CN102183893B - Low-frequency large-deflection adjustable inertia load analog piece - Google Patents
Low-frequency large-deflection adjustable inertia load analog piece Download PDFInfo
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Abstract
The invention discloses a low-frequency large-deflection adjustable inertia load analog piece, which consists of a connecting flange, a gear, connecting brackets, a flexible load main body, a connecting sliding sleeve, a roller and a counter weight mass block, wherein the connecting flange is directly fixedly connected with an output shaft of a solar array driving structure; the connecting flange is connected with the flexible load main body through the connecting brackets and the connecting sliding sleeve; the gear is used for synchronously adjusting an angle between the two connecting brackets, adjusting the rigidity of the inertia load analog piece and guaranteeing that a square tube beam on the end part of the flexible load main body is parallel to the end part of the solar array driving structure; the connecting sliding sleeve freely slides on the square tube beam on the end part of the flexible load main body, and the flexible load main body is symmetrically distributed along an axis of the solar array driving structure; and the counter weight mass block is reasonably arranged on the flexible load main body, the mass distribution of the inertia load analog piece is adjusted, and the inertia of the analog piece is adjusted simultaneously. The inertia load analog piece is simple in structure and convenient to operate, easily adjusts modal frequency and is wide in adjusting range.
Description
Technical field
The present invention relates to a kind of low frequency large deflection adjustable inertia load analog piece, modal stiffness and modal mass that can the free adjustment simulating piece, realize simulation and accurate control of the solar array of different structure model frequency and different inertia, frequency with realistic structure, the simulation test that can be used for low frequency large deflection inertia load is as the simulation test of solar array structure.
Background technology
Present spacecraft is all with large deflection, large-area solar array, easily is subject to the perturbation of external interference and structure thereof self parameter and vibration-generating, and this pointing accuracy and degree of stability impact on spacecraft is very large.It is vertical with sunray that the solar array face will remain, makes it to follow the tracks of the sun, obtains most possibly sun power.
The low frequency Large Amplitude Vibration of solar array can cause the nuisance vibration of solar array driving mechanism, can produce larger shearing and moment of flexure to the point of attachment of solar array and solar array drives structure, even can cause the stuck of the damage of point of attachment structure and axle system, the vibration repeatedly of solar array also can cause the fatigue wear of insulated circuit insulated hull, short-circuit conditions occurs; Thereby affect the normal operation of some equipment of spacecraft, even cause scrapping of spacecraft; In addition, the Large Amplitude Vibration of solar array can affect pointing accuracy and the degree of stability of spacecraft, affects image quality; Therefore measure and analyze the characteristics of mode of solar array, thereby with the safe design of strengthening spacecraft, very important engineering significance is arranged for the attitude control accuracy of analyzing and eliminate disturbance raising spacecraft.
The inertia load analogue means is used for inertial states and the corresponding mode of simulated solar wing windsurfing.Can investigate various performances and the structural strength of solar array driving mechanism under the bringing onto load state by the inertia load analogue means.Can investigate simultaneously different inertia loads to performance index such as the impact of mechanism and mechanism's maximum load-carrying capacities.Common driving mechanism ground experiment is only carried out the moment load test and is not considered inertia load, is difficult to the driveability of real checking driving mechanism.Can carry out semi-physical simulation by the inertia load simulator, examine driving mechanism under extreme conditions to the adaptive faculty of inertia load by ground experiment, test for the driving mechanism driving force necessary data is provided.
Because the model frequency of solar array is very low, and low order frequency (mainly consider, two, three, quadravalence frequency) is comparatively approaching, add the existence of making the factors such as some errors in the simulating piece process, the simulation difficulty of mode that realizes solar array with single low frequency large deflection inertia simulation spare fully is larger, here the low frequency large deflection inertia load analog piece simulation that designs a kind of adjustable rigidity and mass distribution realizes the accurate simulation of solar array model frequency, the solar array of simulating simultaneously the different modalities characteristic.
At present, there is not yet the bibliographical information of relevant low frequency large deflection adjustable inertia load analog piece both at home and abroad.
Summary of the invention
The technical problem to be solved in the present invention is: overcome the deficiencies in the prior art, provide a kind of rigidity and mass distribution adjustable low frequency large deflection inertia load analog piece, this simulating piece is the actual frequency characteristic of Reality simulation solar array accurately, while is due to the adjustability of simulating piece model frequency, can simulate the solar array of different frequency characteristic, increase usable range.
The present invention will solve the technical scheme that its technical matters adopts: a kind of low frequency large deflection adjustable inertia load analog piece comprises: connecting flange 1, two gears 2, two connecting racks 3, two connect sliding sleeves 4, four cylinders 5, flexible load main body 6 and a plurality of weight mass pieces 7; Connecting flange 1 is connected and composed by the flange frame 14-2 of centre by disk end 1-1 and groove font end 1-3; Gear 2 mainly is made of gear body 2-3, gear teeth 2-4 and axis hole 2-5, have keyway 2-1 and gear through hole 2-2 on gear body 2-3, three gear through hole 2-2 are 120 degree and are symmetrically distributed on gear body 2-3, keyway 2-1 leaves on the inside surface of axis hole 2-5, on the distance gear body 2-3 of two gear teeth through hole 2-2 equidistances; Connecting rack 3 comprises large cylinder 3-1, draw bail 3-2, roundlet cylinder 3-3, connecting rack through hole 3-4, key 3-5 and disk 3-6, large cylinder 3-1 and roundlet cylinder 3-3 connect and compose by draw bail 3-2, disk 3-6 and the as a whole structure of large cylinder 3-1, disk 3-6 is positioned at the middle part of large cylinder 3-1, end face and the side of key 3-5 contact with the outside surface of large cylinder 3-1 and the end face of disk 3-6 respectively, and various piece is by being welded to form the integral body with symmetrical structure; Connect sliding sleeve 4 and comprise that first connects sliding sleeve through hole 4-1, threaded hole 4-2, second and connect sliding sleeve through hole 4-3, two base plate 4-6 and back up pad 4-7, the as a whole structure of various piece, two base plate 4-6 and back up pad 4-7 are combined to form left groove 4-4 and right groove 4-5; Flexible load main body 6 comprises end thin-walled square tube beam 6-2 and 6-5, two thin aluminum sheet 6-3 and two solid square beam 6-4 of small bore, two solid square beam 6-4 of small bore are welded in respectively end thin-walled square tube beam 6-2 and 6-5 two ends, three sides of thin aluminum sheet 6-3 weld together with the solid square beam 6-4 of one of them small bore side with end thin-walled square tube beam 6-2 and 6-5 respectively, total is symmetrical along line of symmetry 6-6, the outside surface of end square tube beam 6-2 is marked with scale 6-1, is used for two of the location sliding position that connects sliding sleeve 4; The disk end 1-1 of connecting flange 1 directly and the output shaft of solar array driving mechanism connect firmly by bolt, the groove font end 1-3 of connecting flange 1 and the large cylinder 3-1 of connecting rack 3 pass through bolt-connection, the large cylinder 3-1 of connecting rack 3 can rotate freely around bolt, thereby realizes the adjusting of two connecting rack 3 angles; Gear 2 connects firmly by the gear through hole 2-2 on gear 2 and connecting rack through hole 3-4 with the disk 3-6 of connecting rack 3, keyway 2-1 on gear 2 and the key 3-5 of connecting rack 3 connect, and are used for location (carrying out before the large cylinder 3-1 that is connected to connecting rack 3, the roundlet cylinder 3-3 of gear 2 and connecting rack 3 and draw bail 3-2 welding); The roundlet cylinder 3-3 of connecting rack 3 with connect sliding sleeve 4 on second connect sliding sleeve through hole 4-3 by bolt-connection, the roundlet cylinder 3-3 of connecting rack 3 can rotate freely around bolt; Two first connection sliding sleeve through hole 4-1 and two cylinders 5 of connecting on sliding sleeve 4 pass through two bolt-connections, and cylinder 5 can freely rotate around bolt; The end thin-walled square tube beam 6-2 of flexible load main body 6 is placed in and connects in the left groove 4-4 of sliding sleeve 4, and connecting sliding sleeve 4 can move freely the position by cylinder 5 on the square tube beam 6-2 of the end of flexible load main body 6; Weight mass piece 7 should be according to the model frequency requirement of flexible structure, reasonable Arrangement, be pasted on the beam 6-5 upper and lower surfaces of the end thin-walled square tube beam 6-2 of flexible load main body 6 and a relative side as symcenter is equidistant take the line of symmetry 6-6 of flexible load main body 6, need 4 or 8 masses to get final product; Connecting flange 1 be connected the connection of connecting rack 3, another gear 2 is connected with another connecting rack 3, another connecting rack 3 be connected the connection that connects sliding sleeve 4, another connects being connected of sliding sleeve 4 and another two cylinders 5, and the connection of another connection sliding sleeve 4 and flexible load main body 6 is identical with the connected mode of front.
Principle of the present invention: the disk end of the connecting flange in the present invention directly and the output shaft of solar array driving mechanism (stepper motor) connect firmly by bolt; Connecting flange is connected by two connecting racks and two connection slide blocks with the flexible load main body; Two connecting racks can rotate freely around the bolt of the groove font end of the connecting flange that is attached thereto, thereby realize the adjusting of two connecting rack angles; Two gears connecting firmly from connecting rack relative to engagement rotate guaranteed between two connecting racks with identical corner different turn to synchronous rotation; The other end of two connecting racks can rotate freely around the bolt of the connection slide block that is attached thereto; Two connect sliding sleeve and can be free to slide by cylinder along the square tube beam of flexible load main body, assurance is positioned at apart from equal position, the center of the end square tube beam of flexible load main body, to guarantee the symmetry of total, fix two by puller bolt and connect slide block, realize the fixing of whole mechanism, thereby realize the adjusting of simulating piece rigidity.According to the requirement of characteristics of mode and the inertia of actual flexible structure, with weight mass piece reasonable Arrangement, be pasted on flexible load main body square tube beam, thereby satisfy the requirement of mode inertia.Regulate low frequency large deflection inertia load analog piece rigidity and mass distribution according to the characteristics of mode of actual solar array, the model frequency of accurate control simulation spare, thus satisfy the actual measurement demand.By the low frequency large deflection inertia load analog piece characteristics of mode data analysis to measuring, for the force-bearing situation of actual sun wing driving mechanism, the attitude control of spacecraft and the safe design of spacecraft provide foundation.
The present invention's advantage compared with prior art is:
(1) the present invention by the angle of regulating two connecting racks that relatively rotates of two meshing gears, realizes the adjusting of simulating piece rigidity, has overcome the drawback that needs to make a plurality of supports.
(2) the present invention arranges the weight mass piece by rational position on the square tube beam of flexible load main body both sides, realizes the adjusting of mass distribution, has overcome the drawback that needs to make a plurality of flexible load main bodys.
(3) angle between two connecting racks of the present invention is easy to regulate, and due to the existence of square tube beam high scale, can realize the accurate location of connecting rack, can satisfy the symmetrical requirements of structure.
(4) the present invention adopts puller bolt to realize that two connect the fixing, simple in structure of slide block and flexible load main body, easy operating.
(5) in the present invention, due to the free adjustment of simulating piece rigidity and mass distribution, make the present invention be easy to realize the accurate simulation of true solar array, and can simulate different model, the solar array of different frequency characteristic.
(6) the present invention is simple in structure, easy operating, and the adjustable extent of simulating piece is large, has enlarged usable range, has improved accuracy and the adaptability of simulating piece.
Description of drawings
Fig. 1 is one-piece construction schematic diagram of the present invention;
Fig. 2 is the gear structure schematic diagram in the present invention;
Fig. 3 is the connecting flange structural representation in the present invention;
Fig. 4 is the connecting rack structural representation in the present invention;
Fig. 5 is the connection shift sleeve structure schematic diagram in the present invention;
Fig. 6 is the flexible load agent structure schematic diagram in the present invention;
Fig. 7 is single order mode frequency diagram;
Fig. 8 is the second-order modal frequency diagram;
Fig. 9 is three rank model frequency schematic diagram;
Figure 10 is quadravalence model frequency schematic diagram.
Embodiment
As shown in Figure 1, the present invention is comprised of connecting flange 1, two gears 2, two connecting racks 3, two connection sliding sleeves 4, four cylinders 5, flexible load main body 6, a plurality of weight mass pieces 7, the disk end 1-1 of connecting flange 1 directly and the output shaft of solar array driving mechanism connect firmly by bolt, the groove font end 1-3 of connecting flange 1 and the large cylinder 3-1 of connecting rack 3 pass through bolt-connection, the large cylinder 3-1 of connecting rack 3 can rotate freely around bolt, thereby realizes the adjusting of two connecting rack 3 angles; Gear 2 connects firmly by the through hole 2-2 on gear 2 and connecting rack through hole 3-4 with the disk 3-6 of connecting rack 3, keyway 2-1 on gear 2 and the key 3-5 of connecting rack 3 connect, and are used for location (carrying out before the large cylinder 3-1 that is connected to connecting rack 3, the roundlet cylinder 3-3 of gear 2 and connecting rack 3 and draw bail 3-2 welding); The roundlet cylinder 3-3 of connecting rack 3 with connect sliding sleeve 4 on through hole 4-3 by bolt-connection, the roundlet cylinder 3-3 of connecting rack 3 can rotate freely around bolt; Two through hole 4-1 and two cylinders 5 of connecting on sliding sleeve 4 pass through two bolt-connections, and cylinder 5 can freely rotate around bolt; The end thin-walled square tube beam 6-2 of flexible load main body 6 is placed in and connects in the left groove 4-4 of sliding sleeve 4, connect sliding sleeve 4 and can move freely the position on the square tube beam 6-2 of the end of flexible load main body 6 by cylinder 5, when two connection sliding sleeves 4 slide into the position that needs, hold out against on the square tube beam 6-2 of the end of flexible load main body 6 by the threaded hole 4-2 that connects sliding sleeve 4 with bolt, should hold out against as far as possible, realize the purpose that total is locked; Weight mass piece 7 should be according to the model frequency requirement of flexible structure, reasonable Arrangement, be pasted on the beam 6-5 upper and lower surfaces of the end thin-walled square tube beam 6-2 of flexible load main body 6 and a relative side as symcenter is equidistant take the line of symmetry 6-6 of flexible load main body 6, need 4 or 8 lead materials to make mass and get final product; Connecting flange 1 be connected the connection of connecting rack 3, another gear 2 is connected with another connecting rack 3, another connecting rack 3 be connected the connection that connects sliding sleeve 4, another connects being connected of sliding sleeve 4 and another two cylinders 5, and the connection of another connection sliding sleeve 4 and flexible load main body 6 is identical with the connected mode of front; Two connecting racks 3 can rotate freely around the bolt of the groove font end 1-3 of the connecting flange 1 that is attached thereto, thereby realize the adjusting of two connecting rack 3 angles; Two gears 2 connecting firmly from connecting rack relative to engagement rotate guaranteed two connecting racks 3 with identical corner different turn to synchronous rotation.
As shown in Figure 2, connecting flange 1 is connected and composed by the flange frame 1-2 of centre by disk end 1-1 and groove font end 1-3.
As shown in Figure 3, gear 2 mainly is made of gear body 2-3, gear teeth 2-4 and axis hole 2-5, have keyway 2-1 and gear through hole 2-2 on gear body 2-3, three gear through hole 2-2 are 120 degree and are symmetrically distributed on gear body 2-3, keyway 2-1 leaves on the inside surface of axis hole 2-5, on the distance gear body 2-3 of two through hole 2-2 equidistances, in order to ensure the strength of gear teeth, gear 2 is made by Steel material.
as shown in Figure 4, connecting rack 3 is by large cylinder 3-1, draw bail 3-2, roundlet cylinder 3-3, connecting rack through hole 3-4, key 3-5 and disk 3-6, large cylinder 3-1 and roundlet cylinder 3-3 connect and compose by draw bail 3-2, draw bail 3-2 is small bore rectangle Lvliang City, relatively and total, the cross section is very little, can think rods, disk 3-6 and the as a whole structure of large cylinder 3-1, disk 3-6 is positioned at the middle part of large cylinder 3-1, end face and the side of key 3-5 contact with the outside surface of large cylinder 3-1 and the end face of disk 3-6 respectively, various piece is by being welded to form the integral body with symmetrical structure.
As shown in Figure 5, connect sliding sleeve 4 and comprise through hole 4-1, threaded hole 4-2, connect sliding sleeve through hole 4-3, two base plate 4-6 and back up pad 4-7, the as a whole structure of various piece, two base plate 4-6 and back up pad 4-7 are combined to form left groove 4-4 and right groove 4-5.
as shown in Figure 6, flexible load main body 6 comprises end thin-walled square tube beam 6-2 and 6-5, two thin aluminum sheet 6-3 and two solid square beam 6-4 of small bore, two solid square beam 6-4 of small bore are welded in respectively end thin-walled square tube beam 6-2 and 6-5 two ends, three sides of thin aluminum sheet 6-3 weld together with the solid square beam 6-4 of one of them small bore side with end thin-walled square tube beam 6-2 and 6-5 respectively, total is symmetrical along line of symmetry 6-6, the outside surface of end square tube beam 6-2 is marked with scale 6-1, be used for the position that the center apart from the end square tube beam 6-2 of flexible load main body 6 equates that slides into that two of location connect sliding sleeves 4, to guarantee the symmetry of total, in order to reduce structural strength, increase flexible, the each several part of flexible load main body 6 consists of by aluminum.
As shown in Fig. 1-6, connecting flange 1 is linked into an integrated entity by flange frame 1-2 by disk end 1-1 and groove font end 1-3; Disk end 1-1 directly and the output shaft of solar array driving mechanism (stepper motor) connect firmly by bolt; The groove font end 1-2 of connecting flange 1 and the cylinder 3-1 of connecting rack 3 are by bolt-connection, and the cylinder 3-1 of connecting rack 3 can rotate freely around bolt; Gear 2 connects firmly by through hole 2-2 and connecting rack through hole 3-4 with the disk 3-6 of connecting rack 3, and the keyway 2-1 of gear 2 and the key 3-5 of connecting rack 3 are used for the location; By bolt-connection, the roundlet cylinder 3-3 of connecting rack 3 can rotate freely around bolt the large cylinder 3-3 of connecting rack 3 with the through hole 4-3 that connects sliding sleeve 4; The through hole 4-1 and the cylinder 5 that connect sliding sleeve 4 pass through bolt-connection, and cylinder 5 can freely rotate around bolt; The end square tube beam 6-2 of flexible load main body 6 is placed in and connects in the left groove 4-4 of sliding sleeve 4, and connecting sliding sleeve 4 can move freely the position by cylinder 5 on the square tube beam 6-2 of the end of flexible load main body 6; Weight mass piece 7 can be pasted on beam with the end square tube beam 6-2 of flexible load main body 6 and a relative side as required; The relative rotation of regulating two connecting racks 3 is rotated in engagement by two gears 2; The scale 6-1 that is marked with according to the outside surface of the square tube beam 6-2 of flexible load main body 6, two connect sliding sleeve 4 and slide on the position that the center apart from the end square tube beam 6-2 of flexible load main body 6 equates, to guarantee the symmetry of total; Hold out against on the beam 6-2 of the end of flexible load main body 6 by the threaded hole 4-2 that connects sliding sleeve 4 with bolt, should hold out against as far as possible, realize the purpose that total is locked, satisfy the requirement of simulating piece modal stiffness; According to the inertial properties of actual solar array, on the beam 6-5 with mass reasonable Arrangement, the square tube beam 6-2 that sticks on flexible load main body 6 and a relative side, satisfy the requirement of simulating piece mode inertia; Thereby can satisfy the model frequency characteristic of true solar array.
As shown in Figure 7, single order mode is the outer single order mode of flexural vibration of face;
As shown in Figure 8, second-order modal is single order mode of flexural vibration in face;
As shown in Figure 9, three rank mode single order torsion modes;
As shown in figure 10, quadravalence mode is the outer second order mode of flexural vibration of face.
Simulating piece modal analysis result (Hz)
| Rank number of mode | Frequency | The vibration shape is described |
| 1 | 0.222 | The outer single order of face is crooked |
| 2 | 0.838 | In face, single order is crooked |
| 3 | 1.28 | Single order reverses |
| 4 | 7.13 | The outer second order of face is crooked |
The quadravalence model frequency is all lower, and very approaching, and the end thin-walled square tube beam 6-2 by flexible load main body 6 used and 6-5, two thin aluminum sheet 6-3 and two solid square beam 6-4 of small bore guarantee to realize lower mode; The adjusting that realizes two connecting rack 3 angles is rotated in engagement by two gears 2, can regulate modal stiffness, by the reasonable Arrangement of mass 7, realizes the adjusting of modal mass, thereby simulates accurately each rank mode.
In a word, simulating piece of the present invention is the actual frequency characteristic of Reality simulation solar array accurately, and due to the adjustability of simulating piece model frequency, the solar array that can simulate the different frequency characteristic has increased usable range simultaneously.By the experimental measurement simulating piece, the actual characteristics of mode of solar array is provided, for analyzing solar array to the impact of solar array driving mechanism, improving the attitude control accuracy of spacecraft and the safe design of reinforcement spacecraft provides reliable test data.
The non-elaborated part of the present invention belongs to techniques well known.
Claims (9)
1. a low frequency large deflection adjustable inertia load analog piece, is characterized in that: comprise connecting flange (1), two gears (2), two connecting racks (3), two connection sliding sleeves (4), four cylinders (5), flexible load main body (6) and a plurality of weight mass pieces (7), connecting flange (1) is connected and composed by middle flange frame (1-2) by disk end (1-1) and groove font end (1-3), gear (2) is made of gear body (2-3), the gear teeth (2-4) and axis hole (2-5), have keyway (2-1) and three gear through holes (2-2) in gear body (2-3), keyway (2-1) leaves on the inside surface of axis hole (2-5), on the gear body (2-3) of distance two gear through holes (2-2) equidistance, connecting rack (3) comprises large cylinder (3-1), draw bail (3-2), little cylinder (3-3), connecting rack through hole (3-4), key (3-5) and disk (3-6), large cylinder (3-1) and little cylinder (3-3) connect and compose by draw bail (3-2), disk (3-6) and the as a whole structure of large cylinder (3-1), disk (3-6) is positioned at the middle part of large cylinder (3-1), end face and the side of key (3-5) contact with the outside surface of large cylinder (3-1) and the end face of disk (3-6) respectively, various piece is by being welded to form the integral body with symmetrical structure, connect sliding sleeve (4) and comprise that first connects sliding sleeve through hole (4-1), threaded hole (4-2), the second connection sliding sleeve through hole (4-3), two base plates (4-6) and back up pad (4-7), the as a whole structure of various piece, two base plates (4-6) and back up pad (4-7) be combined to form left groove (4-4) and right groove (4-5), flexible load main body (6) comprises that end thin-walled square tube beam (6-2) reaches (6-5), two thin aluminum sheets (6-3) and two solid square beams of small bore (6-4), two solid square beams of small bore (6-4) are welded in respectively end thin-walled square tube beam (6-2) and reach (6-5) two ends, three sides of thin aluminum sheet (6-3) weld together with the solid square beam of one of them small bore (6-4) side with end thin-walled square tube beam (6-2) and (6-5) respectively, total is symmetrical along line of symmetry (6-6), an outside surface of end square tube beam (6-2) is marked with scale (6-1), be used for two of the location sliding position that connects sliding sleeve (4), the disk end (1-1) of connecting flange (1) directly and the output shaft of solar array driving mechanism connect firmly by bolt, the groove font end (1-3) of connecting flange (1) passes through bolt-connection with the large cylinder (3-1) of connecting rack (3), the large cylinder (3-1) of connecting rack (3) can rotate freely around bolt, thereby realizes the adjusting of two connecting racks (3) angle, gear (2) connects firmly by the gear through hole (2-2) on gear (2) and connecting rack through hole (3-4) with the disk (3-6) of connecting rack (3), keyway (2-1) on gear (2) and the key (3-5) of connecting rack (3) connect, and are used for the location, the little cylinder (3-3) of connecting rack (3) with connect sliding sleeve (4) on second connect sliding sleeve through hole (4-3) by bolt-connection, the little cylinder (3-3) of connecting rack (3) can rotate freely around bolt, two the first connection sliding sleeve through holes (4-1) that connect on sliding sleeve (4) pass through two bolt-connections with two cylinders (5), and cylinder (5) can freely rotate around bolt, end thin-walled square tube beam (6-2) of flexible load main body (6) is placed in and connects in the left groove of sliding sleeve (4) (4-4), and connecting sliding sleeve (4) can move freely the position at the end of flexible load main body (6) square tube beam (6-2) by cylinder (5), weight mass piece (7) is according to the model frequency requirement of flexible structure, reasonable Arrangement is pasted on beam (6-5) upper and lower surfaces of the end thin-walled square tube beam (6-2) of flexible load main body (6) and a relative side as symcenter is equidistant take the line of symmetry (6-6) of flexible load main body (6), connecting flange (1) be connected the connection of connecting rack (3), another gear (2) is connected with another connecting rack (3), another connecting rack (3) be connected the connection that connects sliding sleeve (4), another connects being connected of sliding sleeve (4) and another two cylinders (5), and the connection of another connection sliding sleeve (4) and flexible load main body (6) is identical with the connected mode of front.
2. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: the distance between two through-bore axis of described connecting flange (1) groove font end (1-3) equals two times of two pitch circle radiuses.
3. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1 is characterized in that: described three gear through holes (2-2) are 120 degree and are symmetrically distributed in gear body (2-3).
4. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: described weight mass piece (7) is made by lead material; Described gear (2) is made by Steel material, and all the other structures are aluminum alloy materials to increase the flexible of total.
5. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: the cross section of the draw bail (3-2) of described connecting rack (3) is small bore rectangle Lvliang City, relatively and total, the cross section is very little, can think rods.
6. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: the end square tube beam (6-2) of described flexible load main body (6) and the beam (6-5) of a relative side adopt thin-walled square opening aluminum pipe, can reduce the rigidity of structure, increase flexible.
7. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: described two connection sliding sleeves (4) are positioned at apart from equal position, the center of the end square tube beam (6-2) of flexible load main body (6), to guarantee the symmetry of total.
8. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: the position that slides into needs when two connection sliding sleeves (4), hold out against on the end of flexible load main body (6) square tube beam (6-2) by the threaded hole (4-2) that connects sliding sleeve (4) with bolt, hold out against as far as possible, realize the purpose that total is locked.
9. a kind of low frequency large deflection adjustable inertia load analog piece according to claim 1, it is characterized in that: the number of described mass (7) is 4 or 8.
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| CN103241389B (en) * | 2013-04-25 | 2015-08-05 | 上海卫星工程研究所 | For the mechanism of Zeng Pin in-orbit of spacecraft flexible appendage |
| CN103448923A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Frequency regulation implementing method for deployable flexible appendages of satellites |
| CN106066244B (en) * | 2016-08-04 | 2019-02-19 | 程伟 | A kind of large inertia torsional flexibility load simulating device |
| CN106394945B (en) * | 2016-10-20 | 2017-05-03 | 哈尔滨工业大学 | Solar wing flexibility simulator |
| CN112098041B (en) * | 2020-08-18 | 2021-08-06 | 南京航空航天大学 | Rigidity adjusting device of wing low-speed flutter wind tunnel test model |
| CN114414145B (en) * | 2021-12-21 | 2024-03-12 | 上海利正卫星应用技术有限公司 | Rotational inertia simulation device of sailboard driving mechanism |
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| US20070186677A1 (en) * | 2006-02-14 | 2007-08-16 | Zunino James L Iii | Non-contact rf strain sensor |
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| CN101249897A (en) * | 2008-04-02 | 2008-08-27 | 华南理工大学 | Space sailboard bending and turning mode vibration simulation active control device and method |
| CN101382806A (en) * | 2008-09-28 | 2009-03-11 | 华南理工大学 | Low frequency modal vibration control apparatus and method for simulating bending and torsion for space sailboard |
| CN101387546A (en) * | 2008-10-29 | 2009-03-18 | 华南理工大学 | Space sailboard bend and torsion low frequency mode detecting method and apparatus based on vision |
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