supporting chassis of the inner supporting frame (4), a transfer plate (3) is arranged at the top of the third shafting (3), and the transfer plate (3) rotates around the third shafting (;
the front side and the rear side of each vertical frame are respectively provided with a positioning block (8) at the same height position, the horizontal stop blocks (10) and the vertical stop blocks (11) are both arranged on the inner vertical frame, and the horizontal stop blocks (10) and the positioning blocks (8) are matched for positioning to realize that the included angle between the outer support frame (1) and the inner support frame (4) is 0 degree; the vertical stop block (11) and the positioning block (8) are matched for positioning to realize that the included angle between the inner support frame (4) and the outer support frame (1) is 90 degrees; the adapter plate (3) is positioned by installing a positioning pin on the adapter plate (3).
2. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 1, wherein the tool comprises: the positioning block (8) comprises a positioning plate and a positioning bulge, the positioning bulge is fixed at the center of the positioning plate, and the positioning plate is fixed on the vertical frame through a screw.
3. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 2, wherein the tool comprises: horizontal dog (10) include dog body (21), set up on dog body (21) with protruding complex slotted hole (22) of location of locating piece (8) and with set screw (9) complex screw hole, be equipped with the ladder in dog body (21) and locating plate cooperation department, realize the location of interior support frame (4) in outer braced frame (1) through the cooperation of locating piece (8) and horizontal dog (10) and front and back both sides just to set screw (9) of arranging.
4. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 2, wherein the tool comprises: offer the logical groove (23) that holds the grudging post in one side of vertical dog (11), be equipped with on vertical dog (11) with protruding complex mounting hole (24) in location, offer on the cell wall that holds logical groove (23) with set screw (9) complex screw hole, realize the location of interior braced frame in outer braced frame through the cooperation of locating piece (8) and vertical dog (11) and set screw (9) that the left and right sides was arranged in pairs.
5. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 1, wherein the tool comprises: the adapter plate (3) comprises six satellite mounting positioning holes corresponding to six positioning pins, namely positioning pins 1(25), positioning pins 2(26), positioning pins 3(27), positioning pins 4(28), positioning pins 5(29) and positioning pins 6(30), wherein in the rotating process, the adapter plate (3) is positioned with the positioning pins 2(26) through the positioning pins 1(25) under the state of 0 degrees, is positioned with the positioning pins 4(28) through the positioning pins 3(27) under the state of 90 degrees, is positioned with the positioning pins 6(30) through the positioning pins 5(29) under the state of 180 degrees, and is fixed on the inner support frame through screws.
6. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 1, wherein the tool comprises: the shafting one (7) and the shafting two (5) are identical in structure and respectively comprise a positioning shaft one (15), two angular contact ball bearings (12), an outer supporting seat (14), a bearing end cover one (13) and an inner supporting seat (16), the two angular contact ball bearings (12) are arranged in the outer supporting seat (14) in a back-to-back mode, the positioning shaft one (15) is arranged on the inner ring of the angular contact ball bearing (12), one side of the angular contact ball bearing (12) is positioned through a shaft shoulder, the other side of the angular contact ball bearing is fixed through an adjusting bearing end cover one (13), and the inner supporting seat (16) is positioned with the positioning shaft one (15) through a positioning boss and locked through.
7. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 1, wherein the tool comprises: the shafting III (2) comprises a positioning shaft III (19), a double-row angular contact ball bearing (20), a bearing end cover II (17) and a bearing end cover III (18), the double-row angular contact ball bearing (20) is installed in a middle disc of the inner support frame (4), one end of the double-row angular contact ball bearing is positioned through a shaft shoulder of the positioning shaft III (19), and the inner ring and the outer ring of the other end of the double-row angular contact ball bearing are adjusted through adjusting the bearing end cover II (17) and the bearing end cover III (18) to achieve.
8. The tool for the rapid quality characteristic testing of the mass production of satellites according to claim 1, wherein the tool comprises: the outer supporting frame (1) and the inner supporting frame (4) are formed by welding aluminum alloy sections.
9. The test method of the tool for the rapid quality characteristic test of the mass production of the satellites according to any one of claims 1-8, wherein the test method comprises the following steps: when testing the quality characteristics of the satellite sailboard in the folded state or the unfolded state, the method specifically comprises the following steps:
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame, and connecting the tool with the test table through a screw;
(2) installing a positioning block (8) and a horizontal stop block (10), and adjusting the included angle between the inner support frame (4) and the outer support frame (1) to be 0 degree by adjusting the position of a positioning screw; rotating the adapter plate (3), positioning the adapter plate through the positioning pins 5 and 29 and the positioning pins 6 and 30, and locking the adapter plate with the inner support frame (4) through screws, adjusting the tool to be in a state of 0 degrees of the inner support frame and 180 degrees of the adapter plate, recording the state as state 2, measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) the positioning pins 5(29), the positioning pins 6(30) and the screws are detached, the adapter plate (30) is rotated by 180 degrees, is positioned with the positioning pins 2(26) through the positioning pins 1(25), and is locked with the inner support frame (4) through the screws, the tool is adjusted to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate at the moment, the state is recorded as state 1, and the quality characteristic parameters of the no-load tool in the state 1 are measured and recorded;
(4) dismantling the horizontal stop block (10), manually turning the inner support frame (4) around the first shaft system (7) and the second shaft system (5) by 90 degrees, installing the vertical stop block (11), adjusting the included angle between the inner support frame (4) and the outer support frame (1) to 90 degrees by adjusting the position of a positioning screw, adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of an adapter plate', recording the state as state 3, and measuring and recording the quality characteristic parameters of the no-load tool in the state 3;
(5) the positioning pins 1(25), the positioning pins 2(26) and the screws are disassembled, the adapter plate (3) is rotated by 90 degrees clockwise, the positioning pins 3(27) and the pins (28) are positioned, and the inner support frame (4) is locked by the screws, the tool is adjusted to be in a state of '90 degrees of the inner support frame and 90 degrees of the adapter plate', the state is recorded as state 4, and the quality characteristic parameters of the no-load tool in the state 4 are measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate, and locking the satellite supporting legs through screws; testing and recording parameters of the satellite-X mass center and the satellite-Y mass center in the state 2;
(8) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(9) adjusting the tool to a state 3, testing and recording the satellite + Z centroid parameters in the state 1;
(10) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(11) keeping the tool in the state 3 unchanged, testing and recording parameters of a satellite + Z mass center and a rotating inertia Ix around an X axis in the state 3;
(12) adjusting the tool to a state 4, testing and recording the parameters of the rotational inertia Iy of the satellite in the state 4 around the Y axis;
(13) adjusting the tool to a state 1, testing and recording parameters of + X mass center and + Y mass center of the satellite in the state 1;
(14) adjusting the tool to a state 2, and testing and recording parameters of a satellite-X mass center, a satellite-Y mass center and a rotational inertia Iz around a Z axis in the state 2;
(15) after the test is finished, the satellite is lifted and separated from the tool, and the test bench is restored to the initial state.
10. The test method of the tool for the rapid quality characteristic test of the mass production of the satellites according to any one of claims 1-8, wherein the test method comprises the following steps: when testing the quality characteristics of the satellite sailboard in the unfolded state after the folded state, the method specifically comprises the following steps:
(1) hoisting the tool to the table top of the test table, positioning the tool with the test table through a positioning hole in the bottom surface of the outer support frame (1), and connecting the tool with the test table through a screw;
(2) installing a positioning block (8) and a horizontal stop block (10), and adjusting the included angle between the inner support frame (4) and the outer support frame (1) to be 0 degree by adjusting the position of a positioning screw (9); rotating the adapter plate (3), positioning the adapter plate through a positioning pin 5 and a positioning pin 6, and locking the adapter plate with the inner support frame (4) through a screw, adjusting the tool to be in a state of 0 degrees and 180 degrees of the adapter plate, recording the state as state 2, and measuring and recording the quality characteristic parameters of the no-load tool in the state 2;
(3) the positioning pin 5, the positioning pin 6 and the screw are disassembled, the adapter plate (3) is rotated by 180 degrees, positioned with the positioning pin 2 through the positioning pin 1 and locked with the inner support frame (4) through the screw, the tool is adjusted to be in a state of 0 degree of the inner support frame and 180 degrees of the adapter plate at the moment and is marked as a state 1, and the quality characteristic parameter of the no-load tool in the state 1 is measured and recorded;
(4) dismantling a horizontal stop block (10), manually turning an inner support frame (4) around a first shaft system (7) and a second shaft system (5) by 90 degrees, installing a vertical stop block (11), adjusting the included angle between the inner support frame (4) and an outer support frame (1) to 90 degrees by adjusting the position of a positioning screw (9), adjusting the tool to be in a state of '90 degrees of the inner support frame and 0 degree of an adapter plate', recording the state as 3, and measuring and recording the quality characteristic parameters of the no-load tool in the state of 3;
(5) the positioning pin 1, the positioning pin 2 and the screw are disassembled, the adapter plate (3) is rotated by 90 degrees clockwise, positioned with the positioning pin 4 through the positioning pin 3 and locked with the inner support frame (4) through the screw, the tool is adjusted to be in a state of 90 degrees of the inner support frame and 90 degrees of the adapter plate at the moment and is marked as a state 4, and the quality characteristic parameter of the no-load tool in the state 4 is measured and recorded;
(6) the tool is restored to the state 2;
(7) hoisting the satellite to the position above the tool, positioning the satellite supporting legs through the adapter plate (3), and locking the satellite supporting legs through screws; satellite-X under test State 2Harvesting machineCenter of mass, -YHarvesting machineRecording the centroid parameters;
(8) adjusting the tool to the state 1, testing the satellite + X in the state 1Harvesting machineCenter of mass, + YHarvesting machineRecording the centroid parameters;
(9) adjusting the tool to state 3, testing the satellite + Z in state 3Harvesting machineRecording the centroid parameters;
(10) unfolding and locking the satellite sailboard, and testing the satellite + Z in the state 3Exhibition (or exhibition)Recording the centroid parameters;
(11) adjusting the tool to the state 1, testing the satellite + X in the state 1Exhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Recording the centroid parameters;
(12) adjusting the tool to the state 2, and testing the satellite-X in the state 2Exhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(13) balancing the mass center of the satellite to make the mass center parameter of the satellite meet the requirements of emission and on-orbit;
(14) keeping the tool unchanged in state 2 and testing the satellite-X in state 2Exhibition (or exhibition)Center of mass, -YExhibition (or exhibition)Recording the centroid parameters;
(15) adjusting the tool to the state 1, testing the satellite + X in the state 1Exhibition (or exhibition)Center of mass, + YExhibition (or exhibition)Center of mass and rotational inertia around Z axis Iz exhibitionParameters are recorded;
(16) adjusting the tool to state 3, testing the satellite + Z in state 3Exhibition (or exhibition)Center of mass and rotational inertia around X axis IX exhibitionParameters are recorded;
(17) adjusting the tool to a state 4, and testing the rotational inertia I of the satellite in the state 4 around the Y axisY exhibitionParameters are recorded;
(18) folding and locking the satellite sailboard, and testing the rotational inertia I of the satellite around the Y axis in the state 4y receiveParameters are recorded;
(19) adjusting the tool to state 3, testing the satellite + Z in state 3Harvesting machineCenter of mass and rotational inertia around X axis Ix is receivedParameters are recorded;
(20) adjusting the tool to the state 1, testing the satellite + X in the state 1Harvesting machineCenter of mass, + YHarvesting machineRecording the centroid parameters;
(21) adjusting the tool to the state 2, and testing the satellite-X in the state 2Harvesting machineCenter of mass, -YHarvesting machineCenter of mass and rotational inertia around Z axis Iz is receivedParameters are recorded;
(22) after the test is finished, the satellite is lifted and separated from the test equipment, and the test bench is restored to the initial state.
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Denomination of invention: A fixture and testing method for rapid quality characteristic testing of batch produced satellites

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