CN103274065B - A kind of satellite flexible boom - Google Patents
A kind of satellite flexible boom Download PDFInfo
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- CN103274065B CN103274065B CN201310185036.7A CN201310185036A CN103274065B CN 103274065 B CN103274065 B CN 103274065B CN 201310185036 A CN201310185036 A CN 201310185036A CN 103274065 B CN103274065 B CN 103274065B
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Abstract
The present invention relates to a kind of satellite flexible boom, described satellite flexible boom comprises: be arranged at the soft boom of some sons (2) in satellite spin axis peripheral circumferential, for controlling the control motor (18) of the synchronous and isometric release of the soft boom of each height (2); The soft boom of described each son comprises further: flexible cable (6), for being wound around the winding shaft device (12) of flexible cable (6), this winding shaft device (12) comprises further: center rotating shaft (29) and cable winds axle (7) co-axially fixed with center rotating shaft (29), and described cable winds axle (7) is fixed on the winding bracing strut (17) of axially setting; One section in described flexible cable (6) is wound on cable winds axle (7), and another section of end is provided with an end spheroid (19) and radially distributes and pass a spheroid starting point retainer (4); Described winding bobbin (12) is positioned at the middle part on floor, load cabin (26), and the soft boom of described each height is along floor, load cabin (26) radial development.
Description
Technical field
The present invention relates to the stretch rod device of loading test instrument on satellite, particularly, the present invention relates to a kind of satellite flexible boom.
Background technology
Because satellite flexible boom is usually centered by satellite spin axle and mode in a symmetrical arrangement is arranged on the edge around satellite load storehouse, it is generally identical by the above structure of two covers and the flexible cable boom that discharges of separate and stringent synchronization and forming, as the extended pattern rod assemblies of the overhanging equipment of the satellite health particularly sensor such as electromagnetic detection equipment, for operating in the satellite away from the earth such as outer Magnetopause, its celestial body is often in and thickly reaches in the parcel of tens meters even the large scale magnetosheath layer of more than tens meters, electric field instruments now etc. must have the potentiometric sensor be positioned at outside magnetosheath layer normally to work, therefore this kind of satellite equipment must be equipped with lengthening stretch rod device, but it is extremely difficult for installing the hard stretch rod device that the while of reaching tens meters, quality is lighter again on the satellite of limited dimensions, thus being easy to flexible cable stretch rod device that is folding or that be wound around is a kind of selection preferably.The more convenient practicality of usual winding-type flexible cable boom, and the centnifugal force that can only lean on satellite spin to produce has the end object of certain distance outwards to throw away by being arranged at celestial body outer also distance satellite spin axle, thus the winding cable driving one end to link on it pulls out expansion, forms the flexible cable stretch rod device perpendicular to satellite spin axle.But this kind of device may have certain influence to satellite body such as moment of rotation, spin states etc. mechanics, electromagnetism and celestial body equipment equiblibrium mass distribution etc. design or mode of operation, therefore not only needs the long yardstick boom away from satellite body also to require that boom can not produce the additional moment that may change satellite spin state under normal circumstances.This just requires all booms not only from launching to start to be in isometric attitude with regard to the moment but also also identical apart from the physical quality of per unit length boom in the same radius annular region at satellite spin center, certainly the total mass also having whole to reach the flexible cable boom of tens meters also will be lighter than the total mass of satelloid far away, and it is one of best design plan that the quality of flexible cable boom body only accounts for satellite total mass less than 1%.Therefore need the long boom of a kind of suitable satellite of design to carry relevant satellite equipment.
Summary of the invention
The object of the invention is to, in order to overcome the problems referred to above, provide a kind of satellite flexible boom.
To achieve these goals, the invention provides a kind of satellite flexible boom, described satellite flexible boom comprises:
Be arranged at the soft boom 2 of some sons in satellite spin axis peripheral circumferential, for controlling the control motor 18 of the synchronous and isometric release of the soft boom of each height 2;
The soft boom of described each son comprises further:
Flexible cable 6, for being wound around the winding shaft device 12 being positioned at center, floor 26, load cabin of flexible cable 6, this winding shaft device 12 comprises further: center rotating shaft 29 and cable winds axle 7 co-axially fixed with center rotating shaft 29, and described cable winds axle 7 is fixed on the winding bracing strut 17 of axially setting; One ends wound in described flexible cable 6 is on cable winds axle 7, and other end end is provided with an end spheroid 19 and radially distributes and pass a spheroid starting point retainer 4; Described winding shaft device 12 is positioned at the middle part on floor, load cabin 26, and the soft boom of described each height is along floor 26 radial development of load cabin;
Described spheroid starting point retainer 4 is for remaining on end spheroid 19 in its cup-shaped space until launch flexible cable 6 to open release gate 16;
Described end spheroid 19 will be positioned at the filament shape column type electrode on flexible cable 6 top in the cylindrical electrode bobbin 33 of its spherical shell inside for preserving; And provide spin centnifugal force discharge or launch flexible cable 6 body;
Wherein, the soft boom of each height 2 synchronous and isometric is released through and controls motor 18, with control drop-gear box 30 that motor 18 is connected, cable winds bobbin 7 center rotating shaft 29 and be positioned at the intermeshing synchronous link crowngear 13 in center rotating shaft 29 end and realize the flexible cable that synchronous release outside satelloid goes out equal length;
A center rotating shaft 29 in the soft boom of described son is connected with described drop-gear box 30.
Above-mentioned satellite flexible boom also comprises a protective case 24; this protective case 24 is buckled in the outside of all winding shaft devices 12; and this protective case 24 has some breach 25, the number of breach 25 is identical with the number of the soft boom of son, for through the one section of flexible cable 6 being parallel to floor, load cabin 26.
Above-mentioned winding shaft device 12 also comprises: the conducting slip ring structure that signal multiplex adapter 8 and signal converting contactless switch 5 form;
Described signal converting contactless switch 5 is the multichannel coaxial annular contact 43 of unitary rotation synchronous with center rotating shaft 29, each coaxial annular contact 43 electrically connects to corresponding signal wire (SW) in the flexible cable 6 be wound around and to do mechanically with center rotating shaft 29 coaxial, described signal multiplex adapter 8 for and multiple contact 44 that accepts one to one, multichannel coaxial annular contact 43, for the electric signal from the flexible cable 6 be wound around is forwarded to carry out satellite perceptual signal in central circuit cabinet 20 collection, process and storage;
Wherein, described signal multiplex adapter 8 is fixed on floor, load cabin 26.
Above-mentioned spheroid starting point retainer 4 comprises: release gate 16, base 10, release motor 15 and protector outer casing 14; described protector outer casing 4 cup-shaped is also fixed on base 10; the central axis of its symmetry is along the radial direction perpendicular to satellite spin axis; rim of a cup radially; the cup end, has a butt hole 21 to be connected with cable pillar 11 one end, discharges 16 one-tenth, gate C shape half ring-like body and to be contained on protector outer casing 14 rim of a cup and to control its action by discharging motor 15.
Above-mentioned end spheroid 19 structure is:
Described end spheroid 19 fastens docking by two hemispherical Shells 40 and forms, the support for bobbin frame 34 that one has the regular hexahedron type of the stand frame sidewall 41 of four rectangles is comprised in end spheroid 19, each stand frame sidewall 41 center of symmetry is provided with an axis hole, four axis holes are coplanar, a pair axis hole on left and right stand frame sidewall 41 is for installing cylindricality electrode wires axle 33, another is to the axis hole installing support for bobbin frame spin axis bearing 38 be positioned on two side, front and back, the adjustable pressure bearing 37 being positioned at the applying rotary damping power regulating cylindricality electrode wires axle 33 both sides support for bobbin frame 34 is also equipped with, the locking making leaf spring 31 being wrapped in cylindrical electrode 32 line on cylindrical electrode bobbin 33 and being pressed on the cylindrical electrode 32 of winding, described support for bobbin frame 34 is also provided with through hemispherical Shell 40 center spherical shell spin axis bullport 39 support for bobbin frame spin axis 35 and link the spherical shell shackle 36 of two hemispherical Shells 40,
Wherein, support for bobbin frame spin axis 35 inserts by spherical shell spin axis bullport 39 the spin axis bearing hole 42 that is positioned in support for bobbin frame spin axis bearing 38 thus support for bobbin frame 34 is loaded on end spheroid 19 cavity, described support for bobbin frame spin axis 35 is hollow cylinder structures of charged polar curve bullport, so that the cylindrical electrode of filament type 32 is through wherein being drawn by end spheroid 19 inside.
26 1 sections, floor, load cabin flexible cable 6 is parallel to by cable pillar 11 protection be arranged between spheroid starting point retainer 4 and cable winds axle 7.
The outside being wound in flexible cable on cable winds axle 7 also arranges the locking making leaf spring 9 of a cable;
The locking making leaf spring 9 of described cable have the moment be pressed on be wound around cable volume 45 on, and the locking making leaf spring 9 of described cable becomes the curly form of C font on the cross-sectional plane perpendicular to center rotating shaft 29, one end of C font one end and cable locking making leaf spring 9 body is fixed on and is wound around on bracing strut 17, and the other end is that free end is pressed on the winding cable volume 45 of cable winds axle 7 with elastic type.
Compared with prior art, the invention has the advantages that:
1) single electric machine control four groups of flexible cable synchronous release, simple and reliable for structure;
2) four groups of cables strictly controlling of single motor are synchronous discharge with accurately equal length, both steps unifications, and it is high that cable discharges length accuracy, and error is little;
3) parts are few, simple and reasonable, effectively reduce fault rate, integral structure and good stability, are extremely applicable to working in the harsh environment of space;
Accompanying drawing explanation
Fig. 1 is the 3-D view of satellite flexible boom 1;
Fig. 2 is the three-dimensional assembly drawing that satellite flexible boom 1 is contained on the floor, load cabin 26 of satellite;
Fig. 3 is the tomograph of a set of flexible cable boom 2 part in satellite flexible boom 1;
Fig. 4 is the cutaway view of end spheroid 19 and interior three-dimensional structure thereof;
Fig. 5 is the tomograph after being positioned at the signal converting contactless switch 5 being wound around shaft device 12 side and signal converting contactless switch 8 partial enlargement pulled open.
Accompanying drawing identifies
1, satellite flexible boom 2, sub soft boom 3, synchronous device
4, spheroid starting point retainer 5, signal converting contactless switch 6, flexible cable
7, cable winds axle 8, signal multiplex adapter 9, the locking making leaf spring of cable
10, base seat 11, cable pillar 12, winding shaft device
13, synchronous link crowngear 14, retainer shell 15, release motor
16, discharge gate 17, be wound around bracing strut 18, cable discharges motor
19, end spheroid 20, central circuit cabinet 21, butt hole
22, preamplifier 23, base 24, protective case
25, breach 26, floor, load cabin
27, satellite spin axis 28, synchronous link gear protective case
29, center rotating shaft 30, drop-gear box 31, locking making leaf spring
32, cylindrical electrode 33, cylindrical electrode bobbin 34, support for bobbin frame
35, support for bobbin frame spin axis 36, spherical shell shackle
37, pressure regulates bearing 38, support for bobbin frame spin axis bearing
39, spherical shell spin axis bullport 40, hemispherical Shell 41, stand frame sidewall
42, spin axis bearing hole 43, coaxial annular contact 44, accept contact
45, cable volume is wound around
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the invention will be further described.
Satellite boom of the present invention is a kind of satellite flexible boom be contained on satelloid, and described satellite flexible boom comprises:
The present invention relates to a kind of satellite flexible boom, described satellite flexible boom 1 is by the above separate flexible cable boom 2 of two covers, described flexible cable boom 2 is identical and be center of symmetry around satellite spin axis 27 and winding cable shaft device to different directions synchronous release equal length cable is formed jointly by structure, flexible cable boom 2 is used as the prolongation leg unit of the protruding equipment of satellite health, the electromagnetic susceptibility device of the equipment such as electromagnetic detection equipment is arranged on this kind of away from the extension rod of satellite body, so that the interference of the electromagnetic noise source away from celestial body, specifically, also throw away being arranged in satellite load cabin apart from the radial direction of the end spheroid 19 on satellite spin axis 27 certain distance along spin centnifugal force by satellite spin campaign, thus drive the winding flexible cable 6 linked on end spheroid 19 to pull out the multiple soft boom structure stretching and formed and be symmetrical in satellite spin axis 27 and radially distribute, perpendicular to satellite spin axle at same plane, along one or more different directions, Striking symmetry distributes and synchronous release overlaps a cable just formation satellite flexible boom group with counting of length, wherein, described central circuit cabinet 20 for control motor and run and for the mode of operation of satellite flexible boom and contained Instrument sensor monitoring and control and acquisition of signal, process and storage.
Described flexible cable boom 2 comprises the winding shaft device 12, roll synchronous device 3, flexible cable 6, end spheroid 19 and the spheroid starting point retainer 4 that are wound around flexible cable;
The winding shaft device 12 of described flexible cable comprises cable winds bobbin 7, is wound around bracing strut 17, signal multiplex adapter 8 and signal converting contactless switch 5 and the locking making leaf spring 9 of cable; Wherein be wound around floor 26, the satellite load cabin central region that shaft device 12 is positioned at satellite load cabin, spheroid starting point retainer 4 is positioned at the fringe region scope around satellite load cabin having certain radial distance with satellite spin axis 27; Flexible cable 6 between the spheroid starting point retainer 4 of the winding shaft device 12 in the middle part of satellite and load cabin peripheral position is protected by rigidity cable pillar 11;
Described winding axle synchronous device 3 comprises the cable release motor 18 that the synchronous link crowngear 13 of center rotating shaft 29 end being positioned at each cable winds bobbin 7 and each independent flexible cable share;
Described winding axle synchronous device 3 to go out the flexible cable of equal length by the center rotating shaft 29 of cable release motor 18 and drop-gear box 30, cable winds bobbin 7, the release motor that is positioned at the intermeshing synchronous link crowngear 13 in center rotating shaft 29 end and control circui to synchronous release outside satelloid, the direction of the rotatory inertia moment vector of satellite remains that conservation is constant;
The locking making leaf spring 9 of described cable have the moment be pressed on be wound around cable volume 45 on make its spring bearer plate that can not relax voluntarily, the locking making leaf spring 9 of cable becomes the curly form of C font on the cross-sectional plane perpendicular to center rotating shaft 29, one end of C font one end and cable locking making leaf spring 9 body is fixed on and is wound around on bracing strut 17, and the other end is that free end is pressed on the winding cable volume 45 of cable winds bobbin 7 with elastic type;
Described spheroid starting point retainer 4 comprises release gate 16 and base 10, controls the release motor 15 that end spheroid 19 discharges gate 16, and retainer shell 14 is connected with cable pillar 11 one end at end butt hole 21 place;
Described end spheroid 19 fastens docking by two hemispherical Shells 40 and forms, the support for bobbin frame 34 that one has the regular hexahedron type of the stand frame sidewall 41 of four rectangles is comprised in end spheroid 19, each stand frame sidewall 41 center of symmetry is provided with an axis hole, four axis holes are coplanar, a pair axis hole on left and right stand frame sidewall 41 is used for installing electrodes bobbin 33, another is to the axis hole installing support for bobbin frame spin axis bearing 38 be positioned on two side, front and back, the adjustable pressure bearing 37 being positioned at the applying rotary damping power regulating cylindricality electrode wires axle 33 both sides support for bobbin frame 34 is also equipped with, the locking making leaf spring 31 being wrapped in cylindrical electrode 32 line on cylindrical electrode bobbin 33 and being pressed on the cylindrical electrode 32 of winding, described support for bobbin frame 34 is also provided with through hemispherical Shell 40 center spherical shell spin axis bullport 39 support for bobbin frame spin axis 35 and link the spherical shell shackle 36 of two hemispherical Shells 40, wherein support for bobbin frame spin axis 35 inserts by spherical shell spin axis bullport 39 the spin axis bearing hole 42 that is positioned in support for bobbin frame spin axis bearing 38 thus support for bobbin frame 34 is loaded on end spheroid 19 cavity, described support for bobbin frame spin axis 35 is hollow cylinder structures of charged polar curve bullport, so that the cylindrical electrode of filament type 32 is through wherein being drawn by end spheroid 19 inside.
Described many cover flexible cable booms 2 are round passing satellite load cabin adapter plate and outwards radially arranged by center centered by satellite spin axis 27, installation direction differs the azimuth of the identical number of degrees separately, in the vertical plane surface that end spheroid 19 is in centered by satellite spin axle after launching same circumferentially and mutually equidistant;
The flexible cable 6 of described flexible cable boom 2 is by multi-layer insulation screen layer and is easy to bending multiply signal cable, the flexible cable 6 of each flexible cable boom 2 discharges identical length, and to be wound around the number of turns with total winding number of turns on cable wrap wire axle 7 of, flexible cable 6 and every layer also identical;
Described signal converting contactless switch 5 is multichannel coaxial annular contacts 43 of unitary rotation synchronous with cable winds bobbin 7 both center rotating shaft 29, each coaxial annular contact 43 only to be wound around signal wire (SW) corresponding in flexible cable 6 and electrically connect and to do mechanically coaxial with center rotating shaft 29, the signal multiplex adapter 8 be fixed on accordingly on floor, load cabin 26 plays a part to accept electric signal fixed contact, signal multiplex adapter 8 has and has one to one mechanically the multiple of resilient mounting with the multichannel coaxial annular contact 43 on signal converting contactless switch 5 and accept contact 44, to be transferred in central circuit cabinet 20 from electric signal such as winding flexible cable 6 grade,
Described winding axle synchronous device 3 discharges electric machine rotation by engaging each other into transmission with the synchronous link crowngear 13 of center rotating shaft 29 axle head that cable winds bobbin 7 is fixed as one, and becomes the process of constant velocity tramsmission;
The gross pressure of the locking making leaf spring of described cable 9 to pressed winding flexible cable 6 is not more than end spheroid 19 2 times to the centrifugal tension of direct bearing flexible cable 6 end when reference position;
The locking making leaf spring 9 of the described cable base portion width be pressed on cable winds bobbin 7 is slightly narrower than the width being wound around cable volume 45;
The top of the flexible cable 6 of described flexible cable boom 2 is that a high density integrated circuit having forms and has the active preamplifier 22 that discoid screening can is closed, and preamplifier 22 accepts the electric signal responded to from the cylindrical electrode 32 of the filament type between preamplifier 22 and end spheroid 19;
Described and by the locking making leaf spring 31 of curling shape elastic pressuring plate type being pressed on the C font cross-sectional plane that the filament type cylindrical electrode 32 of winding makes it avoid relaxing voluntarily, locking making leaf spring 31 becomes C font at the cross-sectional plane of the center shaft perpendicular to cylindrical electrode bobbin 33, locking making leaf spring 31 body one end of C font is fixed on the stand frame sidewall 41 at place, center shaft two ends of cylindrical electrode bobbin 33, the other end is free end, and the moment is pressed in the winding electrode roll of cylindrical electrode bobbin 33 with elastic type;
The size of rotary damping power when described control cylindrical electrode bobbin 33 freely rotates is regulated by the adjustable pressure bearing 37 being positioned at axle head, its rational setting range be when the end spheroid 19 in flexible cable 6 leave load cabin arrive the position of half length of predetermined maximum distance time, the centnifugal force suffered by end spheroid 19 starts to increase to gradually to be enough to overcome above-mentioned rotary damping power circle is launched into rectilinear cylindrical electrode 32 around the filament type cylindrical electrode 32 on cylindrical electrode bobbin 33.
Embodiment:
Described satellite flexible boom 1 is whole to be contained on the floor, satellite load cabin 26 of 1500 mm dias, wherein be arranged in the middle part of floor, load cabin 26 is the winding shaft device 12 of satellite flexible boom 1, occupy the border circular areas of about diameter 320 millimeters, whole satellite flexible boom 1 is as illustrated in fig. 1 and 2 made up of jointly 4 groups of flexible cable booms 2, the flexible cable 6 often group is wound around is the 6 core signal wire (SW)s having woven shield, external diameter≤4.0 millimeter, long more than 25 meters of every root flexible cable 6, the minimum bending radius ≈ of flexible cable 6 25 millimeters, flexible cable 6 one end is fixed on and is wound around on bobbin 7, one end links preamplifier 22, preamplifier 22, shell sizes is L12 × φ 15 millimeters, the yardstick being wound around bobbin 7 is L85 × φ 52 millimeters, end spheroid 19 external diameter 68 millimeters, wall thickness 1.2 millimeters, be made up of aluminum alloy, outer plating 3-5 micron thickness low resistive metal coating, spheroid starting point retainer 4 is positioned at the endless belt apart from 130 millimeters, edge, load cabin, spheroid starting point retainer 4 main body becomes hole size L80 × φ 70 millimeters cup-shaped, be made up of a few part, as shown in Figure 1.
Release gate 16 entirety becomes western language C font, release gate 16 is made up of symmetrical two parts, the bottom of two parts is all the sluice gate structure of a hinged formation clamp with base 10, the opening direction of two parts is symmetrical in the symmetrical center line of spheroid starting point retainer 4, two feature bottom are equipped with the gear teeth around its rotating shaft and engage each other, what make two parts opens synchronous and same corner, until open even as big as making end spheroid 19 by space therebetween, be opened into a large C font between the two; When release gate 16 closes, C font top notch is wide about 12 millimeters, and the inside and outside diameter of C font is respectively φ 32 millimeters and φ 66 millimeters, thickness 2 millimeters, and base 10 size is L100 × W80 × H80 millimeter; The rotating speed exported after the release motor 15 power 2W deceleration of Co ntrolled release gate 16 is 0.75 revolutions per second, and retainer shell 14 is connected with one end of cable pillar 11 at end butt hole 21 place, as shown in Figure 2.
Being positioned at winding shaft device 12 apparent size is L125 × φ 95 millimeters, the rigidity cable pillar 11 one-tenth tubulars between spheroid starting point retainer 4, cable pillar 11 internal diameter 15 millimeters, cable pillar 11 wall thickness 1.2 millimeters.Center rotating shaft 29 diameter phi 18 millimeters of cable winds bobbin 7, synchronous link crowngear 13 apparent size of end is L25 × φ 22 millimeters, and the cable release motor 18 power 45W that each independent flexible cable device shares, drop-gear box 30 output revolutions is 2 revolutions per seconds.
L4 × φ 40 (endoporus φ 25) millimeter with each coaxial annular contact 43 size of the multichannel coaxial annular contact 43 of cable winds bobbin 7 synchronous axial system, each coaxial annular contact 43 by the equidistant arrangement of 6 millimeters by insulating material together with center rotating shaft 29 cast solid, center rotating shaft 29 diameter phi 20 millimeters, as shown in Figure 5.
End spheroid 19 external diameter is φ 68 millimeters, wall thickness 1.2 millimeters, and the oncus at the fastening contact endless belt place of hemispherical Shell 40 is to 1.8 millimeters, and inside is provided with docking screw thread M65 × 0.75 fastened, docking threaded collar bandwidth 6 millimeters.
As shown in Figure 4, the size of support for bobbin frame 34 is L50 × W28 × H22 millimeters, the size of left and right stand frame sidewall 41 is L28 × H22 millimeters, cylindrical electrode bobbin 33 size is L25 × φ 35 millimeters, cylindrical electrode 32 size is: length L3000 × diameter phi 0.75 millimeter, the pressure be pressed on the cylindrical electrode 32 of the winding on cylindrical electrode bobbin 33 regulates the damping force range of bearing 37 to be 0.02N-3.0N, locking making leaf spring 31, the diameter phi 3 millimeters of center spherical shell spinning moving axis bullport 39, spinning moving axis 35 diameter phi 12 millimeters of charged polar curve bullport, the spherical shell shackle 36 linking two hemispherical Shells 40 is wide 13 millimeters.
As shown in Figure 1, four cover flexible cable booms 2 round by satellite spin axle 27 through centered by the adapter plate of satellite load cabin and by centrally outside radial array, installation direction differs the azimuth of 90 degree separately, in the vertical plane surface that end spheroid 19 is in centered by satellite spin axle after launching same circumferentially and mutually equidistant.
Cross-sectional plane becomes the size of the locking making leaf spring 9 of the cable of C font to be L70 × φ 6 millimeters, and the subtended angle of C font is 100 degree, and the locking making leaf spring of cable 9 is made up of the good alloy copper sheet of elasticity, as shown in Figures 3 and 4.
The cable that flexible cable 6 is made up of 6 strands of signal wire (SW)s, signal wire (SW) is maximum is ten milliamperes of magnitudes by electric current, flexible cable 6 outermost layer is the screen layer of the weaving filaments one-tenth of good conductive material and is easy to bending, and external diameter≤4.0 millimeter of the flexible cable 6 of each flexible cable boom 2, total length is 30 meters.
As shown in Figure 3, preamplifier 22 apparent size of the top high density integrated circuit having of flexible cable 6 is L20 × φ 35 millimeters.
The size of protective case 24 is H95 × φ 280 millimeters, wall thickness 1.1 millimeters, as shown in Figure 2.
In a word, satellite flexible boom of the present invention comprises central electronic cabinet 20 again separate flexible cable boom 2 identical with many nested structures, flexible cable boom 2 is that the extension apparatus stretched out outside satelloid main body also comes moment stringent synchronization, isometric release by satellite spin, to be arranged on celestial body and radially to throw away by suffered spin centnifugal force on the flexible cable 6 end direct bearing spheroid 19 of satellite spin axle equidistant position, drive direct bearing to be wound around flexible cable 6 and radially stretch pull-out, form the soft boom system perpendicular to satellite spin axle; Flexible cable boom 2 comprises the spooler apparatus 12, roll synchronous device 3, flexible cable 6, end spheroid 19 and the spheroid starting point retainer 4 that are wound around cord cable; Wherein flexible cord winding shaft device 12 comprises cable winds bobbin 7, is wound around bracing strut 17, multi-channel electric signal adapter 8 and signal converting contactless switch 5 and the locking making leaf spring 9 of cable; Be wound around axle synchronous device 3 and comprise the synchronous link crowngear 13 and cable release motor 18 that are positioned at each cable winds bobbin 7 center rotating shaft two ends; Also have an end to receive the cable pillar 11 of starting point retainer shell 14, spheroid starting point retainer 4 comprises release motor 15, release gate 16 and base 10; Support for bobbin frame 34, cylindrical electrode bobbin 33 and cylindrical electrode 32 is comprised in described spheroid 19; The invention has the advantages that: 1) single electric machine control many groups flexible cable synchronous release, simple and reliable for structure; 2) many groups flexible cable that single motor strictly controls synchronously discharges with accurate equal length, both steps unifications, and cable release length accuracy is high, and error is little; 3) parts are few, simple and reasonable, effectively reduce fault rate, integral structure and good stability, are extremely applicable to working in the harsh environment of space.
It should be noted last that, above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted.Although with reference to embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, modify to technical scheme of the present invention or equivalent replacement, do not depart from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of right of the present invention.
Claims (7)
1. a satellite flexible boom, is characterized in that, described satellite flexible boom comprises:
Be arranged at the soft boom of some sons (2) in satellite spin axis peripheral circumferential, for controlling the control motor (18) of the synchronous and isometric release of the soft boom of each height (2);
The soft boom of described each son comprises further:
Flexible cable (6), for being wound around the winding shaft device (12) being positioned at floor, load cabin (26) center of flexible cable (6), this winding shaft device (12) comprises further: center rotating shaft (29) and cable winds axle (7) co-axially fixed with center rotating shaft (29), and described cable winds axle (7) is fixed on the winding bracing strut (17) of axially setting; One ends wound in described flexible cable (6) is on cable winds axle (7), and other end end is provided with an end spheroid (19) and radially distributes and pass a spheroid starting point retainer (4); Described winding shaft device (12) is positioned at the middle part on floor, load cabin (26), and the soft boom of described each height is along floor, load cabin (26) radial development;
Described spheroid starting point retainer (4) is for remaining on end spheroid (19) in its cup-shaped space until launch flexible cable (6) to open release gate (16);
Described end spheroid (19) will be positioned at the filament shape column type electrode on flexible cable (6) top in the cylindrical electrode bobbin (33) of its spherical shell inside for preserving; And provide spin centnifugal force discharge or launch flexible cable (6) body;
Wherein, the soft boom of each height (2) synchronous and isometric is released through and controls motor (18), with control drop-gear box (30) that motor (18) is connected, cable winds axle (7) center rotating shaft (29) and be positioned at the intermeshing synchronous link crowngear (13) in center rotating shaft (29) end and realize synchronous release outside satelloid and go out the flexible cable of equal length;
A center rotating shaft (29) in the soft boom of described son is connected with described drop-gear box (30).
2. satellite flexible boom according to claim 1; it is characterized in that; described satellite flexible boom also comprises a protective case (24); this protective case (24) is buckled in the outside of all winding shaft devices (12); and this protective case (24) has some breach (25); the number of breach (25) is identical with the number of the soft boom of son, for through the one section of flexible cable (6) being parallel to floor, load cabin (26).
3. satellite flexible boom according to claim 1, is characterized in that, described winding shaft device (12) also comprises: the conducting slip ring structure that signal multiplex adapter (8) and signal converting contactless switch (5) form;
Described signal converting contactless switch (5) is the multichannel coaxial annular contact (43) with center rotating shaft (29) synchronous unitary rotation, each coaxial annular contact (43) electrically connects with corresponding signal wire (SW) in the flexible cable (6) be wound around and to do mechanically with center rotating shaft (29) coaxial, described signal multiplex adapter (8) is and multiple contact (44) that accepts one to one, multichannel coaxial annular contact (43), for the electric signal from the flexible cable (6) be wound around is forwarded to the collection carrying out satellite perceptual signal in central circuit cabinet (20), process and storage,
Wherein, described signal multiplex adapter (8) is fixed on floor, load cabin (26).
4. satellite flexible boom according to claim 1, it is characterized in that, described spheroid starting point retainer (4) comprising: release gate (16), base (10), release motor (15) and protector outer casing (14), described protector outer casing (14) cup-shaped is also fixed on base (10), the central axis of its symmetry is along the radial direction perpendicular to satellite spin axis, rim of a cup radially, the cup end, has a butt hole (21) to be connected with cable pillar (11) one end, release gate (16) becomes C shape half ring-like body to be contained on protector outer casing (14) rim of a cup and controls its action by release motor (15).
5. satellite flexible boom according to claim 1, is characterized in that, described end spheroid (19) structure is:
Described end spheroid (19) fastens docking by two hemispherical Shells (40) and forms, the support for bobbin frame (34) that one has the regular hexahedron type of the stand frame sidewall (41) of four rectangles is comprised in end spheroid (19), each stand frame sidewall (41) center of symmetry is provided with an axis hole, four axis holes are coplanar, a pair axis hole on left and right stand frame sidewall (41) is for installing cylindricality electrode wires axle (33), another is to axis hole installing support for bobbin frame spin axis bearing (38) be positioned on two side, front and back, the adjustable pressure bearing (37) being positioned at the applying rotary damping power regulating cylindricality electrode wires axle (33) both sides support for bobbin frame (34) is also equipped with, the locking making leaf spring (31) being wrapped in cylindrical electrode (32) line on cylindrical electrode bobbin (33) and being pressed on the cylindrical electrode (32) of winding, described support for bobbin frame (34) is also provided with through hemispherical Shell (40) center spherical shell spin axis bullport (39) support for bobbin frame spin axis (35) and link the spherical shell shackle (36) of two hemispherical Shells (40),
Wherein, support for bobbin frame spin axis (35) inserts by spherical shell spin axis bullport (39) the spin axis bearing hole (42) that is positioned on support for bobbin frame spin axis bearing (38) thus support for bobbin frame (34) is loaded on end spheroid (19) cavity, described support for bobbin frame spin axis (35) is the hollow cylinder structure of charged polar curve bullport, so that the cylindrical electrode of filament type (32) is through wherein being drawn by end spheroid (19) inside.
6. satellite flexible boom according to claim 1; it is characterized in that, be parallel to (26) one sections, floor, load cabin flexible cable (6) by cable pillar (11) protection be arranged between spheroid starting point retainer (4) and cable winds axle (7).
7. satellite flexible boom according to claim 1, is characterized in that, the outside being wound in the upper flexible cable of cable winds axle (7) also arranges the locking making leaf spring of a cable (9);
The locking making leaf spring of described cable (9) is pressed on and is wound around on cable volume (45), and the locking making leaf spring of described cable (9) becomes the curly form of C font on the cross-sectional plane perpendicular to center rotating shaft (29), one end of C font one end and the locking making leaf spring of cable (9) body is fixed on and is wound around on bracing strut (17), and the other end is that free end is pressed on winding cable volume (45) of cable winds axle (7) with elastic type.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310185036.7A CN103274065B (en) | 2013-05-17 | 2013-05-17 | A kind of satellite flexible boom |
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| CN201310185036.7A CN103274065B (en) | 2013-05-17 | 2013-05-17 | A kind of satellite flexible boom |
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| CN103274065A CN103274065A (en) | 2013-09-04 |
| CN103274065B true CN103274065B (en) | 2015-08-05 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523244B (en) * | 2013-10-25 | 2015-10-07 | 中国科学院空间科学与应用研究中心 | A kind of satellite flexible boom retainer |
| CN103523245B (en) * | 2013-10-25 | 2016-03-30 | 中国科学院空间科学与应用研究中心 | A kind of flexible cable stretch rod device |
| CN104071359B (en) * | 2014-06-11 | 2016-03-30 | 中国人民解放军第二炮兵装备研究院 | The space station of simulation ground gravitational environment and using method |
| CN105711861B (en) * | 2016-03-29 | 2017-12-15 | 上海卫星工程研究所 | Spacecraft single-point Compliant pressure release device |
| CN108454890B (en) * | 2018-02-01 | 2020-08-04 | 中国科学院国家空间科学中心 | Synchronous release device for satellite soft stretching rod |
| CN111169660A (en) * | 2019-12-12 | 2020-05-19 | 北京空间技术研制试验中心 | Exposed load support system for spacecraft |
| CN111175584A (en) * | 2019-12-26 | 2020-05-19 | 兰州空间技术物理研究所 | Low-orbit spacecraft suspension potential detection device and method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1310392A (en) * | 1970-09-29 | 1973-03-21 | British Aircraft Corp Ltd | Cable storing devices |
| FR2518494A1 (en) * | 1981-12-19 | 1983-06-24 | Messerschmitt Boelkow Blohm | MECHANISM FOR FOLDING AND FOLDING A FOLDING STRUCTURE |
| US4561614A (en) * | 1982-12-07 | 1985-12-31 | Rca Corporation | Deployable folded multi-element satellite subsystems |
| CN102501988A (en) * | 2011-09-26 | 2012-06-20 | 北京航空航天大学 | Telescopic space boom mechanism for supporting detection load |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7216833B2 (en) * | 2001-07-30 | 2007-05-15 | Iostar Corporation | In orbit space transportation and recovery system |
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2013
- 2013-05-17 CN CN201310185036.7A patent/CN103274065B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1310392A (en) * | 1970-09-29 | 1973-03-21 | British Aircraft Corp Ltd | Cable storing devices |
| FR2518494A1 (en) * | 1981-12-19 | 1983-06-24 | Messerschmitt Boelkow Blohm | MECHANISM FOR FOLDING AND FOLDING A FOLDING STRUCTURE |
| US4561614A (en) * | 1982-12-07 | 1985-12-31 | Rca Corporation | Deployable folded multi-element satellite subsystems |
| CN102501988A (en) * | 2011-09-26 | 2012-06-20 | 北京航空航天大学 | Telescopic space boom mechanism for supporting detection load |
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Address after: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee after: NATIONAL SPACE SCIENCE CENTER, CAS Address before: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee before: NATIONAL SPACE SCIENCE CENTER, CHINESE ACADEMY OF SCIENCES |
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